Parafoil aircraft applicable to cylindrical space loading

A technology of cylindrical space and aircraft, applied in parafoil aircraft, in the field of parafoil aircraft, can solve the problems of increasing aircraft weight, endurance time, cost increase, etc., and achieve high reliability, high utilization rate, and high degree of modularization Effect

Active Publication Date: 2013-05-15
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

If you want to increase the weight or endurance time of the aircraft, you can only increase the caliber of the

Method used

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  • Parafoil aircraft applicable to cylindrical space loading
  • Parafoil aircraft applicable to cylindrical space loading
  • Parafoil aircraft applicable to cylindrical space loading

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Embodiment Construction

[0028] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0029] Parafoil aircraft of the present invention comprises umbrella body 1 and pod 2, as figure 1 Shown; Wherein, the umbrella body 1 includes a parafoil 101 and a parachute 102 composed of a main parachute 102a and a manipulation cord 102b. The parafoil 101 is an ordinary ram-type parafoil 101, which is connected to the pod 2 through the main parachute rope 102a and the control rope 102b. The main parachute ropes 102a are fixed on the lower surface of the parafoil 101, two by two form a group, and the free ends cross and converge into one strand, forming a Y-shaped bifurcated configuration. The control ropes 102b are fixed on the rear edge of the parafoil 101, and are also formed into a group of two, and the free ends are intersected and converged into one strand, forming a Y-shaped bifurcated configuration. The pod 2 is composed of a control cabi...

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Abstract

The invention discloses a parafoil aircraft applicable to cylindrical space loading. The parafoil aircraft applicable to the cylindrical space loading comprises a parafoil body and a nacelle; the nacelle is entirely cylindrical, and comprises a control cabinet, a power cabinet and a load cabinet which are fixedly arranged in a laminated manner; two rope winding plates are arranged inside the control cabinet; an operation rope in the parafoil body is coiled on each rope winding plate; a main parachute cord is fixed with the both ends of a supporting rod which can be unfolded in the left-right direction and be mounted on the control cabinet; the parafoil body is unfolded by unfolding the supporting rod; and a steering engine controls the rope winding plates to rotate, so that the steering posture of the parafoil aircraft can be controlled. A motor for driving propellers arranged outside the power cabinet to rotate is mounted in the power cabinet, so that the parafoil aircraft climbs out and falls down. The load cabinet can be configured with various types of mission loads aiming at the parafoil aircraft. The parafoil aircraft applicable to the cylindrical space loading, provided by the invention, has the advantages that the high use ratio of the cylindrical space loading the aircraft can be realized; the large-area flexible punching parafoil is used as a lifting surface, so that the lower flight speed can be obtained, and the parafoil aircraft applicable to the cylindrical space loading is applicable to a long-term fixed-point reconnaissance mission; and meanwhile, the parafoil aircraft applicable to the cylindrical space loading has good vertical and transverse stability.

Description

technical field [0001] The invention relates to a parafoil aircraft, which belongs to the field of aircraft design, and specifically relates to a parafoil aircraft suitable for loading in a cylindrical space. Background technique [0002] The artillery-launched aircraft developed by combining unmanned aerial vehicles with artillery shells, rockets and other weapons has the ability to quickly break through the enemy's air defense blockade and reach the designated airspace in a short time. It is especially suitable for high-risk tasks such as frontline tactical reconnaissance and damage assessment. [0003] Since the size of the gun-launched aircraft is restricted by the cylindrical interior space of the gun, the current mainstream gun-launched aircraft adopts the method of deforming and folding rigid wings to meet the different requirements for the shape of the aircraft during the launching and cruising stages. However, the extra deformation and folding mechanisms add extra w...

Claims

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Application Information

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IPC IPC(8): B64C31/036B64D35/02
Inventor 杨华黄俊宋磊刘成解静峰颜旭峰
Owner BEIHANG UNIV
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