| 摘要 |
FIELD: dynamic maneuvering of supersonic aircraft at high altitudes near static ceiling or above it at dynamic modes; study of atmospheric physics; launching rocket-probes. SUBSTANCE: proposed method includes raising carrier-aircraft to altitude corresponding to static ceiling, acceleration of carrier-aircraft to maximum speed and launching rocket with smaller artificial satellite. After acceleration to supersonic speed, dynamic maneuver is performed in vertical plane for raising the carrier-aircraft by ascending curvilinear trajectory to altitude ensured by full specific energy of dynamic maneuver and exceeding static ceiling. Launching the rocket with smaller artificial satellite is performed at preset point of ascending curvilinear trajectory at speed, altitude and angle of inclination of trajectory ensuring injection of satellite into orbit at preset parameters and optimal characteristics. Moment for launching the rocket is selected by means of navigational pilotage complex of carrier-aircraft. At the beginning of pre-launch dynamic maneuver, descent of carrier-aircraft is performed at maximum permissible speed. Besides that, moment of launching the rocket may be determined by preliminary calculations of trajectory of injection; maximum magnitude of horizontal component is determined on this base; for performing pre-launch dynamic maneuver, difference of central angles of carrier-aircraft and point in orbit of artificial satellite and horizontal component of rocket speed at moment of injection into intermediate orbit are calculated. EFFECT: reduced power requirements; enhanced accuracy of injection into orbit. 3 cl, 3 dwg |
