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<p>To address the trajectory optimization requirements for horizontal takeoff and landing (HTOL) vehicles with low fuel consumption and rapid ascent capabilities, this study develops a trajectory optimization framework based on hp-adaptive pseudospectral methods. Considering the time-varying characteristics of engine thrust profiles and aerodynamic parameters, this study systematically formulates operational constraints and establishes a multi-objective optimization model targeting minimized flight duration and fuel consumption. A comprehensive case study is conducted on a turbine-based powered vehicle, with numerical simulations demonstrating full compliance with all physical constraints. The proposed method achieves high-precision trajectory generation with a 30.16-s reduction in ascent time compared to conventional fuel-optimal solutions while maintaining fuel consumption within 0.51<InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(\%\)</EquationSource> <EquationSource Format="MATHML"><math> <mo>%</mo> </math></EquationSource> </InlineEquation> of theoretical minima. This work provides a validated technical pathway for designing time-sensitive rapid ascent trajectories under coupled propulsion–aerodynamic interactions.</p>

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A Rapid Ascent Trajectory Optimization Method for Horizontal Takeoff and Landing Vehicle

  • 期刊论文

  • 发表日期：

    2026年1月24日

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  • Xu-Jin Li,
  • Guang-Chun Zhang,
  • Qun Zhang,
  • Yu-Chuan Hu,
  • Zhe Zhen

摘要

To address the trajectory optimization requirements for horizontal takeoff and landing (HTOL) vehicles with low fuel consumption and rapid ascent capabilities, this study develops a trajectory optimization framework based on hp-adaptive pseudospectral methods. Considering the time-varying characteristics of engine thrust profiles and aerodynamic parameters, this study systematically formulates operational constraints and establishes a multi-objective optimization model targeting minimized flight duration and fuel consumption. A comprehensive case study is conducted on a turbine-based powered vehicle, with numerical simulations demonstrating full compliance with all physical constraints. The proposed method achieves high-precision trajectory generation with a 30.16-s reduction in ascent time compared to conventional fuel-optimal solutions while maintaining fuel consumption within 0.51 \(\%\) % of theoretical minima. This work provides a validated technical pathway for designing time-sensitive rapid ascent trajectories under coupled propulsion–aerodynamic interactions.