Tool kit and method for optimizing high-precision self-adaptation and modular spacecraft trajectory multi-constrained track

A spacecraft, multi-constraint technology, used in instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as large scale of nonlinear problems, low initial value sensitivity, and unstable terminal time, and achieve small scale. , the effect of reducing the sensitivity of the initial value

Active Publication Date: 2014-07-23
HARBIN INST OF TECH
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Problems solved by technology

[0007] The purpose of the present invention is to solve the problem that it is difficult to solve the problem of unfixed terminal time in the traditional method, the low precision cannot solve the two-point boundary value, the sensitivity of the initial value is low, and the scale of the obtained nonlinear problem is large. A multi-constraint trajectory toolkit and method for optimizing high-precision adaptive modular spacecraft trajectory

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  • Tool kit and method for optimizing high-precision self-adaptation and modular spacecraft trajectory multi-constrained track
  • Tool kit and method for optimizing high-precision self-adaptation and modular spacecraft trajectory multi-constrained track
  • Tool kit and method for optimizing high-precision self-adaptation and modular spacecraft trajectory multi-constrained track

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specific Embodiment approach 1

[0041]Specific implementation mode one: a kind of optimized high-precision self-adaptive modular spacecraft ballistic multi-constraint trajectory toolkit of this embodiment specifically includes:

[0042] Simulation platform main interface module, multiple optimization algorithm selection submodule, performance optimization index submodule, multi-constraint condition submodule (can be replaced), ballistic simulation submodule (can be replaced) and data processing and result display submodule; the above Different modules have their own functions and influence each other;

[0043] The main interface module of the simulation platform is user-oriented, including multiple optimization algorithm selection sub-modules, performance optimization index sub-modules, ballistic simulation sub-modules, multi-constraint sub-modules and data processing and result display sub-modules; real platform main The interface module has a special option menu and buttons for the help sub-module, which i...

specific Embodiment approach 2

[0052] Specific embodiment two: the difference between this embodiment and specific embodiment one is that the main interface module of the simulation platform is used to realize the selection of the spacecraft ballistic simulation mode set by the user through the main interface of the simulation platform according to the simulation requirements provided by the user, Load and set the reasonable simulation parameters of the spacecraft ballistic system, control the flow of the spacecraft ballistic simulation operation, query the results of the spacecraft ballistic simulation results to carry out the corresponding ballistic optimization design; (select and set reasonable parameters according to user needs to carry out the corresponding ballistic optimization design); the main interface module of the simulation platform belongs to the interface layer function module, and is the window for users to carry out simulation experiments; it includes a toolbar, a tree menu bar, and an opera...

specific Embodiment approach 3

[0058] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is that: a method for optimizing the multi-constraint trajectory toolkit of high-precision adaptive modular spacecraft trajectory includes the following steps:

[0059] Step 1. Before the spacecraft multi-constraint trajectory optimization toolkit software runs, register the Teechart drawing curve plug-in;

[0060] Step 2: After the Teechart drawing curve plug-in is successfully registered, open the spacecraft multi-constraint trajectory optimization toolkit software in the VC6.0 or higher version environment, compile the .exe file and enter the main interface module of the simulation platform;

[0061] Step 3. In the main interface module of the simulation platform, configure the flight mode and set the parameters in the flight mode setting option interface; the parameter settings include: selecting the flight segment of the missile, setting the parameters of the launch ...

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Abstract

The invention relates to the field of spacecraft trajectory tracks, and provides a tool kit and method for optimizing a high-precision self-adaptation and modular spacecraft trajectory multi-constrained track. By means of the tool kit and method, the problems that in a traditional method, unfixed terminal time is hard to solve, boundary values of two points can not be solved due to low precision, initial value sensitiveness is low and the scale of nonlinearity is large are solved. The tool kit comprises a simulation platform main interface, multiple optimization algorithm selections, performance optimization indexes, multiple constraint conditions and trajectory simulation. The method comprises the following steps of (1) registering curve plug-in, (2) compiling exe files and then getting access to the simulation platform main interface, (3) allocating an airplane mode and setting parameters, (4) optimizing variable initial values, performance index parameters and multiple constraint parameters of multiple optimization algorithms respectively, (5) carrying out simulation setting in a trajectory simulation sub module, (6) processing an optimization and simulation result of the spacecraft trajectory multi-constrained track. The tool kit and method are applied to the field of the spacecraft trajectory multi-constrained tracks.

Description

technical field [0001] The invention relates to a multi-constraint track optimization toolkit and method for optimizing high-precision self-adaptive modularization of spacecraft ballistics. Background technique [0002] Since any problem involving the overall optimization of spacecraft is inseparable from the inspection of the optimized trajectory, trajectory optimization has always been regarded as an important part of the overall optimization. Spacecraft trajectory optimization technology has been developed for more than half a century. The trajectory optimization technology is to establish the flight mechanics equation according to the specified tactical technical indicators, select the main design variables, construct the performance functional, and obtain the optimal flight trajectory by using relevant mathematical methods to solve the optimal variables. In essence, trajectory optimization can be abstracted as an open-loop optimal control problem that solves the extrem...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 郭继峰韦常柱崔乃刚黄荣
Owner HARBIN INST OF TECH
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