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Combined take-off and landing device for hypersonic vehicle wheel-ski

A kind of aircraft, superb technology, applied in the direction of wheels, landing gear, aircraft parts, etc., can solve the problems of lack of directional control ability and small structural space, so as to make up for weak cushioning performance, avoid excessive pressure, and ensure directional stability Effect

Active Publication Date: 2019-05-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This type of landing device occupies a small structural space, is resistant to ultra-high temperature and ultra-high landing horizontal speed, and has a light structural weight, but the traditional skid-type landing device does not have the ability to control the direction

Method used

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  • Combined take-off and landing device for hypersonic vehicle wheel-ski
  • Combined take-off and landing device for hypersonic vehicle wheel-ski
  • Combined take-off and landing device for hypersonic vehicle wheel-ski

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Embodiment Construction

[0024] The present invention will be further explained below in conjunction with the accompanying drawings and specific embodiments.

[0025] This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.

[0026] Such as figure 1 As shown, the wheel-skid combined take-off and landing device for a superb aircraft of the present invention includes a main buffer outer sleeve 1, a main buffer piston rod 2, an upper torsion arm 3, a lower torsion arm 4, a wheel, a hydraulic sensor 12, and a buffer action Module and skid assembly. The main buffer piston rod 2 is movably installed in the main buffer outer sleeve 1, the upper torsion arm 3 is hinged on the main buffer outer sleeve 1, and t...

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Abstract

The invention discloses a combined take-off and landing device for a hypersonic vehicle wheel-ski, which comprises a main buffer outer sleeve (1), a main buffer piston rod (2), wheels, a buffer actuating module and a ski assembly; the buffering actuating module is arranged on the main buffer piston rod (2) at the side surface of the wheels; the buffer actuating module comprises an air cavity (8),an oil cavity (9) and a floating piston (16) which are coaxially arranged; the air cavity (8) is vertically fixed below a buffer actuating module bracket (7), the oil cavity (9) is arranged outside the air cavity (8), and a spring (18) is arranged between the air cavity and the oil cavity; the floating piston (16) is arranged in the air cavity (8) ; a hydraulic sensor (12) for detecting the pressure in the oil cavity (9) in real time is arranged at the lower end of the oil cavity (9) and feeds back to an airplane main control system. The device has the advantages of small size and light weight, and can be applied to a hypersonic vehicle with strict limitation requirements on the size and performance of the take-off and landing device.

Description

technical field [0001] The invention relates to the technical field suitable for autonomous take-off and landing of hypersonic aircraft, in particular to a combined take-off and landing device for hypersonic aircraft. Background technique [0002] Hypersonic aircraft refers to an aircraft that can fly at a speed greater than 5 Ma. It has the characteristics of quick response, super penetration, and flexible maneuvering. It is a new concept weapon that combines strategic deterrence and actual combat application capabilities. This kind of aircraft is mainly used to perform tasks such as force projection, specific area detection and surveillance, ground strike and defense, information support, attack weapons and strategic projection platforms, etc., and has extremely high military value. [0003] This type of aircraft has difficult coordination contradictions with the take-off and landing system in some outstanding overall designs. On the one hand, the aerodynamic shape of a h...

Claims

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Application Information

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IPC IPC(8): B64C25/34B64C25/52B64C25/62
Inventor 魏小辉梁涛涛甘雨聂宏尹乔之
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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