Method for quickly optimizing low-thrust trajectory of periodic orbit phase modulation of three-body system

A system cycle and optimization method technology, applied in the aerospace field, to achieve the effect of improving accuracy and efficiency, wide application range, and low initial value guessing efficiency

Active Publication Date: 2022-03-08
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] In order to solve the phase modulation problem of the periodic orbit in the three-body system with strong nonlinear dynamics, the main purpose of the present invention is to provide a fast optimization method for the low-thrust orbit...

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  • Method for quickly optimizing low-thrust trajectory of periodic orbit phase modulation of three-body system
  • Method for quickly optimizing low-thrust trajectory of periodic orbit phase modulation of three-body system
  • Method for quickly optimizing low-thrust trajectory of periodic orbit phase modulation of three-body system

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Embodiment 1

[0068] Embodiment 1: Two phase points of 0° and 180° on the Halo orbit in the Earth-Moon three-body system are selected as the start and end positions, and the corresponding orbital states are shown in Table 1. The initial mass of the detector is 100kg, and the maximum thrust of the engine is T max =90mN, the specific impulse is = 3100s. The duration of the phasing process is set to 27 days, but it would take about 7 days to shift from 0 degrees to 180 degrees on the Halo orbit, and the implementation is lagging phasing.

[0069] Table 1 Initial and terminal states of the phase modulation track (normalized)

[0070] state x y

z

Vx

Vy

Vz

initial value 1.1087 0 0.0390 0 0.2093 0 end value 1.0353 0 0.0185 0.4202 0.3735 -0.0124

[0071] As shown in Figure 1, this embodiment discloses a three-body system periodic orbit phase modulation method for fast orbit optimization with low thrust.

[0072] As shown in Figure 1,...

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Abstract

The invention discloses a low-thrust trajectory rapid optimization method for periodic orbit phase modulation of a three-body system, and belongs to the technical field of aerospace. The implementation method comprises the following steps: establishing a dynamic model of the detector in consideration of thrust in a three-body system; according to phase modulation orbit constraints and dynamic characteristics, a specific form of a three-body system low-thrust phase modulation optimization problem is given, and the specific form refers to consideration of start and end state equality constraints, thrust component equality constraints and thrust magnitude inequality constraints of a three-body system phase modulation orbit corresponding to start and end moments. The maximum quality of the tail end of the detector is used as a specific form of a phase modulation optimization problem of a performance index; linearization processing is carried out on the established three-body system dynamic model, relaxation processing is carried out on obtained thrust equality constraints, and convexity of the three-body system low-thrust phase modulation optimization problem is achieved; and the optimal phase modulation orbit of the periodic orbit of the three-body system is obtained through numerical integration and successive approximation strategy rapid iteration solution, and rapid optimization of the low-thrust orbit of the three-body system is realized.

Description

technical field [0001] The invention relates to a low-thrust orbit rapid optimization method for phase modulation of a three-body system periodic orbit, and is especially suitable for the rapid optimization of a small-thrust phase modulation orbit considering the initial and final phase constraints of a periodic orbit in a three-body system, and belongs to the field of aerospace technology. Background technique [0002] Due to its special dynamic characteristics, Lagrangian points have been widely focused in recent years. Combining the inherent advantages of three-body dynamics with advanced propulsion technologies can yield richer mission benefits. The large thrust-to-weight ratio of the low-thrust engine greatly reduces the propellant consumption in the mission, so the application prospect of designing low-thrust orbits in the three-body system is excellent. The phasing of Lagrangian point periodic orbits is an essential technique in tasks such as Lagrangian point formati...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 乔栋贾飞达韩宏伟李翔宇
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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