CN110901906B - Ground effect rotor craft and flight mode switching method - Google Patents
Ground effect rotor craft and flight mode switching method Download PDFInfo
- Publication number
- CN110901906B CN110901906B CN201911228262.2A CN201911228262A CN110901906B CN 110901906 B CN110901906 B CN 110901906B CN 201911228262 A CN201911228262 A CN 201911228262A CN 110901906 B CN110901906 B CN 110901906B
- Authority
- CN
- China
- Prior art keywords
- ground effect
- wing
- rotorcraft
- flight
- rotors
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000000694 effects Effects 0.000 title claims abstract description 173
- 238000000034 method Methods 0.000 title claims description 8
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 230000007704 transition Effects 0.000 claims description 15
- 230000004927 fusion Effects 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 6
- 230000002708 enhancing effect Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000007789 sealing Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention belongs to the technology of vertical take-off and landing aircrafts, and particularly relates to a rotor wing aircraft for improving cruising lift-drag ratio and cruising speed by using a ground effect principle. The ground effect rotorcraft comprises a fuselage (1), a rotor system (2), a ground effect wing (3), a side end plate (4), a tail wing (5), an engine (22) and a transmission and tilting system (23). The ground effect wings are symmetrically arranged on two sides of the fuselage, the side end plates are respectively arranged on the outer sides of the low effect wings, the tail wing is positioned at the rear of the fuselage, at least 2 pairs of rotor systems (2) are symmetrically arranged on the tail wing and the side end plates respectively, and the engine (22) is connected with the transmission and tilting system (23) and is connected with the rotor systems (2). The ground effect rotorcraft combines the advantages of the rotorcraft and the ground effect rotorcraft, has a vertical take-off and landing function, and can obtain a larger lift-drag ratio, so that the rotorcraft obtains a larger range and cruising speed, and the application scene and the function of the rotorcraft are effectively improved.
Description
Technical Field
The invention belongs to the ground aircraft technology, and particularly relates to a rotor aircraft for improving cruising lift-drag ratio and cruising speed by using a ground effect principle.
Background
At present, the traditional rotor craft represented by the helicopter generally has the defects of low flying speed and short range, the biggest limiting factor is small lift-drag ratio, the lift-drag ratio of the traditional helicopter is more between 3 and 8, the cruising speed is more about 250km/h, and the range is 300 to 500km; the lift-drag ratio of the tiltrotor aircraft represented by V-22 'hawk' is only between 10 and 12, the cruising speed is about 500km/h, and the range is about 650 km.
The traditional ground effect aircraft has the advantages of high cruising speed and long voyage, but cannot realize vertical take-off and landing, can only take-off and land on the sea, and is difficult to take-off and land on land and ships, so that the practical use is limited greatly, and the application occasions are limited.
US20040244331 discloses a method and apparatus for tiltrotor aircraft flight control which also enables tiltrotor-controlled flights, but which is tilted entirely, and in which the wing is a conventional wing, with low ground effect utilization
Disclosure of Invention
The purpose of the invention is that: the ground effect rotor craft has the advantages of high cruising speed, large range and capability of realizing vertical take-off and landing.
The technical scheme of the invention is as follows: the ground effect rotorcraft comprises a fuselage 1, a rotor system 2, ground effect wings 3, side end plates 4, tail wings 5, an engine 22 and a transmission and tilting system 23, wherein the ground effect wings are symmetrically arranged on two sides of the fuselage, the side end plates are respectively arranged on the outer sides of the low effect wings, the tail wings are positioned at the rear of the fuselage, at least 2 pairs of rotor systems 2 are respectively symmetrically arranged on the tail wings and the side end plates, and the engine 22 is connected with the transmission and tilting system 23 and is connected with the rotor system 2.
The ground effect wing 3 is connected with the fuselage 1 in a fusion way and is arranged in a forward-swept way and used for providing the lift force required by the whole aircraft during forward flight.
The ground effect wing adopts high lift wing section, large torsion and small aspect ratio aerodynamic layout design, and structurally integrates with the fuselage 1 and the side end plate 4,
the ground effect wing adopts a large front edge radius, the relative thickness range of the wing section middle section is 10% -15%, and the lift-drag ratio can be improved by 50% -100% by utilizing the ground effect;
the torsion difference range of the installation angle of the wing tip wing profile and the installation angle of the wing root wing profile is-40 degrees to-60 degrees, so that the ground effect can be effectively enhanced, and the lift-drag ratio of the ground effect wing is improved by 20% -30%;
the range of the small aspect ratio of the ground effect wing is 5-8, so that the ground effect of the ground effect wing can be effectively improved, and the aerodynamic efficiency of the ground effect wing at low speed is improved.
The ground effect wing trailing edge is arranged with a flap 301 for roll manipulation and sealing of the ground effect chamber during forward flight to enhance ground effect.
The side end plate 4 is symmetrically arranged at the wing tip part of the ground effect wing 3 along the longitudinal symmetrical plane of the machine body, is fixedly connected with the ground effect wing, and is divided into a side end plate upper end 41 and a side end plate lower end 42.
The upper end 41 of the side end plate is located on the upper surface of the ground effect wing 3, and the top is used for fixing the rotor system 2.
The lower end 42 of the side end plate is positioned on the lower surface of the ground effect wing 3, forms a ground effect chamber with the ground effect wing 3 and is used as a pontoon.
The tail wing 5 is positioned at the rear part of the machine body 1 and comprises a horizontal tail 51 and a vertical tail 52; the horizontal tails are arranged at the top ends of the vertical tails, the vertical tails 52 are double vertical tails, and are fixedly connected with the machine body 1 in a fusion mode.
Each trailing vertical edge is provided with a rudder 521.
The horizontal tail 51 is arranged on top of the vertical tail 52 and fixedly connected with the vertical tail 52, wherein the rear edge is provided with an elevator 511.
In the vertical take-off and landing flight state, all the rotors are positioned in the approximately vertical direction, and the flight height is not separated from the ground effect height of the rotors.
In the forward flight state, all the rotors are positioned in the approximately horizontal direction, and the flight height is not separated from the ground effect wing action height.
In the forward flight condition, the rotor downstream at the front edge of the side end plate can partially blow into the ground effect chamber, and the ground effect of the ground effect wing is enhanced.
In the forward flying state, the rotor wing down-wash part positioned at the front edge of the horizontal tail blows through the horizontal tail, so that the lifting force of the horizontal tail is increased.
The ground effect rotorcraft has two main modes of flight, a helicopter mode and a ground effect flight mode.
The ground effect rotorcraft has a helicopter flight mode in which rotors 21 provide primary lift and control, with collective pitch variation of four pairs of rotors 21 controlling their lift and yaw attitude, with collective pitch difference of the front two pairs of rotors 21 and the rear two pairs of rotors 21 controlling the pitch attitude, and with collective pitch difference of the left two pairs of rotors 21 and the right two pairs of rotors 21 controlling the roll attitude.
The ground effect rotorcraft has a ground effect flight mode in which lift is provided by the ground effect wing 3 in a ground effect state, roll attitude is controlled by the aileron 301, pitch attitude is controlled by the elevator 511, and yaw attitude is controlled by the rudder 521.
The ground effect rotorcraft has two flight mode switching methods, namely a transition from a helicopter mode to a ground effect flight mode and a transition from a ground effect flight mode to a helicopter mode in a 'ground effect off' mode.
When the helicopter mode is transited to the ground effect flight mode, the helicopter reduces the flight altitude to enable the ground effect wings 3 to capture the ground effect area, firstly, the tail two rotary wings 21 tilt forward to improve the forward flight speed, and after the ground effect wings 3 start to obtain enough lift force, the front two rotary wings 21 start to tilt forward to realize the flight mode switching.
According to the flight mode switching method realized on the basis of the ground effect rotor craft, when the ground effect flight mode is switched from the ground effect mode to the helicopter mode, the front two rotors 21 tilt backwards firstly so as to improve the flight height, and when the lift force of the ground effect wing 3 is reduced, the tail two rotors 21 start to tilt backwards so as to realize the flight mode switching.
The invention has the beneficial effects that: the ground effect rotorcraft combines the advantages of the rotorcraft and the ground effect rotorcraft, and can realize vertical take-off and landing and high-speed ground effect flight by controlling the tilting of the rotor, so that the rotorcraft can obtain larger lift-drag ratio while having the vertical take-off and landing function, so that the rotorcraft obtains larger range and cruising speed, and the application scene and function of the rotorcraft are effectively improved.
Drawings
FIG. 1 is an isometric view of a ground effect rotorcraft in a low vertical takeoff, landing and hover state provided by an embodiment of the present invention;
FIG. 2 is a top view of a ground effect rotorcraft in a low vertical takeoff, landing and hover state provided by an embodiment of the present invention;
FIG. 3 is a front view of a ground effect rotorcraft in a low vertical takeoff, landing and hover state provided by an embodiment of the present invention;
FIG. 4 is an isometric view of a ground effect rotorcraft in a forward flight configuration, according to an embodiment of the present invention;
FIG. 5 is a schematic view of a rotor when vertical;
FIG. 6 is a schematic view of a rotor with the rotor horizontal;
FIG. 7 is a schematic illustration of ground effect rotorcraft range versus altitude for an embodiment of the present invention;
the labels in the figure are respectively:
a body 1; a rotor system 2; a rotor 21; an engine 22; a transmission and tilting system 23; a ground effect wing 3; a flap 301; a side end plate 4; a side endplate upper end 41; a side endplate lower end 42; a tail 5; a horizontal tail 51; a vertical tail 52; elevator 511; rudder 521.
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.
Referring to fig. 1 to 4, a ground effect rotorcraft according to an embodiment of the present invention is shown. The ground effect rotorcraft comprises a fuselage 1, a pair of rotor systems 2, a ground effect wing 3, a side end plate 4 and a tail wing 5. The shape of the machine body 1 is streamline, and the machine body is fixedly connected with the ground effect wing 3 and the tail wing 5 in a fusion mode. The side end plates 4 are symmetrically arranged at the wing tip parts of the ground effect wings 3 along the longitudinal symmetrical plane of the machine body and are divided into upper ends 41 and lower ends 42 of the side end plates. The tail wing 5 is positioned at the rear part of the machine body 1 and comprises a horizontal tail 51 and a vertical tail 52, and the horizontal tail 51 is positioned above the vertical tail 52. The pair of rotor systems 2 are arranged at the top of the side end plate upper end 41 and at the tips of the horizontal tails 51, respectively.
The rotor system 2 comprises a rotor 21, an engine 22 and a transmission and tilting system 23, wherein the rotor 21 is connected with the transmission and tilting system 23, and the transmission and tilting system 23 is connected with the engine 22 through a rotating shaft. The engine 22 drives the transmission and tilting system 23, and the transmission and tilting system 23 is fixedly arranged at the upper part of the side end plate 4 and is used for changing the rotating speed and direction of the rotor wing 21, converting mechanical energy into air kinetic energy and generating lifting force. Wherein, the engine 22 and the transmission and tilting system 23 are fixed on the side end plate 4, and the main body is kept unchanged when the rotor 21 tilts, and the tilting control of the rotor 21 is realized through an internal gear transmission steering mechanism.
The transmission and tilting system 23 is internally provided with a tilting steering transmission mechanism, tilting is realized through the tilting mechanism, and rotation conversion in the horizontal and vertical directions is realized through a steering gear. Referring to fig. 5 and 6, the rotor 21 is driven to tilt between approximately horizontal and approximately vertical directions by tilting the internal transmission structure of the transmission and tilting system 23. When rotor 21 is in an approximately vertical direction, rotor 21 acts as a lift paddle to provide lift and attitude steering forces for the full-aircraft vertical take-off and landing and hover low-speed flight; when rotor 21 is in a nearly horizontal orientation, rotor 21 acts as a propeller to provide power for the full aircraft forward flight.
The ground effect wing is a high-lift wing type, and simultaneously, the ground effect wing is matched with a rotor wing system, so that the ground effect wing adopts a large front edge radius, the relative thickness range of the middle section of the wing is 10% -15%, and the lift-drag ratio can be improved by 50% -100% by utilizing the ground effect.
The torsion difference range of the installation angle of the wing tip wing profile and the installation angle of the wing root wing profile is-40 degrees to-60 degrees, so that the ground effect can be effectively enhanced, and the lift-drag ratio of the ground effect wing is improved by 20% -30%.
The range of the small aspect ratio of the ground effect wing is 5-8, so that the ground effect of the ground effect wing can be effectively improved, and the aerodynamic efficiency of the ground effect wing at low speed is improved.
Therefore, the ground effect wing can provide enough lift force required by the whole aircraft when flying forwards, and quick ground effect flying is realized.
In addition, a flap 301 is arranged on the ground effect wing for roll manipulation and sealing of the ground effect chamber in forward flight to enhance ground effect.
As shown in fig. 3, the upper end 41 of the side end plate is located on the upper surface of the ground effect wing 3, the top is used for fixing the rotor system 2, the lower end 42 of the side end plate is located on the lower surface of the ground effect wing 3, and forms a ground effect chamber with the ground effect wing 3, so as to enhance the ground effect when flying forward. Meanwhile, the lower end 42 of the side end plate can be of a cavity structure, and therefore can serve as a pontoon for keeping the whole machine transversely stable when floating and sliding on the water surface.
The upper end 41 of the side end plate has a small front edge radius and a relative thickness range of 10-12%, and is symmetrical for reducing forward flight resistance.
As shown in fig. 4, the vertical fin 52 is a V-shaped double vertical fin in this embodiment, and is fixedly connected with the fuselage 1 in a fusion manner, and a rudder 521 is disposed at the rear edge of each vertical fin, so as to maintain the heading stability and generate a heading manipulation force in the forward flight state; the horizontal tail 51 is disposed on top of the vertical tail 52 and fixedly connected to the vertical tail 52, wherein an elevator 511 is provided at the central rear edge for maintaining lateral stability and generating pitch manipulation force in a forward flying state.
The flight modes of the 'ground effect' rotor craft provided by the embodiment of the invention are divided into three types: helicopter flight mode, transition flight mode and ground effect flight mode.
In the four-rotor helicopter flight mode, the rotors 21 provide the main lift and control, the lift and yaw attitude of the four-pair rotors 21 are controlled by the collective pitch variation of the four-pair rotors 21, the pitch attitude of the aircraft is controlled by the collective pitch difference of the front two pairs of rotors 21 and the rear two pairs of rotors 21, the roll attitude is controlled by the collective pitch difference of the left two pairs of rotors 21 and the right two pairs of rotors 21, and after the four-rotor state takes off to reach the required speed and height, the rotors 21 start to tilt and transition to the transitional state.
The transition state flight mode mainly comprises two modes, namely a transition from a helicopter mode to a ground effect flight mode and a transition from the ground effect flight mode to the helicopter mode in a 'ground effect disengaging' mode. The first transition helicopter reduces the flying height so that the ground effect wing 3 captures the ground effect area, firstly, the tail two rotors 21 tilt forwards to improve the forward flying speed, and after the ground effect wing 3 starts to obtain enough lift force, the front two rotors 21 start to tilt forwards to realize stable transition; in the second transition state, the front two rotors 21 tilt backward first to increase the flying height, and when the lift force of the ground effect wing 3 is reduced, the rear two rotors 21 start to tilt backward to realize stable transition. The transitional flight state attitude maneuver is maneuvered by the rotor 21 and flaperon 301, elevator 511, rudder 521 in combination.
In the ground effect flight state, lift is provided by the ground effect wing 3 in the ground effect state, the roll attitude is controlled by the flap wing 301, the pitch attitude is controlled by the elevator 511, and the yaw attitude is controlled by the rudder 521. The flight mode is mainly used for cruising flight in a ground effect area.
The ground effect rotor craft combines the vertical flight of the rotor and the ground effect, effectively improves the performance of the craft, and particularly can greatly improve the lift-drag ratio of the rotor craft under the function of realizing vertical take-off and landing.
(1) Cruise flight can increase the lift-drag ratio of the rotorcraft by utilizing the ground effect of the ground effect wings, thereby improving the range of the rotorcraft. The following table shows that the lift-drag ratio of the whole rotorcraft is obviously improved.
All-aircraft lift-drag ratio comparison of various rotor aircraft
| Category(s) | Lift-drag ratio of |
| Helicopter | |
| 3～8 | |
| |
10～12 |
| The |
15～20 |
Referring to fig. 7, a 20 ton range versus altitude curve of the rotorcraft is shown, and it can be seen that the range of the rotorcraft is greatly affected by the altitude, and the altitude is mainly determined by sea conditions. The optimal cruising speed is suitable for sea conditions below three stages. The range of the sea condition under three stages can reach more than 1000 km.
(2) Rotor power may be more useful for forward speed increases in forward flight conditions due to lift-drag ratio increases.
Comparing the rotorcraft performance estimation with each other equipped platform
| Weight of take-off kg | Load kg | Cruising speed km/h | Course km | |
| Tilt rotor aircraft | 23000 | 4600 | 510 | 600 |
| Ground effect rotor craft | 23000 | 4600 | 500 | 1500 |
| Ground effect aircraft | 23000 | 4600 | 400 | 1500 |
| Fixed wing aircraft | 21000 | 4500 | 500 | 1000 |
(3) The rotor craft has the vertical take-off and landing characteristics of the helicopter, so that amphibious landing of complex terrain can be met. In addition, the aircraft can also fly in land effect on flat grasslands, deserts, highways, inland lakes and other terrains, so that the application range is expanded;
(4) Under the same tonnage and same loading condition, the range of the rotor craft is nearly twice that of the rotor craft and is equivalent to that of a fixed-wing aircraft, so that the rotor craft can be used for long-distance and point-to-point transportation and vertical supply in open sea when being expanded into a large-scale craft.
The foregoing is merely a detailed description of the invention, which is not a matter of routine skill in the art. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (18)
1. The ground effect rotorcraft is characterized by comprising a fuselage (1), a rotor system (2), ground effect wings (3), side end plates (4), tail wings (5), an engine (22) and a transmission and tilting system (23), wherein the ground effect wings are symmetrically arranged on two sides of the fuselage, the side end plates are respectively arranged on the outer sides of the low effect wings, the tail wings are positioned behind the fuselage, at least 2 pairs of rotor systems (2) are respectively and symmetrically arranged on the tail wings and the side end plates, and the engine (22) is connected with the transmission and tilting system (23) and is connected with the rotor system (2);
the ground effect wing (3) is in fusion connection with the fuselage (1) and is arranged in a forward-swept manner and is used for providing lift force required by the whole aircraft during forward flight;
the ground effect wing adopts a high lift wing profile, large torsion and small aspect ratio pneumatic layout design, and is structurally integrated with the machine body (1) and the side end plate (4), wherein the ground effect wing adopts a large front edge radius, the relative thickness range of the wing profile middle section is 10% -15%, and the lift-drag ratio can be improved by 50% -100% by utilizing the ground effect; the torsion difference range of the installation angle of the wing tip wing profile and the installation angle of the wing root wing profile is-40 degrees to-60 degrees, so that the ground effect can be effectively enhanced, and the lift-drag ratio of the ground effect wing is improved by 20% -30%; the range of the small aspect ratio of the ground effect wing is 5-8, so that the ground effect of the ground effect wing can be effectively improved, and the aerodynamic efficiency of the ground effect wing at low speed is improved.
2. Ground effect rotorcraft according to claim 1, characterized in that the ground effect wing trailing edge is arranged with a flap (301) for roll manipulation and closure of the ground effect chamber in front flight to enhance ground effect.
3. The ground effect rotorcraft according to claim 1, wherein the side end plates (4) are symmetrically arranged at the wing tip parts of the ground effect wings (3) along the longitudinal symmetry plane of the fuselage, and are fixedly connected with the ground effect wings, and are divided into two parts, namely an upper end (41) of the side end plate and a lower end (42) of the side end plate.
4. A ground effect rotorcraft according to claim 3, characterized in that the upper end (41) of the side end plate is located on the upper surface of the ground effect wing (3), the top being used for fixing the rotor system (2).
5. The ground effect rotorcraft of claim 4, wherein the side end plate lower end (42) is located on the lower surface of the ground effect wing (3), forms a ground effect chamber with the ground effect wing (3), and acts as a pontoon.
6. The ground effect rotorcraft of claim 1, wherein the tail wing (5) is located aft of the fuselage (1) and comprises a horizontal tail (51) and a vertical tail (52); the horizontal tails are arranged at the top ends of the vertical tails, the vertical tails (52) are double vertical tails and are in fusion fixed connection with the machine body (1).
7. The ground effect rotorcraft of claim 6, wherein each trailing edge is provided with a rudder (521).
8. The ground effect rotorcraft of claim 7, wherein the horizontal tail (51) is disposed atop the vertical tail (52) in fixed connection with the vertical tail (52), and wherein the trailing edge is provided with an elevator (511).
9. The ground effect rotorcraft of claim 1, wherein in a vertical take-off and landing flight condition, all rotors are in approximately vertical orientation and the flying altitude does not depart from the ground effect altitude of the rotors.
10. The ground effect rotorcraft of claim 1, wherein in the forward flight condition all rotors are in an approximately horizontal orientation and the flying altitude does not depart from the ground effect wing altitude.
11. The ground effect rotorcraft of claim 2, wherein in a forward flight condition, rotor downflow at the leading edge of the side end plates partially blows into the ground effect chamber, enhancing the ground effect of the ground effect wings.
12. The ground effect rotorcraft of claim 1, wherein in the forward flight condition, the downwash portion of the rotor at the leading edge of the tailback blows across the tailback to increase tailback lift.
13. Ground effect rotorcraft according to any one of claims 1 to 12, characterized by two main modes of flight, a helicopter mode and a ground effect mode of flight.
14. The ground effect rotorcraft of claim 13, having a helicopter flight mode in which the rotors (21) provide primary lift and control, with collective pitch transitions of four pairs of rotors (21) controlling their lift and yaw attitude, the collective pitch difference of the front two pairs of rotors (21) and the rear two pairs of rotors (21) controlling the pitch attitude of the aircraft, and the collective pitch difference of the left two pairs of rotors (21) and the right two pairs of rotors (21) controlling the roll attitude.
15. The ground effect rotorcraft of claim 13, having a ground effect flight mode in which lift is provided by the ground effect wing (3) in ground effect, roll attitude is controlled by the flap (301), pitch attitude is controlled by the elevator (511), yaw attitude is controlled by the rudder (521).
16. The ground effect rotorcraft of claim 13, wherein there are two modes of flight switching methods, a transition from helicopter mode to ground effect flight mode and a transition from ground effect flight mode "off ground effect" to helicopter mode.
17. A method of switching modes of flight implemented on the basis of a ground effect rotorcraft according to claim 13, characterized in that when transitioning from helicopter mode to ground effect mode of flight, the helicopter is lowered in flight altitude so that the ground effect wing (3) captures the ground effect area, first the tail two rotors (21) are tilted forward to increase the forward flight speed, and after the ground effect wing (3) begins to acquire sufficient lift, the front two rotors (21) begin to tilt forward, thereby implementing the mode of flight switching.
18. A method of switching modes of flight based on the ground effect rotorcraft according to claim 13, characterized in that when the transition from ground effect mode "off ground effect" to helicopter mode is made, the front two rotors (21) tilt backward first to increase the flight altitude, and when the lift of the ground effect wing (3) is reduced, the rear two rotors (21) start to tilt backward to switch modes of flight.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228262.2A CN110901906B (en) | 2019-12-04 | 2019-12-04 | Ground effect rotor craft and flight mode switching method |
| PCT/CN2020/000187 WO2021109311A1 (en) | 2019-12-04 | 2020-08-24 | Ground effect based rotorcraft and flight mode switching control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911228262.2A CN110901906B (en) | 2019-12-04 | 2019-12-04 | Ground effect rotor craft and flight mode switching method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110901906A CN110901906A (en) | 2020-03-24 |
| CN110901906B true CN110901906B (en) | 2023-04-25 |
Family
ID=69822061
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911228262.2A Active CN110901906B (en) | 2019-12-04 | 2019-12-04 | Ground effect rotor craft and flight mode switching method |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN110901906B (en) |
| WO (1) | WO2021109311A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901906B (en) * | 2019-12-04 | 2023-04-25 | 中国直升机设计研究所 | Ground effect rotor craft and flight mode switching method |
| NL2026721B1 (en) | 2020-10-21 | 2022-06-16 | Erdem Kazakli Ahmet | An amphibious flight vehicle |
| CN112744352B (en) * | 2021-02-07 | 2022-03-15 | 之江实验室 | Distributed tilting multi-rotor aircraft and flight control method |
| CN113093807B (en) * | 2021-04-07 | 2022-06-21 | 中国船舶科学研究中心 | Ground effect flight control device of unmanned ground effect wing ship |
| CN114212252B (en) * | 2021-06-18 | 2024-02-02 | 上海飞机制造有限公司 | Tandem type tilting wing aircraft and control method |
| CN113277062B (en) * | 2021-06-29 | 2024-08-06 | 长春长光博翔无人机有限公司 | Aircraft and control method thereof |
| CN116443243A (en) * | 2023-04-27 | 2023-07-18 | 中国直升机设计研究所 | A tilt-rotor aircraft and its control method |
| CN117874906B (en) * | 2023-12-15 | 2025-01-07 | 南京航空航天大学 | Construction method of three-dimensional tilting corridor of four-tilting rotor unmanned aerial vehicle |
| CN118965592A (en) * | 2024-08-29 | 2024-11-15 | 蔚蓝空间飞行器有限公司 | Method, device, storage medium and electronic equipment for determining design parameters of tilt-rotor aircraft |
| CN119796490A (en) * | 2025-01-20 | 2025-04-11 | 中科天驰航空科技(烟台)有限公司 | Tilt-rotor aircraft and control method thereof |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2457457A (en) * | 2008-02-13 | 2009-08-19 | Proost Raymond Guido Marie-Jea | A ground effect craft having height stability and pitch stability |
| CN202244080U (en) * | 2011-01-12 | 2012-05-30 | 中国高科集团有限公司 | Ground effect aircraft |
| CN103192989B (en) * | 2013-04-08 | 2016-08-24 | 孙亮 | Land ground effect vehicle |
| US9889927B2 (en) * | 2014-02-06 | 2018-02-13 | Bell Helicopter Textron Inc. | Variable hub-to-hub phasing rotor system |
| US10625852B2 (en) * | 2014-03-18 | 2020-04-21 | Joby Aero, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| CN104554722A (en) * | 2015-01-12 | 2015-04-29 | 章伟义 | Offshore three-wing-surface type B ground-effect wing ship |
| CN204726654U (en) * | 2015-05-08 | 2015-10-28 | 汤旭 | A kind of maple leaf formula ground effect vehicle |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN108284951A (en) * | 2017-12-13 | 2018-07-17 | 中国特种飞行器研究所 | A kind of Combined air cushion airvane ship |
| CN109131867B (en) * | 2018-07-18 | 2023-10-27 | 深圳筋斗云智能科技有限公司 | Aircraft with a plurality of aircraft body |
| CN110901906B (en) * | 2019-12-04 | 2023-04-25 | 中国直升机设计研究所 | Ground effect rotor craft and flight mode switching method |
-
2019
- 2019-12-04 CN CN201911228262.2A patent/CN110901906B/en active Active
-
2020
- 2020-08-24 WO PCT/CN2020/000187 patent/WO2021109311A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2021109311A1 (en) | 2021-06-10 |
| CN110901906A (en) | 2020-03-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110901906B (en) | Ground effect rotor craft and flight mode switching method | |
| US6659394B1 (en) | Compound tilting wing for high lift stability and control of aircraft | |
| CN102826215B (en) | Light and small flying-wing manned aircraft with short takeoff and landing capacity | |
| CN108045575B (en) | Short-distance take-off vertical landing aircraft | |
| CN101875399A (en) | A kind of tilt rotor aircraft adopting side-by-side coaxial twin rotors | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN106240814A (en) | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer | |
| CN106672205B (en) | Layout of a Large Variable Sweep Supersonic Aircraft | |
| US20240174353A1 (en) | Vertical take-off and landing aircraft based on variable rotor-wing technology and dual rotor-wing layout | |
| CN214875553U (en) | Distributed-propulsion tandem high-speed unmanned helicopter | |
| CN106043687B (en) | Twin-engine push-back canard rotor/fixed-wing compound vertical take-off and landing aircraft | |
| CN112027073A (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN113086184B (en) | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft | |
| CN219192548U (en) | V-tail single-push electric vertical take-off and landing composite wing aircraft | |
| CN111959759A (en) | Combined type tilting power longitudinal rotation dual-rotor aircraft | |
| CN117262214A (en) | Amphibious short-distance take-off and landing ground effect aircraft | |
| CN213566473U (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN109677604A (en) | A kind of double-T shaped empennage ground effect vehicle of ultra-large type | |
| CN213566470U (en) | Combined forward-pulling-in longitudinal-row autorotation double-rotor aircraft | |
| CN206202685U (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN213566469U (en) | Combined type side-propulsion longitudinal-row autorotation double-rotor aircraft | |
| CN212501015U (en) | Small unmanned tilt rotor aircraft overall pneumatic layout | |
| US11993366B2 (en) | Wingless VTOL flying land vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |