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A thermal protection device for rockets in extremely cold regions

A technology of protective device and heat preservation device, which is applied to offensive equipment, projectiles, self-propelled projectiles, etc., can solve problems such as blanks, and achieve the effect of fast construction speed and shortened preparation time.

Inactive Publication Date: 2020-10-30
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, no rocket heat preservation device that achieves heat preservation effect has been retrieved, and this field is still blank

Method used

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  • A thermal protection device for rockets in extremely cold regions
  • A thermal protection device for rockets in extremely cold regions
  • A thermal protection device for rockets in extremely cold regions

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] A rocket thermal protection device that can be withdrawn quickly, including an openable truss tube, a power unit, a slide rail and a heat preservation device; hinges and openings are provided on the facade of the openable truss tube to realize the opening and closing There is a pulley device at the bottom of the truss tube that can be opened and closed; the power device provides power for the withdrawal of the truss tube; the slide rail is an I-shaped steel rail fixed on the bottom surface. The pull-out resistance of the truss tube can be realized by cooperating with the pulley device, thereby realizing the stability of the truss tube under wind load.

[0027] The main body of the truss tube is two cylindrical trusses welded by I-shaped columns and angle steels with semicircular cross-sections. There are pulleys at the bottom of the hinge column, semicircular midpoint column and opening position. There is a "scissors twist" connection device in the middle of the truss t...

Embodiment 2

[0029] A rapidly retractable thermal insulation protection device for rockets, comprising an openable truss tube, a power unit, a slide rail and a heating and thermal insulation device; hinges and openings are provided on the facade of the openable truss tube to realize The opening and closing function of the truss tube can be opened and closed. There is a pulley device at the bottom of the truss tube; the power device provides power for the withdrawal of the truss tube; In addition to providing convenience, the pull-out resistance of the truss tube can also be realized by cooperating with the pulley device, thereby realizing the stability of the truss tube under wind load.

[0030] Divide the truss tube into figure 2The three parts shown form a semi-circular truss and two 1 / 4 round trusses, and the trusses of each part can be mutually "emphasis points" to realize symmetrical opening and closing, and are not easy to be stuck. There are pulley devices at the mid-point column ...

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PUM

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Abstract

The invention discloses a rocket thermal insulation protection device capable of being rapidly withdrawn and a method. The protection device comprise a truss barrel capable of being opened and closes,a power device, a sliding rail and a heating thermal insulation device; a hinge is arranged on the vertical surface of the barrel, and an opening is formed in the vertical surface of the barrel, so that the opening and closing function of the barrel is realized; the power device provides power for withdrawing the truss barrel; and the sliding rail is an I-shaped steel rail fixed to the bottom surface, not only can provide convenience for withdrawing the truss barrel, but also can achieve the pulling resistance of the truss barrel through a pulley device, so that the stability of the truss barrel under wind load is achieved. The protection device has the advantages that the construction speed is high, and rocket assembling in extremely cold weather can be completed quickly; and rapid withdrawal can be realized, and the rocket launching preparation time is shortened.

Description

technical field [0001] The invention relates to an independent rocket heat preservation and protection device and method, in particular to a rocket heat preservation and protection device and method for rapid retraction in extremely cold regions. Background technique [0002] The rocket is a complex system integrating nearly a thousand sets of single machines and thousands of large and small parts, which involves some composite materials, especially rubber materials for sealing, such as shock absorbers, airtight storage tanks and tubes in the rocket fairing. The seals in the road may seem like small parts, but they have a vital impact on the overall performance of the rocket. These components and materials are often sensitive to low temperature, and are prone to damage and failure under extremely cold conditions. When the external temperature is extremely low, it is necessary to set up a special thermal protection device to ensure that the temperature of the microenvironmen...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/00
CPCF42B15/00
Inventor 郭全全勾永宝王泽易
Owner BEIHANG UNIV
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