CONTENTS: ABLATIVE THERMAL PROTECTIVE MECHANISM AND NUMERICAL SIMULATION FOR RETURNABLE SATELLITE; ABLATIVE THERMAL PROTECTION STRUCTURE DESIGN OF BALLISTIC RETURN MODULE; THERMAL CONTROL DESIGN OF RETURNABLE SATELLITE; MAIN FACTORS AFFECTING PHOTOGRAPHIC QUALITY OF PRISM SCANNING PANORAMIC CAMERA; ELECTRIC POWER SYSTEM OF RETURNABLE SATELLITES; DEVELOPMENT OF RETURN TECHNOLOGY AND RETURNABLE SPACECRAFT; CHINA'S RETURNABLE SATELLITES; DERIVING RECOVERY MOTION EQUATIONS OF SATELLITE WITH QUATERNION RULE; DIGITAL ATTITUDE CONTROL SYSTEM AND FLIGHT TEST RESULTS OF CHINA'S RETURNABLE SATELLITES. (AN).
Chinese Space Science And Technology
1994
141 pages
Report
No indication
English
Unmanned Spacecraft , Ablative Materials & Ablation , Reentry vehicles , Artificial satellites , Recoverable spacecraft , Mathematical models , Flight testing , Digital systems , Ablation , Attitude control systems , Equations of motion , Numerical analysis , Thermal analysis , Photography , Electric power , Design criteria , Thermal degradation , China , Chinese language , Panoramic cameras , Prisms(Optics) , Thermal insulation , Foreign reports , Spn-19950109112 , Returnable satellites , Thermal protection systems , Translations
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