Carrier rocket and launching supporting tail section thereof

A carrier rocket and tail section technology, which is applied in launch systems, transportation and packaging, aerospace equipment, etc., can solve problems such as difficulty in ensuring load-bearing stability, and achieve the effect of ensuring load-bearing stability

Active Publication Date: 2020-10-30
北京中科宇航技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The tail section of a traditional launch vehicle usually adopts a diffused stringer structure, and the overall rigidity is increased through the middle ring frame, or a casting structure is used to distribute the load evenly to meet the load index received by the tail section, but the launch support of the existing launch vehicle If the tail section is equipped with a roll control device, it is difficult to ensure the stability of its load

Method used

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  • Carrier rocket and launching supporting tail section thereof
  • Carrier rocket and launching supporting tail section thereof
  • Carrier rocket and launching supporting tail section thereof

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Embodiment Construction

[0022] The following describes in detail the embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. In addition, spatial relationship terms such as "upper", "above", "under", "below", etc. are used to facilitate description to explain the positional relationship between two components. The embodiments described below by referring to the drawings are examples It is only used to explain the present invention, but not to limit the present invention.

[0023] see Figure 1 to Figure 3 , the application provides a launch support tail section of a launch vehicle, comprising: an upper support ring 110, a lower support ring 120, a skin 130, a plurality of stringers 140, a multi-section middle frame 150, an upper middle frame 160, a lower middle Frame 170 and roll control mounting bracket 180. ...

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PUM

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Abstract

The invention relates to a carrier rocket and a launching supporting tail section thereof. The launching supporting tail section comprises an upper supporting ring, a lower supporting ring, a skin, stringers, a middle frame, an upper-layer middle frame, a lower-layer middle frame and a roll control mounting support. The stringers are fixed between the upper supporting ring and the lower supportingring, and the skin is fixed on the inner sides of the upper supporting ring, the lower supporting ring and the stringer; the middle frames are arranged on one circumference of the inner side surfaceof the skin, installation vacancies are formed between every two adjacent middle frames end to end in a spaced mode, and the roll control mounting support is installed at the installation vacancies. Connecting parts of two empennages and a rocket are directly inserted into the two adjacent stringers corresponding to the installation vacancies, the connecting parts of the two empennages and the rocket are symmetrically arranged on the upper side and the lower side of the middle frame, and the inner sides of the empennages are hinged to the connecting parts of the empennages and the rocket; andthe upper-layer middle frame is arranged above the installation vacancies, and the lower-layer middle frame is arranged below the installation vacancies. A roll control device is arranged at the launching supporting tail section of the carrier rocket, and bearing stability of the launching supporting tail section is guaranteed.

Description

technical field [0001] The present application relates to the field of launch vehicle technology, in particular to a launch vehicle and its launch support tail section. Background technique [0002] The launch support tail section of the launch vehicle is used as the "cornerstone" for the launch vehicle to be erected. After the rocket is erected, it is fixedly connected to the launch tower platform. The launch support tail section of the launch vehicle bears the vertical weight of the entire arrow. Under the vertical condition of the rocket, the launch support tail section of the launch vehicle bears the bending moment generated by the windward side of the rocket body by the ground wind, and the launch support tail section of the launch vehicle also bears Simplify the braking load during transportation and hoisting, so the load-bearing performance of the launch support tail section of the launch vehicle is particularly important. [0003] The launch support tail section of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G5/00B64G1/00
CPCB64G5/00B64G1/002
Inventor 杨浩亮杨毅强张志博张东博明爱珍孙良杰
Owner 北京中科宇航技术有限公司
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