CN203612203U - Device for effectively increasing helicopter load under same power - Google Patents
Device for effectively increasing helicopter load under same power Download PDFInfo
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- CN203612203U CN203612203U CN201320716922.3U CN201320716922U CN203612203U CN 203612203 U CN203612203 U CN 203612203U CN 201320716922 U CN201320716922 U CN 201320716922U CN 203612203 U CN203612203 U CN 203612203U
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- wings
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- 239000002002 slurry Substances 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 5
- 239000012530 fluid Substances 0.000 abstract description 4
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 abstract description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract 1
- 229910052799 carbon Inorganic materials 0.000 abstract 1
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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Abstract
The utility model provides a device for effectively increasing the helicopter load under the same power. The device is characterized in that a pair of roof wings is additionally mounted above helicopter rotor wings; because the roof wings are round plate-shaped, the bottom surfaces of the roof wings are straight, and the top surfaces of the roof wings are raised upwards, according to the Bernoulli's fluid mechanics principle, as long as air flows through, certain lift force is acted on the roof wings, and compared with the method that two pairs of wings exposed to the rotor wings downwash wind pressure are additionally mounted on a helicopter, the method of the invention has the advantage that the lift force effect is much better, so that the load of the helicopter, on which the device is mounted, can be effectively increased on the premise of not increasing the motor power, the burden of the rotor wings is reduced, the energy consumption of the helicopter is reduced, the carbon emission is reduced, and the environment is protected.
Description
Technical field
A device that effectively increases helicopter load under equal power, 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 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, manufacture and design a kind of device, make the helicopter of installing this device under the prerequisite that does not increase engine power, also can increase the load that even can increase significantly helicopter.
The method that the present invention takes installs one pair of roof limb additional above lifting airscrew.Because the Top 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 roof limb.The size of lift is decided by the size of roof limb and the speed of a ship or plane of aircraft, and the size of roof limb 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 the area size of roof limb as wide as possible therefore increase the deciding factor of airplane ascensional force.
accompanying drawing explanation:fig. 1 is structural representation of the present invention, and [1] is roof limb, and [2] are roof limb bottom surface, is called for short bottom surface, and [3] are roof limb end face, is called for short end face, and [4] are pitman, and [5] are rotor, and [6] are slurry hub, and [7] are rotor dynamical axis, and [8] are fuselage, and [9] are aileron.
specific embodiments:specific embodiment of the invention scheme is fairly simple, and, as long as produce one pair of roof limb according to layout design, the top that is installed at helicopter is just passable.
The Top wing [1] is that a bottom surface [2] is straight, end face [3] projection or bottom surface [2] upwards recessed and recessed cambered surface be less than the disc body of the cambered surface that end face [3] raises up, be arranged on the top center position of rotor [5] by pitman [4] and slurry hub [6]; Because the end face projection bottom surface of the Top wing [1] 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 Top wing [1], distance from bottom is short, flow velocity is slow, and pressure is large, and distance from top is long, flow velocity is fast, pressure is little, lifts power therefore air-flow can produce a lift upwards to bottom surface [2], 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 Top wing [1] is under the state of aircraft normal flight, and the lift bringing to aircraft is much higher than the gravity of the Top wing [1] self.In other words, add and load onto after this Top wing [1] to helicopter, not only can not increase the weight of the burden of aircraft, also instead can increase the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft.A central part again because this Top wing [1] is to meet hydromechanical smooth dish fluid, and in rotor, therefore the resistance of the wind of the hand of rotation causing to rotor while following rotor wing rotation is very little, almost negligible.
In sum, helicopter is being installed after the Top wing of the present invention [1], not only can increase the lift of aircraft, reduce the burden of rotor, reduce the energy consumption of aircraft, and can also reduce the quantity discharged of carbon dioxide, clean atmosphere, reduces environmental protection cost, is good job feelings of benefiting the nation and the people really.
Claims (2)
1. under an equal power, effectively increase the device of helicopter load, formed by roof limb [1], bottom surface [2], end face [3], pitman [4] and rotor [5], slurry hub [6], rotor dynamical axis [7], fuselage [8], aileron [9] etc., it is characterized in that: described roof limb [1] is arranged on the top center position of rotor [5] by pitman [4].
2. the device that effectively increases helicopter load under a kind of equal power claimed in claim 1, is characterized in that: described roof limb [1] is that a bottom surface [2] is straight, the disc body of end face [3] projection, and its bottom surface [2] can be also upwards recessed cambered surfaces.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320716922.3U CN203612203U (en) | 2013-11-13 | 2013-11-13 | Device for effectively increasing helicopter load under same power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320716922.3U CN203612203U (en) | 2013-11-13 | 2013-11-13 | Device for effectively increasing helicopter load under same power |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203612203U true CN203612203U (en) | 2014-05-28 |
Family
ID=50764863
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320716922.3U Expired - Fee Related CN203612203U (en) | 2013-11-13 | 2013-11-13 | Device for effectively increasing helicopter load under same power |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203612203U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627364A (en) * | 2013-11-13 | 2015-05-20 | 银川上河图新技术研发有限公司 | Device for effectively increasing load of helicopter under same power |
-
2013
- 2013-11-13 CN CN201320716922.3U patent/CN203612203U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627364A (en) * | 2013-11-13 | 2015-05-20 | 银川上河图新技术研发有限公司 | Device for effectively increasing load of helicopter under same power |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140528 Termination date: 20151113 |
|
| EXPY | Termination of patent right or utility model |