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Optimization of Perturbation Guidance Parameters based on Adjoint Sensitivity
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Ke YUE1, Junlong WANG1, Hao WEN1, Wenfeng ZHANG2
Missiles and Space Vehicles | 2025, 48(3) : 30 - 37
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Missiles and Space Vehicles | 2025, 48(3): 30-37
Guidance, Navigation and Control
Optimization of Perturbation Guidance Parameters based on Adjoint Sensitivity
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Ke YUE1, Junlong WANG1, Hao WEN1, Wenfeng ZHANG2
Affiliations
  • 1. Nanjing University of Aeronautics and Astronautics, Nanjing, 210016
  • 2. Shanghai Institute of Aerospace Systems Engineering, Shanghai, 201108
Published: 2025-06-25 doi: 10.7654/j.issn.2097-1974.20250305
Outline
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The guidance system, a core subsystem of launch vehicles, is crucial for the successful launch. Perturbation guidance, as the primary guidance method for domestic rockets within the atmosphere, relies on the design efficiency and precision of guidance parameters to determine the overall system performance. Traditionally, the parameter design is carried out by designers through extensive trial calculations and experience-based adjustments, resulting in low efficiency and high costs. To address this issue, an automatic optimization method for perturbation guidance parameters based on adjoint sensitivity and the Adam gradient descent algorithm is proposed. By constructing a point-mass dynamic model of the launch vehicle, the guidance parameter design is transformed into a constrained optimization problem. The adjoint sensitivity method is employed to efficiently compute the gradient of the objective function with respect to parameters, while the Adam algorithm adaptively adjusts the learning rate to achieve parameter auto-tuning. A two-stage launch vehicle is tested under random wind field disturbances. The perturbation guidance control parameters are optimized using a cost function that combines trajectory tracking errors and terminal range deviations. Simulation results show that the compared with the traditional manual tuning method, the proposed method can quickly find suitable control parameters. It provides an efficient and precise solution for the design of perturbation guidance parameters in launch vehicles, significantly reducing simulation time and design costs. The method also offers engineering reference value for improving the optimization efficiency of complex dynamic systems

adjoint sensitivity  /  launch vehicles  /  perturbation guidance  /  parameter optimization  /  Adam
Ke YUE, Junlong WANG, Hao WEN, Wenfeng ZHANG. Optimization of Perturbation Guidance Parameters based on Adjoint Sensitivity[J]. Missiles and Space Vehicles, 2025 , 48 (3) : 30 -37 . DOI: 10.7654/j.issn.2097-1974.20250305
Year 2025 volume 48 Issue 3
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Article Info
doi: 10.7654/j.issn.2097-1974.20250305
  • Receive Date:2025-03-09
  • Online Date:2025-10-27
  • Published:2025-06-25
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History
  • Received:2025-03-09
  • Revised:2025-04-24
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Affiliations
    1. Nanjing University of Aeronautics and Astronautics, Nanjing, 210016
    2. Shanghai Institute of Aerospace Systems Engineering, Shanghai, 201108
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表12种不同金属材料的力学参数

Family
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Number of
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Number of
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鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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