Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force

A technology for vertical take-off and landing and aircraft, applied in the field of modern aerospace, can solve the problems of high energy consumption and large resistance, and achieve the effects of improving flight speed, reducing fuel consumption, and reducing manufacturing and use costs.

Inactive Publication Date: 2016-01-27
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] In order to overcome the deficiencies of large resistance and high energy consumption in the prior art,

Method used

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  • Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force
  • Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force
  • Integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force

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Embodiment Construction

[0042] Such as figure 1 , figure 2 , image 3 Shown are the appearance diagram of the vertical take-off and landing state, the appearance diagram of the cruising flight state and the three views of the cruising flight state of the lift-floating integrated aircraft. Figure 4 It is the front view of the lift-floating integrated aircraft.

[0043] The present embodiment is a vertical take-off and landing aircraft with integrated lifting and floating, comprising a left fuselage 1, a right fuselage 2, a central fuselage 3, a front wing 4, a rear wing 5, a tail brace 6, a vertical tail 7, and a horizontal tail 8, rotor 9, engine 10, front landing gear 11, main landing gear 12, elevator 13 and rudder 14.

[0044] Such as Figure 1~4 As shown, the present embodiment takes the double-deck inflatable row wing as the main body, and the layout of three fuselages. The layout of the three fuselages is: the central fuselage 3 is located in the middle of the front edge of the rear wing...

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Abstract

The invention discloses an integrated general-purpose vertical take-off and landing aircraft based on lifting and floating force. A center fuselage is positioned in the middle of the front edge of a rear tandem wing; a left fuselage and a right fuselage are respectively positioned at wingtips at two ends of the tandem wing, and stretch out forwards; two engines are respectively mounted on the inner side of the left fuselage and the inner side of the right fuselage; tail booms which extend backwards are respectively arranged at the rear end of the left fuselage and the rear end of the right fuselage, and each tail boom and the longitudinal axis of a fuselage form an included angle of 15 degrees. According to the aircraft, a twin-vertical tail layout is adopted; an elevating rudder and steering rudders are respectively arranged on a horizontal tail and vertical tails; each undercarriage is in a front three-point manner; main undercarriages are respectively positioned at the lower part of the left fuselage and the lower part of the right fuselage; the front undercarriage is positioned at the front part of the center fuselage. The aircraft disclosed by the invention has the characteristics of extensive range of application, wide flying regions and high working efficiency; the aircraft is suitable for the fields of transportation, land surveying, resource exploration, environmental monitoring, scientific experiments, aviation trainings, safety patrolling, personnel rescue, express delivery, prevention and treatment for agriculture and forestry, culture and sports, administrative affairs, and tour and sightseeing.

Description

technical field [0001] The invention relates to the field of modern aerospace, in particular to a lifting-floating integrated vertical take-off and landing universal aircraft. Background technique [0002] In order to maintain the basic flight of the aircraft in the air, people generally balance the gravity through the buoyancy and lift of the atmosphere. For aircraft such as airships and hot air balloons that mainly rely on buoyancy to balance gravity, they have the characteristics of simple take-off and landing, hovering in the air, long-term stay in the air, all-weather and multi-purpose, etc. Gas that is lighter than air forms buoyancy. Due to the low density of air, the size of an aircraft relying solely on buoyancy is huge, and the huge size will exceed the limit of material tension. Therefore, not only is it difficult to manufacture large-scale buoyant aircraft, but also the surface flexible material itself There are great constraints on its size. Due to the limited...

Claims

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Application Information

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IPC IPC(8): B64C27/22B64C27/26B64C29/02
Inventor 叶正寅杨磊华如豪叶坤
Owner NORTHWESTERN POLYTECHNICAL UNIV
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