| 摘要 |
PCT No. PCT/RU93/00184 Sec. 371 Date Jun. 29, 1994 Sec. 102(e) Date Jun. 29, 1994 PCT Filed Aug. 4, 1993 PCT Pub. No. WO94/10035 PCT Pub. Date Mar. 11, 1994.The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes. The crew escape system comprises an escape module (24) which is in fact a recoverable ballistic capsule held to the end face of the tail portion of the fuselage (1). The capsule (24) communicates with the crew compartment (10) through a tunnel (25) provided with means for crew transfer from the crew compartment (10) to the capsule (24). The capsule (24) has a front and a rear hatch, an aerodynamic decelerator, and a parachute system. The front portion of the capsule (24) has a heat-protective coating (36). The center of mass of the capsule is displaced towards its front portion. |
