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Grid fin of supersonic velocity guided missile

A grid wing and supersonic technology, which is applied in the field of modern aerospace, can solve the problems of large resistance of grid wings, and achieve the effect of reducing shock wave resistance.

Inactive Publication Date: 2013-06-19
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to further overcome the problem of the large resistance of the grid wing due to the "blocking" phenomenon, the present invention proposes a grid wing of a supersonic missile

Method used

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  • Grid fin of supersonic velocity guided missile
  • Grid fin of supersonic velocity guided missile
  • Grid fin of supersonic velocity guided missile

Examples

Experimental program
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Embodiment Construction

[0030] This embodiment is a supersonic missile grid wing 2 for a cruise missile whose Mach number is designed to be 3, including spanwise partitions and chordwise partitions. The span-wise partition is a partition parallel to the span of the wing, consisting of the first partition 3, the second partition 4, the third partition 5 and the fourth partition 6; the chord-wise partition It is a partition parallel to the chord direction of the wing and consists of the fifth partition 7 , the sixth partition 8 , the seventh partition 9 and the eighth partition 10 .

[0031] The grid wing is the same as the prior art, and is in the shape of a rectangular grid. The length direction of the grid wing is the span direction, and the width direction is the chord direction. The grid wing is composed of span-direction partitions and chord-direction partitions. Four chord-direction partitions are arranged in sequence along the span direction of the wing, and the four span-direction partitions...

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Abstract

A grid fin of a supersonic velocity guided missile comprises spanwise clapboards and chordwise clapboards. An upper supper surface and a lower surface of two sides, in the length direction, of each spanwise clapboard are symmetrical wedge surfaces. A surface, located at a long edge of the front edge of the grid fin, of a fifth clapboard and an eighth clapboard is processed into a wedge surface, and the wedge surface is located on an outer surface of the grid fin. Two surfaces, located at the front edge of the grid fin, of long edges of a sixth clapboard and a seventh clapboard are both processed into wedge surfaces. Wedge surfaces of all the spanwise clapboards and the chordwise clapboards can effectively reduce interference effect from shock waves produced by the chordwise clapboards to reducing shock waves of the spanwise clapboards.

Description

technical field [0001] The invention relates to the field of modern aerospace, in particular to a supersonic missile grid wing for drag reduction by using the principle of wave elimination. Background technique [0002] The grid wing is a multi-faceted wing with a honeycomb structure. Its advantages are that it has aerodynamic characteristics such as a large stall angle of attack and a small hinge moment in a wide range of Mach numbers. It also has light weight, stiffness and bending strength. High structural characteristics of single wing. The use of grid wings on the missile can reduce the mass of the empennage, reduce the power of the steering gear, reduce the separation of airflow during maneuvering flight at high angles of attack, increase the aerodynamic lift and control torque, and further improve the maneuverability of the missile. [0003] However, due to the "choking" phenomenon of the grid wing during supersonic flight, the shock wave resistance of the existing g...

Claims

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Application Information

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IPC IPC(8): F42B10/04
Inventor 叶正寅华如豪李伟杰田八林张伟伟武洁
Owner NORTHWESTERN POLYTECHNICAL UNIV
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