CN203612205U - Device effectively increasing load of helicopter - Google Patents

Abstract

The utility model discloses a device effectively increasing load of a helicopter. A pair of bottom wings is added in the middle of a landing gear of a helicopter. The bottom wing is a round plate-shaped body with a straight bottom surface and an upward raised top surface; according to the Bernoulli hydromechanics principle, certain lift force is applied to the bottom wings as long as air flows; the method is better in lift force effect than the method of additionally mounting two pairs of wings which are exposed to the rotor wing downwash wind pressure, so that the helicopter mounted with the device can increase load greatly under the precondition that engine power is not increased; burden of the rotor wings is decreased; energy consumption of the helicopter is reduced; carbon emission is lowered; the device is environment-friendly.

Description

Can effectively increase a kind of device of helicopter load

Technical field

A kind of device that can effectively increase helicopter load, belongs to air material class.

Background technology

The method that increases helicopter load at present only has two, and one is the power that increases driving engine, makes the revolution of rotor increase or make the diameter of rotor increase or the quantity of paddle is increased, and the 2nd, on fuselage both sides, aileron being installed is wing, increases the lift of aircraft.But these two kinds of methods all exist again fatal weakness, one is to increase the power of driving engine will certainly increase the weight and volume of aircraft, the 2nd, the aileron of installing is in to be washed under aircraft rotary wing under the compressing that wind is downward wind-force, thereby the lift increasing is very limited, although just limited from having increased the lift increasing aileron, consider but but can hang more easily the aspects such as bomb, increase aileron is still very calculated.Does is the lift that can effectively increase aircraft under the prerequisite that does not increase aero-engine power load? this is the thing that helicopter manufacturing firm of China and foreign countries is dreamed of always, but the little method that increases at present helicopter load of effect only has two so far, one is the power that increases driving engine, make the revolution of rotor increase or make the diameter of rotor increase or the quantity of paddle is increased, the 2nd, on fuselage both sides, aileron being installed is wing, increases the lift of aircraft.But these two kinds of methods all exist again fatal weakness, one is to increase the power of driving engine will certainly increase the weight and volume of aircraft, the 2nd, the aileron of installing is in to be washed under aircraft rotary wing under the compressing that wind is downward wind-force, thereby the lift increasing is very limited, although just limited from having increased the lift increasing aileron, consider but but can hang more easily the aspects such as bomb, increase aileron is still very calculated.Does is the lift that can effectively increase aircraft under the prerequisite that does not increase aero-engine power load? this is the thing that helicopter manufacturing firm of China and foreign countries is dreamed of always, but effect is little so far.

Summary of the invention

The present invention does not increase power for above-mentioned helicopter to be just difficult to increase the difficult problem that lift is load, manufactures and designs a kind of device, and the helicopter that makes to install this device also can effectively increase the load of helicopter under the prerequisite that does not increase engine power.

The method that the present invention takes is the wing at the bottom of helicopter landing gear centre installs a pair additional.Because the end wing is a large disc body of the little end face radian of bottom surface radian, therefore according to Bernoulli Jacob's fluid mechanics principle, no matter aircraft moves ahead, side flies or turn, as long as head-on there is distinguished and admirable mistake, just all can give the certain lift of the end wing.The size of lift is decided by the size of the end wing and the speed of a ship or plane of aircraft, and the size of roof limb and the end wing is larger, and more great ， Fan speed is faster for lift, and lift is larger.But because the speed of a ship or plane of getting off the plane in the prerequisite that does not change aero-engine power is certain, be exactly to have increased as wide as possible the area size of the end wing therefore increase the deciding factor of airplane ascensional force.

accompanying drawing explanation:fig. 1 is structural representation of the present invention, and [1] is alighting gear, and [2] are the end wing, and [3] are wing bottom surface, the end, also claim lower surface, [4] be end wing end face, also deserve to be called end face, [5] are pitman, and [6] are rotor, [7] be slurry hub, [8] are rotor dynamical axis, and [9] are fuselage, and [10] are aileron.

specific embodiments:as long as specific embodiment of the invention scheme is fairly simple, the wing at the bottom of producing a pair according to layout design, is installed among the bottom alighting gear of helicopter just passable.

The end wing [2] is that lower surface [3] is straight, upper surface [4] projection, or lower surface [3] upwards recessed but recessed cambered surface be less than the disc body of the cambered surface that upper surface [4] raises up, be arranged among alighting gear [1] by pitman [5]; Because the end face projection bottom surface of the end wing [2] is straight, therefore according to the principle about " the large pressure of flow velocity is little, and the little pressure of flow velocity is large " in Bernoulli Jacob's fluid mechanics, in the time that air flows to the edge of another side from the edge on any one side of the end wing [2], distance from bottom is short, flow velocity is slow, and pressure is large, and distance from top is far away, flow velocity is fast, pressure is little, lifts power therefore air-flow can produce a lift upwards to bottom surface [3], and this power of lifting can be passed through formula

be lift=airfoil lift coefficient × 1/2 × density of air × speed square × wing area tries to achieve.

According to calculating, this end wing [2] is under the state of aircraft normal flight, and the lift bringing to aircraft is much higher than the gravity of himself.In other words, add and load onto after this end wing [2] to helicopter, not only can not increase the weight of the burden of aircraft, also can increase on the contrary the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft.

Be in again the bottom of fuselage due to this end wing [2], the loss of lift causing to aircraft therefore can effectively hide the pressure of the downward wind of aircraft rotary wing (be commonly called as down and wash wind-force), than in addition installing two width additional to helicopter, to be exposed to the lift effect of the wing aileron [10] under rotor downwash wind pressure far better.

The shape of the end wing [2] is except circle is acetabular, also can be oval, leg-of-mutton, foursquare, rectangular, trapezoidal or rhombus, generally in the majority with circle, ellipse and oblong, its width is less than alighting gear, its length and fuselage are suitable, cancave cambered surface is downward, upwards, so equal has increased a wing to aircraft to convex globoidal, can greatly increase the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft, reduce the quantity discharged of carbon dioxide, clean atmosphere, reducing environmental protection cost, is a good thing of benefiting the nation and the people really.

Claims (2)

1. can effectively increase a kind of device of helicopter load, formed by alighting gear [1], the end wing [2], wing bottom surface, the end [3], end wing end face [4], pitman [5] and rotor [6], slurry hub [7], rotor dynamical axis [8], fuselage [9], aileron [10] etc., it is characterized in that: the described end wing [2] is arranged among the alighting gear of aircraft below by pitman [5].

2. a kind of device that can effectively increase helicopter load claimed in claim 1, it is characterized in that: the described end wing [2] be a lower surface flat top end face projection or lower surface upwards recessed but recessed cambered surface be less than the disc body of the cambered surface that upper surface raises up, its profile, except circle, can be also oval, leg-of-mutton, foursquare, rectangular, trapezoidal or rhombus.

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