Abstract
Constraints faced by the ascent stage of horizontal take-off combined power vehicle are complex and diverse, and the span of flight altitude and airspeed is large. These problems will have an adverse impact on the flight process and increase the difficulty of trajectory design in the ascent stage. Aiming at the multi constraints problem of trajectory design in the ascent stage, the longitudinal particle dynamic equation is given, constraints considered are determined, the relationship between constraint conditions and the pitch angle is studied, the pitch angle profile is designed, the calculation flow of the trajectory iterative algorithm is established, a trajectory design method which uses the pitch angle profile is developed, and the trajectory design method is simulated and analyzed. The final simulation results show that, when meeting multiple constraints in the ascent stage, this developed method will solve the trajectory design problem, and this method has certain practical value and engineering value.
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Huang, J., Sun, C., Feng, W. (2023). Ascent Trajectory Design Method for Air-Breathing Combined Power Hypersonic Vehicle. In: Yan, L., Duan, H., Deng, Y. (eds) Advances in Guidance, Navigation and Control. ICGNC 2022. Lecture Notes in Electrical Engineering, vol 845. Springer, Singapore. https://doi.org/10.1007/978-981-19-6613-2_387
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DOI: https://doi.org/10.1007/978-981-19-6613-2_387
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