| 摘要 |
FIELD: transport. ^ SUBSTANCE: spacecraft incorporates heat-insulated blunted cone airframe, a swept wing, components of aerodynamic and gas-dynamic stabilisation and control over pitch, bank and yaw including a tail trimming plate. A swept wing is arranged on the airframe in a mid-wing configuration. The airframe lower surface consists of a rear and a front part coupled with the blunted cone. The spacecraft front part projection onto its vertical symmetry plane forms an outline decrementing towards the rear part, the tangent to the said outline making an angle, at the point of its convergence with the said blunted cone, allowing a tolerable heating the swept wing leading edge. The rear part projection onto the same plane forms an outline converging with the front part outline. The de-orbiting method features using the aforesaid spacecraft at the balancing angles of attack providing for an aerodynamic flow over the said wing forming the flow lines with velocity vectors directed, primarily, along the swept wing leading edge. ^ EFFECT: Reduction of heat load by existing heat-resistant materials and lower operational costs. ^ 2 cl, 12 dwg |
