Gliding vehicles with lift-to-drag ratio over 3.0 in hypersonic flight are naturally hard to demonstrate a horizontal landing, due to its incapable aerodynamic performance in subsonic flight. A new configuration of the gliding vehicle with deployable wings is applied in this paper. With improved planning methods, the landing trajectory is redesigned for TAEM phase and approach and landing phase. Distinct differences of initial states requirements are found in both phases compared to traditional reusable launch vehicles. Simulation results show feasibility of horizontal landing, and deployable wings are necessary to maintain vehicle under strict landing constraints. Finally, using the theory of controllable and reachable set, the feasible area is obtained to provide quantitatively selection of handover states between phases.
Horizontal Landing Trajectory Analysis for Gliding Vehicle with Deployable Wings
Lect. Notes Electrical Eng.
30.10.2021
13 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Horizontal Landing Trajectory Analysis for Gliding Vehicle with Deployable Wings
British Library Conference Proceedings | 2022
|Note on the wings of gliding birds
Engineering Index Backfile | 1930
|Inflatable structures for deployable wings
AIAA | 2001
|