To see the other types of publications on this topic, follow the link: Flight Landing.
Dissertations / Theses on the topic 'Flight Landing'
Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles
Consult the top 47 dissertations / theses for your research on the topic 'Flight Landing.'
Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.
You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.
Browse dissertations / theses on a wide variety of disciplines and organise your bibliography correctly.
1
Hooper, Jack Charles. "Vertical landing flight envelope definition." Thesis, Luleå tekniska universitet, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-80717.
Full textAbstract:
This paper will investigate the development of a landing footprint for a re-entry vehicle. Vehicles can re-enter the atmosphere with a range of orientations, velocities and flight path angles. The central question is whether a vehicle with any combination of these states can be brought to an acceptable landing condition at a particular landing site and with a particular landing speed. To aide in this investigation several models must be implemented, including that of the atmosphere, the vehicles, the Earth, and the aerodynamics. A detailed analysis of the aerodynamic model will be treated, and the equations of motion subject to these aerodynamic laws will then be compared to results from existing atmospheric reentry software. The principles of optimization will then be employed to generate the footprint of landable states, based on maximum and minimum possible downrange distances, for two vehicle concepts.
2
Fitzgerald, Pio. "Flight control system design for autonomous UAV carrier landing." Thesis, Cranfield University, 2004. http://hdl.handle.net/1826/840.
Full textAbstract:
The challenge of integrating the UAV fleet into the carrier landing operational structure
with respect to navigation and control strategies is addressed. A simulation model was
developed which includes an aircraft model, an atmosphere model and an aircraft carrier
motion model. The six degree of freedom non-linear aircraft model is based on the
aerodynamic characteristics of the Mk 4a Jindivik extended to include rudder, spoiler
and thrust vectoring controls, and an undercarriage model. The atmosphere model
includes a carrier landing atmospheric disturbance model. The six degree of freedom
aircraft carrier motion model is based on the ship motion simulation program
SEAWAY.
A Navigation System was developed which conforms to current operational procedures
and future military navigation goals. This Navigation System continuously predicts the
position in space where touchdown on the carrier deck will take place, based on aircraft
position, the relative velocity between the aircraft and carrier, and the motion time
history of the carrier. A reference flight path to the predicted touchdown point is
continuously defined. The aircraft deviation from this flight path is determined and
input to the autoland control system. For the purposes of this study perfection prediction
is assumed.
Automatic flight control systems were developed to assess three control strategies for
suitability to the carrier landing task. The focus of this assessment was on vertical glide
path deviation control. Direct Lift Control was compared to conventional control and
was found to have superior performance, especially in turbulence. As UAV planforms
tend to be tailless, and therefore lateral and pitch control are generated by a common
aerodynamic surface, thrust vectoring was investigated as a means of alleviating
aerodynamic pitch control requirements in the carrier landing task.
An Adaptive Approach Speed Controller was developed as an extension of the
Navigation System. This system synchronises the time that the aircraft passes over the
stern, or ramp, of the carrier with the minimum absolute carrier pitch attitude attainable
for a given range of approach speeds. This system was shown to be an effective method
of minimising the negative effect that carrier motion has on the clearance between the
aircraft and the carrier’s ramp.
3
Wakefield, Nigel Hugh. "Helicopter flight in the airwake of non-aviation ships." Thesis, University of Southampton, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.326729.
Full text
4
Puumala, Rodney. "Ski jumping flight, a kinematic analysis of the mid-flight and preparation for landing phases." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape11/PQDD_0025/MQ52073.pdf.
Full text
5
Roback, Vincent Eric. "Characterization and Helicopter Flight Test of 3-D Imaging Flash LIDAR Technology for Safe, Autonomous, and Precise Planetary Landing." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/76845.
Full textAbstract:
Two flash lidars, integrated from a number of cutting-edge components from industry and NASA, are lab characterized and flight tested under the Autonomous Landing and Hazard Avoidance (ALHAT) project (in its fourth development and field test cycle) which is seeking to develop a guidance, navigation, and control (GNC) and sensing system based on lidar technology capable of enabling safe, precise human-crewed or robotic landings in challenging terrain on planetary bodies under any ambient lighting conditions. The flash lidars incorporate pioneering 3-D imaging cameras based on Indium-Gallium-Arsenide Avalanche Photo Diode (InGaAs APD) and novel micro-electronic technology for a 128 x 128 pixel array operating at 30 Hz, high pulse-energy 1.06 ?m Nd:YAG lasers, and high performance transmitter and receiver fixed and zoom optics. The two flash lidars are characterized on the NASA-Langley Research Center (LaRC) Sensor Test Range, integrated with other portions of the ALHAT GNC system from around the country into an instrument pod at NASA-JPL, integrated onto an Erickson Aircrane Helicopter at NASA-Dryden, and flight tested at the Edwards AFB Rogers dry lakebed over a field of human-made geometric hazards. Results show that the maximum operational range goal of 1000m is met and exceeded up to a value of 1200m, that the range precision goal of 8 cm is marginally met, and that the transmitter zoom optics divergence needs to be extended another eight degrees to meet the zoom goal 6° to 24°. Several hazards are imaged at medium ranges to provide three-dimensional Digital Elevation Map (DEM) information.Master of Science
6
Visser, Bernardus Johannes. "Presisie landing van 'n onbemande vliegtuig." Thesis, Stellenbosch : Stellenbosch University, 2008. http://hdl.handle.net/10019.1/2160.
Full textAbstract:
Thesis (MScEng (Electrical and Electronic Engineering)--Stellenbosch University, 2008.This thesis presents the design of a control system for the autonomous precision landing of an unmanned aerial vehicle aided by an infra red camera for precision position measurements. An optimal kinematics state estimator was designed using two Kalman filters. A Monocular vision algorithm that uses markers on the runway was developed to supply accurate position measurements on the final approach of the landing. Inner-loop controllers as proposed by [14] and implemented in [5] are used to reduce the aircraft dynamics to a point mass with steerable acceleration vector. Outer-loop controllers as proposed by [13] were modified and expanded to guide the aircraft on the circuit and final approach. The hardware in the loop simulator that was designed in [6] was expanded for optical measurements and used to verify the system. An infra red camera node was designed and built to supply the optical measurements. The system was installed on a model aircraft and partially tested with practical test flights.
7
Lee, Kyongsun. "Effects of flight factors on pilot performance, workload, and stress at final approach to landing phase of flight." Doctoral diss., University of Central Florida, 2010. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/4564.
Full textAbstract:
Similarly, the levels of a gliding angle showed the statistical difference on the performance, workload, and stress (HRV, TLX, and LP: all are p less than] .05). During the flight with 4.5 degree, the pilots showed lower performance with higher workload and stress. However, the levels of the flight experience did not have any influence on the performance, workload, and stress levels (AGPTP, LP, TLX, HRV: all are p greater than] .05). In conclusion, flying in Populated area and flying with a 4.5 degree gliding angle increases the workload and stress level of the pilots. In addition, when the pilots were flying over Populated area at Final Approach to L/D phase, they showed lower performance on tracking the glide path. Based on the results, stresses and workload can have a significant impact on flight performance. Therefore, in order to reduce the workload and stress that can cause human errors, it is highly recommended to carefully examine the impact of new flight procedures on pilot workload and stress before they are implemented.; Since human errors are one of the major causes of flight accidents, the design and operation of the modern aircraft system deals with them seriously. Particularly, the pilot workload on aviation causes human errors. Whenever new procedures are introduced and operated, the aircraft capabilities have been checked in every aspect. However, there has been little study on the impact of the new procedures such as LDLP, SCDA, SATS, and Steep Angle approach on the pilot performance, workload, and stress. In this study, different methods have been tried to understand the relationship between new procedures and the pilots in terms of performance, workload, and stress. The flight factors (e.g. flight experience, gliding angle, and approach area) were examined by the pilot performance, workload, and stress at the "Final Approach to L/D" phase using the single engine Cessna 172R type flight simulator. Five students and five instructor pilots from Embry-Riddle Aeronautical University in Dayton Beach, Florida, participated and they flew under four different simulation tasks of gliding angle and approach area. Their Heart Rate Variability (HRV) and NASA-Task Load Index (TLX) were measured to determine their stress level and subjective workload, respectively. In addition, Landing Performance (LP) data (e.g. landing distance, landing speed) and Above Glide Path Tracking Performance (AGPTP) data were also collected to evaluate pilot performance. As a result, the type of approach area showed a significant effect on pilot performance, workload, and stress determined by ANOVA (HRV, TLX, LP, AGPTP: all are p less than] .05). Flying over "Populated" area (e.g. a large city) resulted in lower pilot performance and higher pilot workload and stress than that over "Non-Populated" area (e.g. a grass field).ID: 029049593; System requirements: World Wide Web browser and PDF reader.; Mode of access: World Wide Web.; Thesis (Ph.D.)--University of Central Florida, 2010.; Includes bibliographical references (p. 95-112).
Ph.D.
Doctorate
Department of Industrial Engineering and Management Systems
Engineering and Computer Science
8
Wellons, William Lee. "A shipboard global positioning system carrier phase interferometric aircraft flight reference system." Ohio : Ohio University, 1994. http://www.ohiolink.edu/etd/view.cgi?ohiou1179860957.
Full text
9
Grymin, David J. "Development of a novel method for autonomous navigation and landing of unmanned aerial vehicles /." Online version of thesis, 2009. http://hdl.handle.net/1850/10615.
Full text
10
Murphy, Timothy A. "MLS Flight inspection techniques: Digital filtering and coordinate transformation." Ohio : Ohio University, 1985. http://www.ohiolink.edu/etd/view.cgi?ohiou1184070645.
Full text
11
Wilson, John E. "Hover control for a vertical take-off and landing vehicle." Thesis, Stellenbosch : University of Stellenbosch, 2009. http://hdl.handle.net/10019.1/1753.
Full textAbstract:
Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2009.This thesis details the development and comparison of two linear control systems that performhover control for a vertical take-off and landing unmanned aerial vehicle. A non-linear mathematical model of the aircraft dynamics is developed. A classical successive loop closure control approach is presented, which applies static gains to the decoupled model around hover. A variable gain approach is presented using optimal control, which linearises the aircraftmodel around its state at fixed time steps. Simulation performance and robustness results are examined for both systems. Different aspects of both controller design processes and results are compared, including navigational performance, robustness and ease of use.
12
Saghafi, F. "Development of a simulation tool for flight dynamics and control investigations of articulated vtol unmanned aircraft." Thesis, Cranfield University, 1996. http://dspace.lib.cranfield.ac.uk/handle/1826/4757.
Full textAbstract:
A simulation tool for flight dynamics and control investigations of three different Vertical
Take Off and Landing (VTOL) unmanned aircraft configurations has been developed. A
control concept has been proposed in order to take advantage of the fast response
characteristics of the ordinary small engine/propeller propulsion systems in such aircraft,
as well as replacing the complex rotors used previously in VTOL concepts for small
unmanned aircraft. The simulation model has been established on the basis of the
proposed concept so that it can also be used to study the feasibility of this idea. An
Object-based methodology has been introduced so as to reduce the amount of
aerodynamic required data for the simulation model. The equations of motion associated
with the aircraft multibody system with ten degrees of freedom have been derived using
the Newton-Euler method. The modelling of various subsystems including the propeller
model, the airframe aerodynamics and the engine model has been carried out. A method
for calculating the propellers' slipstream effects on the other components has been
presented. Input data for the simulation model have been estimated, using different
sources. The Advanced Continuous Simulation Language (ACSL) has been used for the
programming of the mathematical model. A series of comprehensive tests have been
carried out in order to demonstrate the validity of the simulation model. The ability of the
simulation model to explain the aircraft modes of motion as well as to discover unknown
nonlinear behaviours and to describe them has been demonstrated.
13
Reichert, Frederick W. "Data link development for the Archytas vertical takeoff and landing transitional flight unmanned aerial vehicle /." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1993. http://handle.dtic.mil/100.2/ADA272499.
Full textAbstract:
Thesis (M.S. in Systems Technology (Command, Control and Communications)) Naval Postgraduate School, June 1993.Thesis advisor(s): Michael K. Shields ; Michael G. Sovereign. "June 1993." Bibliography: p. 84-85. Also available online.
14
Reichert, Frederick W. Jr. "Data link development for the Archytas vertical takeoff and landing transitional flight unmanned aerial vehicle." Thesis, Monterey, California. Naval Postgraduate School, 1993. http://hdl.handle.net/10945/39836.
Full textAbstract:
Approved for public release; distribution is unlimited.This thesis chronicles the development of a data link for the Archytas, a vertical takeoff and landing, transitional flight unmanned aerial vehicle (UAV) prototype being built by the Aeronautics Department at the Naval Postgraduate School. Archytas is intended to be a proof-of-concept platform to satisfy the Navy's real-time, over-the-horizon intelligence mission with a UAV that could be launched and recovered from a small combatant ship. This thesis provides a history of the Archytas command and control data link development, a full description of the data link as delivered for use on the prototype, principles for near term enhancements, and future considerations for the data link should the Archytas concept be adapted for use in an operational combat environment.
15
Lizarraga, Mariano I. "Autonomous landing system for a UAV." Thesis, Monterey California. Naval Postgraduate School, 2004. http://hdl.handle.net/10945/1655.
Full textAbstract:
Approved for public release, distribution is unlimitedThis thesis is part of an ongoing research conducted at the Naval Postgraduate School to achieve the autonomous shipboard landing of Unmanned Aerial Vehicles (UAV). Two main problems are addressed in this thesis. The first is to establish communication between the UAV's ground station and the Autonomous Landing Flight Control Computer effectively. The second addresses the design and implementation of an autonomous landing controller using classical control techniques. Device drivers for the sensors and the communications protocol were developed in ANSI C. The overall system was implemented in a PC104 computer running a real-time operating system developed by The Mathworks, Inc. Computer and hardware in the loop (HIL) simulation, as well as ground test results show the feasibility of the algorithm proposed here. Flight tests are scheduled to be performed in the near future.
Lieutenant Junior Grade, Mexican Navy
16
Whitehead, John Gardner. "An examination of the kinematics and behavior of mallards (Anas platyrhynchos) during water landings." Diss., Virginia Tech, 2020. http://hdl.handle.net/10919/99383.
Full textAbstract:
This dissertation aims to address how a change in landing substrate may change landing kinematics. To examine this possibility, mallards (Anas playtrhynchos) were used as a study species and 177 water landings were recorded through the use of two camera systems with photogrammetric capabilities. This enabled the landing trajectory and landing transition kinematics to be tracked in three dimensions. From the resulting position data three questions were pursued. Do mallards regulate landing kinematics through a ̇-constant strategy? With what kinematics do mallards land on water? Do landing kinematics respond to external factors, such as an obstacle to landing? Chapter 2 assesses the presence of a ̇-constant regulatory strategy and compares the implementation to other landing behaviors. Chapter 3 examines the variation observed in the landing kinematics of mallards, identifies the primary kinematic drivers of that variation, and detects differences in kinematic profile. Chapter 4 inspects the landing kinematics combined with the positions of all other waterfowl in the vicinity to test for the presence of obstacle avoidance behavior.Doctor of Philosophy
Control of landing is an important ability for any flying animal. However, with the exception of perch landing, we know very little about how birds and other flyers land on a variety of different surfaces. Here, we aim to extend our knowledge in this area by focusing on how mallard ducks land on water. This dissertation addresses the following questions. Do mallards regulate landing speed and trajectory the same way as pigeons? At what speeds, angles, and postures do mallards land on water? Can mallards adjust landing behavior to avoid collisions with other birds on the water surface? Chapter 2 determines how mallards regulate landings and how it is similar and different from pigeons and several other flyers. Chapter 3 describes the speeds, angles, and postures used by mallards to land on water. In addition, this chapter finds evidence for at least two different categories of landing performed by mallards. Chapter 4 provides evidence that mallards avoid situations in which a collision with another bird is likely. However, it is unclear if this is an active choice made by the mallard or due to other circumstances related to the landing behavior. Overall, this dissertation illustrates how the landing behavior of mallards is similar to what has been documented in other animals. However there are significant differences such as higher impact speeds, and shallower angles. Both of which are likely related to the ability of water to absorb a greater amount of the impact forces than a perch or the ground would.
17
McGeoch, David James. "Helicopter flight control system design using sliding mode theory : application to handling qualities and shipboard landing." Thesis, University of Glasgow, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.433175.
Full text
18
Kargin, Volkan. "Design Of An Autonomous Landing Control Algorithm For A Fixed Wing Uav." Master's thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608996/index.pdf.
Full textAbstract:
This thesis concerns with the design and development of automatic flight controller strategies
for the autonomous landing of fixed wing unmanned aircraft subject to severe environmental
conditions. The Tactical Unmanned Aerial Vehicle (TUAV) designed at the Middle East Technical University (METU) is used as the subject platform. In the first part of this thesis, a
dynamic model of the TUAV is developed in FORTRAN environment. The dynamic model is
used to establish the stability characteristics of the TUAV. The simulation model also incorporates ground reaction and atmospheric models. Based on this model, the landing trajectory
that provides shortest landing distance and smallest approach time is determined. Then, an
automatic flight control system is designed for the autonomous landing of the TUAV. The
controller uses a model inversion approach based on the dynamic model characteristics. Feed
forward and mixing terms are added to increase performance of the autopilot. Landing strategies are developed under adverse atmospheric conditions and performance of three different
classical controllers are compared. Finally, simulation results are presented to demonstrate the
effectiveness of the design. Simulation cases include landing under crosswind, head wind, tail
wind, wind shear and turbulence.
19
Yildiz, Guray. "Dynamic Approach To Wind Sensitive Optimum Cruise Phase Flight Planning." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12615098/index.pdf.
Full textAbstract:
A Flight Management System (FMS) performs 4 Dimensional flight planningLateral Planning (Calculation of the latitude and longitudes of waypoints), Vertical Planning (Calculation of the altitudes of waypoints) and Temporal Planning(Calculation of Estimated Time of Arrival). Correct and accurate calculation of4D flight path and then guiding the pilot/airplane to track the route in specified accuracy limits in terms of lateral (i.e Required Navigational Performance RNP), vertical (Reduced Vertical Seperation Minima RVSM), and time (Required Time of Arrival RTA) is what FMS performs in brief. Any deviation of planned input values versus actual input values, especially during the emergency cases (i.e burning outoneof engines etc.), causes the aircraft to deviate the plan and requires replanning now taking into consideration the currentsituation. In emergency situations especially in Oceaning Flights (flights whose cruise phase lasts more than 5 hour is called as &ldquo
Oceaning Flights&rdquo
) Optimum Cruise Phase Flight Route Planning plays a vital role. In avionics domain &ldquo
Optimum&rdquo
does not mean &ldquo
shortest path&rdquo
mainly due to the effect of weather data as wind speed and direction directly affects the groundspeed. In the scope of the current thesis, an algorithm employing dynamic programming paradigms will be designed and implemented to find the optimum flight route planning. A top down approach by making use of aircraft route planning ontology will be implemented to fill the gap between the flight plan specific domain knowledge and optimization techniques employed. Where as the algorithm will be generic by encapsulating the aircraft&rsquo
s performance characteristics
it will be evaluated on C-130 aircraft.
20
Smit, Samuel Jacobus Adriaan. "Autonomous landing of a fixed-wing unmanned aerial vehicle using differential GPS." Thesis, Stellenbosch : Stellenbosch University, 2013. http://hdl.handle.net/10019.1/80122.
Full textAbstract:
Thesis (MScEng)--Stellenbosch University, 2013.ENGLISH ABSTRACT: This dissertation presents the design and practical demonstration of a flight control system (FCS) that is capable of autonomously landing a fixed-wing, unmanned aerial vehicle (UAV) on a stationary platform aided by a high-precision differential global positioning system. This project forms part of on-going research with the end goal of landing a fixed-wing UAV on a moving platform (for example a ship’s deck) in windy conditions. The main aim of this project is to be able to land the UAV autonomously, safely and accurately on the runway. To this end, an airframe was selected and equipped with an avionics payload. The equipped airframe’s stability derivatives were analysed via AVL and the moment of inertia was determined by the double pendulum method. The aircraft model was developed in such a way that the specific force and moment model (high bandwidth) is split from the point-mass dynamics of the aircraft (low bandwidth) [1]. The advantage of modelling the aircraft according to this unique method, results in a design that has simple decoupled linear controllers. The inner-loop controllers control the high-bandwidth specific accelerations and roll-rate, while the outer-loop controllers control the low-bandwidth point-mass dynamics. The performance of the developed auto-landing flight control system was tested in software-in-the-loop (SIL) and hardware-in-the-loop (HIL) simulations. A Monte Carlo non-linear landing simulation analysis showed that the FCS is expected to land the aircraft 95% of the time within a circle with a diameter of 1.5m. Practical flight tests verified the theoretical results of the developed controllers and the project was concluded with five autonomous landings. The aircraft landed within a circle with a 7.5m radius with the aiming point at the centre of the circle. In the practical landings the longitudinal landing error dominated the landing performance of the autonomous landing system. The large longitudinal error resulted from a climb rate bias on the estimated climb rate and a shallow landing glide slope.
AFRIKAANSE OPSOMMING: Hierdie skripsie stel die ontwikkeling en praktiese demonstrasie van ʼn self-landdende onbemande vastevlerkvliegtuigstelsel voor, wat op ʼn stilstaande platform te lande kan kom met behulp van ʼn uiters akkurate globale posisionering stelsel. Die projek maak deel uit van ʼn groter projek, waarvan die doel is om ʼn onbemande vastevlerkvliegtuig op ʼn bewegende platform te laat land (bv. op ʼn boot se dek) in onstuimige windtoestande. Die hoofdoel van die projek was om die vliegtuig so akkuraat as moontlik op die aanloopbaan te laat land. ʼn Vliegtuigraamwerk is vir dié doel gekies wat met gepaste avionica uitgerus is. Die uitgeruste vliegtuig se aerodinamsie eienskappe was geanaliseer met AVL en die traagheidsmoment is deur die dubbelependulum metode bepaal. Die vliegtuigmodel is op so ‘n manier onwikkel om [1] die spesifieke krag en momentmodel (vinnige reaksie) te skei van die puntmassadinamiek (stadige reaksie). Die voordeel van hierdie wyse van modulering is dat eenvoudige ontkoppelde beheerders ontwerp kon word. Die binnelusbeheerders beheer die vinnige reaksie-spesifieke versnellings en die rol tempo van die vliegtuig. Die buitelusbeheerders beheer die stadige reaksie puntmassa dinamiek. Die vliegbeheerstelsel is in sagteware-in-die-lus en hardeware-in-die-lus simulasies getoets. Die vliegtuig se landingseienskappe is ondersoek deur die uitvoer van Monte Carlo simulasies, die simulasie resultate wys dat die vliegtuig 95% van die tyd binne in ʼn sirkel met ʼn diameter van 1.5m geland het. Praktiese vlugtoetse het bevestig dat die teoretiese uitslae en die prakties uitslae ooreenstem. Die vliegtuig het twee suksesvolle outomatiese landings uitgevoer, waar dit binne ʼn 7.5m-radius sirkel geland het, waarvan die gewenste landingspunt die middelpunt was. In die outomatiese landings is die longitudinale landingsfout die grootse. Die groot longitudinale landingsfout is as gevolg van ʼn afset op die afgeskatte afwaartse spoed en ʼn lae landings gradiënt.
21
Tong, Peter, and mail@petertong com. "Application of Genetic Algorithm to a Forced Landing Manoeuvre on Transfer of Training Analysis." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080528.114140.
Full textAbstract:
This study raises some issues for training pilots to fly forced landings and examines the impact that these issues may have on the design of simulators for such training. It focuses on flight trajectories that a pilot of a single-engine general aviation aircraft should fly after engine failure and how pilots can be better simulator trained for this forced landing manoeuvre. A sensitivity study on the effects of errors and an investigation on the effect of tolerances in the aerodynamic parameters as prescribed in the Manual of Criteria for the Qualification of Flight Simulators have on the performance of flight simulators used for pilot training was carried out. It uses a simplified analytical model for the Beech Bonanza model E33A aircraft and a vertical atmospheric turbulence based on the MIL-F-8785C specifications. It was found that the effect of the tolerances is highly sensitive on the nature of the manoeuvre flown and that in some cases, negative transfe r of training may be induced by the tolerances. A forced landing trajectory optimisation was carried out using Genetic Algorithm. The forced landing manoeuvre analyses with pre-selected touchdown locations and pre-selected final headings were carried out for an engine failure at 650 ft AGL for bank angles varying from banking left at 45° to banking right at 45°, and with an aircraft's speed varying from 75.6 mph to 208 mph, corresponding to 5% above airplane's stall speed and airplane's maximum speed respectively. The results show that certain pre-selected touchdown locations are more susceptible to horizontal wind. The results for the forced landing manoeuvre with a pre-selected location show minimal distance error while the quality of the results for the forced landing manoeuvre with a pre-selected location and a final heading show that the results depend on the end constraints. For certain pre-selected touchdown locations and final headings, the airplane may either touchdown very close to the pre-selected touchdown location but with greater final h eading error from the pre-selected final heading or touchdown with minimal final heading error from the pre-selected final heading but further away from the pre-selected touchdown location. Analyses for an obstacle avoidance forced landing manoeuvre were also carried out where an obstacle was intentionally placed in the flight path as found by the GA program developed for without obstacle. The methodology developed successfully found flight paths that will avoid the obstacle and touchdown near the pre-selected location. In some cases, there exist more than one ensemble grouping of flight paths. The distance error depends on both the pre-selected touchdown location and where the obstacle was placed. The distance error tends to increase with the addition of a specific final heading requirement for an obstacle avoidance forced landing manoeuvre. As with the case without specific final heading requirement, there is a trade off between touching down nearer to the pre-selected location and touching down with a smaller final heading error.
22
Yoon, Sung Hwan. "STUDIES OF ION DISSOCIATION KINETICS AND MECHANISMS BY SURFACE-INDUCED DISSOCIATION AND INFRARED MULTI-PHOTON DISSOCIATION/SOFT-LANDING." Diss., The University of Arizona, 2010. http://hdl.handle.net/10150/195256.
Full textAbstract:
This dissertation presents dissociation mechanism and dissociation kinetics studies of gas-phase ions using mass spectrometry (MS). Dissociation of a gas-phase ion is related to its fundamental properties such as composition and structure. However, the detailed processes, internal energy deposition during ion activation as well as the mechanism of dissociation, are not fully known. In the present work, ion structural studies from which mechanisms can be inferred were performed using infrared multiphoton dissociation (IRMPD) spectroscopy, soft-landing, IR spectroscopy, and quantum chemical calculations. Kinetics studies involved instrument modification to add surface-induced dissociation (SID) capability and peak shape analysis. Structural studies were performed to determine dissociation mechanisms. The b₂⁺ ion from AGG is an oxazolone structure as indicated by the IRMPD spectrum and quantum chemical calculations. Protonated 4-ethoxymethylene-2-phenyl-2-oxazolin-5- one is also an oxazolone-type structure, while protonated cyclo-AG is a diketopiperazine structure. Soft-landing experiments were carried out to corroborate IRMPD results. Soft-landed protonated cyclo-AG and protonated 4-ethoxymethylene-2-phenyl-2- oxazolin-5-one underwent neutralization and retained their structures. The soft-landed b₂⁺ ion of AGG showed evidence of ring opening and conversion into a linear structure. The modified matrix-assisted laser desorption/ionization (MALDI) time-of-flight (TOF) mass spectrometers with SID capability were used to study fast dissociation kinetics (sub-microsecond dissociation). Silicon nanoparticle assisted laser desorption/ionization (SPALDI) allows the study of small molecule dissociation kinetics for ions without the matrix interference observed in MALDI. Well characterized systems, such as, N(CH₃)₄⁺, N(CD₃)₄⁺, and substituted benzylpyridinium ions were used to confirm reliability of the peak shape analysis. Obtained dissociation rates, of submicrosecond order, are consistent with the known dissociation theories. Dissociation of fullerenes, C₆₀ and C₇₀, was also investigated with the SID method using a fluorocarbon self-assembled monolayer (FSAM) surface. Fullerene ions produced C(2n)⁺ fragments ion in the kinetic energy range of 150-300 eV. At higher than 400 eV, mass spectra showed additional small fragment ions composed of odd numbers of C units. Energy resolved MS/MS curves support parallel dissociation at high SID energies while peak shape analysis explains sequential dissociation at about 150 eV range. Instrument modification of a MALDI-TOF mass spectrometer with SID capability allowed successful studies of fast unimolecular dissociation kinetics of small ions and fullerenes.
23
Du, Yongliang. "Development of real-time flight control system for low-cost vehicle." Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/8621.
Full textAbstract:
In recent years, more and more light aircraft enter our daily life, from Agricultural
applications, emergency rescue, flight experiment and training to Barriers to
entry, light aircraft always have their own advantages. Thus, they have become
more and more popular.
However, in the process of GDP research about Flight Control System design
for the Flying Crane, the author read a lot of literature about Flight Control
System design, then noticed that the research in Flight Control System have
apparently neglected to Low-cost vehicles. So it is necessary to do some study
about Flight Control System for this kind of airplane. The study will more
concern the control law design for ultra-light aircraft, the author hopes that with
an ‘intelligence’ Flight Control System design, this kind of aircraft could
sometimes perform flying tasks according to a prearranged flight path and
without a pilot.
As the Piper J-3 cub is very popular and the airframe data can be obtained
more easily, it was selected as an objective aircraft for the control law design.
Finally, a ¼ scale Piper J-3 cub model is selected and the aerodynamics
coefficients are calculated by DATCOM and AVL. Based on the forces and
moments acting on the aircraft, the trim equilibrium was calculated for getting
proper dynamics coefficients for the selected flight conditions. With the aircraft
aerodynamics coefficients, the aircraft dynamics characteristics and flying
qualities are also analyzed. The model studied in this thesis cannot answer
level one flying qualities in the longitudinal axis, which is required by MIL-F-
8785C. The stability augment system is designed to improve the flying qualities
of the longitudinal axis.
The work for autopilot design in this thesis includes five parts. First, the whole
flight profile is designed to automatically control aircraft from takeoff to landing.
Second, takeoff performance and guidance law is studied. Then, landing
performance and trajectory is also investigated. After that, the control law
design is decoupled into longitudinal axis and later-directional axis. Finally,
simulation is executed to check the performance for the auto-controller.
24
Chren, Tibor. "Návrh podvozku pro letoun Rapid 600." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-229317.
Full textAbstract:
This diploma thesis deals with design of retractable landing gear for Rapid 600 aircraft. The main purpose of this thesis is to analyze different retraction options for front and main landing gear and resulting selection of suitable variants. The thesis is consequently concerned with design of selected options including proposal of automatic landing gear control system and specifying the features and characteristics of this system. In the thesis there is also included the analysis of critical flight conditions which could be detected by this system.
25
Ham, Linda J. "Evaluation of potential changes to the Space Shuttle Orbiter's Flight Control System to increase directional control during post landing rollout." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA340494.
Full textAbstract:
Thesis (M.S. in Astronautical Engineering) Naval Postgraduate School, September 1997."September 1997." Thesis advisor(s): Terrence W. Wilcutt, Richard M. Howard. Includes bibliographical references (p. 111). Also available online.
26
Shollenberger, Tara Krystyna. "Statistical Entry, Descent, and Landing Flight Reconstruction with Flush Air Data System Observations using Inertial Navigation and Monte Carlo Techniques." Thesis, North Carolina State University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3584009.
Full textAbstract:
Research suggests what leaders should do or the qualities or characteristics they should have to be ethical leaders (Brown & Treviño, 2006). The ethical decision-making process that leaders should follow to avoid scandals and unethical behavior are overlooked. Few studies focused on ethical decision-making within higher education. Yet, educational leaders have an ethical responsibility that may be even more complex than those of other leaders due in part to increasingly diverse student populations enrolled in higher education that is having an impact on the growth of educational institutions on a global basis (Shapiro & Stekfovich, 2011). Further, ethical scandals are no longer contained by national borders. The rapid growth of technology coupled with changes in political and societal landscapes has advanced ethical scandals to global prominence. A more collective need to understand ethical values and ethical decision-making practices on a global level has emerged. To be globally effective, leaders must be aware of the similarities and differences across and within cultures that could influence business practices (Resick, Hanges, Dickson, & Mitchelson, 2006). However, cross-cultural research has not yet addressed the topic of ethical decision-making. In this study, the ethical decision-making process of higher education was not only examined in the United Stated but also in Poland. This exploratory study used the Delphi research technique to identify an ethical decision-making definition that higher administration leaders in both the United States and Poland use to make ethical decisions and identify the environmental factors that influence their decisions. Findings showed that the United States and Polish expert panels were different and showed very little in common in the identification of a definition and environmental factors. Lastly, both sets of experts identified a new process for ethical decision-making, each constructing a different ethical decision-making process model. This research on ethical decision-making provided evidence that the Polish and United States cultures are not as similar as identified in previous studies in terms of how they identify ethical decision-making and the factors they identify with influencing ethical decision-making. Using this information will create a better understanding of the practices and approaches to ethics that leaders use because of the huge influence they have and exert on people within their own organization and society around them.
27
Lugo, Rafael Andres. "Statistical Entry, Descent, and Landing Flight Reconstruction with Flush Air Data System Observations using Inertial Navigation and Monte Carlo Techniques." Thesis, North Carolina State University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3584008.
Full textAbstract:
A method is introduced to consider flush air data system (FADS) pressures using a technique based on inertial navigation to reconstruct the trajectory of an atmospheric entry vehicle. The approach augments the recently-developed Inertial Navigation Statistical Trajectory and Atmosphere Reconstruction (INSTAR), which is an extension of inertial navigation that provides statistical uncertainties by utilizing Monte Carlo dispersion techniques and is an alternative to traditional statistical approaches to entry, descent, and landing trajectory and atmosphere reconstruction.
The method is demonstrated using flight data from the Mars Science Laboratory (MSL) entry vehicle, which contained an inertial measurement unit and a flush air data system called the Mars Entry Atmospheric Data System (MEADS). An MSL trajectory and atmosphere solution that was updated using landing site location in INSTAR is first presented. This solution and corresponding uncertainties, which were obtained from Monte Carlo dispersions, are then used in a minimum variance algorithm to obtain aerodynamic estimates and uncertainties from the MEADS observations. MEADS-derived axial force coefficient and freestream density estimates and uncertainties are also derived from the minimum variance solutions independent of the axial force coefficients derived from computation fluid dynamics (CFD), which have relatively high a priori uncertainty. Results from probabilistic analyses of the solutions are also presented.
This dissertation also introduces a method to consider correlated CFD uncertainties in INSTAR. From a priori CFD uncertainties, CFD force and pressure coefficients are dispersed in a Monte Carlo sense and carried over into the reconstructions. An analysis of the subsequent effects on the trajectory, atmosphere, and aerodynamic estimates and statistics is presented.
Trajectory, atmospheric, and aerodynamic estimates compare favorably to extended Kalman filter solutions obtained by the MSL reconstruction team at NASA Langley Research Center. The uncertainties obtained through the methods from this work are generally smaller in magnitude because of assumptions made regarding sources of error in the MEADS pressure transducer uncertainties. Using data-derived uncertainties in the pressure measurement noise covariance results in aerodynamic parameter estimate uncertainties that are in better agreement with the uncertainties derived from the Monte Carlo dispersions. CFD database errors dominate the uncertainties of parameters derived from aerodatabase axial force coefficients.
28
De, Hart Ruan Dirk. "Advanced take-off and flight control algorithms for fixed wing unmanned aerial vehicles." Thesis, Stellenbosch : University of Stellenbosch, 2010. http://hdl.handle.net/10019.1/4179.
Full textAbstract:
Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2010.ENGLISH ABSTRACT: This thesis presents the development and implementation of a position based kinematic guidance system, the derivation and testing of a Dynamic Pursuit Navigation algorithm and a thorough analysis of an aircraft’s runway interactions, which is used to implement automated take-off of a fixed wing UAV. The analysis of the runway is focussed on the aircraft’s lateral modes. Undercarriage and aerodynamic effects are first analysed individually, after which the combined system is analysed. The various types of feedback control are investigated and the best solution suggested. Supporting controllers are designed and combined to successfully implement autonomous take-off, with acceleration based guidance. A computationally efficient position based kinematic guidance architecture is designed and implemented that allows a large percentage of the flight envelope to be utilised. An airspeed controller that allows for aggressive flight is designed and implemented by applying Feedback Linearisation techniques. A Dynamic Pursuit Navigation algorithm is derived that allows following of a moving ground based object at a constant distance (radius). This algorithm is implemented and verified through non-linear simulation.
AFRIKAANSE OPSOMMING: Hierdie tesis handel oor die ontwikkeling en toepassing van posisie-afhanklike, kinematiese leidings-algoritmes, die ontwikkeling van ’n Dinamiese Volgings-navigasie-algoritme en ’n deeglike analise van die interaksie van ’n lugraam met ’n aanloopbaan sodat outonome opstygprosedure van ’n vastevlerk vliegtuig bewerkstellig kan word. Die bogenoemde analise het gefokus op die laterale modus van ’n vastevlerk vliegtuig en is tweeledig behartig. Die eerste gedeelte het gefokus op die analise van die onderstel, terwyl die lugraam en die aerodinamiese effekte in die tweede gedeelte ondersoek is. Verskillende tipes terugvoerbeheer vir die outonome opstygprosedure is ondersoek om die mees geskikte tegniek te bepaal. Addisionele beheerders, wat deur die versnellingsbeheer gebaseerde opstygprosedure benodig word, is ontwerp. ’n Posisie gebaseerde kinematiese leidingsbeheerstruktuur om ’n groot persentasie van die vlugvermoë te benut, is ontwikkel. Terugvoer linearisering is toegepas om ’n lugspoedbeheerder , wat in staat is tot aggressiewe vlug, te ontwerp. ’n Dinamiese Volgingsnavigasie-algoritme wat in staat is om ’n bewegende grondvoorwerp te volg, is ontwikkel. Hierdie algoritme is geïmplementeer en bevestig deur nie-lineêre simulasie.
29
Vomočil, Jan. "Systém pro automatické přistávání quadrocopteru." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2012. http://www.nusl.cz/ntk/nusl-219707.
Full textAbstract:
This thesis describes the design and implementation of systems for automatic landing and stabilization of air vehicle known as Quadrocopter. It focuses on image processing from a camera placed on board of the robot. The aim of image processing is detect landing target and calculate the distance from the desired position. Further is solved vertical stabilization for higher altitudes. For this function is measured atmospheric pressure. Conversely, for low altitude flight is used a ultrasonic range finder. In the conclusion is solved the implementation of the system.
30
Watts, Robert Michael. "Development and evaluation of an automated path planning aid." Thesis, Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33839.
Full textAbstract:
In the event of an onboard emergency, air transport pilots are remarkably adept at safely landing their aircraft. However, the tasks of selecting an alternate landing site and developing a safe path to land are very difficult in the high workload, high stress environment of a cockpit during an emergency. The purpose of this research was to develop an automated path planning aid which would assist the pilot in the completion of these tasks. A prototype was developed to test this concept experimentally. The experiment was also intended to gather further information about how pilots think about and accomplish this task as well as the best ways to assist them.
In order to better understand the priorities and processes pilots use when dealing with emergency planning, a survey of airline pilots was conducted. The results of this survey highlighted the fact that each emergency is unique and has its own set of factors which are critically important. One factor which is important in many emergencies is the need to land quickly. The survey responses indicated that one of the most important characteristics of a useful tool is that it should provide pertinent information in an easy to use manner, and should not divert too much attention from their other tasks.
A number of design goals drove the development of the prototype aid. First, the aid was to work within current aircraft, without requiring substantial redesign on the cockpit. Second, the aid was to help improve pilots' performance without increasing their workload. Finally, the aid was designed to assist pilots in obtaining and processing critical information which influences the site selection and path development tasks. One variation of the aid included a filter dial which allowed pilots to quickly reduce the number of options considered, another variation of the aid did not include such a dial. These two variations of the aid were tested in order to assess the impact of the addition of the filter dial to the system.
Though many of the results did not prove to be statistically significant, they suggest that the addition of a filter dial improved the quality of the selected landing site; however, it also increased the time required for the selection. The results were obtained in both familiar and unfamiliar emergencies. The dial was shown to improve the time to complete the task in the case of unfamiliar emergencies. The experiment also compared an optimal ranking system to a non-optimal system, for which results showed no significant difference between the two. This may imply that while pilots did not tend to over rely on the ranking system, under-reliance may need to be addressed by training and a better understanding of the factors which impact the rankings.
The participants found that the aid facilitates quick and easy access to critical information. The aid was also useful for processing this information by filtering out options which were inappropriate for a given scenario through the use of the filter dial. The participants also made recommendations about possible improvements which could be made to the system such as better filter settings which are more similar to the way that pilots think about their options.
31
Tagebrand, Emil, and Ek Emil Gustafsson. "Dataset Generation in a Simulated Environment Using Real Flight Data for Reliable Runway Detection Capabilities." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-54974.
Full textAbstract:
Implementing object detection methods for runway detection during landing approaches is limited in the safety-critical aircraft domain. This limitation is due to the difficulty that comes with verification of the design and the ability to understand how the object detection behaves during operation. During operation, object detection needs to consider the aircraft's position, environmental factors, different runways and aircraft attitudes. Training such an object detection model requires a comprehensive dataset that defines the features mentioned above. The feature's impact on the detection capabilities needs to be analysed to ensure the correct distribution of images in the dataset. Gathering images for these scenarios would be costly and needed due to the aviation industry's safety standards. Synthetic data can be used to limit the cost and time required to create a dataset where all features occur. By using synthesised data in the form of generating datasets in a simulated environment, these features could be applied to the dataset directly. The features could also be implemented separately in different datasets and compared to each other to analyse their impact on the object detections capabilities. By utilising this method for the features mentioned above, the following results could be determined. For object detection to consider most landing cases and different runways, the dataset needs to replicate real flight data and generate additional extreme landing cases. The dataset also needs to consider landings at different altitudes, which can differ at a different airport. Environmental conditions such as clouds and time of day reduce detection capabilities far from the runway, while attitude and runway appearance reduce it at close range. Runway appearance did also affect the runway at long ranges but only for darker runways.
32
Seďa, Ondřej. "Modifikace letounu RAPID 200 pro vlekání." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2010. http://www.nusl.cz/ntk/nusl-228984.
Full textAbstract:
This master’s thesis deal with design modification of the RAPID 200 (Skyleader 200) airplane for towing at compliance with maximum take-off weight 450 kilogramme. A necessary construction modification, a weight analysis these adjustments and a balance verification are included. The thesis contains of power plants installation consisting from the M 132 engine and the V 541.2 propeller, a towing gear and a landing gear, a load calculation of power plants and towing gear and basic flight performance calculation too. Last but not least valuation of operation ekonomy, operation characteristics assesment and a using of the airplane for specialized duty are included.
33
Arnett, Scott W. "The effect of in-flight perturbations on landing biomechanics." 2007. http://purl.galileo.usg.edu/uga%5Fetd/arnett%5Fscott%5Fw%5F200708%5Fphd.
Full text
34
Huang, Yu-Ming, and 黃裕明. "Determination of Flight Operation in Veer-off Avoidance during Landing." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/80346824000233087108.
Full textAbstract:
碩士中華科技大學
航空機械系飛機系統工程碩士班
103
Wind shear is the type of wind field with varying magnitude and/or direction as encountered by an airplane. Landing in horizontal wind shear has been a safety issue for all types of airplanes. The current airplane design practice and certification account only for constant crosswind. In reality, most crosswind can be classified as wind shear to a certain level. As a result, accidents or incidents, such as hard or porpoise-style (i.e. jumping) landing, oscillation in roll, runway veer-off after touchdown, etc., have been occurring. Although pilot training has been again and again emphasized, unfortunately existing training simulators for landing operation in wind shear have serious shortcomings and may lead to negative training. The latter implies the possibility that when pilots apply what are learned in simulators, the situation may get worse as pointed out by NASA researchers. It should be emphasized that these wind shear effects can also be induced by airplane motion, not just by atmospheric disturbances. System consisting of fuzzy-logic numerical models will be presented to show its effectiveness with several accident flights. Emphasis is placed on finding observable parameters for pilots to make appropriate actions. The latter involve runway veer-off in strong wind shear or crosswind. The results in simulations of fuzzy-logic numerical models have been shown to be much more realistic in wind shear than what can be expected with the existing simulators.
35
Wang, Xiang, and 王翔. "Flight Safety of Transport Aircraft in Landing with Crosswind Effects." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/88865554038914523211.
Full textAbstract:
碩士中華科技大學
飛機系統工程研究所
104
Aircraft landing in crosswind effects has been a safety problem for all types of aircraft. The runway veer-off event due to crosswind effects has been of great concern for the aviation community. The main objective of this research is to present fuzzy-logic modeling (FLM) technique to establish flight control models with the function of nonlinear dynamic inversion based on the datasets from the flight data recorder (FDR) for the purpose to provide improved control strategy and situation awareness. The present thesis employs two twin-jet transports of the same type to do the comparative landing analyses. One is flight safety event with the runway veer-off incident due to crosswind effects and another one is normal flight during the landing. The elevator angles, normal accelerations, descending rates, and flight path angles based on flight data of these two transports are the parameters of the comparative analyses. The focus point is the caused reasons of runway excursion after touchdown. This thesis uses the flight control models of elevator, aileron, and rudder of the runway veer-off event to provide improved control strategy and situation awareness in phases of approach, flare, and after touchdown. The establishments of the methods in avoidance the errors of flight operations to reduce the threat of crosswind effects during the landing for the pilots base on improved control strategy and situation awareness will be demonstrated in the present thesis.
36
Ju, Hann-Shing, and 朱漢興. "Flight and Auto-Landing Controllers Design for Unmanned Aerial Vehicles." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/16022706204343544994.
Full textAbstract:
博士國立中興大學
電機工程學系所
96
This dissertation presents methodologies and techniques for flight control and autolanding of unmanned aerial vehicles (UAVs), thereby carrying out three major missions, including full-envelope flight, optical payload following, and auto-landing. The four control laws of UAV are then developed using adaptive backstepping and intelligent fuzzy logic; they are full-envelope flight control, flight path following the optical payload, auto-landing, and flare control with flight path command. First, the full-envelope flight control is designed via adaptive backstepping for achieving good flying qualities in longitudinal axis for all flight conditions; such an adaptive controller works well for the purpose of accomplishing desired responses under a wide range of flight envelope. Second, the intelligent flight control is proposed to accomplish aircraft following optical payload which is manipulated by an operator; this intelligent strategy combines fuzzy logic control and pursuit guidance such that the target within the camera (optical payload) field-of-view can be observed by an automatic flight maneuver. Third, the auto-landing controller is constructed for glide-slope tracking and the flare maneuver via adaptive backstepping design, and a flight path command generator is established for indirect altitude control in order to provide precise altitude trajectories. This kind of adaptive controller is used to control aircraft from glide-slope to flare by following the flight path angle command for indirect altitude control via elevator and maintaining the constant airspeed control via throttle. Fourth, the two flight-path angle command generators are investigated via adaptive backstepping controller. The landing profiles are shown by the parameters of the command generation to achieve desired touchdown performance, including pitch and altitude trajectories. Aside from theoretical development, numerous simulations and results analyses are provided to show the performance and effectiveness of the proposed controllers.
37
Wang, Jyhshing Jack. "Near-optimum guidance schemes for abort landing flight in a windshear." Thesis, 1988. http://hdl.handle.net/1911/13326.
Full textAbstract:
In this thesis, near-optimum guidance schemes for abort landing trajectories in a windshear are investigated. These near-optimum guidance schemes are based on the properties of the optimum trajectories. The survival capability in a severe windshear is studied. The optimal trajectories are used as ideal benchmarks against which the goodness of any guidance scheme can be measured.
38
"Training in a Modern Age." Master's thesis, 2019. http://hdl.handle.net/2286/R.I.53574.
Full textAbstract:
abstract: This study was undertaken to ascertain to what degree, if any, virtual reality training was superior to monitor based training. By analyzing the results in a 2x3 ANOVA it was found that little difference in training resulted from using virtual reality or monitor interaction to facilitate training. The data did suggest that training involving rich textured environments might be more beneficial under virtual reality conditions, however nothing significant was found in the analysis. It might be possible that significance could be obtained by comparing a virtual reality set-up with higher fidelity to a monitor trial.Dissertation/Thesis
Masters Thesis Engineering 2019
39
Matlala, Puseletso. "Design of a DDP controller for autonomous autorotative landing of RW UAV following engine failure." Thesis, 2016. http://hdl.handle.net/10539/23516.
Full textAbstract:
A dissertation submitted to the Faculty of Engineering and the Built Environment,
University of the Witwatersrand, Johannesburg, in partial fulfilment of the requirements
for the degree of Master of Science in Engineering.
Johannesburg, April 2016A Rotary Wing Unmanned Aerial Vehicle (RW UAV) as a platform and its payload consisting of sophisticated sensors would be costly items. Hence, a RW UAV in the 500 kg class designed to fulfil a number of missions would represent a considerable capital outlay for any customer. Therefore, in the event of an engine failure, a means should be provided to get the craft safely back on the ground without incurring damage or causing danger to the surrounding area. The aim of the study was to design a controller for autorotative landing of a RW UAV in the event of engine failure. In order to design a controller for autorotative landing, an acceleration model was used obtained from a study by Stanford University. FLTSIM helicopter flight simulation package yielded necessary RW UAV response data for the autorotation regimes. The response data was utilized in identifying the unknown parameters in the acceleration model. A Differential Dynamic Programming (DDP) control algorithm was designed to compute the main and tail rotor collective pitch and the longitudinal and lateral cyclic pitch control inputs to safely land the craft. The results obtained were compared to the FLTSIM flight simulation response data. It was noted that the mathematical model could not accurately model the pitch dynamics. The main rotor dynamics were modelled satisfactorily and which are important in autorotation because without power from the engine, the energy in main rotor is critical in a successful execution of an autorotative landing. Stanford University designed a controller for RC helicopter, XCell Tempest, which was deemed successful. However, the DDP controller was designed for autonomous autorotative landing of RW UAV weighing 560 kg, following engine failure. The DDP controller has the ability to control the RW UAV in an autorotation landing but the study should be taken further to improve certain aspects such as the pitch dynamics and which can possibly be achieved through online parameter estimation.
MT 2017
40
LIN, SHENG-HO, and 林勝和. "Analysis of wing structures with vertical takeoff and landing and rapid horizontal flight vehicle." Thesis, 2018. http://ndltd.ncl.edu.tw/handle/3c73pu.
Full textAbstract:
碩士建國科技大學
自動化工程系暨機電光系統研究所
106
In this paper, HYPERMESH∕LS-DYNA finite element analysis method was used, and the structural strength of the wing structures were predicted. Flight conditions of the vehicles were analyzed at 0, 30, 60, and 90 degrees and the strength analyzed from four different angles. Then, the changes and safety of the main structure of the wing of the vehicle discussed and studied. The results showed the adequacy of this vehicle. Hence, this paper can provide the reference basis for the development and design of the wing of any brand new vehicle.
41
Yang, Tzu-Chien, and 楊子健. "A Study on New Attack Helicopter with Unmanned Flight Vehicle System in Anti-landing Operations." Thesis, 2019. http://ndltd.ncl.edu.tw/handle/fy45zy.
Full textAbstract:
碩士崑山科技大學
資訊管理研究所
107
With the modernization of the Armed Forces in China, the CCP's technology is developing rapidly by the along of economic growth recently. Consequently, its weapons and equipments were evolving with each passing day. No matter from information, missiles, and space technology, it is far superior compared to the armed force. Especially, the CCP accelerated the missile's ability to project capability with the high precision after the Gulf War. The ability to anti-missile is an important part of high-tech for long-distance missile projection. In response to the military threats, this studt focuses on using the AH-64E attack helicopter combined with the UAS system to perform an anti-armor attack as follows: 1. How to preserve the combat power under the threat of enemy forces, missiles, air forces and other threats, by incorpotating AH-64E attack helicopter with unmanned aerial vehicle (UAV) system, to assist the commander recognize the whole battlefield. The solution makes it play an important role in defeating the enemy, which means first seeking the whole army and then defeating the enemy. 2. The army continuly gains the AH-64E attack helicopter and UH-60M universal. By incorporating helicopter with UAV information, communication advantages, and the AH-64E attack helicopter, it will expand the battlefield intelligence integration function, speed up the target timeliness and enhance the target strike capability, and make the land navigation operations more effective.
42
Lin, Jing-Hsyuan, and 林敬軒. "An Investigation of Flight Data via Modern Analysis Methods for Civil Transport During Landing Phase." Thesis, 2014. http://ndltd.ncl.edu.tw/handle/34061424713938455226.
Full textAbstract:
碩士淡江大學
航空太空工程學系碩士班
102
In this research, three flight data of Boeing747-400 including two normal and one abnormal are analyzed, which derived from Flight Operations Quality Assurance (FOQA), by using Wavelet Transform and Hilbert-Huang Transform methods. Considering the tremendous amount of relevant parameters involved, such as true airspeed, vertical speed, thrust, angle of attack, wind speed, wind direction, etc., we need to first decompose these engineering data to different frequencies inside the signals, observe their changes, and acquire valuable and meaningful flight interpretations. The main purpose for this work is to figure out unusual warning by contrasting with the analyses via two theoretical methods. In this study, we re-establish two-dimensional horizontal wind fields by data taken from Flight Data Recorder (FDR) via the equations of flight mechanics and the system of dead-reckoning. Then we could analyze parameters of wind speed and wind direction into HHT and Wavelet Transform formats. HHT is a modern tool for non-linear and non-stationary time series interpretation, and has a high-resolution spectrum compared to traditional methods for understanding background physical meaning. In the cases studied, HHT gave results much sharper than those from any of the traditional analytical methods in the time-frequency-energy representations. Moreover, traditional methods such as Fourier transform (FT) and short-time fast Fourier (STFT), utilizing fixed window to analyze frequencies in signal, but Wavelet Transform applying a dilation window function to fit the length of the data, and it really work out on decomposing from high-frequency to low-frequency oscillation in signals. Therefore, Wavelet Transform obtains more prominent results in the frequency domain. Data generated consequences of HHT and Wavelet method, compared with each other, in order to see clearly the results which were demonstrated. Comprehensive the interpretations of two methods combined with the report of Aviation Safety Council give us more precise analytical results in landing profile and physical phenomena. Moreover, our expectation is to obtain the "prediction warning message" which would pose a serious threat to flight safety before the occurrence of accident/incident from observing the abnormal parameters data set.
43
Hsu, Yen-Chuan, and 許炎泉. "The Difference between Pilot’s Stress Workload and Personality Trait during Landing Phase with Flight Simulator." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/30827478728356191102.
Full textAbstract:
碩士國立成功大學
工業與資訊管理學系專班
94
Flight is the three-dimensional motion which differs from human normal movement. It must monitor the environment changing and complex flight control system in all the time. The pilot experienced lots of mental workload in the routine flight. Upon emergency situation, the load became more and more. If the pilot could not handle properly, it would cause the flight accident. The domestic and foreign statistic data indicated that landing is the major phase which occurs an accident during the flight. So, the purpose in this study is to research 1) the pilot encounter factor (various environments, sudden event etc.) during landing phase, 2) the pilot bear the stress load and 3) personal difference. This study focused thirty two male pilots volunteered on the Air Force in-service. First, adopt 3 factor fixed effects model design, the environmental factors including visibility, crosswind and unexpected events by means of the simulator to duplicate flight situation. Electrocardiogram was recorded continuously during the experiment. And, using both physiological and multidimensional subjective-ratings measurements (heart rate and NASA Task Load Index, respectively), it explored the difference about the stress load during landing phase with three-way analysis of variance model. Second, it concluded the pilots’ personality traits trend according to Big-Five personality trait model and analyzed the stress load and personality traits difference during landing phase with one-way and two-way analysis of variance model. This result presented that Surgency and Conscientiousness are the high ratio in the service pilot personality traits. When encountering the sudden event and landing the operation, the pilots have the Surgency and Conscientiousness traits were no significance on mental workload. Effort, mental demand, and performance are valuably the important results in the NASA Task Load Index assessment. It performed the landing operation using Instrument Landing System during the landing phase, and crosswind and sudden event would be the main effect which caused the pilot mental workload difference in NASA Task Load Index and heart rate.
44
Wei, Hwang Jyh, and 黃志偉. "A Study on the Safe Operating Envelopes of a Helicopter/Ship Landing Set by Flight Qualities." Thesis, 2006. http://ndltd.ncl.edu.tw/handle/59744187163557853388.
Full textAbstract:
碩士國防大學中正理工學院
兵器系統工程研究所
94
In this thesis, the investigation of onboard helicopter flight safe operating envelopes in different kinds of sea conditions set by flying qualities during landing are of particular interest. This thesis includes five key steps: Firstly, incorporating the six degree-of-freedom equations of motion and the steady-state airwake on the flight deck, the helicopter/ship recovery model is established. Second, we analyse the influence of ship speed and wave cycle to the ship motions in different kinds of sea conditions. Third, three kinds of controller are designed by flight quality to simulate the driving technologies and experiences of the three levels of pilot. The Quickness Criteria flight qualities in ADS-33 are introduced to determine the closed loop poles. Fourth, we define the theoretical flight safe operating envelope of onboard helicopter and the simulation processes to determine the theoretical flight safe operating envelope for helicopter landing on a ship. Fifth, the differences of the theoretical flight safe operating envelopes in different kinds of sea conditions and controllers are studied. Finally, we use of Matlab in Virtual reality Toolbox to simulate the scene when a helicopter lands on a ship. This thesis is expected to be helpful to the pilot training, flight safety and analysis of the margin of the helicopter/ship flight safe operating envelope.
45
Klein-Miloslavich, Andreas. "Modeling, simulation, hardware development, and testing of a lab-scale airborne wind energy system." Thesis, 2020. http://hdl.handle.net/1828/11508.
Full textAbstract:
Airborne Wind Energy Systems (AWES) harness the power of high-altitude winds using tethered planes or kites. Continuous and reliable operation requires that AWES become autonomous devices, but the wind intermittency forces the system to repeatedly take-off to start, and land to shut-off. Therefore, a common approach to facilitate the operation is implementing Vertical take-off and landing (VTOL) functionality. This thesis models and simulates AWES flights working towards the implementation of flight controller hardware and autonomous operation of an AWES demonstrator platform.
The Ardupilot open-source autopilot platform provides a convenient tool for modeling, simulation, and hardware implementation of small-scale airplanes. An AWES lab-scale demonstrator was developed to obtain operational insight, get preliminary flight data, and real-world experience in this technology. A quadplane was developed by combining a structurally reinforced glider with VTOL and autopilot components. Its performance is obtained from static and aerodynamic studies and converted into the Ardupilot parameter format to define it in the simulation.
An AWES flight model was developed from the ground up to evaluate the performance of a simple flight controller in trajectory tracking. The Ardupilot Software-in-Loop (SIL) tool expands the simulation capabilities by running the flight controller code without requiring any hardware. This allowed controller tuning and flight plan evaluation with a more advanced fight model. AWES crosswind flight simulation was only possible due to the incorporation of an elastic tether and an ideal winch into the physics model. As a result, different trajectories and configurations were tested to find the optimal parameters that were uploaded to the flight controller board.
The operational capabilities of the AWES demonstrator were expanded with a flight testing campaign. By targeting individual objectives, each test gradually increased its complexity and ensured that the flight envelope was safely expanded. The results were validated with the simulation before moving on to the next flight test. The testing campaign is still underway due to challenges and limitations presented by the legal and logistical aspects of operating the quadplane. However, preliminary flight tests in VTOL mode have been completed and were consistent with the simulated results in terms of autonomous waypoint navigation and attitude control.Graduate
46
Chiu, Shin-yi, and 邱信誼. "Investigation of the Key Factors of Human Error with Multicriteria Analysis - Case study of the Maintenanse System for Landing Gear,Flight Operators and Engine." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/wgqfpm.
Full textAbstract:
碩士國立高雄第一科技大學
機械與自動化工程研究所
99
The study of human error in maintenance of the impact of Air Force aircraft, and landing gear systems, flight operations department and maintenance of the engine system operators is analyzed, the questionnaire structure is the core concept SHELL mode, the reason for classification of human error induced for the LS (people to software), LH (people to hardware), LE (people to the environment), L (of their own limitations), LL (people to people) in five dimensions and the layer is divided into 17 criteria, the use of multi-criteria decision analysis theory of AHP, CRITIC method, the standard deviation method and Grey method were seeking their weights, the weight of AHP by subjective analysis and found that the major factor inducing human error is the whole L (of their own restrictions) in the first place, which replaced the "staff of the psychological state of" maximum value for the weights, showing that psychological adjustment to staff the root causes of human errors induced. Supplemented by the objective weight CRITIC method, the standard deviation method and the weight of ash analysis of the implementation of related laws, there is a significant causal relationship exists, the gray relational method is obtained by "lack of equipment or hand tools," the first sort, showing that a lack of equipment, a great impact, maintenance staff to achieve the task, as must use non-standard hand tools to perform the repair, which will indirectly causing psychological stress, inconsistent with hand tools to perform the repair, construction quality be compromised, resulting in more effective, even derivative accident unfortunate.
47
Wang, Zion, and 汪錫恩. "A Study of Relative Risk Comparison on Runway Length of Major Airports in Taiwan Influencing the Flight Safety during Take-off and Landing Phases." Thesis, 2008. http://ndltd.ncl.edu.tw/handle/43777670667922928672.
Full textAbstract:
碩士國立成功大學
交通管理學系碩博士班
96
Runway overrun and excursion have always been the major causes of aircraft accidents during landing and take-off phases. According to the statistics of ASC, these types of accidents shared 8 out of 29 domestic accidents during 1997-2006, the highest number among all types of accidents. In order to improve the worldwide flight safety, ICAO emphasizes not only on preventing human errors and system failures but also on improving the safety of airports and air traffic services, which enlarge the conception of system safety from human, software, and hardware factors to environmental factors. Along with the evolution of concepts in flight safety and risk management, how to control risk within an acceptable level turns out to be quite significant in the idea of safety. The meaning of risk refers to “the likelihood of severity,” involving with the probability, exposure, and severity of events. Therefore, the ideal risk management lies on ordering the priority of events according to their exposure, severity and probability. However, because of the limitation of budget or financial resources, the authorities of civil aviation can’t focus on the development of “each” airport which results in imbalanced development of overall region or nation and inefficient utility of airports, thus “the plan of airport system,” related to the regional or national development, being much emphasized. In other words, different airports should undertake adequate risk assessment while increasing, expanding or maintaining facilities related to safety so that the capital and cost can be utilized efficiently, especially in the runway length and airport safety area in airside facilities, which will directly influence the flight safety during landing and take-off. The analyses of relative risk on runway length of major airports in Taiwan are according to the sum value of product of landing and take-off risk probability, exposure, and severity of different aircraft types of each airport in the year of 2006. In the aspect of risk probability, this research coordinates both Kirkland’s logistic regression model of landing overrun affected by the runway excess distance and Wong’s logistic regression model of takeoff/landing overrun sponsored by FAA in order to analyze aircraft overrun probability influenced by the runway distance available and runway distance required. The coefficients of the models are influenced by the rate of overall overrun accidents, the size and usage of different aircraft types, the average crosswind etc., and are transferred and localized according to the probability of overrun accidents occurred in Taiwan, aircraft types and airports. The runway distance available is affected by the different types of announced runway distance and runway end safety area (RESA); The runway distance required is affected by the types of aircrafts and engines, aircraft weights, the temperatures, elevations and headwinds of airports, the slopes and wet conditions of runway etc. Due to the difficulties of collecting the updated and micro data of all above-mentioned factors including accident and non-accident aircrafts, this research analyzes the risks of airports by the macro statistics or representative data. In the aspect of risk exposure, this research takes the numbers of departures and arrivals of each type of aircraft in each airport as its basis, and classifies the exposure by the time proportion of different slippery runway conditions. In the aspect of risk severity, this research converts the factors influencing severity of runway overrun as the sum of risk cost, such as the damage of aircraft, causalities of passengers and personnel, indemnification for baggage and cargos, and the loss of fuel etc., according to the average prices of aircrafts in international markets, the rates of hull-loss and substantial, the rates of fatalities and injuries, the indemnification regulated in international conventions and domestic regulations, and the price of fuel etc.