CN105711822A - Establishing method of helicopter adopting tumbler mode in air - Google Patents
Establishing method of helicopter adopting tumbler mode in air Download PDFInfo
- Publication number
- CN105711822A CN105711822A CN201610190257.7A CN201610190257A CN105711822A CN 105711822 A CN105711822 A CN 105711822A CN 201610190257 A CN201610190257 A CN 201610190257A CN 105711822 A CN105711822 A CN 105711822A
- Authority
- CN
- China
- Prior art keywords
- power source
- tunnel type
- flexible film
- stretching resistance
- wind
- 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
- 230000003068 static effect Effects 0.000 claims abstract description 8
- 230000002153 concerted effect Effects 0.000 claims description 9
- 244000124765 Salsola kali Species 0.000 claims description 7
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
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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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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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
- B64D27/16—Aircraft characterised by the type or position of power plants of jet type
- B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Professional, Industrial, Or Sporting Protective Garments (AREA)
Abstract
The invention discloses an establishing method of a helicopter adopting a tumbler mode in the air. In order to solve the technical problems, the technical scheme is adopted as follows: a direct power source of the helicopter is mounted in a wind tunnel type helicopter body, and high-speed air flow generated in the wind tunnel type helicopter body serves as a second power source; in order to catch and utilize the second power source, an anti-tensile retracting film is mounted on the inner wall of the wind tunnel type helicopter body. According to the Bernoulli's theorem of dynamic pressure and static pressure of aerodynamics, static pressure exists between the anti-tensile retracting film and the inner wall of the wind tunnel type helicopter body, the high-speed air flow outside the anti-tensile retracting film generates dynamic pressure to the anti-tensile retracting film, and the dynamic pressure is remarkably smaller than the static pressure. The anti-tensile retracting film and the wind tunnel type helicopter body mounted together with the anti-tensile retracting film are pushed to the direction opposite to the high-speed air flow through the pressure difference produced inside and outside the anti-tensile retracting film, and the second power source propelling the helicopter to fly is formed. The direct power source and the second power source generate resultant force, so that the helicopter can vertically take off and land.
Description
Technical field
The present invention relates to the constructive method of a kind of type aircraft, i.e. a kind of aerial roly-poly type 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 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 type aircraft, i.e. a kind of aerial roly-poly type helicopter constructive method, the method use the counteracting force of propeller or jet as aircraft direct driving force source simultaneously, make its air-flow produced produce to make a concerted effort jointly to advance aircraft flight as the second power source again, 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 stretching resistance Flexible film at wind-tunnel type body inwall.According to aerodynamicDynamic pressure, static pressureBernoulli's theoremIt can be seen that be static pressure between stretching resistance Flexible film and wind-tunnel type body inwall, and stretching resistance Flexible film is produced dynamic pressure and is significantly less than static pressure by the high velocity air outside stretching resistance Flexible film.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 advancing 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.In order to effective regulable control stretching resistance Flexible film forms the second power source, we this aircraft high velocity air entrance, between wind-tunnel type body and stretching resistance Flexible film, adjustment air bag or the sectional shelf-unit of similar tube are installed, by regulating the relaxation of air bag or sectional shelf-unit, control relaxation regulable control second power source of stretching resistance Flexible film.Formed because the second power source is the union centre to centre heart line of making a concerted effort produced by 360 degree of wind-tunnel type bodies of periphery and stretching resistance Flexible film, 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, carrier can be made with joint efforts to move to the earth's core rightabout, carry when making a concerted effort aircraft enter aerial time, due to make a concerted effort centrostigma in the surface of center of gravity, which forms the skyborne tumbler pattern of aircraft, namely the safest most stable mode gone straight up to, does not namely separately add external force and can not change the pattern of posture.When aircraft horizontal flight, reducing flight resistance to improve air speed, aircraft needs extract the air regulated in air bag out or shrink sectional shelf-unit, makes stretching resistance Flexible film be close to wind-tunnel type body inwall.Aircraft relies on direct driving force and airfoil lift high-speed flight.
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, 3. scalable air bag, 4. turbofan engine, 5. heading control loop, 6. wing, 7. undercarriage in figure.
Detailed description of the invention:
In FIG, wind-tunnel type body (1) top is close in wind-tunnel type body and is installed stretching resistance Flexible film (2), scalable air bag (3) is installed between wind-tunnel type body (1) and stretching resistance Flexible film (2), turbofan engine (4) is installed in wind-tunnel type body (1) lower central position, turbofan engine (4) heading control loop mounted below (5), wind-tunnel type body (1) both sides external installs wing (6), the outside undercarriage mounted below (7) of wind-tunnel type body (1).When scalable air bag (3) gassy, after turbofan engine (4) starts, this aircraft is gone straight up to just as tumbler and is flown in the air；So the present invention is called a kind of aerial roly-poly type helicopter constructive method.Referring to Fig. 1.
Claims (3)
1. an aerial roly-poly type 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. the aerial roly-poly type helicopter constructive method of one according to claim 1, it is characterized in that: catch and utilize the second power source to flutter, we install stretching resistance elastica at wind-tunnel type body inwall, it is static pressure between stretching resistance Flexible film and wind-tunnel type body inwall, and stretching resistance Flexible film is produced dynamic pressure and is significantly less than static pressure by the high velocity air outside stretching resistance Flexible film.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 advancing 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.
3. the aerial roly-poly type helicopter constructive method of one according to claim 1, it is characterized in that: in order to effective regulable control stretching resistance Flexible film forms the second power source, this aircraft high velocity air entrance, between wind-tunnel type body and stretching resistance Flexible film, adjustment air bag or the sectional shelf-unit of similar tube are installed, by regulating the relaxation of air bag or sectional shelf-unit, control relaxation regulable control second power source of stretching resistance Flexible film.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610190257.7A CN105711822A (en) | 2016-03-30 | 2016-03-30 | Establishing method of helicopter adopting tumbler mode in air |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610190257.7A CN105711822A (en) | 2016-03-30 | 2016-03-30 | Establishing method of helicopter adopting tumbler mode in air |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105711822A true CN105711822A (en) | 2016-06-29 |
Family
ID=56158203
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610190257.7A Pending CN105711822A (en) | 2016-03-30 | 2016-03-30 | Establishing method of helicopter adopting tumbler mode in air |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105711822A (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 |
| RO127094B1 (en) * | 2010-08-18 | 2015-11-27 | Marius Brebenel | Lenticular aircraft with blades |
-
2016
- 2016-03-30 CN CN201610190257.7A patent/CN105711822A/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 |
| RO127094B1 (en) * | 2010-08-18 | 2015-11-27 | Marius Brebenel | Lenticular aircraft with blades |
Non-Patent Citations (1)
| Title |
|---|
| 陈浮等: "《空气动力学基础》", 31 January 2015, 哈尔滨工业大学出版社 * |
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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 | ||
| DD01 | Delivery of document by public notice |
Addressee: Yang Qingtai Document name: the First Notification of an Office Action |
|
| DD01 | Delivery of document by public notice | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160629 |
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| RJ01 | Rejection of invention patent application after publication |