CN105775143A - Method for forming centralization booster helicopters - Google Patents
Method for forming centralization booster helicopters Download PDFInfo
- Publication number
- CN105775143A CN105775143A CN201610220165.9A CN201610220165A CN105775143A CN 105775143 A CN105775143 A CN 105775143A CN 201610220165 A CN201610220165 A CN 201610220165A CN 105775143 A CN105775143 A CN 105775143A
- Authority
- CN
- China
- Prior art keywords
- tunnel type
- tensile
- wind
- helicopters
- power source
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000002153 concerted effect Effects 0.000 claims description 9
- 230000003068 static effect Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract 1
- 230000005484 gravity Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a method for forming centralization booster helicopters.The method includes that direct power sources of the helicopters are mounted in wind tunnel type bodies, so that high-speed airflow generated by the direct power sources in the wind tunnel type bodies can be used as a second power source; tensile-resistant stretching films which are controlled by an upper closed loop and a lower closed loop are mounted in a wind inlet of each wind tunnel type body in order to capture and utilize the second power source, and are in the shapes of De Laval nozzles when the corresponding helicopter runs; as known according to aerodynamic dynamic pressure and static pressure Bernoulli's theorems, static pressures are applied to the outsides of the tensile-resistant stretching films, and dynamic pressures which are applied to the tensile-resistant stretching films by high-speed airflow in the tensile-resistant stretching films are obviously lower than the static pressures; the tensile-resistant stretching films and the wind tunnel type bodies mounted with the tensile-resistant stretching films are pushed to the direction opposite to the high-speed airflow under the effect of internal and external pressure difference of the tensile-resistant stretching films, and accordingly second power sources for propelling the helicopters to fly can be formed; resultant force can be generated by the direct power sources and the second power sources, so that the helicopters can vertically rise and fall.
Description
Technical field
The present invention relates to a kind of course of new aircraft constructive method, i.e. a kind of righting power-assisted driven helicopter constructive method.
Background technology
Currently known aircraft is used mostly the counteracting force power as aircraft of propeller or jet, and efficiency low-function is poor, and particularly jet power is not easy the power as driven helicopter.
Summary of the invention
In order to overcome the deficiency of existing aircraft, the present invention provides the constructive method of a kind of course of new aircraft, i.e. a kind of righting power-assisted driven helicopter constructive method.The method use the counteracting force of propeller or jet as aircraft direct driving force source simultaneously, then make its air-flow produced produce, as the second power source, common propulsion aircraft flight of making a concerted effort, increase aircraft vertical simultaneously and play drop.
The technical solution adopted for the present invention to solve the technical problems is: the present invention is arranged on the direct driving force source of this aircraft in wind-tunnel type body so that it is the high velocity air produced in wind-tunnel type body is as the second power source.Catching and utilize the second power source to flutter, we install the stretching resistance Flexible film controlled by upper and lower two closed-loops at wind-tunnel type body air inlet, make stretching resistance Flexible film become De Laval noz(zle) shape when aircraft runs.According to aerodynamicDynamic pressure, static pressureBernoulli's theoremIt can be seen that be static pressure outside stretching resistance Flexible film, and the dynamic pressure that in stretching resistance Flexible film, stretching resistance Flexible film is produced by high velocity air is significantly less than static pressure.The inside and outside pressure reduction produced of stretching resistance Flexible film pushes the rightabout of high velocity air to stretching resistance Flexible film and the wind-tunnel type body that is installed together with it, forms the second power source of propulsion aircraft flight.Direct driving force source and the second power source produce to make a concerted effort, and make this aircraft have the ability VTOL.Formed because the second power source is the union centre to centre heart line of making a concerted effort produced by 360 degree of stretching resistance Flexible films of wind-tunnel type body periphery, so the centrage that wind-tunnel type body center line is exactly the second power source power also overlaps with the centrage of direct driving force source power, form identical the making a concerted effort in direction, the centrostigma made a concerted effort the second power source near aircraft top.The weight (center of gravity) of aircraft is the direct driving force source of bottom in this aircraft wind-tunnel type body.So, according to object of which movement law, when make a concerted effort more than centrifugal force and in opposite direction with centrifugal force time, can make with joint efforts carrier to the earth's core rightabout move namely to aerial sports.Carry when making a concerted effort aircraft enter aerial time, owing to the centrostigma made a concerted effort is in the surface of center of gravity, aircraft is not only helped to add the second power source, and the direction ascended to heaven vertically upward in righting direct driving force source, so the present invention is called a kind of righting power-assisted driven helicopter constructive method.
The invention has the beneficial effects as follows, it was found that the new method of flight gone straight up to by aircraft, open the frontier of aircraft flight transport.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the present invention is further described.
Fig. 1 is the vertical section structural map of the present embodiment.
1. wind-tunnel type body, 2. stretching resistance Flexible film in figure, 3. propeller and electromotor, 4. go up closed-loop, 5. descends closed-loop, 6. electromotor fixed system, 7. heading control loop, and 8. main post is held concurrently undercarriage.
Detailed description of the invention:
In FIG, wind-tunnel type body (1) top is close to wind-tunnel entrance and is installed stretching resistance Flexible film (2), stretching resistance Flexible film (2) is controlled and location by upper closed-loop (4) and (5) two closed-loops of lower closed-loop, electromotor fixed system (6) is fixed on propeller and electromotor (3) in wind-tunnel type body (1), heading control loop (7) is fixed under electromotor fixed system (6), main post holds concurrently undercarriage (8) by fixing wind-tunnel type body (1), upper closed-loop (4) and lower closed-loop (5) are fixed-type for aircraft and double undercarriage function, complete a kind of righting power-assisted driven helicopter constructive method patent.Referring to Fig. 1.
Claims (2)
1. a righting power-assisted driven helicopter constructive method, is characterized in that: the present invention is arranged on the direct driving force source of this aircraft in wind-tunnel type body so that it is produce high velocity air in wind-tunnel type body as the second power source.
2. a kind of righting power-assisted driven helicopter constructive method according to claim 1, it is characterized in that: catch and utilize the second power source to flutter, we install the stretching resistance Flexible film controlled by upper and lower two closed-loops at wind-tunnel type body air inlet, make stretching resistance Flexible film become De Laval noz(zle) shape when aircraft runs, the inside and outside pressure reduction produced of stretching resistance Flexible film pushes the rightabout of high velocity air to stretching resistance Flexible film and the wind-tunnel type body that is installed together with it, form the second power source of propulsion aircraft flight, direct driving force source and the second power source produce to make a concerted effort, this aircraft vertical is made to rise and fall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610220165.9A CN105775143A (en) | 2016-04-11 | 2016-04-11 | Method for forming centralization booster helicopters |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610220165.9A CN105775143A (en) | 2016-04-11 | 2016-04-11 | Method for forming centralization booster helicopters |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105775143A true CN105775143A (en) | 2016-07-20 |
Family
ID=56396187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610220165.9A Pending CN105775143A (en) | 2016-04-11 | 2016-04-11 | Method for forming centralization booster helicopters |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105775143A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2012511C1 (en) * | 1993-08-31 | 1994-05-15 | Фирма "ВИСТ" | Hybrid flying vehicle |
| CN2646046Y (en) * | 2003-02-08 | 2004-10-06 | 杨清太 | Novel helicopter |
| CN1944188A (en) * | 2005-10-03 | 2007-04-11 | 王新云 | Aircraft with centrifugal fan capable of vertically taking off and landing |
| RO127094A2 (en) * | 2010-08-18 | 2012-02-28 | Marius Brebenel | Lenticular aircraft with blades |
-
2016
- 2016-04-11 CN CN201610220165.9A patent/CN105775143A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2012511C1 (en) * | 1993-08-31 | 1994-05-15 | Фирма "ВИСТ" | Hybrid flying vehicle |
| CN2646046Y (en) * | 2003-02-08 | 2004-10-06 | 杨清太 | Novel helicopter |
| CN1944188A (en) * | 2005-10-03 | 2007-04-11 | 王新云 | Aircraft with centrifugal fan capable of vertically taking off and landing |
| RO127094A2 (en) * | 2010-08-18 | 2012-02-28 | Marius Brebenel | Lenticular aircraft with blades |
Non-Patent Citations (1)
| Title |
|---|
| 陈浮等: "《空气动力学基础》", 31 January 2015 * |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160720 |