The lifting-body type vehicle is one of the rnost promising candidate for future reusable launch systems. In JAXA, the LIFLEX (Lifting-body Flight Experiment) was planned with the main purpose of developing automatic landing technology, which is one of the most important issue in realising lifting-body type re usable launch vehicles. The authors were in charge of the flight control system of the experimental vehicle for Lifting-body Flight Experiment (LIFLEX), The logistical and Lateral control systems were' design by apply in the MDM/MDP (Multiple Delay Model/Multiple Design Pint) method to linearised systems of the vehicle derived from the nominal reference trajectory. The designed control systems were evaluated using the six degree-of-freedom nonlinear flight simulation program. This paper reports the outline and design procedure of these flight control systems.
JAXA Research and Development Report. Nov. 2010
2010
32 pages
Report
No indication
English
Aerodynamics , Space Technology , Physics , Unmanned Spacecraft , Jet & Gas Turbine Engines , Space Launch Vehicles & Support Equipment , Aerothermodynamics , Lifting Body , Experimental design , Re-Entry Vehicle , Flight Control Systems , Automatic Landing , Japan , Space Plane , Hypersonic speed , Trajectory , Flight simulation , Six-Degree-of-Freedom Simulations , Foreign technology , Space Transportation System , Lifting-body Flight Experiment (LIFLEX)
JAXA Research and Development Report. Sep. 2010
NTIS | 2010
JAXA Research and Development Report. Dec. 2010
NTIS | 2010
TIBKAT | 2003-2005 ; damit Erscheinen eingestellt
|Microgravity Research Projects in JAXA
AIAA | 2005
|