Rocket engine nozzle swing simulation analysis method and system

A rocket engine and simulation analysis technology, applied in the field of rockets, can solve the problems of heavy workload, inability to solve the nozzle can not be reversed, high programming ability requirements of designers, etc., to achieve the effect of reducing labor intensity, good portability and applicability

Active Publication Date: 2020-08-18
北京中科宇航技术有限公司
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Problems solved by technology

The disadvantages of this method are: the workload is large when calculating point by point, and the method of solving constraint equations by programming requires high programming ability of designers
[0004] Second, establish a motion simulation method, establish a motion simulation analysis in the 3D motion simulation software, use a spherical joint to replace the joint bearing of the nozzle swing center and the servo actuator, and replace the elongation and shortening of the servo actuator with a translational hinge , arranging the dynamic measurement features to get the stroke curves of the two servo actuators. The defect of this method is that the spherical joint constraint is established when the nozzle swings in the full axis, but the spherical joint constraint cannot solve the problem that the nozzle cannot be twisted during the swing process. question

Method used

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  • Rocket engine nozzle swing simulation analysis method and system
  • Rocket engine nozzle swing simulation analysis method and system
  • Rocket engine nozzle swing simulation analysis method and system

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Effect test

Embodiment 1

[0040] Such as figure 1 As shown, the application provides a rocket engine nozzle swing simulation analysis method, the simulation analysis method includes the following steps:

[0041] Step S1, establishing a parameterized three-dimensional constrained simulation model of nozzle swing geometry.

[0042] On the existing parametric 3D modeling software, a parametric nozzle swing geometric 3D constraint simulation model is established, and simple geometric constraints are performed on the nozzle swing process.

[0043] Such as figure 2 As shown, step S1 includes:

[0044] Step S110, establishing the swing geometry of the nozzle before swinging in the three-dimensional space.

[0045] Specifically, the structure size of the nozzle before the nozzle swing and the position constraint before the swing are established. Among them, the structural size of the nozzle is pre-designed according to the design of the engine; the position constraint is the swing geometry before the swing ...

Embodiment 2

[0093] Such as Figure 9 As shown, the present application provides a rocket engine nozzle swing simulation analysis system 100, the simulation analysis system includes: a model building module 10, used to establish a parameterized nozzle swing geometry three-dimensional constraint simulation model;

[0094] The driving parameter setting module 20 is used to set the driving parameters in the three-dimensional constraint simulation model of the parameterized nozzle swing geometry;

[0095] The generation module 30 is used to analyze the sensitivity of the actuator according to the set driving parameters, and generate the stroke curve and data of the actuator during the swinging process of the nozzle.

[0096] The beneficial effect that this application realizes is as follows:

[0097] (1) This application establishes a parameterized three-dimensional constrained simulation model of the nozzle swing geometry. The designer of the swing nozzle does not need to calculate the zero ...

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Abstract

The invention provides a rocket engine nozzle swing simulation analysis method and system. The rocket engine nozzle swing simulation analysis method comprises the following steps: establishing a parameterized nozzle swing geometric three-dimensional constraint simulation model; setting driving parameters in the parameterized nozzle swing geometry three-dimensional constraint simulation model; according to the set driving parameters, conducting sensitivity analysis on the actuator, and generating a stroke curve and data of the actuator in the swing process of the spray pipe. According to the rocket engine nozzle swing simulation analysis method, a parameterized nozzle swing geometry three-dimensional constraint simulation model is established, and actuator stroke curve data is directly generated during nozzle design and used for verifying a rocket flight control algorithm.

Description

technical field [0001] The present application relates to the field of rocket technology, in particular to a simulation analysis method and system for nozzle swing of a rocket engine. Background technique [0002] In rocket engine oscillating nozzle, when the center of oscillating nozzle and the upper fulcrum coincide with the plane perpendicular to the engine axis, two servo actuators at 90 degrees to each other will oscillate without involvement when the nozzle oscillates. When the pivot center of the nozzle and the plane perpendicular to the engine axis of the upper fulcrum do not coincide, the two actuators at 90 degrees to each other form a geometric constraint when the nozzle swings, thus causing the dragged swing of the nozzle. The existing rocket engine Nozzle swing analysis methods include the following two methods: [0003] First, establish the analysis method of the constraint equation. First, establish the assumptions: (1) the nozzle cannot be twisted; (2) the d...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/20G06F111/04
CPCG06F30/17G06F30/20G06F2111/04Y02T90/00
Inventor 张翔赖谋荣马玉海杨毅强
Owner 北京中科宇航技术有限公司
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