Abstract
Launch vehicle tests include many important activities, particularly during the development phase. However, when the rocket begins launch services, system level tests focus on avionics system integration after assembly, mainly by simulating flight processes, also known as general check in China. The general check is performed hierarchically. The control (or GNC) subsystem is checked first, and then other systems, such as the telemetry system, etc. The shutdown time of every stage may be controlled around the theoretical value by modeling the shutdown equation.
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References
Song ZY (2014) High reliability design for launch vehicle control system. China Aerospace Publishing House, Beijing, pp 262–297 (in Chinese)
Xu YW (editor in chief) (1992) Control system (3). Missile and aerospace collection—liquid ballistic missile and launch vehicle series. China Aerospace Publishing House, Beijing (in Chinese)
Fan JS, Zhang HX, Yang JH (2007) Automatic test and fault diagnosis for subsystem test system of missile’s control system. Ordnance Ind Autom (10):72–74 (in Chinese)
Wang JH (1999) The design of LM-3A launch vehicle dynamically measuring-control system. Missiles Space Veh (4):23–27 (in Chinese)
Sun NS (2003) Application of redundant design technology in the flight control system of launch vehicle (2). Aerosp Control 21(2):68–80 (in Chinese)
Zeng GS, Shen WG, Shi L et al (2005) High reliability triple redundancy servomechanism system. Aerosp Control 23(1):35–40 (in Chinese)
Zhao SJ, Zhao YX, Jiang QY et al (2012) The 2nd stage servo-mechanism system for liquid oxygen-kerosene manned launch vehicle. Manned Spaceflight 18(5):5–11 (in Chinese)
Liu XY, Peng QS (2009) Solution and realization of rocket-borne pyrotechnics auto-test. J Projectiles, Rockets, Missiles Guidance 29(5):232–234 (in Chinese)
Wu MQ, Liu HB, Yang XR et al (2013) Method and development of launch vehicle launch pad perpendicularity adjustment. Missiles and Space Veh (2):30–35 (in Chinese)
Mayer J The space shuttle vehicle checkout involving flight avionics software. AIAA, AIAA81-2141
Song ZY (2014) High reliability design for launch vehicle control system. China Aerospace Publishing House, Beijing, pp 236–237 (in Chinese)
Zhang J, Sun NS (1999) Exciting methods of inertial instruments in closed-loop flight simulation of launch vehicle. Aerosp Control (4):27–30, 37 (in Chinese)
Zhou H, Song ZY (2013) The design and research of closed loop general testing technique based on BMU and LVDS bus. Aerosp Control 31(3):45–49 (in Chinese)
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© 2018 Springer Nature Singapore Pte Ltd. and National Defense Industry Press, Beijing
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Song, Z. (2018). System Level Testing. In: The Test and Launch Control Technology for Launch Vehicles. Springer, Singapore. https://doi.org/10.1007/978-981-10-8712-7_4
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DOI: https://doi.org/10.1007/978-981-10-8712-7_4
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