CN118163943A - Distributed hybrid power vertical take-off and landing aircraft and vertical take-off and landing control method thereof - Google Patents
Distributed hybrid power vertical take-off and landing aircraft and vertical take-off and landing control method thereof Download PDFInfo
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- CN118163943A CN118163943A CN202410606216.6A CN202410606216A CN118163943A CN 118163943 A CN118163943 A CN 118163943A CN 202410606216 A CN202410606216 A CN 202410606216A CN 118163943 A CN118163943 A CN 118163943A
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- 238000000034 method Methods 0.000 title claims abstract description 22
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 55
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 230000008569 process Effects 0.000 claims description 8
- 239000000446 fuel Substances 0.000 claims description 7
- 238000005096 rolling process Methods 0.000 claims description 7
- 239000000295 fuel oil Substances 0.000 claims description 4
- 230000008859 change Effects 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 3
- 238000010168 coupling process Methods 0.000 claims description 3
- 238000005859 coupling reaction Methods 0.000 claims description 3
- 239000013585 weight reducing agent Substances 0.000 abstract description 3
- 230000008901 benefit Effects 0.000 description 3
- 230000005611 electricity Effects 0.000 description 3
- 241000272517 Anseriformes Species 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
- B64C15/12—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Wind Motors (AREA)
Abstract
The invention provides a distributed hybrid power vertical take-off and landing aircraft and a vertical take-off and landing control method thereof, wherein the aircraft comprises a fuselage, wings, duckwings and a power system, and is characterized in that: the front part of the fuselage is provided with a duck wing, and the rear part of the fuselage is provided with a wing penetrating through the fuselage; the wing sequentially comprises an inner section wing, a connecting nacelle and an outer section wing from the fuselage to the outside, wherein a flap control surface is arranged at the rear edge of the inner section wing, and an aileron control surface is arranged at the rear edge of the outer section wing; the power system comprises a generator, and a duck wing duct fan and a wing duct fan which are connected with the generator, wherein the duck wing duct fan is distributed at the lower part of the duck wing, and the wing duct fan is distributed inside the inner section of the wing. The invention not only can ensure the vertical take-off and landing of the aircraft, but also can ensure higher cruising speed and aerodynamic characteristics, and realizes weight reduction and energy saving in a hybrid power mode.
Description
Technical Field
The invention relates to the technical field of aviation aircrafts, in particular to a distributed hybrid power vertical take-off and landing aircraft and a vertical take-off and landing control method thereof.
Background
The distributed hybrid power vertical take-off and landing aircraft is a new energy aircraft suitable for different take-off environments. The rotor helicopter has the advantages of excellent cruise performance and taking-off and landing advantages of the rotor helicopter, can have good field performance and flight performance in various flight environments and various task states, can achieve the compromise of performance, efficiency, cost and benefit, and can improve flight safety.
The distributed aircraft is to disperse the power units, and can provide lift, increase aerodynamic gain, increase lift-drag ratio and the like. The aircraft can improve the energy utilization efficiency, so that the defects of short range and high consumption of an oil-driven system of a pure electric system can be overcome, and the pneumatic-appearance and high-energy-efficiency propulsion system of the aircraft has larger application value for military small unmanned aerial vehicles, medium-sized and small civil unmanned aerial vehicles or large-sized transportation vehicles.
The current lack of design level and detailed fuselage integration technology for this type of aircraft, due to the presence of distributed power systems, places higher demands on the pneumatics and architecture, and due to the presence of electrical systems, also the arrangement of the interior thereof should be carefully considered.
Disclosure of Invention
The invention aims to solve the problems in the prior art, and provides a distributed hybrid power vertical take-off and landing aircraft and a vertical take-off and landing control method thereof, which not only can ensure that the aircraft takes off and lands vertically, has better transverse and longitudinal stability, but also can ensure higher cruising speed and aerodynamic characteristics, and realize weight reduction and energy conservation in a hybrid power mode.
The invention provides a distributed hybrid power vertical take-off and landing aircraft, which comprises a fuselage, wings, a duck wing and a power system, wherein the duck wing is arranged at the front part of the fuselage, and the wings penetrating through the fuselage are arranged at the rear part of the fuselage; the wing sequentially comprises an inner section wing, a connecting nacelle and an outer section wing from the fuselage to the outside, wherein a flap control surface is arranged at the rear edge of the inner section wing, and an aileron control surface is arranged at the rear edge of the outer section wing; the power system comprises a generator, and a duck wing duct fan and a wing duct fan which are connected with the generator, wherein the duck wing duct fan is distributed at the lower part of the duck wing, and the wing duct fan is distributed inside the inner section of the wing.
Further improved, the machine body adopts streamline design, the upper surface is flat, and the lower surface is less than other parts of the machine body in the thickness of the tail part of the machine body and is provided with a reverse recess. The passenger cabin is arranged at the front part of the machine body, the cargo cabin and the folding seats are arranged at the middle part of the machine body and used for transporting goods and personnel, and the cabin door is arranged at the tail part, so that personnel and goods can conveniently come in and go out; the fuselage was 15.5 meters long, 2.8 meters high and 2.7 meters wide.
Further improved, the length of the inner Duan Jiyi is 6.9m, the aspect ratio is 3.8, the root tip ratio is 1, and the sweepback angle is 0 degrees.
Further improved, the flap is a retreating slotted flap, and the deflection angle is 0-90 degrees.
Further improved, the outer section wing has a span length of 14.4m, an aspect ratio of 8, a root tip ratio of 1.25 and a sweepback angle of 30 degrees.
Further improved, the duck wing span is 7m long, the aspect ratio is 7-9.5, the root tip ratio is 1-1.67, the sweepback angle is 10-40 degrees, the long-distance coupling duck wing layout is adopted, the duck wing actuation mode is a full-motion duck wing, and the duck wing deflection angle is 0-90 degrees.
Further improved, the power system adopts serial hybrid power of fuel oil and storage batteries, and the generator is arranged in the wing connection nacelle.
The vertical take-off and landing control method of the distributed hybrid power vertical take-off and landing aircraft comprises the following steps of:
1) When the aircraft takes off and land vertically, the duck wings and the duck wing duct fans arranged on the duck wings deflect to 90 degrees together, and the wing flaps deflect to 90 degrees vertically to the aircraft body; the wing ducted fans deflect the jet downwards by using deflected wing flaps to generate jet lift, and meanwhile, the jet speed on the upper surface of the wing is accelerated by the retreating flaps to generate additional lift.
2) When the aircraft cruises in horizontal flight, the duckwings and the duckwing duct fans arranged on the duckwings deflect to 0 degrees, and the wing flaps deflect to 0 degrees; the wing and the wing duct fan jet to generate thrust and the wing generate lift.
In the vertical take-off and landing process, step 1) performing pitching attitude control on the aircraft through the change of the thrust of the duck wing ducted fans, rolling attitude control on the aircraft through the difference of the thrust of the left and right ducted fans, and yaw attitude control on the aircraft through the left and right differential deflection of the duck wings and the flaps; and 2) in the horizontal flight cruising process, the aileron deflects to control the attitude of rolling of the aircraft, the duck wing deflects to control the attitude of pitching of the aircraft, and the left and right ducted fan thrust difference controls the attitude of yawing of the aircraft.
Further improved, the power system adopts a series hybrid power mode, and the fuel drives the generator to generate electricity so as to drive the ducted fan to work. The aircraft can utilize the left and right ducted fan thrust differences for yaw control. The take-off and landing phases are battery powered to provide power support for the take-off and landing phases, thereby reducing the fuel consumption due to vertical take-off and landing. The fuel power is adopted in the flight stage, so that the ducted fan is driven and is powered by a battery, and the extra weight of the battery for realizing the whole-process flight is avoided.
The invention has the beneficial effects that:
1. the invention selects the power mode of the distributed duct fans, so that the aircraft has enough power propulsion and certain cruising ability.
2. The invention can realize vertical take-off and landing through forms of mechanism transformation and the like, has better transverse and longitudinal stability, and can also ensure higher cruising speed and aerodynamic characteristics.
3. The invention realizes weight reduction and energy saving in a hybrid power mode.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a perspective view of a distributed hybrid vertical takeoff and landing aircraft in a flat flight configuration according to an embodiment of the present invention;
FIG. 2 is a side view of a distributed hybrid vertical takeoff and landing aircraft in a flat flight configuration, according to an embodiment of the present invention;
FIG. 3 is a front view of a distributed hybrid vertical takeoff and landing aircraft in a flat flight configuration, according to an embodiment of the present invention;
FIG. 4 is a top view of a distributed hybrid vertical takeoff and landing aircraft in a flat flight configuration according to an embodiment of the present invention;
FIG. 5 is a cross-sectional view A-A of FIG. 4;
FIG. 6 is a top view of a distributed hybrid vertical take-off and landing aircraft in a vertical take-off configuration according to an embodiment of the present invention;
fig. 7 is a sectional view of B-B in fig. 6.
Reference numerals illustrate:
1. a fuselage (11, passenger compartment, 12, cargo compartment, 13, cabin door); 2. wings (21, outer section wings, 211, ailerons, 22, connecting nacelle, 23, inner Duan Jiyi, 231, flaps); 3. a duck wing; 4. the power system (41, duck wing ducted fans, 42, wing ducted fans).
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides a distributed hybrid power vertical take-off and landing aircraft, which is shown in figures 1-3 and comprises a fuselage 1, wings 2, a duck wing 3 and a power system 4, wherein the duck wing is arranged at the front part of the fuselage, and the wings penetrating through the fuselage are arranged at the rear part of the fuselage; the wing sequentially comprises an inner section wing 23, a connecting nacelle 22 and an outer section wing 21 from the fuselage to the outside, wherein a flap 231 control surface is arranged at the rear edge of the inner section wing, and an aileron 211 control surface is arranged at the rear edge of the outer section wing; the power system comprises a generator, and a duck wing duct fan 41 and a wing duct fan 42 which are connected with the generator, wherein the duck wing duct fan is distributed and arranged at the lower part of the duck wing, and the wing duct fan is distributed and arranged inside the inner section of the wing.
Further improved, the machine body adopts streamline design, the upper surface is flat, and the lower surface is less than other parts of the machine body in the thickness of the tail part of the machine body and is provided with a reverse recess. The passenger cabin 11 is arranged at the front part of the machine body, the cargo cabin 12 and folding seats are arranged at the middle part of the machine body and used for transporting goods and personnel, and the cabin door 13 is arranged at the tail part, so that personnel and goods can conveniently come in and go out; the fuselage was 15.5 meters long, 2.8 meters high and 2.7 meters wide.
Further improved, the length of the inner Duan Jiyi is 6.9m, the aspect ratio is 3.8, the root tip ratio is 1, and the sweepback angle is 0 degrees. The trailing edge of the inner section wing is provided with a flap, and the flap is a backward slit flap which can deflect to 90 degrees; the outer section wing has a span length of 14.4m, an aspect ratio of 8, a root tip ratio of 1.25 and a sweepback angle of 30 degrees, and the trailing edge of the outer section wing is provided with an aileron control surface, so that the rolling motion of the aircraft can be controlled.
Further improved, the flap is a retreating slotted flap, and the deflection angle is 0-90 degrees.
Further improved, the outer section wing has a span length of 14.4m, an aspect ratio of 8, a root tip ratio of 1.25 and a sweepback angle of 30 degrees.
Further improved, the duck wing span is 7m long, the aspect ratio is 5, the root tip ratio is 1.25, the sweepback angle is 32 degrees, the long-distance coupling duck wing layout is adopted, the duck wing actuation mode is a full-motion duck wing, and the duck wing deflection angle is 0-90 degrees.
Further improved, the power system adopts serial hybrid power of fuel oil and storage batteries, and the generator is arranged in the wing connection nacelle.
The vertical take-off and landing control method of the distributed hybrid power vertical take-off and landing aircraft comprises the following steps of:
1) When the aircraft takes off and land vertically, the duck wings and the duck wing duct fans arranged on the duck wings deflect to 90 degrees together, and the wing flaps deflect to 90 degrees vertically to the aircraft body; the wing ducted fans deflect the jet downwards by using deflected wing flaps to generate jet lift, and meanwhile, the jet speed on the upper surface of the wing is accelerated by the retreating flaps to generate additional lift.
2) When the aircraft cruises in horizontal flight, the duckwings and the duckwing duct fans arranged on the duckwings deflect to 0 degrees, and the wing flaps deflect to 0 degrees; the wing and the wing duct fan jet to generate thrust and the wing generate lift.
In the vertical take-off and landing process, step 1) performing pitching attitude control on the aircraft through the change of the thrust of the duck wing ducted fans, rolling attitude control on the aircraft through the difference of the thrust of the left and right ducted fans, and yaw attitude control on the aircraft through the left and right differential deflection of the duck wings and the flaps; and 2) in the horizontal flight cruising process, the aileron deflects to control the attitude of rolling of the aircraft, the duck wing deflects to control the attitude of pitching of the aircraft, and the left and right ducted fan thrust difference controls the attitude of yawing of the aircraft.
Further improved, the power system adopts a series hybrid power mode, and the fuel drives the generator to generate electricity so as to drive the ducted fan to work. The aircraft can utilize the left and right ducted fan thrust differences for yaw control. The take-off and landing phases are battery powered to provide power support for the take-off and landing phases, thereby reducing the fuel consumption due to vertical take-off and landing. The fuel power is adopted in the flight stage, so that the ducted fan is driven and is powered by a battery, and the extra weight of the battery for realizing the whole-process flight is avoided.
The specific implementation flow of the vertical take-off and landing is as follows:
In a specific embodiment, as shown in fig. 4-7, the aircraft is parked on land as shown in fig. 4, and upon mission take-off, the fully-actuated canard is deflected to 90 ° with the canard ducted fan mounted thereon, perpendicular to the airframe, with the wing flaps deflected to 90 °, to the condition shown in fig. 6. The wing ducted fans utilize deflected wing flaps to deflect jet downwards to generate jet lift. After the take-off task is completed, the duck wings and wing flaps recover to a non-deflection form, so that the cruising task is realized. The landing phase may be consistent with the takeoff state.
The aircraft uses the battery to store energy to provide power during taking off and landing, so as to generate enough taking off and landing thrust, and when cruising, the aircraft is powered by fuel oil, and the power generator is driven to generate electricity to drive the ducted fan to complete flying, and meanwhile, the power is supplied to the battery to ensure the power requirement during landing.
In this specification, each embodiment is described in a progressive manner, and identical and similar parts of each embodiment are all referred to each other, and each embodiment mainly describes differences from other embodiments. In particular, for the equipment examples, what has been described above is merely a preferred embodiment of the invention, which, since it is substantially similar to the method examples, is described relatively simply, as relevant to the description of the method examples. The foregoing is merely illustrative of specific embodiments of the present invention, and the scope of the invention is not limited thereto, since modifications and substitutions will be readily made by those skilled in the art without departing from the spirit of the invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a distributed hybrid vertical take-off and landing aircraft, includes fuselage, wing, duck wing and driving system, its characterized in that: the front part of the fuselage is provided with a duck wing, and the rear part of the fuselage is provided with a wing penetrating through the fuselage; the wing sequentially comprises an inner section wing, a connecting nacelle and an outer section wing from the fuselage to the outside, wherein a flap control surface is arranged at the rear edge of the inner section wing, and an aileron control surface is arranged at the rear edge of the outer section wing; the power system comprises a generator, and a duck wing duct fan and a wing duct fan which are connected with the generator, wherein the duck wing duct fan is distributed at the lower part of the duck wing, and the wing duct fan is distributed inside the inner section of the wing.
2. The distributed hybrid vertical takeoff and landing aircraft according to claim 1, characterized in that: the machine body is in streamline design, the upper surface is flat, and the lower surface is smaller than other parts of the machine body in thickness at the tail part of the machine body and is provided with a reverse recess.
3. The distributed hybrid vertical takeoff and landing aircraft according to claim 1, characterized in that: the internal Duan Jiyi has a length of 6.9m, an aspect ratio of 3.8, a root tip ratio of 1 and a sweepback angle of 0 degrees.
4. A distributed hybrid vertical takeoff and landing aircraft according to claim 1 or 3, characterized in that: the flap is a retreating slotted flap, and the deflection angle is 0-90 degrees.
5. The distributed hybrid vertical takeoff and landing aircraft according to claim 1, characterized in that: the outer section wing has a span length of 14.4m, an aspect ratio of 8, a root tip ratio of 1.25 and a sweepback angle of 30 degrees.
6. The distributed hybrid vertical takeoff and landing aircraft according to claim 1, characterized in that: the duck wing span is 7m long, the aspect ratio is 7-9.5, the root tip ratio is 1-1.67, the sweepback angle is 10-40 degrees, the long-distance coupling duck type layout is adopted, the actuation mode of the duck wing is a full-motion duck wing, and the deflection angle of the duck wing is 0-90 degrees.
7. The distributed hybrid vertical takeoff and landing aircraft according to claim 1, characterized in that: the power system adopts fuel oil and storage battery serial hybrid power, and the generator is arranged in the wing connection nacelle.
8. A method of controlling vertical take-off and landing of a distributed hybrid vertical take-off and landing aircraft according to claim 1, comprising the steps of:
1) When the aircraft takes off and land vertically, the duck wings and the duck wing duct fans arranged on the duck wings deflect to 90 degrees together, and the wing flaps deflect to 90 degrees vertically to the aircraft body; the wing ducted fans deflect jet flow downwards by using deflected wing flaps to generate jet flow lift force, and meanwhile, the jet flow speed on the upper surface of the wing is accelerated by the retreating flaps so as to generate additional lift force;
2) When the aircraft cruises in horizontal flight, the duckwings and the duckwing duct fans arranged on the duckwings deflect to 0 degrees, and the wing flaps deflect to 0 degrees; the wing and the wing duct fan jet to generate thrust and the wing generate lift.
9. The vertical take-off and landing control method for a distributed hybrid vertical take-off and landing aircraft of claim 8, wherein: in the vertical take-off and landing process, performing pitching attitude control on the aircraft through the change of the thrust of the duck wing ducted fans, performing rolling attitude control on the aircraft through the difference of the thrust of the left and right ducted fans, and performing yaw attitude control on the aircraft through the left and right differential deflection of the duck wings and the flaps; and 2) in the horizontal flight cruising process, the aileron deflects to control the attitude of rolling of the aircraft, the duck wing deflects to control the attitude of pitching of the aircraft, and the left and right ducted fan thrust difference controls the attitude of yawing of the aircraft.
10. The vertical take-off and landing control method for a distributed hybrid vertical take-off and landing aircraft of claim 8, wherein: in the step 1) of the vertical take-off and landing process, the generator is powered by a battery to provide power support for the take-off and landing stage, and in the step 2) of the horizontal flight cruising process, the generator adopts fuel power to drive the ducted fan and is powered by the battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410606216.6A CN118163943B (en) | 2024-05-16 | 2024-05-16 | Distributed hybrid power vertical take-off and landing aircraft and vertical take-off and landing control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410606216.6A CN118163943B (en) | 2024-05-16 | 2024-05-16 | Distributed hybrid power vertical take-off and landing aircraft and vertical take-off and landing control method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN118163943A true CN118163943A (en) | 2024-06-11 |
| CN118163943B CN118163943B (en) | 2024-10-08 |
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| CN202410606216.6A Active CN118163943B (en) | 2024-05-16 | 2024-05-16 | Distributed hybrid power vertical take-off and landing aircraft and vertical take-off and landing control method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180086447A1 (en) * | 2016-09-08 | 2018-03-29 | Hop Flyt Inc | Aircraft having independently variable incidence channel wings with independently variable incidence channel canards |
| CN110316370A (en) * | 2019-06-25 | 2019-10-11 | 北京航空航天大学 | A kind of layout and control method of distributed-power tilting wing aircraft |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN114104282A (en) * | 2021-10-28 | 2022-03-01 | 上海磐拓航空科技服务有限公司 | Ducted fan tilt-turn wing vertical take-off and landing aircraft |
| US20220371446A1 (en) * | 2021-05-19 | 2022-11-24 | Lilium Eaircraft Gmbh | Electrical fault isolation in a power distribution network of an aircraft |
| EP4361026A1 (en) * | 2022-10-27 | 2024-05-01 | Lilium eAircraft GmbH | Wing |
-
2024
- 2024-05-16 CN CN202410606216.6A patent/CN118163943B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180086447A1 (en) * | 2016-09-08 | 2018-03-29 | Hop Flyt Inc | Aircraft having independently variable incidence channel wings with independently variable incidence channel canards |
| CN110316370A (en) * | 2019-06-25 | 2019-10-11 | 北京航空航天大学 | A kind of layout and control method of distributed-power tilting wing aircraft |
| CN111268120A (en) * | 2020-03-11 | 2020-06-12 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| US20220371446A1 (en) * | 2021-05-19 | 2022-11-24 | Lilium Eaircraft Gmbh | Electrical fault isolation in a power distribution network of an aircraft |
| CN114104282A (en) * | 2021-10-28 | 2022-03-01 | 上海磐拓航空科技服务有限公司 | Ducted fan tilt-turn wing vertical take-off and landing aircraft |
| EP4361026A1 (en) * | 2022-10-27 | 2024-05-01 | Lilium eAircraft GmbH | Wing |
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| Publication number | Publication date |
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| CN118163943B (en) | 2024-10-08 |
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