Airborne embedded vertical launching device

A vertical launch and missile launch technology, applied in the field of vertical launch, can solve problems such as limiting the maneuverability and attack potential of combat aircraft, and achieve the effect of improving attack and defense capabilities

Inactive Publication Date: 2021-03-12
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] With the improvement of the dynamic capabilities of new manned/unmanned combat aircraft in the future, the traditional method o...

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  • Airborne embedded vertical launching device
  • Airborne embedded vertical launching device

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Embodiment Construction

[0023] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The invention belongs to the technical field of vertical launching, and particularly relates to an airborne embedded vertical launching device. The device comprises a mounting frame, a fuel gas exhaust pipeline, a heat insulation box body and an emission controller. A plurality of vertical launching wells arrayed in a matrix mode are arranged on the mounting frame, missiles are mounted in the vertical launching wells, and missile launching opening covers are arranged at the ends of the vertical launching wells. One end of the fuel gas exhaust pipeline is connected with the mounting frame, an internal channel of the fuel gas exhaust pipeline is communicated with the vertical launching wells, and a machine body flame exhaust opening cover is arranged at the other end of the fuel gas exhaustpipeline. The heat insulation box body is installed in a machine body and used for containing the mounting frame, the vertical launching wells and the fuel gas exhaust pipeline. The emission controller is used for controlling the launching of the missiles. After being assembled to an aircraft, the aircraft not only reserves the forward missile attacking capacity, but also has the attacking capacity towards the upper portion and the lower portion of the aircraft body, and the attacking and defending capacity of the combat aircraft in short-distance air combats is improved.

Description

technical field [0001] The application belongs to the technical field of vertical launching, and in particular relates to an airborne embedded vertical launching device. Background technique [0002] Combat air-to-air missiles are the main short-range air combat weapons of current combat aircraft. Affected by the way weapons are mounted, combat air-to-air missiles usually adopt the external / internal suspension along the course. Although advanced combat air-to-air missiles already have a large off-axis launch angle, in order to improve the hit rate in actual use, they still seek to attack from the rear hemisphere of the target. [0003] With the improvement of the dynamic capabilities of new manned / unmanned combat aircraft in the future, the traditional method of launching missiles in short-range combat has limited the maneuverability and attack potential of combat aircraft in close-range air combat. [0004] Therefore, it is desirable to have a technical solution to overcom...

Claims

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Application Information

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IPC IPC(8): F41F1/00
CPCF41F1/00
Inventor 岳智敏王玉浩张健
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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