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Rocket recovery trajectory optimization method with optimal terminal time estimation

A technology for trajectory optimization and time estimation, which is applied to systems, instruments, geometric CAD, etc. for space vehicles to return to the earth's atmosphere.

Pending Publication Date: 2022-03-01
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Description
  • Claims
  • Application Information

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Problems solved by technology

In the existing research on lossless convexization methods, there are few studies on determining the optimal terminal time, and the calculation efficiency of estimating the optimal terminal time is poor

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  • Rocket recovery trajectory optimization method with optimal terminal time estimation
  • Rocket recovery trajectory optimization method with optimal terminal time estimation
  • Rocket recovery trajectory optimization method with optimal terminal time estimation

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Embodiment Construction

[0074] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0075] The invention provides a rocket recovery trajectory optimization method with optimal terminal time estimation, which can quickly estimate the optimal terminal time, has good convergence performance, has high precision and calculation efficiency, and has the potential of online application.

[0076] 1 Problem description

[0077] (1) Kinetic model

[0078] Regardless of the rotation of the earth, regard the earth as a uniform sphere, ignore the influence of the Coriolis inertial force, consider the drag and lift, and define the coordinate system of the landing point as figure 2 shown. In the figure, the origin O of the coordinate system is the landing point, the Oy axis is vertical to the ground, the Ox axis is in the same direction as the projection of the velocity vector on the ground at the initial moment, and the Oz axis and the Ox and Oy axes...

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Abstract

The invention discloses a rocket recovery trajectory optimization method with optimal terminal time estimation, which comprises the following steps of: firstly, demonstrating a rocket sublevel acceleration change trend based on an optimal control theory, and further giving an analysis form of a terminal acceleration upper bound by utilizing terminal state constraint; meanwhile, in consideration of the flight state of a rocket sublevel landing section, the thrust adjusting capacity of an engine, the mass flow of a spray pipe and other limiting conditions, the acceleration change rate relative to the speed change rate (acceleration) in the vertical landing process is small, and the maximum acceleration is selected as a lower bound judgment index. Finally, according to the continuous change characteristic of the rocket sub-level acceleration, a terminal acceleration estimation formula in an n-order polynomial form is introduced, and the upper bound and the lower bound of the optimal terminal time are given by comparing the terminal acceleration estimation value in the polynomial form with the upper bound of the terminal acceleration; according to the method, the optimal terminal time can be quickly estimated, the convergence performance is good, the precision and the calculation efficiency are high, and the potential of online application is achieved.

Description

technical field [0001] The invention belongs to the technical field of rocket recovery, and in particular relates to a rocket recovery trajectory optimization method with optimal terminal time estimation. Background technique [0002] How to quickly enter space at low cost has always been an important research topic in the field of space delivery since human beings started space exploration activities. With the repeated success of Space X's Falcon rocket recovery and reuse, the vertical take-off and landing reusable launch vehicle solution has received widespread attention. body reuse, its typical flight profile is as figure 1 shown. [0003] According to the flight environment and dynamic characteristics of the reusable rocket sub-stage, the vertical recovery process can be divided into an attitude adjustment segment, a flight repair segment, a high-altitude descent segment, a power deceleration segment, an aerodynamic deceleration segment, and a vertical landing segment....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15B64G1/62G06F119/14
CPCG06F30/15B64G1/62G06F2119/14Y02T10/40
Inventor 郭杰相岩王肖史鹏飞唐胜景
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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