A double-helix inflatable deployable spin-stabilized deceleration vehicle

A spin-stabilized, double-helix technology, applied in the direction of aerospace vehicle guidance devices, can solve problems such as instability and inability to spin attitude, and achieve the effect of increasing the drag area

Active Publication Date: 2017-01-25
HARBIN INST OF TECH
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  • Claims
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Problems solved by technology

[0003] In order to solve the problems of the existing air-deployable deceleration vehicle technology that cannot spin itself and the attitude is unstable during flight, the present invention provides a double-helix inflatable expansion-type spin-stabilized deceleration vehicle

Method used

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  • A double-helix inflatable deployable spin-stabilized deceleration vehicle
  • A double-helix inflatable deployable spin-stabilized deceleration vehicle
  • A double-helix inflatable deployable spin-stabilized deceleration vehicle

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Embodiment Construction

[0012] The technical solution of the present invention will be further described below in conjunction with the accompanying drawings, but it is not limited thereto. Any modification or equivalent replacement of the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention should be covered by the present invention. within the scope of protection.

[0013] Such as Figure 1-5 Said, the double-helix inflatable expansion-type spin-stabilized deceleration vehicle provided by the present invention consists of a rigid spherical nose cone 1, an inflatable ring resistance surface 2, a segmented diaphragm, a high-pressure gas cylinder 3, a decompression valve 4, a conduit 9, a cylindrical The load box consists of 8 seven parts, among which:

[0014] The resistance surface of the inflatable ring is a double helix formed by double helix rings, wherein: the double helix ring is composed of A helix ring 5 and...

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Abstract

The invention discloses a double-helix inflatable deployment type spinning-stability reduction aircraft. The spinning-stability reduction aircraft comprises a rigid spherical nose cone, an inflatable circular-ring resistance surface, a sectional type diaphragm, a high-pressure gas cylinder, a pressure decompression valve, a guide tube and a cylindrical load box. The double-helix inflatable deployment type spinning-stability reduction aircraft provided by the invention is initially in a collapsed state; and when the aircraft reaches a predetermined rail, the pressure decompression valve is started, the high-pressure gas cylinder in the rigid nose cone starts inflating gas, and two spiral gas-inflating rings sequentially pass through the inner diaphragm to spirally ascend, expand, stretch and form. By virtue of ring slots between adjacent two spiral circular rings which are symmetrical clockwise (or anticlockwise) with a difference of 180 degrees, the structure spins up by virtue of aerodynamic force generated by detour-flow gas, so that the stability problem in a process that an inflatable deployment type reduction aircraft structure flies to enter or re-enter is solved; meanwhile, the resistance area of the structure is greatly improved by virtue of an inflatable deployment part, so that the reduction of the aircraft structure is effectively realized, and recycling of the load box is completed.

Description

technical field [0001] The invention relates to a double-helix inflatable expansion type spin-stabilized deceleration aircraft, which belongs to the field of variable configuration structure design of aerospace vehicles. Background technique [0002] CN104290921A discloses an inflatable deployment aerodynamic damping reducer structure. The inflatable deployment type deceleration aircraft has the disadvantage that it cannot spin itself during flight, cannot achieve spin stability, and is prone to the problem of structural attitude rollover. Contents of the invention [0003] In order to solve the problems of inability to spin itself and unstable attitude during flight in the existing technology of the inflatable deployable deceleration aircraft, the present invention provides a double-helix inflatable deployable spin-stabilized deceleration aircraft. [0004] The purpose of the present invention is achieved through the following technical solutions: [0005] A double-helix...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/28
Inventor 卫剑征谭惠丰侯雪苗常青林国昌谢志民
Owner HARBIN INST OF TECH
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