Multi-body simulation data interaction method for launch vehicle

A technology for launch vehicles and simulation data, which is applied in the fields of electrical digital data processing, design optimization/simulation, special data processing applications, etc. Uniform effect

Active Publication Date: 2017-02-08
BEIJING INST OF ASTRONAUTICAL SYST ENG +1
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  • Abstract
  • Description
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Problems solved by technology

The state switching of these components is connected in time, and at the same time there is complex data exchange between the components, the simu...

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  • Multi-body simulation data interaction method for launch vehicle

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Embodiment Construction

[0033] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0034] The present invention establishes a flexible multi-body dynamics virtual prototype, replaces the currently commonly used mathematical model, and carries out the dynamics simulation of the launch vehicle. The specific multi-body simulation data interaction method of the launch vehicle includes the following steps:

[0035] (1), set up rocket finite element calculation model by finite element software, and verify the correctness of finite element model by modal test result, enter step (2) after verification is correct, the finite element software that adopts among the present invention is Patran.

[0036] (2) Carry out the shutdown analysis of the launch vehicle, update or obtain the current timing time, which is realized by the timing generator, and the specific implementation method is as follows:

[0037] (2.1) Establish a timing array d...

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Abstract

The invention relates to a multi-body simulation data interaction method for a launch vehicle. The method comprises the following steps: step (1), establishing a finite element model of the launch vehicle; step (2), performing shutdown analysis of the launch vehicle, updating or acquiring the current time sequence; step (3), performing time series analysis for each component of the launch vehicle and acquiring the status of each component of the launch vehicle through the time sequence and a preset offset value; step (4), configuring status parameters for each component of the launch vehicle, establishing interactive data cards between various components, and filling the interactive data cards with output parameters of the various components under the current status; and step (5), using a Lagrange equation of the first kind to discretize the finite element model established in the step (1) and external forces generated by the various components in the step (4) into differential-algebraic equations, solving the equations, and obtaining the displacement and load of each node in the finite element model of the launch vehicle. The multi-body simulation data interaction method for the launch vehicle provided by the invention realizes the general dynamics simulation of the launch vehicle, and realizes the calculation of the flight trajectory, attitude and load of the launch vehicle.

Description

technical field [0001] The invention relates to a multi-body dynamics simulation method with instruction actions, in particular to a launch vehicle multi-body simulation data interaction method, which belongs to the field of launch vehicle dynamics simulation. Background technique [0002] During the flight of the launch vehicle, after each component switches the state according to the sequence and time series instructions, the rocket is controlled to work in the new state. For example, the engine starts and generates thrust after receiving the start-up command, the propellant in the storage tank is consumed accordingly, and the orbital attitude of the rocket body changes continuously. Similar parts include solid small rockets, breakaway springs, explosive bolts, arrow-on computers, pneumatic forces, and more. The state switching of these components is connected in time, and at the same time, there is complex data exchange between the components, making simulation programmi...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 汤波张兵张欢程兴杨云飞陈宇胡鹏翔李君马英黄辉陈风雨赵治华容易
Owner BEIJING INST OF ASTRONAUTICAL SYST ENG
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