适用于天基测控小范围视线角约束的运载火箭轨道优化设计

Launch Vehicle Trajectory Optimal Design for Small-scale Line-of-sight Constraint of Space-based TT&C Technology

测控系统对运载火箭的约束是轨道优化设计的重要条件。随着卫星平台高度和宽度的增加,导致天基测控视线角约束越来越严苛。为保证发射大型卫星任务仍适用于天基测控,对运载火箭轨道进行优化设计,以运载能力最优为目标,迭代飞行程序角,满足天基测控小范围视线角约束条件,进而延长测控弧段。分析了运载火箭轨道优化设计对天基测控特性的改善作用。

The constraints of measurement and control system are crucial criteria for launch vehicle trajectory optimal design. The increase of width and height of satellite platform ultimately results in much more stringent constraints. Trajectory optimal design was carried out to insure space-based TT＆amp;C（tracking, telemetry and communications） technology still adaptable for large satellites, take optimal launch capability as the target, iterate flight program angle, and satisfy small-scale line-of-sight constraint, then extend observe and control period. The improvement of trajectory optimal design for space-based TT＆amp;C characteristic is presented.