Folding type hybrid wing power device of helicopter
By designing a foldable hybrid wing power plant, combined with the advantages of propellers and fixed wings, the problems of complex and difficult operation of existing helicopter technology are solved, and more stable and efficient flight performance is achieved.
Patent Information
- Application Number
- CN202510244717.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-02-23
- Publication Date
- 2025-05-13
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
Existing helicopters mainly rely on propellers to provide lift, flight power and steering power. The technology is complex and difficult to operate. It is difficult to effectively balance and stabilize with propellers alone.
A folding hybrid wing power plant is designed, combining the advantages of propellers and fixed wings. Through components such as brackets, hydraulics, fixed wings, tilt tracks, propellers and airflow accelerators, the coordinated work of propellers and fixed wings is achieved, providing lift and thrust, and the folding and deployment of the wings is achieved through the tilt tracks and airflow accelerators.
The device simplifies the structure and handling of the helicopter, is able to provide stable lift and thrust during vertical take-off and horizontal flight phases, improves the balance stability and flight speed of the helicopter, and reduces the distance to taxi and take-off.
Smart Images
Figure CN119975809A_ABST
Abstract
Description
1. Technical Field
[0001] The device belongs to the technical field of helicopter equipment production. 2. Background Technology
[0002] The existing helicopter propeller device has the blades on top and the engine at the bottom. A hinge structure is used to control the horizontal deflection angle of the blades in order to increase or decrease lift. A control rudder is used to control the flight state of the helicopter. The technology is complex and difficult to operate. For single-rotor helicopters, the torque generated by the rotation of the main rotor requires a tail wing to generate reverse thrust to offset the torque generated by the main rotor and keep the helicopter balanced and stable. For twin-rotor helicopters, the two propellers rotate in opposite directions and generate torques in opposite directions. When they are equal in size, they can offset each other to keep the fuselage balanced and stable. Existing helicopters rely solely on the rotation of propellers to provide lift, flight power and steering power for the helicopter. Fixed-wing aircraft use aerodynamic principles and rely on fixed wings to provide lift for the aircraft. III. Summary of the invention
[0003] (I) The technical problem to be solved by the device is: how to provide a hybrid wing power device consisting of a propeller and a fixed wing for a helicopter and the folding problem of the device.
[0004] (II) Technical solutions adopted:
[0005] 1. The overall technical solution is: the bracket is installed above the fuselage, and two fixed wings are installed symmetrically on both sides of the bracket. The hydraulic device connects the bracket and the fixed wing to control the folding and unfolding of the fixed wing; a tilt track is installed between the front and rear wings, an engine is installed above the tilt track, and a propeller is installed below the tilt track. The two engines and propellers rotate in opposite directions; the front airflow accelerator is installed above the leading edge of the front wing, and the rear airflow accelerator is installed below the tilt track and propeller, which can be tilted to the front of the rear wing with the tilt track. During the vertical take-off and landing stage of the helicopter, the propeller provides lift; during the horizontal flight stage, the front and rear wings provide lift, and the propeller provides thrust. Use an airflow accelerator to increase the velocity of the airflow on the upper surface of the wing.
[0006] 2. The foldable hybrid wing power unit includes: a bracket and a hydraulic device, two fixed-wing systems, two tilting tracks and control systems, two propeller systems, two front airflow accelerators, two rear airflow accelerators, etc.
[0007] 3. Bracket and hydraulic device. The cross section of the bracket is in the shape of an "I". The base is installed longitudinally above the fuselage. Hinges are installed on the left and right sides of the bracket crossbar for symmetrical installation of the fixed wing. Two columns are installed above the "I"-shaped bracket. Swivels are installed on both sides of the top of the columns. The oil cylinder of the hydraulic device is installed on the swivel.
[0008] 4. The fixed-wing system is divided into two parts: the left fixed-wing system and the right fixed-wing system. The fixed-wing is divided into a front wing and a rear wing. The cross-section of the front wing and the rear wing is a convex upper and flat lower structure. The two ends of the front wing and the rear wing are connected by two connecting frames to form a fixed-wing system. The tilt track bearing seat mounting holes and the motor mounting holes are arranged in the middle of the two connecting frames, and the tilt track and the motor are installed on the connecting frames; a hinge mounting hole is arranged on one side of the fixed-wing system, and the two fixed-wing systems are symmetrically installed on both sides of the bracket crossarm through hinges.
[0009] Hydraulic device connecting rod connection points are arranged on the front wing and the rear wing, and one end of the connecting rod of the hydraulic device on the bracket is connected with the two wings to control the fixed wing to fold and unfold upward.
[0010] 5. The tilt track is annular with a cross frame in the middle. A transmission shaft hole is drilled in the center of the cross frame. The diameter of the hole is larger than the diameter of the engine transmission shaft to facilitate the passage of the transmission shaft. Engine mounting holes are set on the cross around the transmission shaft hole. The engine can be installed and fixed above the center of the circular track with the transmission shaft facing downward.
[0011] Two concentric shafts are set on the outer side of the track at both ends of the track frame, one long and one short. A large gear is installed on the inner side of the long shaft, a bearing is installed on the outer side, and a bearing is installed on the short shaft. The motor is installed on the connecting frame, and a small gear is installed on the motor to mesh with the large gear on the track. The motor controls the track to tilt forward or backward. The bearings of the two tilting tracks are symmetrically installed on the connecting frame of the fixed wing through the bearing seat. The tilting track is located between the front wing and the rear wing.
[0012] 6. A propeller system consists of multiple blades, rollers and turntables.
[0013] The turntable is circular, with a transmission shaft mounting hole in the center and multiple blade mounting holes evenly and symmetrically arranged around it.
[0014] The blade is rectangular, with a petiole and a rotating shaft respectively arranged at the two ends of a long side, a mounting hole is drilled on the petiole, and a roller is installed on the rotating shaft. When the blade petiole is installed on the turntable, the axis of the roller rotating shaft is perpendicular to and crosses the axis of the engine transmission shaft.
[0015] There are two types of blades. One is that the blade plane is at an acute angle to the lower right with respect to the petiole, which is suitable for propellers rotating counterclockwise. Multiple identical blades can be installed on a turntable, which is installed below the engine drive shaft that rotates counterclockwise. When the engine drives the blades to rotate counterclockwise, downward wind force is generated, that is, upward lift is generated. The other is that the blade plane is at an acute angle to the lower left with respect to the petiole, which is suitable for propellers rotating clockwise. Multiple identical blades can be installed on a turntable, which is installed below the engine drive shaft that rotates clockwise. When the engine drives the blades to rotate clockwise, downward wind force is generated, that is, upward lift is generated. The two propellers work independently, and the lift generated is superimposed on each other, which is the lift of the entire helicopter's vertical ascent stage. The lift generated by the propeller is related to the bending angle of the blades, the length and width of the blades, the number of blades, the rotation speed of the blades, etc. The larger the length and width of the blades, the greater the number of blades, and the faster the rotation speed, the greater the lift generated when the blades rotate. The deflection angle between 10° and 30° is more appropriate. The length, width, and deflection angle of the two blades are the same, and the number of blades installed on the two propellers is equal.
[0016] The turntable of the counterclockwise rotating propeller is installed at the lower end of the right engine transmission shaft and below the tilt track, and the turntable of the clockwise rotating propeller is installed at the lower end of the left engine transmission shaft and below the tilt track. The roller corresponds to and contacts the bottom of the circular track.
[0017] The torque generated by the propeller rotating counterclockwise is counterclockwise, and the torque generated by the propeller rotating clockwise is clockwise. When the two propellers rotate at the same speed, the torques generated are equal in magnitude and opposite in direction, which can offset each other and keep the fuselage balanced and stable. When the two propellers rotate at different speeds, the torques generated are also different. When the counterclockwise propeller rotates at a higher speed, the helicopter fuselage will rotate counterclockwise, and vice versa, the helicopter will rotate clockwise.
[0018] 7. The front airflow accelerator is composed of a movable plate, a fixed plate, a support, a swivel, a small hydraulic device, etc. The fixed plate and the movable plate are both rectangular, the fixed plate is wider than the movable plate, a support is installed in the middle of the short side of the fixed plate, a swivel is installed on the top of the support, a swivel sleeve is installed in the middle of the short side of the movable plate, and the movable plate is installed on the fixed plate; the small hydraulic device cylinder is installed on the fixed plate, and the end of the connecting rod is installed on the movable plate. The small hydraulic device controls the opening or closing of the movable plate, forming a funnel or inverted funnel shape with the fixed plate. The fixed plate of the front airflow accelerator is installed on the front wing, and the funnel outlet is aligned with the front edge of the front wing.
[0019] The front airflow accelerator has three functions: first, it increases the airflow velocity on the upper surface of the front wing to increase lift; second, it blocks the airflow to prevent the helicopter from moving forward; third, it changes the upward flow direction of the airflow to increase the downward pressure and make the helicopter nose down. The front airflow accelerator does not work during the vertical take-off and landing phase of the helicopter, and only provides accelerated and decelerated airflow during the forward taxiing or flight phase of the helicopter.
[0020] ① The movable plate opens upward at a certain angle from the parallel airflow inlet, and the movable plate and the fixed plate form a funnel shape to collect and compress the airflow, increase the flow rate, and greatly increase the airflow velocity on the upper surface of the front wing. At this time, two kinds of lift are generated: the upward resistance of the airflow on the movable plate and the lift generated by the front wing, which can make the helicopter fly forward steadily.
[0021] ② The air flow inlet of the movable plate quickly opens upward at a large angle, and the movable plate and the fixed plate form a funnel shape to collect and compress the air flow, increase the flow rate, and the air flow velocity on the upper surface of the front wing increases significantly. At this time, two kinds of lift are generated: the upward resistance of the air flow to the movable plate increases rapidly and the lift generated by the front wing increases rapidly, which can enable the helicopter to climb rapidly.
[0022] ③ The movable plate opens upward to the maximum angle, closing the airflow outlet and blocking the airflow from passing through. A resistance wall is formed at the front of the accelerator, which can prevent the helicopter from moving forward.
[0023] ④ The movable plate gradually closes downward from the horizontal to a certain angle until the movable plate and the fixed plate form an inverted funnel shape. The airflow produces downward pressure on the movable plate. At the same time, the airflow bypasses the upper surface of the front wing upward. The front wing does not generate lift, allowing the helicopter to dive downward.
[0024] 8. The inlet of the rear airflow accelerator is trapezoidal, with multiple inward-inclined grid plates built in, and the outlet faces the collection plate. After collection and acceleration, a strip of airflow is formed, and the collection plate is slightly longer. The rear airflow accelerator is hoisted on the tilt track and below the propeller through a bracket. Its strip outlet is perpendicular to the fuselage level, collecting and accelerating the middle part of the airflow generated by the propeller.
[0025] The rear airflow accelerator can be tilted together with the tilt track. When the tilt track propeller tilts forward to a vertical state, the outlet of the rear airflow accelerator is in a horizontal state, and the outlet is aligned with the front edge of the rear wing. The propeller blows air horizontally backward, and the airflow generated after being accelerated by the rear airflow accelerator flows through the upper surface of the rear wing. The airflow is accelerated again on the upper surface of the rear wing. The gas flow rate flowing through the upper surface of the rear wing is much greater than the airflow speed under the rear wing without acceleration, and the lift generated by the rear wing will also be greatly increased.
[0026] The rear airflow accelerator blows air downward during the helicopter's vertical takeoff and landing phase, generating lift but no horizontal thrust. During the tilt track's tilt from horizontal to vertical direction, part of the lift generated by the propeller is converted into thrust, the lift gradually decreases, and the thrust gradually increases. When the track is in a vertical state, the thrust generated by the propeller is the largest and the lift is reduced to zero.
[0027] 9. Instructions for use: (1) Operate the hydraulic device to unfold the hybrid wings on both sides to a horizontal state.
[0028] (2) Operate the two motors to keep the tilt-orbit propellers on both sides in a horizontal state, with the propellers and the rear airflow accelerator outlet facing downward.
[0029] (3) Start both engines and increase the throttle. The propellers rotate and blow air downward to generate lift. Continue to increase the throttle to raise the helicopter to a certain height. Reduce the throttle and the helicopter descends to the ground, completing takeoff and landing.
[0030] (4) When the helicopter is at a certain altitude, the small hydraulic device is operated to open the movable plate to a certain angle, so that the front accelerator is in the accelerator flow state, and the two motors are operated to tilt the two tilt-track propellers forward and continuously increase the tilt angle. The propellers blow air backward and downward, generating lift and forward thrust at the same time, so that the helicopter flies forward. At this time, the two propellers, front wing, and rear wing provide lift for the helicopter, and the two propellers provide power for forward flight and power for turning left and right.
[0031] (5) When the helicopter is at a certain altitude, the small hydraulic device is operated to open the movable plate to a certain angle, so that the front accelerator is in the accelerator flow state, and the two motors are operated to tilt the two tilt-track propellers forward to a vertical state. The front wing generates lift, and the two propellers blow air horizontally backward. Part of the airflow generated by the propellers is accelerated by the rear airflow accelerator and then flows through the upper surface of the rear wing, and then accelerated by the rear wing surface. The airflow that is not accelerated by the accelerator flows through the lower surface of the rear wing, which can make the helicopter fly at high speed.
[0032] When the two tilt-orbit propellers are in a vertical state, all the lift generated by the propellers is converted into thrust, greatly increasing the helicopter's flight speed; the air flowing through the upper surface of the rear wing is accelerated three times by the propeller, the rear airflow accelerator, and the rear wing convex surface, and the flow velocity difference generated by the upper and lower surfaces is further expanded, further increasing the lift.
[0033] (6) When the helicopter is ascending or in horizontal flight, if the speed of the left propeller is reduced or the speed of the right propeller is increased, the thrust on the left side of the helicopter will be less than that on the right side, which will cause the helicopter to turn left; otherwise, the helicopter will turn right.
[0034] (7) On the airport runway (ship), fix the helicopter with both fixed wings fully deployed, the two tilting tracks in a vertical position, the front airflow accelerator open at a certain angle, and the outlet of the rear airflow accelerator facing backwards; start the two engines, make the two propellers rotate and blow air horizontally backwards, and part of the airflow generated by the propellers is accelerated by the rear airflow accelerator and then flows through the upper surface of the rear wing. The airflow that is not accelerated by the gas velocity accelerator flows under the rear wing. Increase the engine throttle and propeller speed. The rear wing of the helicopter can generate a large lift when it is stationary. At this time, the front wing and propeller do not generate lift; release the helicopter, the helicopter rushes forward, and the front wing generates two types of lift due to air resistance and the velocity difference between the upper and lower surfaces of the front wing. Both the front wing and the rear wing generate lift, which allows the helicopter to glide a short distance before taking off.
[0035] (8) In flight, the tilt-orbit propeller is controlled to tilt backward from a vertical state to a horizontal state, the thrust gradually decreases, and the flight speed decreases; the propeller speed is reduced to land on the ground.
[0036] (9) In flight, the front accelerator's small hydraulic device is controlled to quickly increase the opening of the front airflow accelerator. The upward resistance of the air on the movable plate increases, and the lift increases. At the same time, the airflow speed flowing through the front wing surface increases, and the lift of the front wing increases. These two types of lift enable the helicopter to quickly climb.
[0037] (10) In flight, the front accelerator hydraulic device is controlled to tilt the movable plate forward and downward to form an inverted funnel shape. The downward resistance of the air on the movable plate increases, causing the nose of the helicopter to be pressed downward. At the same time, the airflow speed flowing over the front wing surface decreases, reducing the lift of the front wing, causing the helicopter to dive downward and lower its flight altitude.
[0038] (III) Beneficial effects: 1. The foldable hybrid wing power device has a simple structure and is easy to operate. 2. The device can not only provide lift for the helicopter, but also provide thrust for forward flight and power for turning left and right. The lift generated by the propeller can be fully converted into thrust, greatly improving the forward flight speed of the helicopter. 3. The use of airflow accelerators, front wings and rear wings to provide lift for the helicopter in flight can effectively increase the helicopter's load capacity. 4. The helicopter can taxi and take off at the airport (ship), with a short taxiing distance, and the fixed wings occupy less ground space when folded.
[0039] (IV) Scope of application: The foldable hybrid wing power device is applicable to the power platform of helicopters and the power platform of unmanned aerial vehicles. IV. Description of the drawings In the figure, the curved arrows and straight arrows represent the wind direction.
[0041] Figure 1 Side view of the bracket system; Figure 2 Side view of the bracket system;
[0042] Figure 3 Front view of the bracket system; Figure 4 Front view of the fixed-wing system;
[0043] Figure 5 Side view of the fixed-wing system; Figure 6 Track front view;
[0044] Figure 7 Track side view; Figure 8 Front view of the propeller blade; Fig. 9 Counterclockwise blade side view;
[0045] Fig.10 Clockwise blade side view; Fig.11 Front view of the turntable;
[0046] Fig.12 Schematic diagram of propeller rotating clockwise; Fig.13 Schematic diagram of a propeller rotating counterclockwise;
[0047] Fig.14 Front view of the bracket and two fixed-wing system installation structures;
[0048] Fig.15 Side view of the bracket and two fixed-wing system mounting structures;
[0049] Fig.16 Schematic diagram of the folding of the bracket and two fixed-wing systems;
[0050] Fig.17 Front view of the installation structure of the tilt-track, motor and fixed-wing system;
[0051] Fig.18 Side view of the rear airflow accelerator; Fig.19 Side view of the rear airflow accelerator;
[0052] Fig. 20 Schematic diagram of the installation structure of the track, engine and propeller system;
[0053] Fig.21 Installation structure diagram of track, engine, propeller system and rear airflow accelerator;
[0054] Fig. 22 Side view of the front airflow accelerator; Fig.23 Schematic diagram of the horizontal state of the front airflow accelerator;
[0055] Fig.24 The front airflow accelerator is in an inverted funnel-shaped side view;
[0056] Fig.25 Schematic diagram of the front airflow accelerator and front wing mounting structure and airflow;
[0057] Fig.26 The inverted funnel state of the front airflow accelerator and the front wing installation structure and airflow schematic diagram;
[0058] Fig. 27 Schematic diagram of the principle of vertical take-off and landing of a helicopter;
[0059] Fig.28 Schematic diagram of the helicopter's horizontal flight principle;
[0060] 1. Cylinder mounting point 2. Column 3. Hinge 4. Bracket 5. Support column 6. Base 7. Connecting rod mounting point 8. Hinge mounting hole 9. Bearing seat hole 10. Connecting frame 11. Hinge mounting hole 12. Front wing 13. Rear wing 14. Circular track 15. Drive shaft hole 16. Short shaft 17. Petiole hole 18. Petiole 19. Blade 20. Rotating shaft 21. Turntable 22. Drive shaft mounting hole 23. Petiole mounting hole 24. Roller 25. Hydraulic device cylinder 2 6. Connecting rod mounting point 27. Large gear 28. Bearing, bearing seat 29. Motor 30. Small gear 31 Airflow inlet 32. Inclined grille plate 33. Collecting plate 34. Airflow outlet 35. Rear airflow accelerator 36. Engine 37. Hanger 38. Swivel, swivel sleeve 39. Movable plate 40. Fixed plate 41. Support 42. Small hydraulic device 43. Front airflow accelerator 44. Rear airflow accelerator 45. Long shaft 46. Engine mounting hole 47. Cross V. Specific implementation methods
[0061] 1. Figure 1 In the invention, hinges (3) are installed on both sides of the support bracket (4), and oil cylinder installation points (1) are arranged on both sides of the top of the two columns (2).
[0062] 2. Figure 4 In the invention, two connecting frames (10) connect the front wing (12) and the rear wing (13), the connecting frames are provided with bearing seat holes (9) and hinge mounting holes (8, 11), and connecting rod connection points (7) are provided on the front wing and the rear wing.
[0063] 4. Figure 6 In the invention, a transmission shaft hole (15) is punched in the center of the cross of the cross-ring track, an engine mounting hole (46) is punched in the periphery, and a major axis (45) and a minor axis (16) are installed at the outer end of the track (14).
[0064] 5. Fig.12 In the invention, a roller (24) is mounted on the rotating shaft of the blade, and the blade handles (18) of four clockwise rotating blades (19) are mounted on a rotating disk (21), forming a propeller rotating in the clockwise direction.
[0065] 6. Fig.13In the invention, a roller (24) is mounted on the rotating shaft of the blade, and the blade handles (18) of four counterclockwise rotating blades (19) are mounted on a rotating disk (21), thereby forming a propeller that rotates counterclockwise.
[0066] 7. Fig.15 In the invention, two fixed-wing systems are symmetrically mounted on both sides of a support bracket (4) through hinges (3), and a hydraulic device (25) connects the column (2) and the front wing (12) and the rear wing (13).
[0067] 8. Fig.17 In the invention, the tilting track is installed on the connecting frame (10) through a bearing and a bearing seat (28), a large gear (27) is installed on the long axis, and a motor (29) is installed on the connecting frame, and its small gear (30) is meshed with the large gear.
[0068] 9. Fig.19 The inlet of the rear airflow accelerator (35) is trapezoidal, and has multiple inclined grilles (32) built in, all of which are inclined toward the collecting plate (33).
[0069] 10. Fig.21 In the invention, the engine (36) is installed above the center of the track (14), the transmission shaft passes through the track downward, the turntable (21) of the propeller is installed at the lower end of the transmission shaft, and the rear airflow accelerator is installed on the outside of the track (14) through the bracket (37), with the outlet facing downward.
[0070] 11. Fig. 22 , 26 In the invention, the fixed plate (40) of the front accelerator is installed in front of the front wing (12), and the small hydraulic device (42) connects the movable plate (39) and the fixed plate.
Claims
1. A folding hybrid wing power device for a helicopter, characterized in that: Two fixed-wing systems are installed on both sides of the bracket. The fixed wings can be folded and unfolded. A tilt track is installed between the front wing and the rear wing. The motor and the tilt track are installed on the connecting frame. The propeller and the rear airflow accelerator are installed under the tilt track. The two propellers rotate in opposite directions. The front airflow accelerator is installed at the front end of the front wing.
2. The foldable hybrid wing power device for a helicopter according to claim 1, characterized in that: The cross section of the bracket is in the shape of an "I", hinges are installed on the brackets on both sides, two columns are arranged above the bracket, and cylinders of the hydraulic device are installed on both sides of the top of the columns.
3. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The two ends of the front wing and the rear wing are connected by a connecting frame, a hinge mounting hole is set on one side of the front wing and the rear wing, and two identical fixed wings are symmetrically installed on the brackets on both sides of the bracket. Connecting rod connecting holes are set on the front wing and the rear wing, which are connected to the hydraulic connecting rod of the hydraulic device. The hydraulic device controls the folding and unfolding of the fixed wings on both sides.
4. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The tilt track is ring-shaped with a cross frame in the middle. A transmission shaft hole is drilled in the center of the cross frame, and engine mounting holes are set on the crosses around the transmission shaft hole; two concentric shafts, one long and one short, are set on the outside of the track at both ends of one track frame. A large gear is installed on the inside of the long shaft, and bearings and bearing seats are installed on the outside; bearings and bearing seats are installed on the short shaft; a small gear is installed on the motor, which meshes with the large gear on the track to control the tilt of the track.
5. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The blade is rectangular, with a petiole and a rotating shaft respectively arranged at the two ends of one long side, a mounting hole is punched on the petiole, and a roller is installed on the shaft at the end of the blade; relative to the petiole, the blade plane is at an acute angle to the right and below with respect to the petiole, and is suitable for a propeller device rotating in a counterclockwise direction. The petioles of multiple blades are installed on a turntable to form a propeller rotating in a counterclockwise direction; Relative to the petiole, the blade plane is at an acute angle to the left and downward with respect to the petiole plane, and is suitable for a device rotating in a clockwise direction. The petioles of multiple blades are mounted on a turntable.
6. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The engine is installed above the center of the circular track, the turntable is installed at the lower end of the engine transmission shaft and below the circular track, and the roller corresponds to and contacts the bottom of the circular track; the counterclockwise rotating propeller is installed on the right track, and the clockwise rotating propeller is installed on the left track.
7. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The fixed plate of the front airflow accelerator is installed on the front wing, and the movable plate is installed on the column above the fixed plate through a rotating shaft. A small hydraulic device connects the movable plate and the front end of the fixed plate to control the up and down movement of the movable plate.
8. The folding hybrid wing power device for a helicopter according to claim 1, characterized in that: The inlet of the rear airflow accelerator is trapezoidal, with multiple inclined grilles built in, and the outlet is toward the collecting plate. It is installed on the track and below the propeller, and can tilt with the track.