Flight dynamics and control, vehicle design, optimization and its nume rical method are employed to optimize the ascent trajectories and airbreathing propulsion system performance of two-stage-to-orbit (TSTO) launch vehicles with horizontal takeoff (HTO).
英
美
- 基于Sanger的氣動(dòng)外形、推進(jìn)系統模型、質(zhì)量模型等，采用飛行力學(xué)、最優(yōu)控制理論及其數值計算等方法，研究了二級入軌水平起飛載機最小起飛質(zhì)量的上升軌跡，得到了給定任務(wù)需求條件下吸氣式組合發(fā)動(dòng)機總體性能（推力、燃料消耗率隨飛行軌跡的變化規律）要求。
