CN112278239A - A non-stall floating lift airfoil of an aircraft and its realization method - Google Patents
A non-stall floating lift airfoil of an aircraft and its realization method Download PDFInfo
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- CN112278239A CN112278239A CN202011241453.5A CN202011241453A CN112278239A CN 112278239 A CN112278239 A CN 112278239A CN 202011241453 A CN202011241453 A CN 202011241453A CN 112278239 A CN112278239 A CN 112278239A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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Abstract
The invention discloses a non-stall floating lift wing surface of an aircraft and an implementation method thereof. The non-stall floating lift wing surface comprises a floating lift wing surface, a connecting rotating shaft and an attack angle adjusting control surface, wherein the floating lift wing surface is a lift wing surface with an independent floating attack angle and is used for generating the aerodynamic lift required by an aircraft, and the aerodynamic attack angle and the pitching attitude angle of a fuselage are mutually independent; the connecting rotating shaft is used for connecting the floating lift wing surface and the machine body, the pitching angles of the floating lift wing surface and the machine body are mutually independent, and the floating lift wing surface can freely rotate around the connecting rotating shaft relative to the machine body in a pitching mode; the attack angle adjusting control surface is used for adjusting the flight attack angle of the floating lift wing surface, so that the floating lift wing surface is stabilized at a set attack angle, and the wing surface is ensured not to stall in the flight process. When the aircraft flies, the attack angle of the floating wing is only related to the flying speed direction, the lift force of the aircraft is adjusted by adjusting the attack angle adjusting control surface, and the attack angle of the floating wing is adaptively balanced on the attack angle set by the attack angle adjusting control surface.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a non-stall floating lift wing surface of an aircraft and an implementation method thereof.
Background
The wings of the fixed-wing aircraft are fixedly connected with the aircraft body, and the aircraft can be crashed due to the risk of stalling with an overlarge attack angle in the flight process. On a vertical take-off and landing fixed wing aircraft with a power system thrust direction parallel to an aircraft body, when a vertical mode is converted into a horizontal mode, a stalling process exists on wings, so that mode conversion cannot be stably completed; on a manned fixed-wing aircraft, the member cabin is fixedly connected with the wings, and a large pitch angle exists in the cabin in the taking-off and landing stages, so that riding comfort is influenced.
Disclosure of Invention
The invention aims to provide a non-stall floating lift wing surface of an aircraft and an implementation method thereof, which can eliminate the risk of stall of the lift of the aircraft, ensure that the lift of the aircraft is not stalled no matter what flight attitude, and provide stable lift for the aircraft.
The technical solution for realizing the purpose of the invention is as follows: the utility model provides an aircraft does not stall unsteady lift airfoil, includes unsteady lift airfoil, connection pivot, angle of attack regulation control plane, wherein:
the floating lift wing surface is a lift wing surface with an independent floating attack angle and is used for generating the aerodynamic lift required by the aircraft, and the aerodynamic attack angle and the pitching attitude angle of the aircraft body are independent;
the connecting rotating shaft is used for connecting the floating lift wing surface and the machine body, the pitching angles of the floating lift wing surface and the machine body are mutually independent, and the floating lift wing surface can freely rotate around the connecting rotating shaft relative to the machine body in a pitching mode;
the attack angle adjusting control surface is used for adjusting the flight attack angle of the floating lift wing surface, so that the floating lift wing surface is stabilized at a set attack angle, and the wing surface is ensured not to stall in the flight process.
Furthermore, the connecting rotating shaft is fixedly connected with the floating lift wing surface, and the whole shaft of the connecting rotating shaft penetrates through the machine body and is suspended on the machine body.
Furthermore, the connecting rotating shaft is fixedly connected with the floating lift wing surface, and the connecting rotating shaft half shaft is connected with the machine body.
Further, the connecting rotating shaft can rotate relative to the machine body in a pitching degree of freedom, and therefore the wing surface lifting force is transmitted.
Further, the attack angle adjusting control surface is an adjusting control surface installed on the floating wing.
Further, the angle of attack adjusting control surface is an adjusting control surface extending out of the wing.
An implementation method of a non-stall floating lift wing surface of an aircraft comprises the following specific steps:
the connecting rotating shaft is fixedly connected with the floating lift wing surface, the floating lift wing surface is connected to the airframe through the connecting rotating shaft, the pitch angles of the floating lift wing surface and the airframe are mutually independent, and the floating lift wing surface freely rotates around the connecting rotating shaft relative to the airframe in a pitching mode;
when the aircraft flies, the attack angle of the floating wing is only related to the flying speed direction and is not related to the attitude of the aircraft body, the adjustment of the lift force required by the aircraft is realized by adjusting the attack angle adjusting control surface, and the attack angle of the floating wing is self-adaptively balanced on the attack angle set by the attack angle adjusting control surface.
Further, when the floating lift wing surface is applied to a vertical take-off and landing aircraft, the take-off process is as follows:
firstly, in a vertical takeoff initial state, the aircraft flies vertically upwards to a set height;
secondly, in a vertical-to-horizontal acceleration state, the vertical upward speed of the aircraft is gradually reduced, the horizontal flying speed is gradually increased, the attack angle of the floating lift wing surface is adaptive to the flying combined speed vector direction, and the size of the attack angle is controlled by an attack angle adjusting control surface, so that the lift efficiency of the lift wing surface is kept during the vertical rotation and horizontal flying process of the aircraft;
and finally, in a flat flight state, the conversion from vertical to flat flight is completed, the size of the attack angle of the floating lift wing surface in the flat flight state is still controlled by the attack angle adjusting control surface, or the floating lift wing surface and the body are locked in rotation freedom degree, and the floating lift wing surface is converted into a conventional fixed wing aircraft.
Compared with the prior art, the invention has the following remarkable advantages: (1) the floating lift wing surface is connected with the fuselage through the rotating shaft, so that mutual independence of the floating lift wing surface and the fuselage attack angle is realized, the wing surface attack angle is controlled by adjusting the control surface, the problem of stalling of wings of an aircraft (the floating lift wing surface) is avoided, and the safety of the aircraft is improved; (2) for a vertical take-off and landing aircraft (VTOL), in the mode conversion of vertical flight and horizontal flight, the problem of stalling of a floating lift wing surface is avoided, so that stable mode conversion is realized; (3) when the passenger car is applied to a manned aircraft, the whole-course level or other required postures of the passenger compartment can be realized, the riding comfort is improved, and the passenger car has higher practical value.
Drawings
FIG. 1 is a schematic view of a floating wing of the present invention aircraft non-stall buoyant lift airfoil.
FIG. 2 is a schematic illustration of the installation of a floating wing of the present invention aircraft non-stalled buoyant lift airfoil to the fuselage.
Fig. 3 is a sequence diagram of states of a vertical takeoff floating wing, wherein (a) is a vertical takeoff initial state diagram, (b) is a state diagram of vertical rotation and horizontal acceleration 1, (c) is a state diagram of vertical rotation and horizontal acceleration 2, and (d) is a state diagram of complete flat flight.
Detailed Description
The invention relates to a method for realizing a non-stall aircraft wing surface, which is characterized in that a floating lift wing surface and an engine body pitching freedom degree are removed from constraint to achieve the mutual independence of a wing surface attack angle and an engine body pitching angle, the floating lift wing surface is used for adjusting a pneumatic attack angle of the floating lift wing surface through an independent floating lift wing surface adjusting mechanism, and the floating lift wing surface is kept in a non-stall attack angle range all the time.
The floating lift wing surface of the general aircraft is fixedly connected with the aircraft body, and the wing surface attack angle and the aircraft body pitch angle are independent from each other by removing the restriction of the pitching freedom degree of the floating lift wing surface and the aircraft body. The main floating lift wing surface and the body can be connected through a rotating shaft, so that the floating lift wing surface only transmits lift force and does not transmit pitching moment, and the pitching freedom degrees of the body and the wings are mutually independent.
On the premise that the floating lift wing surface floats, the trim attack angle of the floating lift wing surface is adjusted through the mechanism, so that the fixed attack angle flying of the floating lift wing surface is realized, and the stalling problem is avoided. The trim attack angle of the floating lift airfoil is adjusted mainly by changing the aerodynamic shape, and can be realized by an additional control surface at the trailing edge of the airfoil and also can be realized by connecting a lifting control surface outside the airfoil.
The invention relates to a non-stall floating lift wing surface of an aircraft, which comprises a floating lift wing surface 1, a connecting rotating shaft 2 and an attack angle adjusting control surface 3, wherein:
the floating lift wing surface 1 is a lift wing surface with an independent floating attack angle and is used for generating the aerodynamic lift required by the aircraft, and the aerodynamic attack angle is independent of the pitching attitude angle of the aircraft body 4;
the connecting rotating shaft 2 is used for connecting the floating lift wing surface 1 and the machine body 4, the pitching angles of the floating lift wing surface 1 and the machine body 4 are mutually independent, and the floating lift wing surface 1 can freely rotate around the connecting rotating shaft 2 relative to the machine body 4 in a pitching mode;
the attack angle adjusting control surface 3 is used for adjusting the flight attack angle of the floating lift wing surface 1, so that the floating lift wing surface is stabilized at a set attack angle, and the wing surface is ensured not to stall in the flight process.
Furthermore, the connecting rotating shaft 2 is fixedly connected with the floating lift wing surface 1, and the whole shaft of the connecting rotating shaft 2 passes through the machine body 4 and is suspended on the machine body 4.
Furthermore, the connecting rotating shaft 2 is fixedly connected with the floating lift wing surface 1, and the half shaft of the connecting rotating shaft 2 is connected with the machine body 4.
Further, the connecting rotating shaft 2 can rotate relative to the body 4 in a pitching degree of freedom, and therefore the wing surface lifting force is transmitted.
Further, the attack angle adjusting control surface 3 is an adjusting control surface installed on the floating wing.
Further, the attack angle adjusting control surface 3 is an adjusting control surface extending out of the wing.
An implementation method of a non-stall floating lift wing surface of an aircraft comprises the following specific steps:
the connecting rotating shaft 2 is fixedly connected with the floating lift wing surface 1, the floating lift wing surface 1 is connected to the machine body 4 through the connecting rotating shaft 2, the pitching angles of the floating lift wing surface 1 and the machine body 4 are mutually independent, and the floating lift wing surface 1 freely rotates around the connecting rotating shaft 2 in a pitching mode relative to the machine body 4;
when the aircraft flies, the attack angle of the floating wing 2 is only related to the flying speed direction and is not related to the posture of the fuselage 4, the adjustment of the lift force required by the aircraft is realized by adjusting the attack angle adjusting control surface 3, and the attack angle of the floating wing 2 is self-adaptively balanced on the attack angle set by the attack angle adjusting control surface 3.
Further, when the floating lift wing surface is applied to a vertical take-off and landing aircraft, the take-off process is as follows:
firstly, in a vertical takeoff initial state, the aircraft flies vertically upwards to a set height;
secondly, in a vertical rotation horizontal acceleration state, the vertical upward speed of the aircraft is gradually reduced, the horizontal flying speed is gradually increased, the attack angle of the floating lift wing surface 1 is adaptive to the flying combined speed vector direction, and the attack angle is controlled by the attack angle adjusting control surface 3, so that the lift efficiency of the lift wing surface is kept during the vertical rotation horizontal flying process of the aircraft;
and finally, in a flat flight state, the conversion from vertical to flat flight is completed, the size of the attack angle of the floating lift wing surface 1 in the flat flight state is still controlled by the attack angle adjusting control surface 3, or the floating lift wing surface 1 and the aircraft body 4 are locked in rotation freedom degree and converted into a conventional fixed wing aircraft.
The invention is described in further detail below with reference to the figures and the embodiments.
Examples
The invention is mainly composed of a floating lift wing surface 1, a connecting rotating shaft 2 and an attack angle adjusting control surface 3, wherein the floating lift wing surface 1 is used for generating aerodynamic lift required by an aircraft, the connecting rotating shaft 2 is used for being connected with a fuselage 4 and can still freely rotate around the rotating shaft after being connected, and the attack angle adjusting control surface 3 is used for adjusting the flight attack angle of the floating lift wing surface.
The floating lift wing surface 1 is a lift wing surface with an independent floating attack angle and is used for generating the aerodynamic lift required by the aircraft, and the aerodynamic attack angle and the pitching attitude angle of the aircraft body are independent; the connecting rotating shaft 2 is used for connecting the floating lift wing surface 1 and the airframe and transferring the wing surface lift force, the pitching angles of the floating lift wing surface 1 and the airframe are mutually independent, and the floating lift wing surface 1 can freely rotate around the connecting rotating shaft 2 relative to the airframe in a pitching mode; the attack angle adjusting control surface 3 is used for adjusting the flight attack angle of the floating lift wing surface 1, the floating lift wing surface 1 is stabilized at a set attack angle, the wing surface is guaranteed not to stall in the flight process, and the attack angle adjusting control surface 3 is of a conventional control surface structure and is not described any more.
The connecting rotating shaft 2 is fixedly connected with the floating lift wing surface 1, the connecting rotating shaft 2 can penetrate through the airframe 4 in a full shaft mode and be suspended on the upper surface and the lower surface of the airframe in a hanging mode, and can also be connected with the airframe in a half shaft mode, the core of the connecting rotating shaft 2 is that the connecting rotating shaft can freely or/and limitedly rotate relative to the airframe 4 in a pitching degree of freedom, and reliable transmission of the wing surface lift force is achieved.
The attack angle adjusting control surface 3 is an adjusting control surface arranged on the floating lift wing surface 1, and the attack angle adjusting control surface 3 can also be an adjusting control surface extending out of the wing.
Fig. 2 is a schematic diagram of a floating lift wing surface installed on an aircraft, 4 is a fuselage, 5 is a power device, the floating wing surface is connected to the fuselage 4 through a rotating shaft 2, when the aircraft flies, the attack angle of the floating lift wing surface 1 is only related to the flight speed direction and is not related to the posture of the fuselage 4, the lift force required by the aircraft to adjust is achieved through adjusting an attack angle adjusting control surface 3, and the attack angle of the floating lift wing surface 1 is in self-adaptive balance on the attack angle set by the attack angle adjusting control surface 3, so that the risk of wing surface stall is avoided.
FIG. 3 is an application of the floating lift airfoil to a VTOL aerial vehicle, and FIG. 3(a) is a vertical takeoff initial state diagram, wherein the aerial vehicle flies vertically upwards to a certain height, FIG. 3(b) and (c) are diagrams of the acceleration state from vertical to horizontal, at this time, the vertical upward speed of the aircraft is gradually reduced, the horizontal flight speed is gradually increased, the attack angle of the floating lift wing surface (1) is adaptive to the flight combined speed vector direction, the attack angle is controlled by the attack angle adjusting control surface (3), therefore, the aircraft is ensured to keep the lift wing surface at high lift efficiency in the vertical rotation and horizontal flight process, the transition from vertical flight to horizontal flight is completed in the flight state of fig. 3(d), the transition from vertical flight to horizontal flight is completed, the size of the attack angle of the floating lift wing surface 1 in the horizontal flight state is still controlled by the attack angle adjusting control surface 3, and the floating lift wing surface 1 and the aircraft body 4 can be locked in rotation freedom degree and converted into a conventional fixed wing aircraft.
Because the core of the invention is the floating wing with the attack angle independent of the pitch angle of the fuselage, the fuselage attitude stabilizing and adjusting mechanism of the aircraft fuselage, such as the stabilizing wing surface and the control surface of the lifting, pitching and rolling, or the method for realizing the fuselage attitude adjustment by vector thrust, is not described.
Claims (8)
1. The utility model provides an aircraft does not stall unsteady lift airfoil which characterized in that, includes unsteady lift airfoil (1), connection pivot (2), angle of attack regulation control surface (3), wherein:
the floating lift wing surface (1) is a lift wing surface with an independent floating attack angle and is used for generating the aerodynamic lift required by the aircraft, and the aerodynamic attack angle is independent of the pitching attitude angle of the aircraft body (4);
the connecting rotating shaft (2) is used for connecting the floating lift wing surface (1) and the machine body (4), the pitching angles of the floating lift wing surface (1) and the machine body (4) are mutually independent, and the floating lift wing surface (1) can freely rotate around the connecting rotating shaft (2) in a pitching mode relative to the machine body (4);
the attack angle adjusting control surface (3) is used for adjusting the flight attack angle of the floating lift wing surface (1), so that the floating lift wing surface is stabilized at a set attack angle, and the wing surface is ensured not to stall in the flight process.
2. The aircraft stall-free buoyant lift airfoil of claim 1, wherein the connecting shaft (2) is fixedly connected to the buoyant lift airfoil (1), and the connecting shaft (2) is suspended from the fuselage (4) in full axis through the fuselage (4).
3. The aircraft non-stall buoyant lift airfoil of claim 1, wherein the connecting shaft (2) is fixedly connected to the buoyant lift airfoil (1), and the connecting shaft (2) is connected to the fuselage (4) by a shaft half.
4. The aircraft non-stall buoyant lift airfoil of claim 2 or 3, wherein the connecting shaft (2) is rotatable in a pitch degree of freedom with respect to the fuselage (4) enabling the transfer of airfoil lift.
5. The aircraft non-stall buoyant lift airfoil of claim 4, wherein the angle of attack rudder surface (3) is a rudder surface mounted on a buoyant wing.
6. The aircraft non-stall buoyant lift airfoil of claim 4, wherein the angle of attack rudder surface (3) is a rudder surface extending out of the wing.
7. An implementation method of a non-stall floating lift airfoil of an aircraft is characterized by comprising the following steps:
the connecting rotating shaft (2) is fixedly connected with the floating lift wing surface (1), the floating lift wing surface (1) is connected to the machine body (4) through the connecting rotating shaft (2), the pitching angles of the floating lift wing surface (1) and the machine body (4) are mutually independent, and the floating lift wing surface (1) freely rotates around the connecting rotating shaft (2) in a pitching mode relative to the machine body (4);
when the aircraft flies, the attack angle of the floating wing (2) is only related to the flying speed direction and is not related to the posture of the fuselage (4), the adjustment of the lift force required by the aircraft is realized by adjusting the attack angle adjusting control surface (3), and the attack angle of the floating wing (2) is self-adaptively balanced on the attack angle set by the attack angle adjusting control surface (3).
8. The method for implementing a non-stalled floating lift airfoil for an aircraft according to claim 7, wherein the floating lift airfoil is used in a VTOL aircraft for taking off as follows:
firstly, in a vertical takeoff initial state, the aircraft flies vertically upwards to a set height;
secondly, in a vertical rotation horizontal acceleration state, the vertical upward speed of the aircraft is gradually reduced, the horizontal flying speed is gradually increased, the attack angle of the floating lift wing surface (1) is adaptive to the flying combined speed vector direction, and the attack angle is controlled by the attack angle adjusting control surface (3), so that the lift efficiency of the lift wing surface is kept during the vertical rotation horizontal flying process of the aircraft;
and finally, the flying wing is in a flat flying state, the conversion from vertical to flat flying is completed, the size of the attack angle of the floating lift wing surface (1) in the flat flying state is still controlled by the attack angle adjusting control surface (3), or the floating lift wing surface (1) and the aircraft body (4) are locked in the rotational freedom degree, and the flying wing is converted into a conventional fixed wing aircraft.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011241453.5A CN112278239A (en) | 2020-11-09 | 2020-11-09 | A non-stall floating lift airfoil of an aircraft and its realization method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011241453.5A CN112278239A (en) | 2020-11-09 | 2020-11-09 | A non-stall floating lift airfoil of an aircraft and its realization method |
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| WO2019104796A1 (en) * | 2017-11-28 | 2019-06-06 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| US10589838B1 (en) * | 2019-06-11 | 2020-03-17 | The Suppes Family Trust | Multicopter with passively-adjusting tiltwing |
| CN213974434U (en) * | 2020-11-09 | 2021-08-17 | 中国人民解放军总参谋部第六十研究所 | Aircraft non-stall floating lift wing surface |
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2020
- 2020-11-09 CN CN202011241453.5A patent/CN112278239A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2231477C1 (en) * | 2003-03-11 | 2004-06-27 | Буданов Станислав Васильевич | Aircraft |
| CN206552260U (en) * | 2017-03-02 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of efficient vertically taking off and landing flyer |
| WO2019104796A1 (en) * | 2017-11-28 | 2019-06-06 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle |
| CN110418755A (en) * | 2017-11-28 | 2019-11-05 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle |
| CN107933909A (en) * | 2017-12-17 | 2018-04-20 | 北京天宇新超航空科技有限公司 | A kind of high-speed and high-efficiency tilting wing unmanned vehicle |
| US10589838B1 (en) * | 2019-06-11 | 2020-03-17 | The Suppes Family Trust | Multicopter with passively-adjusting tiltwing |
| CN213974434U (en) * | 2020-11-09 | 2021-08-17 | 中国人民解放军总参谋部第六十研究所 | Aircraft non-stall floating lift wing surface |
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Country or region after: China Address after: No.2, Huangpu Road, Xuanwu District, Nanjing, Jiangsu Province, 210016 Applicant after: China Rongtong Group 60th Research Institute Address before: No. 2 Huangpu Road, Xuanwu District, Nanjing City, Jiangsu Province Applicant before: NO.60 INSTITUTE OF THE HEADQUARTERS OF GENERAL STAFF OF PLA Country or region before: China |