Relevant bibliographies by topics / Launch vehicle navigation testing

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Launch vehicle navigation testing'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Launch vehicle navigation testing"

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Driscoll, Frederick R., Pierre-Philippe J. Beaujean, and William A. Venezia. "Development and Testing of an A-Sized Rapidly Deployable Navigation and Communication GATEWAY Buoy." Marine Technology Society Journal 40, no. 1 (March 1, 2006): 36–46. http://dx.doi.org/10.4031/002533206787353600.

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A rapidly deployable, intelligent GATEWAY buoy system, capable of both air and sea deployment, has been developed to aid in the navigation and communication of Autonomous Underwater Vehicles (AUVs). The device is based around the A-sized (sonobuoy) standard and is deployable from aircraft, helicopters, ships and submarines using pressure and gravity launch tubes or charge-activated devices. The system consists of Florida Atlantic University (FAU) and Woods Hole Oceanographic Institute (WHOI) acoustic modems, both capable of providing Long Base Line (LBL) positioning, Global Positioning System (GPS) Wide Area Augmentation System (WAAS), and Radio Frequency (RF) communications. It utilizes a combined parachute and anchor, a low drag inflatable buoy, and an intelligent scope-adjusting mooring line spool. The design is based around a “fire-and-forget” methodology which, when the system is turned on and launched, requires no initial knowledge of the operating environment. The interoperable acoustic communication (ACOMMS) system can be operated at ranges up to 3000 meters and can achieve a true data rate of up to 860 bits-per-second using reliable spread-spectrum frequency modulation. The LBL positioning system operates sequentially and does not preclude acoustic communications. Switching between protocols (FAU or WHOI) is achieved through an automated process or is requested via RF commands. The mechanical system is modular and compact. The system is capable of operating in depths between 5 m and 200 m, in conditions up to sea state 3, and in currents up to 1.5 m/s. The mooring is versatile and able to hold in bottom types ranging from mud and sand to broken rock and reef.
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Zosimovych, Nickolay, Niu Xiaodong, Alex Noel Joseph Raj, Alessandro Simeone, and Xiongbin Peng. "Integrated Guidance System of a Commercial Launch Vehicle." MATEC Web of Conferences 179 (2018): 03002. http://dx.doi.org/10.1051/matecconf/201817903002.

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This paper proposes a concept of integrated on-board navigation systems for commercial launch vehicles in the context of the current task, and provided mathematical models of its elements for different variants of designing structure and composition. Has been set and simulated the technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to insert small artificial Earth satellites into low and medium circular orbits with application of GPS technologies.
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Hassani, Mehdi, Jafar Roshanian, and A. Majid Khoshnood. "A reliable analytical navigation system based on symmetrical dynamic behavior of control channels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 1 (October 2, 2016): 190–99. http://dx.doi.org/10.1177/0954410016664917.

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This study develops an advanced fault recovery strategy to improve the reliability of an aerospace launch vehicle navigation system. The proposed strategy contains fault detection features and can reconfigure the system against common faults in the aerospace launch vehicle navigation system. For this purpose, fault recovery system is constructed to detect and reconfigure normal navigation faults operating as a soft sensor, based on the symmetrical dynamic behavior of the yaw and pitch channels of the vehicle. In the face of pitch channel sensor failure, the Auto Regression Exogenous model of the yaw channel of the vehicle is identified using the recursive instrumental variable methodology. Based on the symmetrical behavior of the aerospace launch vehicle in the yaw and pitch channels, the Auto Regression Exogenous model of the yaw channel is substituted by the dynamic model of the pitch one and consequently, the pitch-rate gyroscope output is constructed to provide fault-tolerant navigation solution. The novel aspect of paper is employing symmetrical dynamic behavior of the yaw and pitch channels as an online tuning of analytical fault recovery solution against unforeseen variations due to its hardware/software property. In this regard, a nonlinear model of the aerospace launch vehicle is simulated using specific navigation failures and the results verified the feasibility of the proposed system. Simulation results and sensitivity analysis show that the proposed techniques can produce more effective estimation results than those of the previous techniques, against sensor failures.
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Lipnitskiy, Yuriy Mikhaylovich, and Aleksandr Victorovich Safronov. "GROUND TESTING OF THE LAUNCH VEHICLE ACOUSTICS." TsAGI Science Journal 45, no. 3-4 (2014): 237–54. http://dx.doi.org/10.1615/tsagiscij.2014011945.

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Xu, Bo, Dan Dan Wang, and Zhen Sheng Cheng. "Error Modeling and Simulation Analysis for the Vehicle Launching System Erecting." Advanced Materials Research 566 (September 2012): 680–84. http://dx.doi.org/10.4028/www.scientific.net/amr.566.680.

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Horizontal collimation is the development tendency of the vehicle launching system. During the erect process, the launching system's navigation precision depends on the strap-down inertial navigation system calculation on the launch carrier. So the analysis of every inertial component's error which produces in the inertial navigation process is very necessary. This paper sets the model of the whole erect process, including the launch of the erect drive, the scaling factor,and zero position and installation error of the inertial components. It analyzes the various factors influence on the navigation precision in detail. It provides a good simulation basis and design basis for the error distribution and precision analysis of horizontal collimation technology. And it also provides analysis results for its application and extension, plan making, precision evaluation.
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Zosimovych, Nickolay. "Selecting Design Objectives for an Integrated Guidance System of a Commercial Launch Vehicle with Application of GPS Technologies." Open Aerospace Engineering Journal 6, no. 1 (October 11, 2013): 6–19. http://dx.doi.org/10.2174/1874146001306010006.

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In this article have been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies and has been set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.
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Piatak, David J., Martin K. Sekula, and Russ D. Rausch. "Ares Launch Vehicle Transonic Buffet Testing and Analysis Techniques." Journal of Spacecraft and Rockets 49, no. 5 (September 2012): 798–807. http://dx.doi.org/10.2514/1.a32175.

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Manwatkar, Sushant, S. V. S. Narayana Murty, and P. Ramesh Narayanan. "Failure Analysis of AISI 302 Steel Compression Spring Used in Flush and Purge Valve of Liquid Engine." Materials Science Forum 830-831 (September 2015): 705–8. http://dx.doi.org/10.4028/www.scientific.net/msf.830-831.705.

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AISI 302 stainless steel is used for making compression springs for launch vehicle programmes. One such AISI 302 stainless steel compression spring used in flush and purge valve of liquid engine of a satellite launch vehicle failed during testing. The failure was at the second round of spring and it failed in a slanted type fracture. Detailed metallurgical analysis indicated that the failure was due to fatigue.
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Song, Haryong, and Yongtae Choi. "Distributed multiple model extended information filter with unbiased mixing for satellite launch vehicle tracking." International Journal of Distributed Sensor Networks 14, no. 4 (April 2018): 155014771876926. http://dx.doi.org/10.1177/1550147718769263.

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A distributed extended information filter-based interacting multiple model estimator with unbiased mixing is proposed for satellite launch vehicle tracking. In this problem, multiple heterogeneous sensors such as radars, telemetry systems receiving onboard Global Positioning System—inertial navigation system data, and electro-optical targeting systems are used. The extended information filter is used for nonlinear estimation dealing with ballistic model and spherical coordinate observation. The multiple Markov switching models comprise thrusting and coasting modes having different state vector dimensions for the launch vehicle. To effectively combine both state vectors, an unbiased mixing technique is applied and then the distributed extended information filter integrates local states and information matrix contributions. Hence, the proposed algorithm takes into account both heterogeneity of tracking sensors and multiplicity of vehicle’s dynamic model. We prove the superiority of the proposed algorithm by conducting Monte Carlo simulation with nominal trajectory data of Korea Space Launch Vehicle-1. Comparative simulation results demonstrate that the performance of the proposed method has been improved in vehicle’s position root mean square error.
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Chen, Kai, Fuqiang Shen, Jun Zhou, and Xiaofeng Wu. "SINS/BDS Integrated Navigation for Hypersonic Boost-Glide Vehicles in the Launch-Centered Inertial Frame." Mathematical Problems in Engineering 2020 (November 12, 2020): 1–16. http://dx.doi.org/10.1155/2020/7503272.

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According to the trajectory specialty of hypersonic boost-glide vehicles, a strapdown inertial navigation system/BeiDou navigation satellite system (SINS/BDS) algorithm based on the launch-centered inertial (LCI) frame for hypersonic vehicles is proposed. First, the related frame system, especially the launch earth-centered inertial (LECI) frame, and the SINS mechanization in the LCI frame are introduced. Second, SINS discrete updating algorithms in the LCI frame for the compensation of coning, sculling, and scrolling effects are deduced in the attitude, velocity, and position updating algorithms, respectively. Subsequently, the Kalman filter of the SINS/BDS integrated navigation in the LCI frame is obtained. The method of converting BDS receiver position and velocity from the Earth-centered Earth-fixed (ECEF) frame to the LCI frame is deduced through the LECI frame. Finally, taking the typical hypersonic boost-glide vehicles as the object, the SINS/BDS algorithm vehicle field test and hardware-in-the-loop simulation are performed.
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Dissertations / Theses on the topic "Launch vehicle navigation testing"

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Schrock, Ken, Todd Freestone, and Leon Bell. "GPS RECEIVER SELECTION AND TESTING FOR LAUNCH AND ORBITAL VEHICLES." International Foundation for Telemetering, 2000. http://hdl.handle.net/10150/608283.

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International Telemetering Conference Proceedings / October 23-26, 2000 / Town & Country Hotel and Conference Center, San Diego, California
NASA Marshall Space Flight Center’s Bantam Robust Guidance Navigation & Control Project is investigating off the shelf navigation sensors that may be inexpensively combined into Kalman filters specifically tuned for launch and orbital vehicles. For this purpose, Marshall has purchased several GPS receivers and is evaluating them for these applications. The paper will discuss the receiver selection criteria and the test equipment used for evaluation. An overview of the analysis will be presented including the evaluation used to determine their success or failure. It will conclude with goals of the program and a recommendation for all GPS users.
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Rose, Michael Benjamin. "Statistical Methods for Launch Vehicle Guidance, Navigation, and Control (GN&C) System Design and Analysis." DigitalCommons@USU, 2012. https://digitalcommons.usu.edu/etd/1278.

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A novel trajectory and attitude control and navigation analysis tool for powered ascent is developed. The tool is capable of rapid trade-space analysis and is designed to ultimately reduce turnaround time for launch vehicle design, mission planning, and redesign work. It is streamlined to quickly determine trajectory and attitude control dispersions, propellant dispersions, orbit insertion dispersions, and navigation errors and their sensitivities to sensor errors, actuator execution uncertainties, and random disturbances. The tool is developed by applying both Monte Carlo and linear covariance analysis techniques to a closed-loop, launch vehicle guidance, navigation, and control (GN&C) system. The nonlinear dynamics and flight GN&C software models of a closed-loop, six-degree-of-freedom (6-DOF), Monte Carlo simulation are formulated and developed. The nominal reference trajectory (NRT) for the proposed lunar ascent trajectory is defined and generated. The Monte Carlo truth models and GN&C algorithms are linearized about the NRT, the linear covariance equations are formulated, and the linear covariance simulation is developed. The performance of the launch vehicle GN&C system is evaluated using both Monte Carlo and linear covariance techniques and their trajectory and attitude control dispersion, propellant dispersion, orbit insertion dispersion, and navigation error results are validated and compared. Statistical results from linear covariance analysis are generally within 10% of Monte Carlo results, and in most cases the differences are less than 5%. This is an excellent result given the many complex nonlinearities that are embedded in the ascent GN&C problem. Moreover, the real value of this tool lies in its speed, where the linear covariance simulation is 1036.62 times faster than the Monte Carlo simulation. Although the application and results presented are for a lunar, single-stage-to-orbit (SSTO), ascent vehicle, the tools, techniques, and mathematical formulations that are discussed are applicable to ascent on Earth or other planets as well as other rocket-powered systems such as sounding rockets and ballistic missiles.
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Arslan, Suat. "Testing and evaluation of the Small Autonomous Underwater Vehicle Navigation System (SANS)." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2000. http://handle.dtic.mil/100.2/ADA376607.

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Thesis (M.S. in Electrical Engineering) Naval Postgraduate School, March 2000.
Thesis advisor(s): Yun, Xiaoping; Bachmann, Eric R. "March 2000." Includes bibliographical references (p. 93-94). Also available online.
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Galles, Marc Alexander. "Passive Disposal of Launch Vehicle Stages in Geostationary Transfer Orbits Leveraging Small Satellite Technologies." DigitalCommons@CalPoly, 2021. https://digitalcommons.calpoly.edu/theses/2337.

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Once a satellite has completed its operational period, it must be removed responsibly in order to reduce the risk of impacting other missions. Geostationary Transfer Orbits (GTOs) offer unique challenges when considering disposal of spacecraft, as high eccentricity and orbital energy give rise to unique challenges for spacecraft designers. By leveraging small satellite research and integration techniques, a deployable drag sail module was analyzed that can shorten the expected orbit time of launch vehicle stages in GTO. A tool was developed to efficiently model spacecraft trajectories over long periods of time, which allowed for analysis of an object’s expected lifetime after its operational period had concluded. Material limitations on drag sail sizing and performance were also analyzed in order to conclude whether or not a system with the required orbital performance is feasible. It was determined that the sail materials and configuration is capable of surviving the expected GTO environment, and that a 49 m2 drag sail is capable of sufficiently shortening the amount of time that the space vehicles will remain in space.
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Hastings, Benjamin E. "Design of a Micro Wireless Instrumented Payload for Unmanned Vehicle Testing." Thesis, Virginia Tech, 2006. http://hdl.handle.net/10919/34531.

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The testing of unmanned vehicles presents a need for an independent device capable of accurately collecting position and orientation data. While commercial-off-the-shelf components could be pieced together to sense and record this information, this is an expensive, large, and heavy solution, not suitable for small or aerial vehicles. The micro wireless instrumented payload, or μWIP, was designed precisely for this purpose.

The μWIP includes a GPS receiver, 3-axis accelerometer, 3-axis gyroscope, and 3-axis magnetometer which are used to measure an unmanned vehicle's position and orientation. The device also uses a secure digital card for data storage, and an 802.11b module to provide wireless connectivity. Additionally, the μWIP contains a on-board battery and the circuitry required to charge it. Firmware for the ARM7 processor was written to allow sensor calibration and data transmission, and a user interface was designed to run on a personal computer.

The finished design is a tiny 3''x5''x1'', and weighs a mere 0.8 pounds including battery and antennas. It is capable of continuously streaming accurate GPS and inertial data over an 802.11b wireless network for over 5 hours. Having a bill of materials cost just over $600, the μWIP is also more cost effective than any alternative solutions.

This thesis details the hardware and software design of the μWIP, as well as the initial testing, calibration, and evaluation of the device.


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Gow, Joel A. "Testing the HG1700 inertial measurement unit for implementation into the AIRES unmanned underwater vehicle." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Jun%5FGow.pdf.

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Thesis (M.S. in Applied Science (Physical Oceanography))--Naval Postgraduate School, June 2005.
Thesis Advisor(s): Anthony J. Healey, Edward B. Thornton. Includes bibliographical references (p. 49). Also available online.
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Lopez, Christian W. "UAV Formation Flight Utilizing a Low Cost, Open Source Configuration." DigitalCommons@CalPoly, 2013. https://digitalcommons.calpoly.edu/theses/1089.

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The control of multiple unmanned aerial vehicles (UAVs) in a swarm or cooperative team scenario has been a topic of great interest for well over a decade, growing steadily with the advancements in UAV technologies. In the academic community, a majority of the studies conducted rely on simulation to test developed control strategies, with only a few institutions known to have nurtured the infrastructure required to propel multiple UAV control studies beyond simulation and into experimental testing. With the Cal Poly UAV FLOC Project, such an infrastructure was created, paving the way for future experimentation with multiple UAV control systems. The control system architecture presented was built on concepts developed in previous work by Cal Poly faculty and graduate students. An outer-loop formation flight controller based on a virtual waypoint implementation of potential function guidance was developed for use on an embedded microcontroller. A commercially-available autopilot system, designed for fully autonomous waypoint navigation utilizing low cost hardware and open source software, was modified to include the formation flight controller and an inter-UAV communication network. A hardware-in-the-loop (HIL) simulation was set up for multiple UAV testing and was utilized to verify the functionality of the modified autopilot system. HIL simulation results demonstrated leader-follower formation convergence to 15 meters as well as formation flight with three UAVs. Several sets of flight tests were conducted, demonstrating a successful leader-follower formation, but with relative distance convergence only reaching a steady state value of approximately 35 +/- 5 meters away from the leader.
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Lai, Jun-Xu, and 賴俊旭. "Development and Validation of a Highly Modularized and Highly-Fidelity Simulator for Guidance Navigation and Control of Launch Vehicle." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/9jrj9t.

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碩士
國立交通大學
機械工程系所
105
In general, satellite launcher takes off vertically from launch pad, flies through the atmosphere so that it can perform orbit insertion where rocket shall propel itself up to the designated inertia velocity required for its payload to orbit the Earth. During the course of flight, several disturbances, such as aerodynamic force, wind gust, imperfection of sensor/actuator between real and measurement/command, guidance law, autopilot law and timing of flight sequences will ultimately impact the accuracy of final orbit insertion. As a result, there is a need to build a simulation tool to evaluate the impact toward the accuracy of orbit insertion owing to those disturbances, laws and timing of actions during the flight. In this thesis, a highly modularized simulation tool with high fidelity capable of simulating the flight of a rocket based on its physical properties is modified based on publicly available GNC (guidance navigation and control). The newly developed code has gone through numerous validation simulations against the original code. The simulator considers these aforementioned disturbances, navigation, guidance and control laws and sequence of ignition/separation actions along with designated timing. The sequence of actions during flight are summarized as follows. First, thruster vector control (TVC) vector tilts at an angle immediately after rocket taking off. After the jettison of first stage, the second stage starts a gravity turn in a near zero angle of attack manner to minimize the aerodynamic loss during flight. After the second stage engine cuts off, the rocket coasts for a certain period of time until its attitude reaches a appropriate flight path angle. Later, the third stage engine ignites and the activates a close loop control using reaction control system (RCS) or TVC with guidance using Powered Explicit Guidance (PEG) will be enabled for accurate orbit insertion. For the proposed flight sequence, the simulation suggests that the timing or the proper flight path angle to enable the close-loop PEG on the third stage will impact the accuracy of the final orbit insertion. Further investigation of this particular factor is performed by the comparison of orbit insertion accuracy for different flight path angles. Completion of this simulation tool shall benefit our future development in Processor-In-the-Loop (PIL) and Hardware-In-the-Loop (HIL).
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(9713948), Michael R. Thompson. "Design of Quasi-Satellite Science Orbits at Deimos." Thesis, 2020.

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In order to answer the most pressing scientific questions about the two Martian moons, Phobos and Deimos, new remote sensing observations are required. The best way to obtain global high resolution observations of Phobos and Deimos is through dedicated missions to each body that utilize close-proximity orbits, however much of the orbital tradespace is too unstable to realistically or safely operate a mission.

This thesis explores the dynamics and stability characteristics of trajectories near Deimos. The family of distant retrograde orbits that are inclined out of the Deimos equatorial plane, known as quasi-satellite orbits, are explored extensively. To inform future mission design and CONOPS, the sensitivities and stability of distant retrograde and quasi-satellite orbits are examined in the vicinity of Deimos, and strategies for transferring between DROs are demonstrated. Finally, a method for designing quasi-satellite science orbits is demonstrated for a set of notional instruments and science requirements for a Deimos remote sensing mission.
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(11068791), Athul Pradeepkumar Girija. "A Systems Framework and Analysis Tool for Rapid Conceptual Design of Aerocapture Missions." Thesis, 2021.

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Aerocapture offers a near propellantless and quick method of orbit insertion at atmosphere bearing planetary destinations. Compared to conventional propulsive insertion, the primary advantage of using aerocapture is the savings in propellant mass which could be used to accommodate more useful payload. To protect the spacecraft from the aerodynamic heating during the maneuver, the spacecraft must be enclosed in a protective aeroshell or deployable drag device which also provides aerodynamic control authority to target the desired conditions at atmospheric exit. For inner planets such as Mars and Venus, aerocapture offers a very attractive option for inserting small satellites or constellations into very low circular orbits such as those used for imaging or radar observations. The large amount of propellant required for orbit insertion at outer planets such as Uranus and Neptune severely limits the useful payload mass that can delivered to orbit as well as the achievable flight time. For outer planet missions, aerocapture opens up an entirely new class of short time of flight trajectories which are infeasible with propulsive insertion. A systems framework for rapid conceptual design of aerocapture missions considering the interdependencies between various elements such as interplanetary trajectory and vehicle control performance for aerocapture is presented. The framework provides a step-by-step procedure to formulate an aerocapture mission starting from a set of mission objectives. At the core of the framework is the ``aerocapture feasibility chart", a graphical method to visualize the various constraints arising from control authority requirement, peak deceleration, stagnation-point peak heat rate, and total heat load as a function of vehicle aerodynamic performance and interplanetary arrival conditions. Aerocapture feasibility charts have been compiled for all atmosphere-bearing Solar System destinations for both lift and drag modulation control techniques. The framework is illustrated by its application to conceptual design of a Venus small satellite mission and a Flagship-class Neptune mission using heritage blunt-body aeroshells. The framework is implemented in the Aerocapture Mission Analysis Tool (AMAT), a free and open-source Python package, to enable scientists and mission designers perform rapid conceptual design of aerocapture missions. AMAT can also be used for rapid Entry, Descent, and Landing (EDL) studies for atmospheric probes and landers at any atmosphere-bearing destination.
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Books on the topic "Launch vehicle navigation testing"

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Schiffbauer, William H. A locomotion emulator for testing mine vehicle navigation. Washington: U.S. Dept. of the Interior, Bureau of Mines, 1991.

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Mackall, Dale A. The X-33 extended flight test range. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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Mackall, Dale A. The X-33 extended flight test range. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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Mackall, Dale A. The X-33 extended flight test range. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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Sharma, Ashley. X-33 integrated test facility extended range simulation. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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Project Apollo: The test program. Burlington, Ont: Apogee Books, 2005.

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Godwin, Robert. Project Apollo: Exploring the Moon. Burlington, Ont: Apogee Books, 2006.

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Testing and Evaluation of the Small Autonomous Underwater Vehicle Navigation System (SANS). Storming Media, 2000.

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M, McNelis Anne, and United States. National Aeronautics and Space Administration., eds. Acoustic testing of the Cassini spacecraft and Titan IV payload fairing. [Washington, DC]: National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. Options for flight testing rocket-based combined-cycle (RBCC) engines. Reston, VA: American Institute of Aeronautics and Astronautics, 1996.

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Book chapters on the topic "Launch vehicle navigation testing"

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Chambon, Emmanuel, Pierre Apkarian, and Laurent Burlion. "Flexible Launch Vehicle Control Using Robust Observer-Based Controller Obtained through Structured H ∞ Synthesis." In Advances in Aerospace Guidance, Navigation and Control, 23–38. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17518-8_2.

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Meghanath, G., V. Venkata Ramakrishna, A. Veerraju, and Jopaul K. Ignatius. "A New Multi-shaker System Development For Testing Launch Vehicle Subassemblies." In Lecture Notes in Mechanical Engineering, 315–24. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5862-7_26.

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Tang, Yi, Wenan Zhong, Junming Shou, and Wenfeng Hu. "Exploration of BD2/SINS Deeply Integrated Navigation in CZ-7 Launch Vehicle Guidance System." In China Satellite Navigation Conference (CSNC) 2014 Proceedings: Volume III, 627–37. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54740-9_55.

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Li, Chong, Xianqing Yi, Yue Zhao, and Zhenwei Hou. "Research on Space-Based Measurement and Control Scheme of Launch Vehicle Based on BeiDou Navigation Satellite System." In Lecture Notes in Electrical Engineering, 45–58. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-0005-9_4.

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Yelamarthi, Kumar, Raghudeep Kannavara, and Sanjay Boddhu. "A Perceptual Computing Based Gesture Controlled Quadcopter for Visual Tracking and Transportation." In Unmanned Aerial Vehicles, 131–41. IGI Global, 2019. http://dx.doi.org/10.4018/978-1-5225-8365-3.ch005.

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One of the fundamental challenges faced by an inexperienced user in portable unmanned aerial vehicle (UAV) such as quadcopters is flight control, often leading to crashes. Addressing this challenge, and leveraging upon the technological advancement in perceptual computing and computer vision, this research presents a modular system that allows for hand gesture based flight control of UAV, alongside a transport mechanism for portable objects. In addition to ascertain smooth flight control by avoiding obstacles in navigation path, real-time video feedback is relayed from the UAV to user, thus allowing him/her to take appropriate actions. This paper presents the design implementation by discussing the various sub-systems involved, inter system communication, and field tests to ascertain operation. As presented from testing results, the proposed system provides efficient communication between the subsystems for smooth flight control, while allowing for safe transport of portable objects.
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Conference papers on the topic "Launch vehicle navigation testing"

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Kerr, Murray, Andres Marcos, and Luis Peñín. "Development and Testing of a GNC-FDI Filter for a Reusable Launch Vehicle during Ascent." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8195.

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Zhou, You, and Mao-zhi Wang. "Launch Vehicle Testing Simulation System." In 2011 International Conference on Computational and Information Sciences (ICCIS). IEEE, 2011. http://dx.doi.org/10.1109/iccis.2011.170.

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Hanson, John, and Robin Pinson. "Calculating Launch Vehicle Flight Performance Reserve." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6650.

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Shtessel, Yuri, Christian Tournes, Don Krupp, Yuri Shtessel, Christian Tournes, and Don Krupp. "Reusable launch vehicle control in sliding modes." In Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3533.

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Das, Renjith, and A. Ferdinand Christopher. "Automated Testing for Launch Vehicle Instrumentation." In 2018 Fourteenth International Conference on Information Processing (ICINPRO). IEEE, 2018. http://dx.doi.org/10.1109/icinpro43533.2018.9096677.

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Plaisted, Clinton, and Alexander Leonessa. "Expendable Launch Vehicle Adaptive Autopilot Design." In AIAA Guidance, Navigation and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-7126.

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LeFevre, Brian, and Ratneshwar Jha. "Hybrid Adaptive Launch Vehicle Ascent Flight Control." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5958.

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Blanchet, Pat, Joshua Eckler, and Bruce Bartos. "Wind persistency determined launch commit criteria for the Delta launch vehicle." In AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4403.

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OKUNO, YOSHINORI, and SHIGEYA WATANABE. "Optimal launch trajectory of a hypersonic research vehicle." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4302.

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CHEN, EUGENE, FREDERICK BOELITZ, and JEANNE SULLIVAN. "Trajectory optimization for a National Launch System vehicle." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3713.

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