Relevant bibliographies by topics / Launch Vehicle Failure

Contents

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

Academic literature on the topic 'Launch Vehicle Failure'

Author: Grafiati
Published: 4 June 2021
Last updated: 13 February 2022

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Journal articles on the topic "Launch Vehicle Failure"

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Liao, Guorui, Jinjie Liu, and Tianheng Dou. "Research on attitude control strategy of single engine failure in the first-stage flight phase of new generation launch vehicle." MATEC Web of Conferences 336 (2021): 02001. http://dx.doi.org/10.1051/matecconf/202133602001.

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The successful launching of the new generation of launch vehicle is of great practical significance to the development of China Space, and the cryogenic liquid engine commonly used in the launch vehicle has a certain probability of failures, which may affect the success or failure of rocket launching. In this paper, a Bolza problem optimization algorithm based on Radau pseudo-spectral method is proposed to solve the problem of single engine failure in the first-stage flight phase of the new generation launch vehicle by simulating fault injection and taking the attitude angle as optimal control
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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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WANG, Cong, Zhengyu SONG, and Qinghai GONG. "Autonomous trajectory planning for launch vehicle under thrust drop failure." SCIENTIA SINICA Informationis 49, no. 11 (2019): 1472–87. http://dx.doi.org/10.1360/ssi-2019-0132.

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Yan, Tinggui, Xiaoqian Chen, Shipeng Li, Li Ma, Jian Bai, and Zhifang Yang. "A Bayesian Network Approach to Launch Vehicle Software Failure Prediction." International Journal of Multimedia and Ubiquitous Engineering 11, no. 11 (2016): 325–34. http://dx.doi.org/10.14257/ijmue.2016.11.11.29.

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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 (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 t
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Murty, S. V. S. Narayana, Sushant K. Manwatkar, and P. Ramesh Narayanan. "Failure analysis of a vibration isolator used in launch vehicle applications." Case Studies in Engineering Failure Analysis 3 (April 2015): 1–9. http://dx.doi.org/10.1016/j.csefa.2014.07.003.

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Murugesan, V., P. S. Sreejith, M. Gopakumar, P. Damodaran, and M. Premdas. "Failure Analysis of a Launch Vehicle Umbilical Shutter Mechanism During Vibration Qualification." Journal of Failure Analysis and Prevention 18, no. 3 (2018): 457–64. http://dx.doi.org/10.1007/s11668-018-0442-4.

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B., Biju Prasad, Biju N., and Radhakrishna Panicker M.R. "High redundancy electromechanical actuator for thrust vector control of a launch vehicle." Aircraft Engineering and Aerospace Technology 91, no. 8 (2019): 1122–32. http://dx.doi.org/10.1108/aeat-06-2018-0165.

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Purpose The purpose of this paper is to design an electromechanical actuator which can inherently tolerate a stuck or loose failure without any need for fault detection isolation and reconfiguration. Design/methodology/approach Generalized design methodology for a thrust vector control application is adopted to reduce the design iterations during the initial stages of the design. An optimum ball screw pitch is selected to minimize the motor sizing and maximize the load acceleration. Findings A high redundancy electromechanical actuator for thrust vector control has lower self-inertia and highe
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Lee, Jung-Ryul, and Dipesh Dhital. "Review of flaws and damages in space launch vehicle: Structures." Journal of Intelligent Material Systems and Structures 24, no. 1 (2012): 4–20. http://dx.doi.org/10.1177/1045389x12458041.

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A space launch vehicle is a complex engineering structure. It consists of several structural and system components that are stably stored for extended periods and that at the launch moment, must function precisely. However, this presents a number of unique challenges as well as the possibility of various flaws and damages during the manufacturing, assembly, or ground handling phase. Mechanical and chemical complexity, long service lives, aging materials, and designs with small margins are typical of space launch vehicle components. The performance and characteristics of the components can be s
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Deng, Jia, Shi Hua Bi, and Shao Zhen Yu. "Research on the Effect of Moulded Surfaces of Deflectors." Advanced Materials Research 951 (May 2014): 53–57. http://dx.doi.org/10.4028/www.scientific.net/amr.951.53.

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Whether the gas jet is deflected smoothly or not directly affects the success or failure of launch, during the progress of the land-based missile with the vehicle-mounted vertically thermal launch. This paper uses 3-D dynamical simulation of gas jet to analyse basic deflecting features of triple-faced deflectors and double-faced ones with different moulded surfaces. The result shows that, triple-faced deflectors deflect quite smoothly and requite large area of the firing position. With some differences, double-faces deflectors protect the vehicle and wheels much better and requite more of the
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Dissertations / Theses on the topic "Launch Vehicle Failure"

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Losik, Len. "STOPPING LAUNCH PAD DELAYS, LAUNCH FAILURES, SATELLITE INFANT MORTALITIES AND ON ORBIT SATELLITE FAILURES USING TELEMETRY PROGNOSTIC TECHNOLOGY." International Foundation for Telemetering, 2007. http://hdl.handle.net/10150/604550.

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ITC/USA 2007 Conference Proceedings / The Forty-Third Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2007 / Riviera Hotel & Convention Center, Las Vegas, Nevada<br>Telemetry Prognostics is Failure Prediction using telemetry for launch vehicle and satellite space flight equipment to stop launch failures, launch pad delays, satellite infant mortalities and satellite on orbit failures. This technology characterizes telemetry behaviors that are latent, transient, and go undetected by the most experienced engineering personnel and software diagnostic tools du
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Losik, Len. "Launch Vehicle and Satellite Independent Failure Analysis Using Telemetry Prognostic Algorithms." International Foundation for Telemetering, 2008. http://hdl.handle.net/10150/606189.

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ITC/USA 2008 Conference Proceedings / The Forty-Fourth Annual International Telemetering Conference and Technical Exhibition / October 27-30, 2008 / Town and Country Resort & Convention Center, San Diego, California<br>Unique vehicle designs encourage the use of the builder to complete its own failure analysis. Current failure analysis practices use telemetry and diagnostic technology developed over the past 100 years to identify root-cause. When telemetry isn't available speculation is used to create a list of prioritized, potential causes. Prognostic technology consists of generic algorithms
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Losik, Len. "Using Generic Telemetry Prognostic Algorithms for Launch Vehicle and Spacecraft Independent Failure Analysis Service." International Foundation for Telemetering, 2009. http://hdl.handle.net/10150/606037.

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ITC/USA 2009 Conference Proceedings / The Forty-Fifth Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2009 / Riviera Hotel & Convention Center, Las Vegas, Nevada<br>Current equipment and vehicle failure analysis practices use diagnostic technology developed over the past 100 years of designing and manufacturing electrical and mechanical equipment to identify root cause of equipment failure requiring expertise with the equipment under analysis. If the equipment that failed had telemetry embedded, prognostic algorithms can be used to identify the determinis
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Losik, Len. "Stopping Launch Vehicle Failures Using Telemetry to Measure Equipment Usable Life." International Foundation for Telemetering, 2012. http://hdl.handle.net/10150/581848.

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Launch vehicle equipment reliability is driven by infant mortality failures, which can be eliminated using a prognostic analysis prior, during and/or after the exhaustive and comprehensive dynamic environmental factory acceptance testing. Measuring and confirming equipment performance is completed to increase equipment reliability by identifying equipment that fails during test for repair/replacement. To move to the 100% reliability domain, equipment dynamic environmental factory testing should be followed by a prognostic analysis to measure equipment usable life and identify the equipment tha
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Losik, Len. "Stopping Launch Vehicle Failures Using Telemetry to Measure Equipment Usable Life." International Foundation for Telemetering, 2011. http://hdl.handle.net/10150/595729.

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ITC/USA 2011 Conference Proceedings / The Forty-Seventh Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2011 / Bally's Las Vegas, Las Vegas, Nevada<br>Launch vehicle equipment reliability is driven by infant mortality failures, which can be eliminated using a prognostic analysis prior, during and/or after the exhaustive and comprehensive dynamic environmental factory acceptance testing. Measuring and confirming equipment performance is completed to increase equipment reliability by identifying equipment that fails during test for repair/replacement. To mo
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Losik, Len. "Using Generic Telemetry Prognostic Algorithms for Launch Vehicle and Spacecraft Independent Failure Analysis Service." International Foundation for Telemetering, 2010. http://hdl.handle.net/10150/605927.

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ITC/USA 2010 Conference Proceedings / The Forty-Sixth Annual International Telemetering Conference and Technical Exhibition / October 25-28, 2010 / Town and Country Resort & Convention Center, San Diego, California<br>Current failure analysis practices use diagnostic technology developed over the past 100 years of designing and manufacturing electrical and mechanical equipment to identify root cause of equipment failure requiring expertise with the equipment under analysis. If the equipment that failed had telemetry embedded, prognostic algorithms can be used to identify the deterministic beha
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Losik, Len. "Relying on Telemetry for Mission Critical Decisions: Lessons Learned from NASA's Reusable Launch Vehicle for Use on the Air Force's Next Generation Reusable Launch Vehicle." International Foundation for Telemetering, 2012. http://hdl.handle.net/10150/581746.

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ITC/USA 2012 Conference Proceedings / The Forty-Eighth Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2012 / Town and Country Resort & Convention Center, San Diego, California<br>The U.S. Air Force's next generation reusable booster (NGRSB) offers the opportunity for the Space Command to use intelligent equipment for decision making replacing personnel, increasing safety and mission assurance by removing decisions from program management personnel who may not have had any flight-test experience. Adding intelligence to launch vehicle and spacecraft equipm
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Losik, Len. "Using Telemetry to Measure Equipment Reliability and Upgrading the Satellite and Launch Vehicle Factory ATP." International Foundation for Telemetering, 2011. http://hdl.handle.net/10150/595730.

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ITC/USA 2011 Conference Proceedings / The Forty-Seventh Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2011 / Bally's Las Vegas, Las Vegas, Nevada<br>Satellite and launch vehicles continues to suffer from catastrophic infant mortality failures. NASA now requires satellite suppliers to provide on-orbit satellite delivery and a free satellite and launch vehicle in the event of a catastrophic infant mortality failure. A high infant mortality failure rate demonstrates that the factory acceptance test program alone is inadequate for producing 100% reliability
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Losik, Len. "A Case for Waste Fraud and Abuse: Stopping the Air Force from Purchasing Spacecraft That Fail Prematurely." International Foundation for Telemetering, 2011. http://hdl.handle.net/10150/595787.

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ITC/USA 2011 Conference Proceedings / The Forty-Seventh Annual International Telemetering Conference and Technical Exhibition / October 24-27, 2011 / Bally's Las Vegas, Las Vegas, Nevada<br>Spacecraft and launch vehicle reliability is dominated by premature equipment failures and surprise equipment failures that increase risk and decrease safety, mission assurance and effectiveness. Large, complex aerospace systems such as aircraft, launch vehicle and satellites are first subjected to most exhaustive and comprehensive acceptance testing program used in any industry and yet suffer from the high
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Books on the topic "Launch Vehicle Failure"

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United States. Congress. House. Committee on Science, Space, and Technology (2011). Subcommittee on Space and Aeronautics. Lessons from the Soyuz rocket failure and return to flight: Hearing before the Subcommittee on Space and Aeronautics, Committee on Science, Space, and Technology, House of Representatives, One Hundred Twelfth Congress, first session, Wednesday, October 12, 2011. U.S. G.P.O., 2011.

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Failure Analysis and Mechanical Tests of Failed Aluminum Alloy 7277 Rivets on Armored Vehicle Launched Bridges. Storming Media, 1996.

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Mechanical Tests and Failure Analysis on Selected Components of the Class 60 Armored Vehicle Launched Bridge (AVLB) During the Class 70 Modification Program. Storming Media, 1996.

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Book chapters on the topic "Launch Vehicle Failure"

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Deng, Guanqian, Guiyou Hao, Yingjie Lv, and Ying Zhou. "Research on Intermittent Failure Mechanism of the Electrical Connector of the Missile Launch Vehicle." In Man-Machine-Environment System Engineering. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-2481-9_28.

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"Failure of 17-4 PH Stainless Steel Bolts on a Titan Space Launch Vehicle." In ASM Failure Analysis Case Histories: Mechanical and Machine Components. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.mech.c9001727.

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Conference papers on the topic "Launch Vehicle Failure"

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Hanson, John, Ashley Hill, and Bernard Beard. "Launch Vehicle Failure Dynamics and Abort Triggering Analysis." In AIAA Guidance, Navigation, and Control Conference. American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6502.

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LEONARD, BYRON, and WILLIAM KISKO. "Liquid propulsion considerations in projecting launch vehicle failure probabilities." In Space Programs and Technologies Conference. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1334.

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Manning, Ted A., Scott L. Lawrence, Hamed S. Nejad, and Ken Gee. "Intermediate failure states in simulation-based launch vehicle risk study." In 2010 Annual Reliability and Maintainability Symposium (RAMS). IEEE, 2010. http://dx.doi.org/10.1109/rams.2010.5448010.

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Hosangadi, Ashvin, and Nateri Madavan. "Simulation of Propellant Explosions Resulting from Crew Launch Vehicle Tank Failure." In 26th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-6912.

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Edwards, John, Scott Farner, Gary Gershzohn, et al. "Space Transportation - Delta Launch Vehicle System Health Monitoring, Failure Detection, Diagnosis and Response." In AIAA SPACE 2007 Conference & Exposition. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-6122.

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Losik, Len. "Using Generic Telemetry Prognostic Algorithms for Launch Vehicle and Spacecraft Independent Failure Analysis." In AIAA SPACE 2010 Conference & Exposition. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-8757.

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MUTHUKUMAR, S., K. PANOOP SHANKAR, N. VIJAY, P. SUBHASH CHANDRA BOSE, and Y. SREENIVAS RAO. "Failure Mode Effect and Critically Analysis of Divert Attitude Control System of Launch Vehicle." In 31st International Symposium on Ballistics. DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/ballistics2019/33157.

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Kattakuri, Vikranth, and Jitesh H. Panchal. "Spacecraft Failure Analysis From the Perspective of Design Decision-Making." In ASME 2019 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/detc2019-98420.

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Abstract Space mission-related projects are demanding and risky undertakings because of their complexity and cost. Many missions have failed over the years due to anomalies in either the launch vehicle or the spacecraft. Projects of such magnitude with undetected flaws due to ineffective process controls account for huge losses. Such failures continue to occur despite the studies on systems engineering process deficiencies and the state-of-the-art systems engineering practices in place. To further explore the reasons behind majority of the failures, we analyzed the failure data of space missio
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Foster, Chad R. "Test Uncertainty and Failure Mode Discovery." In ASME 2014 Internal Combustion Engine Division Fall Technical Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/icef2014-5421.

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An uncertainty metric is used to prioritize testing for initial product development. Similar metrics are used in signal processing, cryptography, and digital communication. The greatest benefit of this metric is to maximize testing value to discover failures. A major drawback is a reduction in the accuracy of launch reliability estimates. A preferred approach uses two separate testing processes, the first will increase the initial issue discovery using the uncertainty metric while the second increases the accuracy of the reliability estimation. Engine development data is presented to highlight
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Williams, Craig H., Lawrence J. Ross, and J. Joe Nieberding. "A Prognostic Launch Vehicle Probability of Failure Assessment Methodology for Conceptual Systems Predicated on Human Causal Factors." In 2018 AIAA SPACE and Astronautics Forum and Exposition. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-5413.

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