CN114476036A - Power layout framework of high-speed gyroplane - Google Patents
Power layout framework of high-speed gyroplane Download PDFInfo
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- CN114476036A CN114476036A CN202210153335.1A CN202210153335A CN114476036A CN 114476036 A CN114476036 A CN 114476036A CN 202210153335 A CN202210153335 A CN 202210153335A CN 114476036 A CN114476036 A CN 114476036A
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- speed
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- ducted fan
- gyroplane
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- 230000005540 biological transmission Effects 0.000 claims description 3
- 230000002787 reinforcement Effects 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000006386 neutralization reaction Methods 0.000 description 1
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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
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8209—Electrically driven tail rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8227—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising more than one rotor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a power layout framework of a high-speed gyroplane, and relates to the technical field of high-speed gyroplanes, general aircrafts, aviation electric propulsion and rim motors. The power layout framework decouples the take-off and landing power and the cruise power of the high-speed gyroplane, and the main rotor of the high-speed gyroplane only provides lift force to realize the take-off and landing functions; converting a part of engine power into electric energy by using a generator and providing the electric energy to a distributed electric ducted fan propeller behind the fuselage to provide horizontal cruising thrust; the ducted propeller is connected with the fuselage through a support capable of tilting; the tail part adopts a rim electric fan design. The invention simplifies the complex structure of the main rotor shaft drive of the rotorcraft; the integral structural strength of the main rotor wing is increased, and the cruising flight speed upper limit is improved; the tiltably-rotatable distributed electric ducted fan is utilized, so that the maneuvering performance and the take-off and landing speed of the flight are improved; the electric tail rotor of the flange of the tail part further improves the pneumatic performance and the cruising speed.
Description
Technical Field
The invention relates to the technical field of aviation electric propulsion, in particular to a power layout framework of a high-speed gyroplane.
Background
With the development and planning of the general aviation industry, the proposal of carbon neutralization strategy and the development of aviation electric propulsion technology in China, an aircraft capable of rapidly realizing point-to-point transportation needs to be developed, and the important position of the gyroplane in the general aviation field is determined by the advantage of vertical take-off and landing of the gyroplane. However, the conventional rotorcraft has the defects of poor overall aerodynamic performance, low flying speed, high pollution, small load and the like, and is difficult to meet the point-to-point high-speed transportation requirement of future general aviation. The traditional rotorcraft needs the aircraft body and the main rotor to tilt downwards for a certain angle when cruising, and the component of the thrust of the main rotor in the horizontal direction is utilized to realize flat flight, so that the power propulsion mode has low efficiency and low speed, and the shaft drive system of the main rotor is very complex, the construction and maintenance cost is high, and the strength is insufficient; in addition, conventional tail rotors are driven by extended engine linkages, which are also costly and not strong enough.
Disclosure of Invention
The invention aims to solve the technical problem of the background art, in particular to the problem of low cruising speed of the traditional gyroplane, provides a power layout framework of the high-speed gyroplane, is in accordance with the universal aviation development of the new era, not only keeps the advantages of vertical take-off and landing of the gyroplane, but also meets the propelling requirement of high-speed flight, has the advantages of small pollution, large load, high safety and the like, and has wide application prospect.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the power layout framework of the high-speed gyroplane comprises a main rotor, an engine, a generator, a distributed electric ducted fan, a tiltable bracket, an auxiliary lift force short wing and a tail electric wheel flange tail rotor, wherein the power of the main rotor is provided by the engine; the generator converts shaft power led out from the engine accessory casing into electric energy, and the electric energy is transmitted to the electric ducted fan and the tail electric wheel flange tail rotor through the motor controller.
Further, the flight power of the high-speed rotorcraft is decoupled into lift-take-off and horizontal cruise power.
Further, the lift take-off and landing power of the high-speed rotorcraft comprises lift provided by a main rotor of the rotorcraft, lift provided by an auxiliary lift short wing during cruising and downward thrust provided by the tilted electric ducted fan; the required size of lift can be adjusted according to the flight operating mode of difference, has improved the holistic mobility performance and the security performance of high-speed gyroplane.
Further, the horizontal cruise power of a high-speed rotorcraft is the rearward horizontal thrust generated by the distributed electric ducted fans.
Further, the main rotor of the high-speed gyroplane only provides lift force, a front-back pitching transmission mechanism is omitted in the main shaft structure, only a structure for changing a deflection angle is reserved, and reinforcement is carried out in the horizontal movement direction.
Furthermore, the electric ducted fan is arranged behind the body of the high-speed gyroplane through a tiltable bracket in a distributed layout mode; when cruising, the electric ducted fan generates backward horizontal thrust, and when taking off and landing, the electric ducted fan tilts downwards to provide downward thrust.
Furthermore, the tail rotor of the high-speed gyroplane adopts the rim electric tail rotor, and the tail rotor is arranged in the gyroplane body, so that the horizontal flight resistance is reduced, and the pneumatic performance is improved.
Further, the length of the tilting bracket of the electric ducted fan is short, and the bracket arms form an airplane wing shape.
Furthermore, the auxiliary lift short wing is arranged right in front of the electric ducted fan, so that the lift force on the rear side of the airplane body during cruising can be improved.
Compared with the prior art, the invention has the following beneficial effects:
(1) the flight power of the high-speed gyroplane is decoupled into the lifting force take-off and landing power and the horizontal cruising power, so that the flight speed can be improved, and the safety and the maneuverability are improved;
(2) the complexity and the weight of a main rotor shaft drive structure are reduced, and the structural strength is higher;
(3) the electric ducted fan capable of tilting is adopted for propulsion, so that the pollution is less, the propulsion efficiency is higher, the flying speed is higher, and the maneuvering performance is stronger;
(4) the tail electric wheel flange tail rotor is adopted, the pneumatic performance is better, the maneuvering performance is better, and the flying speed is improved.
Drawings
Figure 1 is a power layout architecture diagram of a high-speed rotorcraft according to the present invention;
FIG. 2 is a schematic representation of the power layout architecture of the high-speed rotorcraft of the present invention during vertical take-off and landing;
fig. 3 is a cross-sectional view of an electric ducted fan in the power layout architecture of a high-speed rotorcraft according to the present invention;
FIG. 4 is a diagram of an electric rim tail rotor in the power layout architecture of a high-speed rotorcraft according to the present invention;
fig. 5 is a schematic diagram of the energy distribution in the power layout architecture of a high-speed rotorcraft according to the present invention.
In the figure: 1. the main rotor, 2, electronic ducted fan of distributing type, 3, support that can rotate, 4, the auxiliary lift short wing, 5, the electronic rim tail-rotor of afterbody, 51, the tail will, 52, the rim driving motor stator of afterbody, 53, the rim driving motor rotor of afterbody.
Detailed Description
The technical scheme of the invention is further explained by combining the drawings and the embodiment:
the present invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
Examples
Fig. 1 shows a power layout framework of a high-speed rotorcraft according to the present invention, which mainly comprises a main rotor 1, an engine, a generator, a distributed electric ducted fan 2, a tiltable bracket 3, an auxiliary lift short wing 4, and a tail electric rim tail rotor 5. The flight power of a high-speed rotorcraft is decoupled into lift take-off and landing power and horizontal cruise power. As shown in fig. 2, the lift take-off and landing power of a high-speed rotorcraft includes the lift provided by the main rotor 1 of the rotorcraft, the lift provided by the auxiliary lift stub 4 during cruising, and the downward thrust provided by the tilted electric ducted fan 2; the required size of lift can be adjusted according to the flight operating mode of difference, has improved the holistic mobility performance and the security performance of high-speed gyroplane. The main rotor 1 of the high-speed rotorcraft only provides lift, the transmission mechanism of pitching back and forth is cancelled in the main shaft structure 11, only the structure for changing the deflection angle is reserved, and the structure is reinforced in the horizontal movement direction. The horizontal cruising power of the high-speed gyroplane is backward horizontal thrust generated by a distributed electric ducted fan; as shown in fig. 1, the electric ducted fan 2 is installed behind the fuselage of the high-speed rotorcraft through a tiltable bracket 3 in a distributed layout manner; the length of the tiltable bracket 3 is shorter, and the bracket arm is shaped like an airplane wing; when cruising, the electric ducted fan generates backward horizontal thrust; when taking off and landing, the electric ducted fan tilts downwards to provide downward thrust. The tail rotor of the high-speed rotorcraft adopts the rim electric tail rotor 5, as shown in fig. 4, the tail rotor 51 and the rim motor rotor 53 are integrated together, and the rim motor stator 52 is arranged in the body, so that the flight resistance of the tail part of the high-speed rotorcraft can be reduced when the high-speed rotorcraft is horizontal, and the pneumatic performance is improved. The auxiliary lift short wing 4 is arranged right in front of the electric ducted fan, so that the lift force on the rear part of the airplane body can be improved during cruising.
The above-mentioned embodiments further describe the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above-mentioned embodiments are only for illustrating the technical ideas of the present invention and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like based on the technical solutions of the present invention should be included in the scope of the present invention according to the technical ideas of the present invention.
Claims (9)
1. A power layout architecture of a high-speed rotorcraft, characterized in that: the power layout framework consists of a main rotor, an engine, a generator, a distributed electric ducted fan, a tiltable bracket, an auxiliary lift force short wing and a tail wheel rim electric tail rotor; the flight power of the high-speed rotorcraft is decoupled into lift take-off and landing power and horizontal cruise power.
2. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the lift force lifting power comprises lift force generated by a main rotor wing of the rotorcraft, lift force provided by an auxiliary lift force short wing during cruising and downward thrust provided by a tilting electric ducted fan; the required size of lift can be adjusted according to the flight operating mode of difference, has improved the holistic mobility performance and the security performance of high-speed gyroplane.
3. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the horizontal cruise power is the backward horizontal thrust generated by the tiltable electric ducted fan.
4. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the main rotor of the high-speed gyroplane only provides lift force, a front-back pitching transmission mechanism is cancelled in the main shaft structure, only a structure for changing a deflection angle is reserved, and reinforcement is carried out in the horizontal movement direction.
5. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the electric ducted fan adopts a distributed layout scheme of a plurality of small powers and is arranged behind the machine body by utilizing a support capable of tilting; when cruising, the electric ducted fan generates backward horizontal thrust; when taking off and landing, the electric ducted fan tilts downwards to provide downward thrust; the combination of the thrust and the lift force is more flexible, and the maneuverability and the safety performance are improved.
6. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the tail rotor adopts a rim electric tail rotor, and is arranged in the machine body, so that the horizontal flight resistance is reduced, and the pneumatic performance is improved.
7. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the length of the tilting bracket of the electric ducted fan is shorter, and the bracket arms form an airplane wing shape.
8. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the auxiliary lift short wing is arranged right in front of the electric ducted fan, so that the lift force borne by the rear part of the airplane body during cruising can be improved.
9. A power layout architecture for a high-speed rotorcraft according to claim 1, wherein: the generator converts shaft power led out from the engine accessory casing into electric energy, and the electric energy is transmitted to the electric ducted fan and the tail electric wheel flange tail rotor through the motor controller; the main rotor power comes from the shaft power of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210153335.1A CN114476036B (en) | 2022-02-18 | 2022-02-18 | Power layout architecture of high-speed gyroplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210153335.1A CN114476036B (en) | 2022-02-18 | 2022-02-18 | Power layout architecture of high-speed gyroplane |
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| Publication Number | Publication Date |
|---|---|
| CN114476036A true CN114476036A (en) | 2022-05-13 |
| CN114476036B CN114476036B (en) | 2024-02-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210153335.1A Active CN114476036B (en) | 2022-02-18 | 2022-02-18 | Power layout architecture of high-speed gyroplane |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974348A (en) * | 2017-05-31 | 2018-12-11 | 贝尔直升机德事隆公司 | The rotor braking effect for making main rotor slow down using electric distributed reaction torque generator and reversed electric motor thrust |
| US20200172234A1 (en) * | 2018-11-30 | 2020-06-04 | William J. Neff | Propulsion system for an aerial vehicle |
| US20210047029A1 (en) * | 2019-08-15 | 2021-02-18 | Bell Textron Inc. | Centerline Tiltrotor |
| US20210047028A1 (en) * | 2019-08-14 | 2021-02-18 | Bell Textron Inc. | Compound Helicopter Having a Tiltable Jet Engine |
| US20210114740A1 (en) * | 2019-10-18 | 2021-04-22 | The Boeing Company | Rotary electric engines, aircraft including the same, and associated methods |
| CN114670999A (en) * | 2020-12-24 | 2022-06-28 | 中国科学院沈阳自动化研究所 | Water-air dual-purpose propeller adopting double motors |
-
2022
- 2022-02-18 CN CN202210153335.1A patent/CN114476036B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974348A (en) * | 2017-05-31 | 2018-12-11 | 贝尔直升机德事隆公司 | The rotor braking effect for making main rotor slow down using electric distributed reaction torque generator and reversed electric motor thrust |
| US20200172234A1 (en) * | 2018-11-30 | 2020-06-04 | William J. Neff | Propulsion system for an aerial vehicle |
| US20210047028A1 (en) * | 2019-08-14 | 2021-02-18 | Bell Textron Inc. | Compound Helicopter Having a Tiltable Jet Engine |
| US20210047029A1 (en) * | 2019-08-15 | 2021-02-18 | Bell Textron Inc. | Centerline Tiltrotor |
| US20210114740A1 (en) * | 2019-10-18 | 2021-04-22 | The Boeing Company | Rotary electric engines, aircraft including the same, and associated methods |
| CN114670999A (en) * | 2020-12-24 | 2022-06-28 | 中国科学院沈阳自动化研究所 | Water-air dual-purpose propeller adopting double motors |
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| Publication number | Publication date |
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| CN114476036B (en) | 2024-02-02 |
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