Abstract
The exploitation of rocket guidance technology on the basis of the guidance law of Space Shuttle and Pegasus rocket was performed. A new efficient method of numerical iteration solution to the boundary value problem was put forward. The numerical simulation results have shown that the method features good performances of stability, robustness, high precision, and algebraic formulas in real computation. By virtue of modern DSP ( digital signal processor) high speed chip technology, the algorithm can be used in real time and can adapt to the requirements of the big primary bias of rocket guidance.
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References
Mchenry R L. Space Shuttle ascent guidance, navigation, and control [J]. J Astronaut Sci, 1979,27(1):1–38.
Jaggers R L. An Explicit Solution to the Exoatmospheric Powered Flight Guidance and Trajectory Optimization Problem for Rocket Propelled Vehicles [R]. AIAA 1051, 1977,782–798.
Rovner Daniel. GN & C for Pegasus Air-Launched Space Booster:Design and First Flight Results [R]. NASA 911105, 1991, 450–458.
Macpheson Duncan. An Explicit Solution to the Powered Flight Dynamics of a Rocket Vehicle [R]. AD-293892, 1980, 358–367.
Han Zhuzhai. Method of iterative guidance for rocket vehicle [J]. Journal of Astronautics, 1983,12(1): 12–18 (in Chinese).
Cheng Guocai. Optimal Guidance and Control of Ballistic Missile [M]. National University of Defense Technology Press, Changsha, 1990 (in Chinese).
Jia Peiran. Flight Mechanics of Long Range Rocket [M]. National University of Defense Technology Press, Changsha, 1993 (in Chinese).
[8] Ren Xuan. Orbital Mechanics of Artificial Satellite [M]. National University of Defense Technology Press, Changsha, 1988 (in Chinese).
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Communicated by MA Xing-rui
Project supported by the National High-Tech Research and Development Program of China (863 Program) (No. 863702011)
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Liu, Xj., Yuan, Tb. A new efficient method to boundary value problem for ballistic rocket guidance. Appl. Math. Mech.-Engl. Ed. 26, 1375–1381 (2005). https://doi.org/10.1007/BF03246242
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DOI: https://doi.org/10.1007/BF03246242