| 摘要 |
rocketry and space engineering; control of light flying vehicles (having mass up to 1 t) launched at intercontinental range by means of light launch vehicles, for example, ballistic missiles of submarines. SUBSTANCE: flying vehicle is accelerated in eastern direction till circular velocity is attained in apogee of flight trajectory up to 100 km. After passage of apogee, flying vehicle is set in flat ricocheting at trajectory steepness within ±2°, at diving and pitching-up respectively. These manoeuvres are altered in areas where phantom acceleration measured on board and Coriolis acceleration in Earth system are equal. EFFECT: possibility of attaining intercontinental range of flight of light flying vehicle at minimum heating and minimum level of g-loads. 2 dwg, 1 tbl |
