An overview of the research on flight control technology for H-2 Orbiting Plane (HOPE) are presented. Trial production and test were conducted on the guidance control computer functional model to be used later for flight control system testing, focusing on realizing high speed computing unit with 32 bit Micro Processor Unit (MPU), mating evaluation of trial produced components, structure to facilitate subjecting them to various tests, including flight control test, and reduction of weight, power consumption, and size. Analysis using the research Function Simulation Program (FSP) used for simulating the Guidance Control Program (GCP), verification of GCP computation logic, and validate mission constants and preliminary design of the research GCP were conducted. Research was conducted on onboard software validation system, which consists of design analysis system, and onboard software production and validation systems. Dynamic wind tunnel test of HOPE was conducted in cooperation with the National Aerospace Laboratory (NAL) for the purpose of acquiring data concerning stability, controllability, and control principle design. Fundamental review of onboard computer and definition study of landing simulation were conducted.
Hope Hikou Seigyo Gijutsu No Kenkyuu (Research on Hope Flight Control Technology)
1992
6 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Control Devices & Equipment , Navigation & Guidance System Components , Aerospace planes , Automatic flight control , Automatic landing control , Japanese spacecraft , Spacecraft control , Spacecraft guidance , Airborne/spaceborne computers , Program verification (Computers) , Spacecraft design , Wind tunnel tests , Foreign technology
Hope No Kenkyuu (Research on Hope)
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