Journal articles: 'Aircraft controls'

1

Zhang, X., B. Xiong, and G. Kuang. "AIRCRAFT SEGMENTATION IN SAR IMAGES BASED ON IMPROVED ACTIVE SHAPE MODEL." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-3 (April 30, 2018): 2331–35. http://dx.doi.org/10.5194/isprs-archives-xlii-3-2331-2018.

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In SAR image interpretation, aircrafts are the important targets arousing much attention. However, it is far from easy to segment an aircraft from the background completely and precisely in SAR images. Because of the complex structure, different kinds of electromagnetic scattering take place on the aircraft surfaces. As a result, aircraft targets usually appear to be inhomogeneous and disconnected. It is a good idea to extract an aircraft target by the active shape model (ASM), since combination of the geometric information controls variations of the shape during the contour evolution. However, linear dimensionality reduction, used in classic ACM, makes the model rigid. It brings much trouble to segment different types of aircrafts. Aiming at this problem, an improved ACM based on ISOMAP is proposed in this paper. ISOMAP algorithm is used to extract the shape information of the training set and make the model flexible enough to deal with different aircrafts. The experiments based on real SAR data shows that the proposed method achieves obvious improvement in accuracy.

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Robinson, K. "Engine Controls for Integrated Aircraft Systems." Aircraft Engineering and Aerospace Technology 58, no. 4 (April 1986): 8–15. http://dx.doi.org/10.1108/eb036267.

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Wright, W. E., and J. C. Hall. "Advanced Aircraft Gas Turbine Engine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 561–64. http://dx.doi.org/10.1115/1.2906205.

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With the advent of vectored thrust, vertical lift, and fly-by-wire aircraft, the complexity of aircraft gas turbine control systems has evolved to the point wherein they must approach or equal the reliability of current quad redundant flight control systems. To advance the technology of high-reliability engine controls, one solution to the Byzantine General’s problem (Lamport et al., 1982) is presented as the foundation for fault tolerant engine control architecture. In addition to creating a control architecture, an approach to managing the architecture’s redundancy is addressed.

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Zikmund, Pavel, Lukáš Dubnický, Michaela Horpatzká, Miroslav Macík, and Ivo Jebáček. "Flight Test of Pilot-Aircraft Haptic Feedback System." MATEC Web of Conferences 304 (2019): 06005. http://dx.doi.org/10.1051/matecconf/201930406005.

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This research is focused on an innovative improvement of pilot-aircraft interaction and is targeted on small aircraft. Haptic feedback is performed by actuators mounted on an aircraft's controls. The purpose of the actuators on a control stick and pedals is stall warning and a pilot guiding to safe and economical flight regimes. The feedback system mediates airflow data as angles of attack and sideslip. The paper brings results of a flight test of the proposed system. Qualitative evaluation of the haptic feedback inflight is presented. Benefits of the system are presented on a sideslip during turning. Some recommendations for the haptic pilot-aircraft interaction are stated within the discussion of the flight test results.

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Zajdel, Albert, Cezary Szczepański, Mariusz Krawczyk, Jerzy Graffstein, and Piotr Masłowski. "Selected Aspects of the Low Level Automatic Taxi Control System Concept." Transactions on Aerospace Research 2017, no. 2 (June 1, 2017): 69–79. http://dx.doi.org/10.2478/tar-2017-0016.

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Abstract Taxiing of manned and remotely piloted aircraft is still performed by pilots without using a system of automatic control of direction and speed. Several reasons have emerged in recent years that make the automation of taxiing an important design challenge. The reasons are: decreased airport capacity due to the growing number of aircraft, poor ground operation conditions during poor visibility conditions, an increase in workload of pilots and air traffic controllers and the integration of simultaneous ground operations of manned and remotely piloted air vehicles. This paper presents selected aspects of the concept of a Low Level Automatic Taxi Control System. In particular, it emphasizes the means of controlling an aircraft during taxiing, accuracy requirements of the system and proposes control techniques. The resulting controller of the system is adaptable for different aircrafts. The actuators and their mechanical connections to available controls are the aircraft specific part and are designed for the particular type – in this case – a general aviation light airplane.

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Dos Santos, Guilherme P., Adriano Kossoski, Jose M. Balthazar, and Angelo Marcelo Tusset. "SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight." International Journal of Robotics and Control Systems 1, no. 2 (May 26, 2021): 131–44. http://dx.doi.org/10.31763/ijrcs.v1i2.329.

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This paper presents the design of the LQR (Linear Quadratic Regulator) and SDRE (State-Dependent Riccati Equation) controllers for the flight control of the F-8 Crusader aircraft considering the nonlinear model of longitudinal movement of the aircraft. Numerical results and analysis demonstrate that the designed controllers can lead to significant improvements in the aircraft's performance, ensuring stability in a large range of attack angle situations. When applied in flight conditions with an angle of attack above the stall situation and influenced by the gust model, it was demonstrated that the LQR and SDRE controllers were able to smooth the flight response maintaining conditions in balance for an angle of attack up to 56% above stall angle. However, for even more difficult situations, with angles of attack up to 76% above the stall angle, only the SDRE controller proved to be efficient and reliable in recovering the aircraft to its stable flight configuration.

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Bhardwaj, P., H. J. Kelley, and E. M. Cliff. "Aircraft Cruise Performance Optimization using Chattering Controls." IFAC Proceedings Volumes 20, no. 5 (July 1987): 175–80. http://dx.doi.org/10.1016/s1474-6670(17)55082-x.

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Stevens, B. L., F. L. Lewis, and F. Al-Sunni. "Aircraft flight controls design using output feedback." Journal of Guidance, Control, and Dynamics 15, no. 1 (January 1992): 238–46. http://dx.doi.org/10.2514/3.20824.

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Greshnikov, I. I. "Gaze Control Function Implementation in the Aircraft Cockpit Displays and Controls." INFORMACIONNYE TEHNOLOGII 27, no. 8 (August 11, 2021): 445–48. http://dx.doi.org/10.17587/it.27.445-448.

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The paper analyzes modern solutions applicable to advanced cockpit development using the gaze control function. Based on the analysis, the conclusion is made about the practicability of using the gaze control function and the intelligent information system is being developed for testing this function on the basis of universal cockpit prototyping bench.

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Ochi, Y. "Flight Control System Design for Propulsion-Controlled Aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 4 (April 1, 2005): 329–40. http://dx.doi.org/10.1243/095441005x30289.

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The loss of an aircraft's primary flight controls can lead to a fatal accident. However, if the engine thrust is available, controllability and safety can be retained. This article describes flight control using engine thrust only when an aircraft has lost all primary flight controls. This is a kind of flight control reconfiguration. For safe return, the aircraft must first descend to a landing area, decelerate to a landing speed, and then be capable of precise flight control for approach and landing. For these purposes, two kinds of controllers are required: a controller for descent and deceleration and a controller for approach and landing. The former controller is designed for longitudinal motion using a model-following control method, based on a linear quadratic regulator. The latter is designed by an H∞ state-feedback control method for both longitudinal and lateral-directional motions. Computer simulation is conducted using linear models of the Boeing 747. The results indicate that flight path control, including approach and landing, is possible using thrust only; however, speed control proves more difficult. However, if the horizontal stabilizer is available, the airspeed can be reduced to a safe landing speed.

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McLean, D. "Aircraft flight control systems." Aeronautical Journal 103, no. 1021 (March 1999): 159–66. http://dx.doi.org/10.1017/s0001924000064976.

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Abstract This paper presents a short account of the flight control systems used in commercial transport, military combat and general aviation aircraft. The effects of aircraft safety, reliability and weather delays on satisfactory aircraft operations are shown to be significant reasons for the extensive use of flight control systems. The principles of flight control, the sensors and actuators required and the various modes which can be selected are treated, together with a short account of the primary flying controls and the use of manual reversion in emergency situations. The paper concludes with a consideration of the fly-by-wire (FBW) and fly-fby-light concepts, and covers relaxed static stability, carefree manoeuvring and the use of canards before discussing some FBW flight control systems which are used in passenger aircraft.

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Guo, Dong, Min Xu, Shi Lu Chen, and Yu Qian. "A New Method for Modeling of Fully Flexible Aircrafts." Advanced Materials Research 383-390 (November 2011): 2350–55. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.2350.

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The purpose of this study is to produce a modeling capability for integrated flight dynamics of flexible aircraft that can better predict some of the complex behaviors in flight due to multi-physics coupling. Based on the studying of the exiting modeling approaches, the author put forward a new modeling method, and developed a new formulation integrating nonlinear rigid-body flight mechanics and linear aeroelastic dynamics for fully elastic aircrafts using Lagrangian mechanics. The new equations of motion overcome the disadvantages of the exiting methods, and include automatically all six rigid-body degrees of freedom and elastic information, the seamless integration is achieved by using the same reference frame and the same variables to describe the aircraft motions and the forces acting on it, including the aerodynamic forces. The formulation is modular in nature, in the sense that the structural model, the aerodynamic theory, and the controls method can be replaced by any other ones to better suit different types of aircraft.

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Elfitra Desifatma. "Electrical Wing Prototype Anti Icing pada Pesawat Komersil." Jurnal Jaring SainTek 2, no. 2 (October 29, 2020): 34–41. http://dx.doi.org/10.31599/jaring-saintek.v2i2.331.

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The accumulation of ice on the aircraft's wings can cause a decrease in the aerodynamic properties of the aircraft, increase in weight, and it is difficult to control the aircraft so that it affects aircraft safety. Icing handling on aircraft is growing. One of the newest systems being developed is electrical anti-icing. Therefore, the researcher designed a prototype of an anti-icing electrical wing on a commercial aircraft with advantages in terms of maintenance and lighter components. The purpose of making this prototype is to design an anti-icing electrical wing in the form of a prototype and can be used as an anti-icing. The prototype consists of three parts, namely input, control unit, and heating element. The heating element working system is by attaching the heating element to the surface of the wing, so when the tool is active through the controls, the heating element will work with an indication of the LED on. After testing the Prototype electrical anti-icing function that has been made, it can be used as a de-icing that removes icing that has already frozen on the leading edge.

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Brumbaugh, Randal W. "Aircraft model for the AIAA controls design challenge." Journal of Guidance, Control, and Dynamics 17, no. 4 (July 1994): 747–52. http://dx.doi.org/10.2514/3.21263.

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Retnowati, Nurcahyani Dewi, Yenni Astuti, and Supri Ermanto. "ANIMASI 3D PENDUKUNG SIMULASI FUNGSI FLIGHT CONTROLS DAN LANDING GEARS SUPRI SUKHOI SUPERJET 100." Conference SENATIK STT Adisutjipto Yogyakarta 1 (December 1, 2013): 93. http://dx.doi.org/10.28989/senatik.v1i0.43.

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Animations are one of multimedia technology which can accelerate the perspective about something, including the aircraft flight controls and landing gears function. Production process of animation on 3 Dimensional Aircraft model Supri Sukhoi Superjet 100 using NURBS Modelling method. Production process of animation on 3 Dimensional Aircraft model Supri Sukhoi Superjet 100 using Pre Production, Production and Post Production, that the result can be presented in the form of simulation video, Flash game, and Powerpoint game. The special effect that added into model, video and game make it more attractive. The Results are tested on number of respondents who are Experts in the Aircraft Engineering. The Data showed that Almost to 100 percent of the components and fuctions of the aircraft.

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Gallimore, Jennie J., James McCracken, and Janet Gerace. "Hardware and Human Factors Issues for Military Automatic Brightness Controls." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 39, no. 1 (October 1995): 89–92. http://dx.doi.org/10.1177/154193129503900121.

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Electronic displays have replaced many mechanical displays in aircraft. The “glass” cockpit continues to advance. Electronic displays required adjustment of luminance (often referred to as brightness) and contrast as the ambient environment changes. Requiring pilots to manually control brightness creates additional pilot workload. Instead, automatic brightness controls (ABCs) have been suggested. The purpose of this paper is to summarize a research plan for the development of an ABC for military aircraft.

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Anton, N., and R. M. Botez. "Weight functions method for stability analysis applied as design tool for Hawker 800XP aircraft." Aeronautical Journal 119, no. 1218 (August 2015): 981–98. http://dx.doi.org/10.1017/s0001924000004280.

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Abstract A new method for system stability analysis, the weight functions method, is applied to estimate the longitudinal and lateral stability of a Hawker 800XP aircraft. This paper assesses the application of the weight functions method to a real aircraft and a method validation with an eigenvalues stability analysis of the linear small-perturbation equations. The method consists of finding the weight functions that are equal to the number of differential equations required for system modelling. The aircraft’s stability is determined from the sign of the total weight function – the sign should be negative for a stable model. Aerodynamic coefficients and stability derivatives of the mid-size twin-engine corporate aircraft Hawker 800XP are obtained using the in-house FDerivatives code, recently developed at our laboratory of applied research in active controls, avionics and aeroservoelasticity LARCASE. The results are validated with the flight test data supplied by CAE Inc. for all considered flight cases. This aircraft model was chosen because it was part of a research project for FDerivatives code and continued with weight function method for stability analysis in order to develop a design tool, based only on the aircraft geometrical parameters for subsonic regime. The following flight cases are considered: Mach numbers = 0·4 and 0·5, altitudes = 3,000m, 5,000m, 8,000m and 10,000m, and angles-of-attack α = –5° to 20°.

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LEWIS, F. L., F. AL-SUNNI, and B. L. STEVENS. "Digital tracker with output feedback: application to aircraft controls." International Journal of Systems Science 25, no. 12 (December 1994): 2065–77. http://dx.doi.org/10.1080/00207729408949337.

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Lichota, Piotr. "Multi-Axis Inputs for Identification of a Reconfigurable Fixed-Wing UAV." Aerospace 7, no. 8 (August 5, 2020): 113. http://dx.doi.org/10.3390/aerospace7080113.

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Designing a reconfiguration system for an aircraft requires a good mathematical model of the object. An accurate model describing the aircraft dynamics can be obtained from system identification. In this case, special maneuvers for parameter estimation must be designed, as the reconfiguration algorithm may require to use flight controls separately, even if they usually work in pairs. The simultaneous multi-axis multi-step input design for reconfigurable fixed-wing aircraft system identification is presented in this paper. D-optimality criterion and genetic algorithm were used to design the flight controls deflections. The aircraft model was excited with those inputs and its outputs were recorded. These data were used to estimate stability and control derivatives by using the maximum likelihood principle. Visual match between registered and identified outputs as well as relative standard deviations were used to validate the outcomes. The system was also excited with simultaneous multisine inputs and its stability and control derivatives were estimated with the same approach as earlier in order to assess the multi-step design.

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Yomchinda, Thanan, Joseph F. Horn, and Jack W. Langelaan. "Modified Dubins parameterization for aircraft emergency trajectory planning." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 2 (August 6, 2016): 374–93. http://dx.doi.org/10.1177/0954410016638869.

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This paper presents a trajectory parameterization method for calculating emergency flight paths with variable airspeeds under conditions of constant wind. The method is based on the Dubins curve; however, it has been modified to allow for acceleration along the path and finite rate of change in turn rate. The aircraft’s planar trajectory from an initial condition to a terminal condition is parameterized into a small set of path-defining variables. The method uses a number of closed-form solutions and simple iteration schemes to efficiently calculate a path that meets the specified constraints. The parametrized path can then be optimized to minimize a performance objective for real-time emergency path planning. For emergency flight planning, the vertical degree of freedom is treated as a function of the aircraft state and parametric controls, and the optimization is formulated to ensure touchdown at a desired location and aircraft state. The performance of the proposed method is investigated using several test cases, including landing of a commercial jet following total loss of thrust and autorotative recovery of a utility helicopter following total loss of power.

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Crowther, W. J., P. I. A. Wilde, K. Gill, and S. M. Michie. "Towards Integrated design of fluidic flight controls for a flapless aircraft." Aeronautical Journal 113, no. 1149 (November 2009): 699–713. http://dx.doi.org/10.1017/s0001924000003365.

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Abstract Fluidic flight controls enable forces and moments for flight vehicle trim and manoeuvre to be produced without use of conventional moving surface controls. This paper introduces a methodology for the design of Circulation Control (CC) and Fluidic Thrust Vectoring (FTV) as fluidic controls for roll and pitch. Work was undertaken as part of the multidisciplinary FLAVIIR project, with the goal of providing full authority fluidic flight controls sufficient for a fully flapless flight of an 80kg class demonstrator aircraft known as DEMON. The design methodology considers drag, mass, volume and pneumatic power requirements as part of the overall design cost function. It is shown that the fundamental flow physics of both CC and FTV are similar, and hence there are strong similarities to the design approach of each. Flight ready CC and FTV hardware has been designed, manufactured and ground tested. The CC system was successfully wind tunnel demonstrated on an 85% scale half model of the DEMON. The design condition of a control ΔCL of 0·1 was achieved with a blowing coefficient of 0·01, giving a useable control gain of 10. The FTV system was static tested using a micro gas turbine source. The control characteristic was ‘N’ shaped, consisting of an initial high gain response in a negative sense (gain = −30) followed by a low gain response in a positive sense (gain = +3) at higher blowing rate. CC and FTV control hardware directly contributes to around 6% to the overall mass of the flight vehicle, however provision of pneumatic power carries a significant mass penalty unless generated as part of an integrated engine bleed system.

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Tishchenko, Aramis Viktorovich, Anatoly Mikhailovich Kulabukhov, and Victor Alexandrovich Masalskiy. "SYNTHESIS OF AN ADAPTIVE AUTOMATIC SYSTEM OF AIRCRAFT CONTROLS WITH MULTIDIMENSIONAL PI-REGULATOR." Journal of Rocket-Space Technology 27, no. 4 (December 30, 2019): 79–85. http://dx.doi.org/10.15421/51913.

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The article presents the synthesis of a functional diagram of an adaptive automatic control system (ACS) for controlling an aircraft with an automatically reconfigurable multidimensional PI controller, which provides the minimum static and minimum mean square error of control with minimal energy consumption for the formation of the control exposure. The synthesis of ACS algorithms is performed as a result of solving the problem of conditionally minimizing the quadratic functional of the generalized work (taking into account restrictions on state variables and control actions given by differential equations of the control object (CO) and inequalities). The mathematical description of the multidimensional CO is carried out using the CO model in the state space, which automatically takes into account the mutual influence of individual control loops on each other. As the state variables of the aircraft, linear displacements, speeds and accelerations of the center of mass of the aircraft, and angular displacements, speeds and accelerations of the rotational movement of the aircraft relative to the center of mass are used. The matrix equation of dynamics of the aircraft is formed by a system of nonlinear differential equations of the first order of forces and moments of forces acting on the aircraft. To ensure the minimum static control error, integrators are included in the ACS (for each control action). The algorithm for the formation of control actions of the extended CO, providing the declared properties of the ACS, is obtained as a result of solving the problem of conditional minimization of the generalized work functional. The task of conditional minimization of a functional with constraints is performed by the maximum principle. The resulting two-point boundary value problem is transformed by the invariant immersion method into a Cauchy problem for optimal values of state variables. The evaluation of the characteristics of a specific adaptive ACS for the spacecraft is expected to be obtained as a result of further research by mathematical modeling.

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Bäuerle, N., O. Engelhardt-Funke, and M. Kolonko. "ROUTING OF AIRPLANES TO TWO RUNWAYS: MONOTONICITY OF OPTIMAL CONTROLS." Probability in the Engineering and Informational Sciences 18, no. 4 (October 2004): 533–60. http://dx.doi.org/10.1017/s0269964804184088.

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We consider the problem of routing incoming airplanes to two runways of an airport. Due to air turbulence, the necessary separation time between two successive landing operations depends on the type of airplane. When viewed as a queuing problem, this means that we have dependent service times. The aim is to minimize the waiting times of aircrafts. We consider here a model in which arrivals form a stochastic process and the decision-maker does not know anything about future arrivals. We formulate this as a problem of stochastic dynamic programming and investigate the monotonicity of optimal routing strategies with respect to the workload of the runways, for example. We show that an optimal strategy is monotone (i.e., of switching type) only in a restricted case where decisions depend on the state of the runways only and not on the type of the arriving aircraft. Surprisingly, in the more realistic case where this type is also known to the decision-maker, monotonicity need not hold.

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Eklund, J. Mikael, and Michael J. Korenberg. "Simulation of Aircraft Pilot Flight Controls Using Nonlinear System Identification." SIMULATION 75, no. 2 (August 2000): 72–81. http://dx.doi.org/10.1177/003754970007500201.

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Stroman, Richard O., and Aaron Kahn. "Development and Integration of Controls for a PEMFC Powered Aircraft." ECS Transactions 11, no. 1 (December 19, 2019): 1493–504. http://dx.doi.org/10.1149/1.2781062.

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Seng, Gary T. "Overview of NASA research in fiber optics for aircraft controls." ISA Transactions 28, no. 2 (January 1989): 25–29. http://dx.doi.org/10.1016/0019-0578(89)90037-2.

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Chen, Jie, Senyao Chen, Cunbao Ma, Zhengdong Jing, and Qingshan Xu. "Fault Detection of Aircraft Control System Based on Negative Selection Algorithm." International Journal of Aerospace Engineering 2020 (November 4, 2020): 1–10. http://dx.doi.org/10.1155/2020/8833825.

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The aircraft control system controls the whole flight movement process. Its fault detection can assist the aircraft PHM system in making decisions and completing the targeted maintenance, which is of great significance to improve the safety and reliability of the aircraft. In this paper, by taking advantage of the strong leaning and intelligent recognition ability and the characteristic of less information required in the negative selection artificial immune system, a fault detection method is proposed for aircraft control system based on negative selection algorithm. Basically, after extracting the fault characteristics from the aircraft flight parameters, the negative selection module is utilized to generate fault detectors to monitor the aircraft control system. Afterward, the hypothesis test is introduced to evaluate the detector coverage more efficiently, and the detector cover area is optimized by applying geometric mathematics in the optimization of the detector center position and radius. The method is verified by simulation of a certain aircraft control system, and the results show that it has a good detection effect on the system faults.

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Khairuddin, Ismail Mohd, Anwar P. P. A. Majeed, Ann Lim, Jessnor Arif M. Jizat, and Abdul Aziz Jaafar. "Modelling and PID Control of a Quadrotor Aerial Robot." Advanced Materials Research 903 (February 2014): 327–31. http://dx.doi.org/10.4028/www.scientific.net/amr.903.327.

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This paper elucidates the modeling of a + quadrotor configuration aerial vehicle and the design of its attitude and altitude controllers. The aircraft model consists of four fixed pitch angle propeller, each driven by an electric DC motor. The hovering flight of the quadrotor is governed by the Newton-Euler formulation. The attitude and altitude controls of the aircraft were regulated using heuristically tuned (Proportional-Integral-Derivative) PID controller. It was numerically simulated via Simulink that a PID controller was sufficient to bring the aircraft to the required altitude whereas the attitude of the vehicle is adequately controlled by a PD controller.

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Lee, R. N. "Development of Active Control Technology for the Next Generation of Combat Aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 206, no. 1 (January 1992): 15–25. http://dx.doi.org/10.1243/pime_proc_1992_206_235_02.

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In the mid 1970s British Aerospace recognized that active control technology offered considerable benefits in terms of improved performance and combat effectiveness for future combat aircraft. However, the introduction of such technology carried with it a significant development risk. In order to minimize that risk, a series of flight demonstrator programmes were initiated. This paper describes the principles of active control and the very successful fly-by-wire Jaguar and experimental aircraft demonstrator flight test programmes which progressively demonstrated the viability and benefits of active controls to the extent that this technology is being fully utilized on the new European fighter aircraft.

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Davies, W. J., and R. W. Vizzini. "Engine Control Reliability and Durability Improvement Through Accelerated Mission Environmental Testing." Journal of Engineering for Gas Turbines and Power 109, no. 2 (April 1, 1987): 142–45. http://dx.doi.org/10.1115/1.3240016.

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The integration of aircraft control systems for future weapon systems will require the engine control system to meet the mission reliability of the flight control system. This will be accomplished through system redundancy and verified by accelerated environmental testing. Combined environment reliability testing (CERT) will assure control system structural integrity and reliability growth of engine-mounted digital electronic controls. Pratt & Whitney, under contract to the U.S. Navy, has recently completed a 10,000-hr CERT program. Dual full authority digital electronic controls (FADEC), connected by a fiber optic data link, were subjected to environmental tests simulating a composite F-14 mission profile. The FADEC units were also exposed to periodic high vibration levels which would be experienced after foreign object damage and salt spray testing to simulate aircraft carrier environment. The test results are reported herein providing insight not only into the reliability and durability of digital electronic controls but also into the equipment and procedures required for testing of future military and commercial engine control systems.

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Steer, A. J. "Design criteria for conceptual sizing of primary flight controls." Aeronautical Journal 108, no. 1090 (December 2004): 629–41. http://dx.doi.org/10.1017/s0001924000000464.

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Abstract The European Supersonic Commercial Transport’s control surface configuration is based largely on Concorde’s and has been scaled to provide comparable un-augmented stability and manoeuvre performance. Hence, optimising the surface size could provide significant performance benefits in terms of reduced drag, noise, structural and actuator power requirements. Adequate control power will be required to meet current civil aviation regulations whose primary aim is to ensure the aircraft can be flown safely during both normal and emergency operation. Additional design criteria, combined with the optimum longitudinal control laws, are required to ensure desirable handling qualities with minimum pilot workload. Two critical low-speed flight conditions, normal and emergency, together with associated aircraft configurations for control surface sizing have been identified. The rudder must provide sufficient control power to achieve positive heading changes subsequent to a double asymmetric engine failure during normal operation. The fin should be sized to satisfy Dutch roll stability criteria with the un-augmented aircraft in its emergency configuration. The dual functionality of the elevons require that they are sized using both pitch and roll performance and handling quality criteria. The bank angle capture requirement provides the most critical elevon design case, the satisfaction of which also ensures adequate pitch control power. Validation using ‘pilot-in-the-loop’ simulation will be required whilst more explicit control surface size optimisation would require the definition of limiting airspeeds and operating conditions applicable to the European Supersonic Commercial Transport. Additional studies of control power requirements during transonic and supersonic cruise may also be required.

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Aust and Pons. "Bowtie Methodology for Risk Analysis of Visual Borescope Inspection during Aircraft Engine Maintenance." Aerospace 6, no. 10 (October 2, 2019): 110. http://dx.doi.org/10.3390/aerospace6100110.

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Background—The inspection of aircraft parts is critical, as a defective part has many potentially adverse consequences. Faulty parts can initiate a system failure on an aircraft, which can lead to aircraft mishap if not well managed and has the potential to cause fatalities and serious injuries of passengers and crew. Hence, there is value in better understanding the risks in visual inspection during aircraft maintenance. Purpose—This paper identifies the risks inherent in visual inspection tasks during aircraft engine maintenance and how it differs from aircraft operations. Method—A Bowtie analysis was performed, and potential hazards, threats, consequences, and barriers were identified based on semi-structured interviews with industry experts and researchers’ insights gained by observation of the inspection activities. Findings—The Bowtie diagram for visual inspection in engine maintenance identifies new consequences in the maintenance context. It provides a new understanding of the importance of certain controls in the workflow. Originality—This work adapts the Bowtie analysis to provide a risk assessment of the borescope inspection activity on aircraft maintenance tasks, which was otherwise not shown in the literature. The consequences for maintenance are also different compared to flight operations, in the way operational economics are included.

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Rohacs, Jozsef, Istvan Jankovics, and Daniel Rohacs. "Less-skilled pilot decision support." Aircraft Engineering and Aerospace Technology 91, no. 5 (May 13, 2019): 790–802. http://dx.doi.org/10.1108/aeat-12-2017-0269.

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PurposeThe purpose of this paper is to overview the systems and their elements developing for supporting the less-skilled pi-lots.Design/methodology/approachSeveral European (like EPATS, SAT-Rdmp, Pplane, Esposa, Clean Sky2) and national projects (NASA SATS, Hungarian SafeFly) develop the personal/small aircraft and personal/small aircraft transportation systems. The projects had analysed the safety aspects, too, and they underlined the aircraft will be controlled by so-called less-skilled pilots (owners, renters), having less experiences. The paper defines the cross-connected controls, introduces the methods of subjective analysis in pilot decision processes, improves the pilot workload model, defines the possible workload management and describes the developing pilot decision support system.FindingsAnalysing the personal/small aircraft safety aspects, a unique and important safety problem induced by less-skilled pilots has been identified. The considerable simplification of the air-craft control system, supporting the pilot subjective decisions and introducing the pilot work-load management, may eliminate this problem.Research limitations/implicationsOnly the system elements have been used in concept validation tests.Practical implicationsThe developing pilot supporting system in its general form has on - board and ground sub-systems, too, except a series of elements integrated into the pilot cockpit environment and control system. Several system elements (sensors, integrated controls, etc.) might be implement now, but the total system need further studies. The subjective decision process needs further development of the methodology and concept validation.Social implicationsThe system may catalyse the society acceptance of the personal aircraft and their safer piloting, applicability.Originality/valueThe paper introduces an original supporting system for less-skilled pilots.

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Chen, Quanlong, Shanyong Zhao, Ke Lu, Senkui Lu, Chunsheng Liu, and Renliang Chen. "The Investigation on L 1 Adaptive Control of the Tilt-Rotor Aircraft." International Journal of Aerospace Engineering 2021 (June 19, 2021): 1–13. http://dx.doi.org/10.1155/2021/9912618.

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Considering the uncertainty of the flight dynamics model of the tilt-rotor aircraft in different flight modes, an L 1 adaptive controller for full flight modes control system of tilt-rotor aircraft is designed. Taking advantage of the separation of robustness and adaptive design of the L 1 adaptive controller, adaptive gain, and low-pass filter are designed to achieve the desired control performance and meet the requirements of flight quality. The simulations of XV-15 tilt-rotor aircraft in helicopter mode and airplane mode are carried out. Then, the simulation of conversion mode is further carried out. The results show that the tilt-rotor aircraft can track the reference signal well under the L 1 control system. In addition, the changes of states as well as controls in conversion mode flight are quite smooth which is very meaningful for engineering application.

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Chrif, Labane, Zemalache Meguenni Kada, and Tahar Mohamed. "Flight-Path Tracking Control of an Aircraft Using Backstepping Controller." TELKOMNIKA Indonesian Journal of Electrical Engineering 15, no. 2 (August 1, 2015): 270. http://dx.doi.org/10.11591/tijee.v15i2.1539.

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For transportation aircraft, the primary control objective for an autopilot system engaged during approach and landing is relative to the flight path tracking on the basis of highly simplified linear models of flight dynamics. The dynamics governing the flight path of an aircraft are in general highly nonlinear and involve complex physics for which no accurate models are available. In this paper a nonlinear model describing the longitudinal equations of motion in strick feedback form is derived. Backstepping is utilized for the construction of a globally stabilizing controller with a number of free parameters. It is implemented a controller with an internal loop controls involving the pitch rate of the aircraft and an external loop which includes angle of attack, path angle and pitch angle. Finally, nonlinear simulation results for a longitudinal model of a transportation aircraft are displayed and discussed.

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Szczepankowski, Andrzej, and Janusz Szymczak. "Initiation of Damage to the Hot Part of Aircraft Turbine Engines." Research Works of Air Force Institute of Technology 38, no. 1 (August 1, 2016): 61–74. http://dx.doi.org/10.1515/afit-2016-0006.

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Abstract In the paper, the initiation causes of damage to flame tubes of a basic combustion chamber and turbine units, which are the most common in the operation process of aircraft turbine engines (ATE), were presented. They were illustrated with the use of numerous examples of progressing degradation of the surface condition of parts and components of various types of aircraft engines which was found during endoscopic controls. On the basis of the systematic observation results, the process of destruction of the turbine rotor ring blades’ surface was discussed. The attention was paid to the current and still valid evaluation of the aircraft turbine engine’s suitability for further operation, taking into account the specifics of its use.

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MATSUSHITA, Hiroshi. "Active Controls of Aircraft Structural Modes(Semsing and Active Control Technology in Recent Dynamic Problems)." Journal of the Society of Mechanical Engineers 89, no. 811 (1986): 662–67. http://dx.doi.org/10.1299/jsmemag.89.811_662.

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Kopasakis, George, John C. DeLaat, and Clarence T. Chang. "Adaptive Instability Suppression Controls Method For Aircraft Gas Turbine Engine Combustors." Journal of Propulsion and Power 25, no. 3 (May 2009): 618–27. http://dx.doi.org/10.2514/1.36777.

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YOSHIDA, Hirokazu, and Shinya SATO. "THE TECHNOLOGY TREND AND PERSPECTIVE OF HYDRAULICS IN AIRCRAFT FLIGHT CONTROLS." Proceedings of the JFPS International Symposium on Fluid Power 2008, no. 7-1 (2008): 161–64. http://dx.doi.org/10.5739/isfp.2008.161.

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Yu, Minghui, Xue Gong, Guowei Fan, and Yu Zhang. "Trajectory Planning and Tracking for Carrier Aircraft-Tractor System Based on Autonomous and Cooperative Movement." Mathematical Problems in Engineering 2020 (June 13, 2020): 1–24. http://dx.doi.org/10.1155/2020/6531984.

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The solution of how to plan out the cooperative moving trajectory autonomously and control the motion of carrier-based aircraft timely and accurately is the key to helping improve the overall deck operation efficiency. The main problem discussed in this article is coordinated trajectory planning strategy for multicarrier aircraft and cooperative control between tractor and carrier aircraft. First, the kinematic model and three-degree-of-freedom dynamics model of the towbarless traction system are established. Then, a coevolution mechanism for aircraft systems is proposed to ensure coordinated trajectory planning among multiple aircraft and a trajectory adapted to the tractor-aircraft system is generated based on the hybrid RRT∗ algorithm. Next, a double-layer closed-loop controller is designed for the trajectory tracking of the tractor-aircraft system on the deck under the constraints of incomplete constraints and various physical conditions. It includes an outer model predictive controller which effectively controls the cooperative motion between the carrier aircraft and tractor and an inner torque control strategy based on adaptive fuzzy PID control which strictly ensures the stability of the system. Simulation results demonstrate that the controller is more rapid, more accurate, and more robust in tracking line trajectory with initial deviation, sine curve with large curvature, and complex trajectories on decks compared with backstepping control and LQR algorithm.

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Miwa, Masafumi, Shinji Uemura, and Akitaka Imamura. "Arbitrary Attitude Hovering Control of Quad Tilt Rotor Helicopter." Journal of Robotics and Mechatronics 28, no. 3 (June 17, 2016): 328–33. http://dx.doi.org/10.20965/jrm.2016.p0328.

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[abstFig src='/00280003/08.jpg' width=""300"" text='Arbitrary attitude hovering' ] The quad tilt rotor helicopter (QTRH), a tilt-rotor aircraft prototype, has fixed wings for long-range high-speed flight. Its rotor-tilt mechanism controls 4 rotor-tilt angles independently and controls its roll and pitch angles similarly to a multirotor helicopter. It controls yaw angle by thrust vectoring and moves forward and backward by tilting its rotors. Rotor-tilting maneuvers are the initial stage of flight-mode transition between helicopter and fixed-wing modes.

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Tomlinson, S. P., and D. G. Tilley. "Computer Modelling of Aircraft Hydraulic Systems Using Bathfp." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 2 (July 1993): 139–43. http://dx.doi.org/10.1243/pime_proc_1993_207_258_02.

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The computer simulation package BATHfp has been developed at the Fluid Power Centre, University of Bath to perform transient time domain simulations of fluid power systems. Utilities are provided which allow new models to be introduced into the component database. This enables the package to be tailored to particular dedicated areas of interest such as aircraft flight controls, braking and landing gear and fuel flow systems. This paper describes the application of BATHfp to aircraft hydraulic systems. An example is taken of an electrohydraulic position control system which uses an actuator to move an aileron according to a desired schedule. Parametric variations are made to illustrate how system performance can be improved.

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Донець, Олександр Дмитрович, and Володимир Олександрович Кудрявцев. "ОСОБЛИВОСТІ ЗАБЕЗПЕЧЕННЯ АЕРОДИНАМІЧНИХ ХАРАКТЕРИСТИК РЕГІОНАЛЬНОГО ПАСАЖИРСЬКОГО ЛІТАКА." Open Information and Computer Integrated Technologies, no. 83 (May 23, 2019): 106–33. http://dx.doi.org/10.32620/oikit.2019.83.08.

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Principal results of the computational and research work performed during development of a regional passenger aircraft to ensure its aerodynamic characteristics are given. When creating the An-148-100/An-158 family of aircraft, such level of the aircraft aerodynamic perfection was achieved, which ensured fulfillment of the specified requirements for their flight performance – maximum speed, cruising flight altitude and flight range with different payloads. The developed aerodynamic configuration made it possible to create a family of regional passenger high-wing planes with a flight speed of up to 870 km/h (true speed) (M = 0.8), which have no analogues in the world aviation industry. Developed for the An-148-100 / An- 158 aircraft, supercritical profiles of the new generation with a large maximum relative thickness formed the basis of the aerodynamic configuration of a high-speed wing with moderate sweep. The aircraft lift-to-drag ratio in cruise flight is Kcruise = 15.8, which corresponds to the worldwide values. Developed aerodynamic configuration of the wing high-lift devices provides high bearing properties of the wing during take-off and landing stages, which allows to fully meet the requirements for the runway required length of the base airfields Lrun = 1485...1950 m. Developed algorithms are implemented in the electric remote control system and provide necessary standard characteristics of stability, controllability and flight dynamics in the main control mode. Selected margins of the aircraft’s own static stability and effectiveness of its controls ensure safe completion of the flight in standby control mode. The certification flight tests of the An-148-100/An-158 airplanes confirmed full compliance of their take-off and landing performance, as well as the stability, controllability and flight dynamics characteristics with the requirements of the Certification basis in both standard and in failure situations tested in flight tests. Necessary and sufficient amount of experimental work was conducted in the lowspeed and high-speed wind tunnels of the ANTONOV SC and TsAGI to verify the aerodynamic and spin characteristics of the An-148-100/An-158 airplane models, which improved the aerodynamic configuration of the aircraft and its individual units and allowed to apply the work results in calculation of aircraft strength, as well as for development of their systems.

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Campa, G., S. Wan, M. R. Napolitano, B. Seanor, and M. L. Fravolini. "Design of formation control laws for manoeuvred flight." Aeronautical Journal 108, no. 1081 (March 2004): 125–34. http://dx.doi.org/10.1017/s0001924000151577.

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Abstract This paper presents identification, control synthesis and simulation results for an YF-22 aircraft model designed, built, and instrumented at West Virginia University. The ultimate goal of the project is the experimental demonstration of formation flight for a set of 3 of the above models. In the planned flight configuration, a pilot on the ground maintains controls of the leader aircraft while a wingman aircraft is required to maintain a pre-defined position and orientation with respect to the leader. The identification of both a linear model and a nonlinear model of the aircraft from flight data is discussed first. Then, the design of the control scheme is presented and discussed with an emphasis on the amount of information, relative to the leader aircraft, needed by the wingman to maintain formation. Using the developed nonlinear model, the control laws for a maneuvered flight of the formation are then simulated with Simulink® and displayed with the Virtual Reality Toolbox®. Simulation studies have been performed to evaluate the effects of specific parameters and the system robustness to atmospheric turbulence. The conclusions from this analysis have allowed the formulation of specific guidelines for the design of the electronic payload for formation flight.

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Ghiţescu, Ion-Marius, Maria Luminita Scutaru, Marilena Ghiţescu, Paul Nicolae Borza, and Marin Marin. "New Command Mechanism of Flaps and Wings of a Light Sport Aircraft." Symmetry 13, no. 2 (January 29, 2021): 221. http://dx.doi.org/10.3390/sym13020221.

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Commercial aircraft have well-designed and optimized systems, the result of a huge experience in the field, due to the large fleet of aircraft in operation. For light, utility, or sports aircraft, with a multitude of shapes, tasks, and construction types, there are different solutions that seek to best meet the requirements of the designed aircraft. In this sense, for a sport plane, an increased maneuverability is desired, and the system that controls flaps and wing must be properly designed. A new flap mechanism command solution is proposed and justified in the paper, for use in sports and recreational aviation, in order to achieve angles of braking greater than 40°, take-off and landing in a shorter time and over a shorter distance, as well as the gliding of the aircraft in critical flight conditions or when fuel economy is needed. A finite element model is used to verify the optimized command system for the flap and wing and to check if the strength structure of the aircraft is properly designed. The main result consists of the new design command system for flaps and wings and in verifying, by calculation, the acceptability of the new mechanism proposed from the point of view of the strength of the materials.

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Bennoud, Salim, and Zergoug Mourad. "The Non Destructive Testing Methods Applied to Detect Cracks in the Hot Section of a Turbojet." Applied Mechanics and Materials 61 (June 2011): 79–83. http://dx.doi.org/10.4028/www.scientific.net/amm.61.79.

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All aircraft whatever they are; are regularly audited. These controls are mainly visual and external; other controls such as "major inspection" or "general revisions” are more extensive and require the dismantling of certain parts of the aircraft. Some parts of the aircraft remain inaccessible and are therefore more difficult to inspect (compressor, combustion chamber, and turbine). The means of detection must ensure controls either during initial construction, or at the time of exploitation of all the parts. The Non destructive testing (NDT) gathers the most widespread methods for detecting defects of a part or review the integrity of a structure. The aim of this work is to present the different (NDT) techniques and to explore their limits, taking into account the difficulties presented at the level of the hot part of a turbojet, in order to propose one or more effective means, non subjective and less expensive for the detection and the control of cracks in the hot section of a turbojet. To achieve our goal, we followed the following steps: - Acquire technical, scientific and practical basis of magnetic fields, electrical and electromagnetic, related to industrial applications primarily to electromagnetic NDT techniques. - Apply a scientific approach integrating fundamental knowledge of synthetic and pragmatic manner so as to control the implementation of NDT techniques to establish a synthesis in order to comparing between the use of different methods. - To review recent developments concerning the standard techniques and their foreseeable development: eddy current, ultrasonic guided waves ..., and the possibility of the implication of new techniques.

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Rosenblad, L. E. "Evaluation of Control Techniques for Aircraft Propulsion Systems." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 229–32. http://dx.doi.org/10.1115/1.2906167.

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This paper discusses the evaluation of modern controls for aircraft propulsion systems. Modern control techniques offer potential advantages over classical approaches. The benefits of multivariable optimization and guaranteed robustness are becoming increasingly attractive as aircraft become more highly integrated and complex. However, validation of modern control techniques has remained theoretical and applications have been restricted to the laboratory. To apply these techniques, the airframer must establish means to understand, evaluate, and verify them. Douglas has established an approach based on digital computer simulation facility to meet these ends. The major elements of this facility are: real-time dynamic system simulation; multivariable compensator generation; and hardware-in-the-loop closure. The facility is intended to serve as a stepping stone to flight test capability while retaining design and test flexibility. Features such as sensor synthesis and noise injection will ensure applicability to real-world implementation. This facility is being used in the evaluation of an integrated secondary system.

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Richter, Hanz. "Multiple Sliding Modes with Override Logic: Limit Management in Aircraft Engine Controls." Journal of Guidance, Control, and Dynamics 35, no. 4 (July 2012): 1132–42. http://dx.doi.org/10.2514/1.55922.

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Rahman, Naveed U., and James F. Whidborne. "Propulsion and Flight Controls Integration for a Blended-Wing-Body Transport Aircraft." Journal of Aircraft 47, no. 3 (May 2010): 895–903. http://dx.doi.org/10.2514/1.46195.

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Castilho, Diogo Silva, Ligia M. S. Urbina, and Donizeti de Andrade. "STPA for continuous controls: A flight testing study of aircraft crosswind takeoffs." Safety Science 108 (October 2018): 129–39. http://dx.doi.org/10.1016/j.ssci.2018.04.013.

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Journal articles on the topic 'Aircraft controls'

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