A Parametric Judgment Method for Binding Position of Solid Binding Rockets

A judgment method and parametric technology, applied in the field of aerospace, can solve problems such as design efficiency and achieve the effect of optimizing design and avoiding duplication of labor

Active Publication Date: 2019-02-05
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Abstract
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Problems solved by technology

[0007] The purpose of the present invention is to solve the problem of design efficiency in the analysis of the mechanical characteristics of the solid-bound launch vehicle in the prior art, and to propose a parametric determination method for the binding position of the solid-bound launch vehicle

Method used

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  • A Parametric Judgment Method for Binding Position of Solid Binding Rockets
  • A Parametric Judgment Method for Binding Position of Solid Binding Rockets
  • A Parametric Judgment Method for Binding Position of Solid Binding Rockets

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Embodiment

[0027] Taking the determination of the binding position of a certain type of rocket as an example, the structural diagram of the rocket is as follows: figure 1 shown, press figure 2 To establish the rocket coordinate system, use the "I-II-III-IV" rocket coordinate system, that is, the Cartesian coordinate system of the right-hand rule. The quadrants of the rocket coordinate system II coincide, the positive direction of the x-axis of the coordinate system follows the right-hand rule and points to the negative direction of the rocket arrow axis (that is, the fairing points to the direction of the tail section of the rocket), and the origin of the coordinate system is located at the theoretical cusp of the von Karman curve of the fairing.

[0028] For the binding form of solid bound rockets, the analysis model adopts the three-bar connection form, such as image 3 As shown, the binding position is closer to the origin of the coordinate system, which is the front binding. Ball ...

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Abstract

The present invention relates to a parameterization determination method of strap-on positions of a solid strap-on rocket, and belongs to the aerospace field. The determination method comprises first simplifying a rocket model by using a beam-lumped mass model, selecting a first strap-on combination position as an original position, and performing finite element modeling and resolving on the whole rocket by using a finite element method; and then changing the strap-on position, obtaining a parameterization formal model described by PCL language through the model of the first strap-on combination position, modeling and resolving again after the strap-on position of the original model is replaced by the new strap-on position, and resolving models of remained strap-on positions by using the same method. According to the determination method, duplication of labor brought to designers during a finite element modeling process of changing the strap-on positions of the solid strap-on rocket is avoided, design efficiency of rocket mechanical characteristic analysis is improved, and combined with the prior art in the engineering field, optimal design of the solid strap-on rocket can be achieved.

Description

technical field [0001] The invention relates to a parameterized determination method for the bundling position of a solid-bound rocket, belonging to the field of aerospace. Background technique [0002] The launch vehicle is an effective technical means to send ground payloads into space orbit. my country's current lunar exploration project, space station project and Mars program are closely related to launch vehicle technology. Among them, the analysis of the mechanical characteristics of the rocket is a key part of the design stage of the launch vehicle. In view of the difference in the binding position of the booster, in order to obtain the best binding position, it is necessary to carry out parametric modeling and analysis on the launch vehicle. [0003] The mechanical properties of a launch vehicle include static properties and dynamic properties. The mass characteristics play an important role in the analysis of the mechanical properties of the launch vehicle, and th...

Claims

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Application Information

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Patent Type & AuthorityPatents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23
Inventor周思达余磊刘莉
OwnerBEIJING INSTITUTE OF TECHNOLOGYGY