CN112027074A - Combined type tilting wing longitudinal wing-changing counter-speed rotor aircraft - Google Patents
Combined type tilting wing longitudinal wing-changing counter-speed rotor aircraft Download PDFInfo
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- 238000006243 chemical reaction Methods 0.000 claims abstract description 7
- 238000004146 energy storage Methods 0.000 claims description 15
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- 238000010248 power generation Methods 0.000 claims description 9
- 239000013589 supplement Substances 0.000 claims description 9
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 6
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- 230000009471 action Effects 0.000 claims description 4
- 150000001875 compounds Chemical class 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 125000004122 cyclic group Chemical group 0.000 claims description 2
- 238000010276 construction Methods 0.000 abstract description 2
- 230000007123 defense Effects 0.000 abstract description 2
- 238000013016 damping Methods 0.000 description 2
- 230000003111 delayed effect Effects 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- YFGHCGITMMYXAQ-UHFFFAOYSA-N 2-[(diphenylmethyl)sulfinyl]acetamide Chemical compound C=1C=CC=CC=1C(S(=O)CC(=O)N)C1=CC=CC=C1 YFGHCGITMMYXAQ-UHFFFAOYSA-N 0.000 description 1
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- 229960001165 modafinil Drugs 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
-
- 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
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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Abstract
The invention relates to a vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft. The combined type tilting wing longitudinal variable wing counter-speed rotor aircraft is characterized in that a main lift rotor set 5 is arranged on the upper portion of an engine body 1 in a longitudinal mode, two pairs of convertible blades 9 are arranged on the main lift rotor set 5, fixed wings 2 are arranged in the middle of the engine body 1, power short wings 4 are arranged on the fixed wings 2, ailerons 8 are arranged on the power short wings 4, and a horizontal tail wing 3, a vertical tail wing 6 and an undercarriage 7 are arranged on the engine body 1. The power short wing 4 is tilted, and the rotor wing-wing conversion enables the combined type tilting wing longitudinal array variable wing counter-speed rotor aircraft to really become a high-speed helicopter capable of vertically taking off, landing and hovering, and has great significance in national economy and national defense construction.
Description
Technical Field
The invention relates to a vertical take-off and landing (VTOL) high-efficiency and high-speed aircraft.
Background
The existing fixed wing aircraft can fly forwards at a high speed, but takes off by depending on a runway. Has the loss of speed and can not vertically take off, land and hover. The helicopter has vertical take-off and landing capability, can hover in the air, does not depend on an airport, but cannot fly forwards at high speed and high efficiency. The research and development of a composite aircraft which has vertical take-off and landing capability, can hover in the air and can fly forwards at high speed and high efficiency is always the direction of the effort of the aviation industry.
The development types can be generally classified as: composite, tilting and stalling. The composite rotors can be classified into two types, one type is a conventional rotor, and the other type is an ABC rotor; the tilting type can be classified into two types, one type is wing tilting type, and the other type is rotor wing tilting type; the stall category can also be divided into two categories, one category is rotor fixing category and the other category is rotor collecting category.
Typical machine types include: x2, S-97, SB-1 from Western Spanish, Inc., of hybrid, X3 from European helicopter, Inc. Examples of the tilting type include V-22 and V-280 by Bell and X-18 by Hiller. The stop-rotation type comprises the following steps: m85 by NASA, a disk-plane by modafinil, CR/W by Boeing. The multi-rotor composite type blackdog developed in Israel is provided.
In view of the existing research and mass-produced models, the technical implementation path is compromised. At the same time of pursuing high speed, the flight efficiency is sacrificed.
The CR/W of Boeing company introduces the concept of composite variable wing (blade variable wing), but in the forward flying flight of CR/W from low speed to high speed, the realization is more complex because the single rotor wing group changes the wing and is driven by high-pressure jet. Because the single rotor wing group is adopted, the variable wing is adopted, and the operation authority is insufficient, the design concept can not be realized.
Disclosure of Invention
The utility model provides a compound type verts wing column and becomes contrary fast rotor craft of wing, its characterized in that 1 upper portion of organism is listed as and is arranged main lift rotor group 5, has arranged two pairs of convertible paddle 9 on the main lift rotor group 5, and fixed wing 2 has been arranged at 1 middle part of organism, and power short wing 4 has been arranged at fixed wing 2 both ends, has arranged aileron 8 on the power short wing 4, has arranged horizontal tail wing 3, vertical tail wing 6, undercarriage 7 on the organism 1.
The aircraft as claimed in claim 1, wherein the main lift rotor group 5 is arranged on the body 1 in a longitudinal row, and is used for bearing the main lift of the aircraft in vertical take-off and landing, hovering and cruise modes of a longitudinal helicopter, and the power short wing 4 is used for playing the auxiliary lift; and the aircraft is controlled in a tandem double-rotor helicopter mode during vertical take-off and landing, hovering and cruise in a tandem helicopter mode, and the power short wing 4 plays an auxiliary control role.
The aircraft as claimed in claim 1, wherein the two pairs of main lift rotor sets 5 arranged in the upper part of the aircraft body 1 in the longitudinal row are driven to rotate by power during vertical takeoff and landing, hovering and helicopter mode flight in the longitudinal row.
The main lift rotor set according to claim 1 and 2, characterized in that each pair of main lift rotor sets 5 is introduced with counter-speed rotor technology, two convertible blades 9 with small aspect ratio are installed, the convertible blades 9 are designed symmetrically at the front and rear edges, and the convertible blades 9 have variable total pitch and cyclic pitch.
The main lift rotor set 5 according to claim 1 is disengageable from the drive, and when the drive is disengaged, the rotating shaft can be stopped and locked by the damper, and the convertible blades 9 can be locked at 90 degrees vertical to the body 1, the total torque variation of the convertible blades 9 is zero, and the convertible blades 9 become the wings; the two pairs of longitudinal main lift rotor wing groups 5 are converted into two pairs of fixed wings to realize rotor wing-wing conversion; the two pairs of convertible blades 9 can be sweeped backwards by the converted wing through a mechanism, and the sweeped wing is changed.
The aircraft of claim 1, wherein the aircraft is configured to fly and control in a tandem twin rotor helicopter flight mode during a vertical takeoff and landing, hovering, and low speed cruise flight in the tandem twin rotor helicopter mode.
The device as claimed in claim 1, wherein the fixed wing 2 is arranged in the middle of the body 1 and is used for compensating the lift force of the forward flight.
The device as claimed in claim 1, wherein the two ends of the fixed wing 2 are provided with the power short wings 4, and the power short wings 4 can tilt upwards and vertically to generate auxiliary lift force and auxiliary control force; forward longitudinal tilting generates forward flying power.
The aircraft of claim 1, wherein the aircraft is driven by the front flying of the power short wing 4, the main lift rotor group 5 is driven to rotate by self-driving force and inflow driving force, the aircraft is in a composite flight stage of a tandem dual-rotor helicopter and a self-rotating rotor aircraft, and the flight control is cooperatively controlled by two flight control modes of the tandem dual-rotor helicopter and the tandem self-rotating dual-rotor aircraft; the incoming flow driving force gradually takes over the self-driving force of the main lift rotor set 5, the self-driving is disconnected, the main lift rotor set 5 is in an incoming flow driving state and is changed into a longitudinal autorotation dual-rotor flight mode, the main lift rotor set 5 and the fixed wings 2 keep the flight lift of the aircraft, and the aircraft enters a fixed wing aircraft and longitudinal autorotation dual-rotor flight composite flight control mode.
According to claims 1 and 9, the aircraft is completely transformed into a fixed-wing aircraft, by the main lift rotor group 5 being transformed into a fixed-wing, fixed-sweep wing, flying in fixed-wing aircraft mode.
The aircraft as claimed in claim 1, wherein the aircraft can rotate, glide and land under the action of the incoming flow after losing power due to the autorotation characteristic of the aircraft under the action of the incoming flow; the rollable landing gear 7 can be driven by the power wing 4 to take off and land when the rollable landing gear has a rollable landing condition.
The combined type tilting wing longitudinal variable wing counter-speed rotor craft as claimed in claim 1, wherein the combined type tilting wing longitudinal variable wing counter-speed rotor craft adopts a distributed power design, and the main lift rotor set 5 and the power short wing 4 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set 5 is driven by electric power, the power short wing 4 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set 5 during vertical take-off and landing, hovering and multi-rotor mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.
The beneficial effects are that:
1. introduction of counter-speed rotor rvr (reverse vector rotor): the RVR (reverse vector rotor) rotor adopts a symmetrical wing type design, introduces the autorotation of the rotor, adopts a mechanism of reducing the rotating speed of the rotor and adds forward thrust to reduce the load of a paddle and expand a performance envelope, and can overcome the problems on the traditional helicopter. 1. The influence of air compressibility is reduced by reducing the rotor speed 2. the stall of the retreating blade is delayed by the symmetrical wing profile and the high-order harmonic control 3. the tip/accident interference noise is avoided 4. the tip vortex and the interference generated by the tip vortex and the airframe are avoided. ".
2. The load efficiency and the control redundancy of the aircraft can be effectively improved by adopting the power short wing capable of tilting; the power system and the short wing are integrally tilted, so that the disturbance of the power system and the wings can be reduced, and the flying efficiency is improved.
3. Introduction of tandem dual rotors: the tandem double-rotor layout solves the reaction torque, and compared with the jet driving of M85 of CR/W, NASA of Boeing company, the circulation control technology simplifies the driving and control modes; due to the longitudinal arrangement, the disturbance is symmetrical when the rotor is stopped and the wings are changed, and the problem of insufficient control authority of the existing stalling design is solved.
4. The introduction of the double-rotation rotor technology and the distributed power and the hybrid power: 1. the problem of using traditional power mode to require to many drives is solved, can conveniently realize rotor variable speed, stall, simple structure. 2. The vertical take-off and landing and hovering of the aircraft are realized. 3. The forward and backward traveling stall of the high-speed forward flight is delayed, and the flight efficiency is greatly improved. 4. Because the proportion of the landing, hovering and helicopter mode cruising time in the line-by-line tasks of the aircraft is lower, and the waste weight of the power storage system is lower than that of a full-electric drive aircraft, a new approach is created for the full-electrochemical and hybrid power application of an aircraft power system. 5. Because the aircraft has the characteristics of incoming flow driving, the aircraft can rotate, slide down and land after losing power, can slide and take off under the condition of sliding and taking off, and greatly improves the load efficiency.
The rotor-wing conversion enables the composite type tilting wing longitudinal variable wing counter-speed rotor aircraft to really become a high-speed helicopter capable of vertically taking off, landing and hovering, and has great significance in national economy and national defense construction.
Description of the drawings.
FIG. 1 is a vertical take-off and landing, hovering side view.
Fig. 2 shows a side view of a dual rotor wing in forward flight.
Fig. 3 is a front flying side view of the straightening vane.
Fig. 4 is a front flying side view of the variable sweep wing.
In the accompanying fig. 1-4: 1-body; 2-fixed wings; 3-horizontal tail wing; 4-power short wing; 5-a main lift rotor set; 6-vertical tail; 7-a landing gear; 8, an aileron; 9-convertible paddle.
And (5) implementing the method.
As shown in fig. 1-4, two main lift rotor sets 5 are arranged in front-back longitudinal rows on the upper portion of a compound tilt wing longitudinal row variable wing counter-speed rotorcraft body 1. The main lift rotor wing group 5 has the functions of changing total distance and periodic distance, the rotating directions of the front rotor wing and the rear rotor wing are opposite, and the front rotor wing and the rear rotor wing can overcome reaction torque; the main lift rotor wing group 5 has the functions of damping stall of a main driving shaft, positioning locking and power disconnection; the convertible paddle 9 is converted into a fixed wing, and the backward sweeping function can be selected and designed.
Two pairs of convertible blades 9 with small aspect ratio are arranged on the main lift Rotor set 5, a counter-speed Rotor (RVR-Reverse vector Rotor) technology is introduced, and the wing profiles are symmetrical at the front edge and the rear edge.
Fixed wing 2 has been arranged at combined type wing vertical counter-speed variable wing aircraft organism 1 middle part that verts, and fixed wing 2, fixed wing 2 both ends are arranged there is power stub 4, have arranged aileron 8 on the power stub 4, and power stub 4 can upwards vertically vert, vertically verts forward.
The main lift rotor set 5 is driven by independent power to provide main lift and control force when vertically taking off and landing, hovering and flying at low speed, and the power short wing 4 vertically tilts upwards to generate auxiliary lift and auxiliary control force.
When flying forwards, the power short wing 4 longitudinally tilts forwards to provide forward power, the flying speed is gradually increased, the lift force of the fixed wing 2 is gradually increased, the driving power of the main lift rotor wing set 5 is gradually replaced by the flow driving power, and the aircraft performs compound flight and control mode conversion to the fixed wing aircraft and the double-autorotation rotor aircraft. At the moment, the aircraft flies forward and is controlled in a combined mode of a fixed wing aircraft and a self-rotating rotor aircraft.
In order to further increase the flying speed, the total distance can be changed to zero through the function of changing the distance, the main driving shaft stops rotating in a damping mode, the positioning locking mode and the main driving shaft stops rotating and is locked, and the convertible paddle 9 is locked at the position 90 degrees vertical to the machine body 1. At the moment, the main lift rotor wing group 5 is changed into two fixed wings which are connected with the middle fixed wing in series, the aircraft completely flies at high speed in a fixed wing aircraft mode, and the aircraft is controlled through the ailerons 8, the vertical tail wing 6 and the parallel tail wing 3.
In order to enable the aircraft to fly at a higher speed, the convertible blades 9 can be designed to have a backswept function, and the backswept of the convertible blades 9 can further improve the lift-drag ratio of the aircraft and realize supersonic flight.
Because aircraft main lift rotor group 5 has the self-rotation characteristic under the incoming current, when losing power, usable its rotation gliding characteristic, the rotation gliding is safe to be descended.
When the runway take-off and landing condition is met, the power short wing 4 provides forward power, the main lift rotor group 5 can rotate in a rotor mode or change the wing into a fixed wing, and the aircraft can take off and land in a runway way.
The combined type tilting wing longitudinal variable wing counter-speed rotor aircraft adopts a distributed power design, and a main lift rotor wing group 5 and a power short wing 4 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set 5 is driven by electric power, the power short wing 4 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set 5 during vertical take-off and landing, hovering and multi-rotor mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.
Claims (12)
1. The utility model provides a compound type verts wing column and becomes contrary fast rotor craft of wing, its characterized in that 1 upper portion of organism is listed as and is arranged main lift rotor group 5, has arranged two pairs of convertible paddle 9 on the main lift rotor group 5, and fixed wing 2 has been arranged at 1 middle part of organism, and power short wing 4 has been arranged at fixed wing 2 both ends, has arranged aileron 8 on the power short wing 4, has arranged horizontal tail wing 3, vertical tail wing 6, undercarriage 7 on the organism 1.
2. The aircraft as claimed in claim 1, wherein the main lift rotor group 5 is arranged on the body 1 in a longitudinal row, and is used for bearing the main lift of the aircraft in vertical take-off and landing, hovering and cruise modes of a longitudinal helicopter, and the power short wing 4 is used for playing the auxiliary lift; and the aircraft is controlled in a tandem double-rotor helicopter mode during vertical take-off and landing, hovering and cruise in a tandem helicopter mode, and the power short wing 4 plays an auxiliary control role.
3. The aircraft as claimed in claim 1, wherein the two pairs of main lift rotor sets 5 arranged in the upper part of the aircraft body 1 in the longitudinal row are driven to rotate by power during vertical takeoff and landing, hovering and helicopter mode flight in the longitudinal row.
4. The main lift rotor set according to claim 1 and 2, characterized in that each pair of main lift rotor sets 5 is introduced with counter-speed rotor technology, two convertible blades 9 with small aspect ratio are installed, the convertible blades 9 are designed symmetrically at the front and rear edges, and the convertible blades 9 have variable total pitch and cyclic pitch.
5. The main lift rotor set 5 according to claim 1 is disengageable from the drive, and when the drive is disengaged, the rotating shaft can be stopped and locked by the damper, and the convertible blades 9 can be locked at 90 degrees vertical to the body 1, the total torque variation of the convertible blades 9 is zero, and the convertible blades 9 become the wings; the two pairs of longitudinal main lift rotor wing groups 5 are converted into two pairs of fixed wings to realize rotor wing-wing conversion; the two pairs of convertible blades 9 can be sweeped backwards by the converted wing through a mechanism, and the sweeped wing is changed.
6. The aircraft of claim 1, wherein the aircraft is configured to fly and control in a tandem twin rotor helicopter flight mode during a vertical takeoff and landing, hovering, and low speed cruise flight in the tandem twin rotor helicopter mode.
7. The device as claimed in claim 1, wherein the fixed wing 2 is arranged in the middle of the body 1 and is used for compensating the lift force of the forward flight.
8. The device as claimed in claim 1, wherein the two ends of the fixed wing 2 are provided with the power short wings 4, and the power short wings 4 can tilt upwards and vertically to generate auxiliary lift force and auxiliary control force; forward longitudinal tilting generates forward flying power.
9. The aircraft of claim 1, wherein the aircraft is driven by the front flying of the power short wing 4, the main lift rotor group 5 is driven to rotate by self-driving force and inflow driving force, the aircraft is in a composite flight stage of a tandem dual-rotor helicopter and a self-rotating rotor aircraft, and the flight control is cooperatively controlled by two flight control modes of the tandem dual-rotor helicopter and the tandem self-rotating dual-rotor aircraft; the incoming flow driving force gradually takes over the self-driving force of the main lift rotor set 5, the self-driving is disconnected, the main lift rotor set 5 is in an incoming flow driving state and is changed into a longitudinal autorotation dual-rotor flight mode, the main lift rotor set 5 and the fixed wings 2 keep the flight lift of the aircraft, and the aircraft enters a fixed wing aircraft and longitudinal autorotation dual-rotor flight composite flight control mode.
10. According to claims 1 and 9, the aircraft is completely transformed into a fixed-wing aircraft, by the main lift rotor group 5 being transformed into a fixed-wing, fixed-sweep wing, flying in fixed-wing aircraft mode.
11. The aircraft as claimed in claim 1, wherein the aircraft can rotate, glide and land under the action of the incoming flow after losing power due to the autorotation characteristic of the aircraft under the action of the incoming flow; the rollable landing gear 7 can be driven by the power wing 4 to take off and land when the rollable landing gear has a rollable landing condition.
12. The combined type tilting wing longitudinal variable wing counter-speed rotor craft as claimed in claim 1, wherein the combined type tilting wing longitudinal variable wing counter-speed rotor craft adopts a distributed power design, and the main lift rotor set 5 and the power short wing 4 are driven independently; the device can be driven by full electric power or hybrid power; the full-power drive is powered by the energy storage system, or the power generation system and the energy storage system are powered in a mixed mode; the hybrid power drive is that the main lift rotor wing set 5 is driven by electric power, the power short wing 4 is driven by the power of traditional fuel and drives the power generation system to supplement the electric energy to the energy storage system, so as to supplement the electric energy consumption of the main lift rotor wing set 5 during vertical take-off and landing, hovering and multi-rotor mode cruise; the energy storage system can also adopt a driving system of the main lift rotor set 5 to be designed into a driving and power generation integrated system, and when the aircraft flies in a rotation rotor mode, power is generated to supplement electric energy to the energy storage system.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910479481.1A CN112027074A (en) | 2019-06-04 | 2019-06-04 | Combined type tilting wing longitudinal wing-changing counter-speed rotor aircraft |
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| CN201910479481.1A CN112027074A (en) | 2019-06-04 | 2019-06-04 | Combined type tilting wing longitudinal wing-changing counter-speed rotor aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455670A (en) * | 2020-12-09 | 2021-03-09 | 杭州巨泳科技有限公司 | Flight control method of full-motion wing aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112455670A (en) * | 2020-12-09 | 2021-03-09 | 杭州巨泳科技有限公司 | Flight control method of full-motion wing aircraft |
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Application publication date: 20201204 |