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Convex optimization-based fast trajectory optimization method of vertical take-off and landing reusable launch vehicle

A trajectory optimization, vertical take-off and landing technology, applied in the direction of integrated navigator, internal combustion piston engine, mechanical equipment, etc., can solve the problems that cannot meet the needs of return guidance

Inactive Publication Date: 2019-03-15
HARBIN INST OF TECH
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AI Technical Summary

Problems solved by technology

[0003] In order to solve the technical problem that traditional off-line trajectory optimization cannot meet the requirements of return guidance, the present invention solves the problem of high-precision return and landing guidance of vertical take-off and landing reusable vehicles under the framework of closed-loop guidance method based on online optimization, and proposes a method based on Convex optimized fast trajectory optimization method for vertical take-off and landing reusable vehicle

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  • Convex optimization-based fast trajectory optimization method of vertical take-off and landing reusable launch vehicle
  • Convex optimization-based fast trajectory optimization method of vertical take-off and landing reusable launch vehicle
  • Convex optimization-based fast trajectory optimization method of vertical take-off and landing reusable launch vehicle

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Embodiment 1

[0060] A fast trajectory optimization method for a vertical take-off and landing reusable carrier based on convex optimization, the optimization method comprising:

[0061] Step 1: Establish an optimization model for the return and landing trajectory of the vertical take-off and landing reusable vehicle;

[0062] Step 2, discretize the return landing trajectory optimization model;

[0063] Step 3: Convexize the discrete trajectory optimization problem;

[0064] Step 4: Establish a sequential convexization algorithm that guarantees convergence performance.

[0065] Among them, the specific process of establishing the return and landing trajectory optimization model of the vertical take-off and landing reusable vehicle described in step 1 is as follows: Aiming at the return and landing problem of the vertical take-off and landing reusable vehicle, a trajectory optimization model with the most economical fuel as the performance index is established. The trajectory optimization ...

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Abstract

The invention relates to a convex optimization-based fast trajectory optimization method of a vertical take-off and landing reusable launch vehicle, and belongs to the technical fields of aircraft trajectory optimization and guidance. The method comprises the following steps: step 1, establishing an optimization model for a return landing trajectory of the vertical take-off and landing reusable launch vehicle; step 2, discretizing the optimization model for the return landing trajectory; step 3, convexing a discretized trajectory optimization problem; and step 4, establishing a sequence convexing algorithm capable of ensuring the convergence performance. The method provided by the invention has the characteristics of high precision, high accuracy and solving fastness.

Description

technical field [0001] The invention relates to a rapid trajectory optimization method for a vertical take-off and landing reusable carrier based on convex optimization, and belongs to the technical field of aircraft trajectory optimization and guidance. Background technique [0002] Accurate soft landing is a classic problem with a long history of research and practice at home and abroad. In recent years, as the Falcon-9 (Falcon-9) rocket of the United States Space Exploration Technology Corporation has successfully launched and recovered its sub-stages, the vertical takeoff and landing reusable launch vehicle (Vertical Takeoff Vertical Landing Reusable Launch Vehicle, VTVL-RLV) Level return technology has attracted extensive attention from scholars at home and abroad. Sub-level return guidance is a key technology of VTVL-RLV. During the sub-level return process, it is necessary to use limited control capabilities to achieve a wide range of deceleration, meet process const...

Claims

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24Y02T10/40
Inventor 韦常柱崔乃刚王劲博李源徐大富
Owner HARBIN INST OF TECH
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