Short take-off all-rotor single-seat autogiro

Abstract

The application discloses a short-distance take-off full-cabin single-seat autorotating rotorcraft, and relates to the technical field of rotorcrafts. The rotorcraft comprises a machine body, a rotor system, a tail wing, a take-off structure, a power system and a control system. The machine body constitutes the main bearing structure of the autorotating rotorcraft and forms a cabin space for an operator to sit in. The rotor system is arranged above the machine body and rotates automatically under the action of air flow to generate lift force, thereby realizing the flight of the autorotating rotorcraft. The tail wing is arranged at the tail of the machine body and is used for providing directional stability and control moment during flight. The application has the effect of short-distance take-off and greatly improves the applicability of the rotorcraft in narrow spaces. In addition, the linkage design of the control system makes the adjustment of flight attitude, heading and speed more intuitive and convenient, greatly reduces the technical threshold for pilots, and makes the rotorcraft more suitable for single-person operation. Furthermore, the efficient cooperation of the power system and the rotor system further enhances the stability and safety of flight.

Description

Technical Field

[0001] This invention relates to the field of rotorcraft technology, and in particular to a full-cabin single-seat autogyro capable of short-distance takeoff. Background Technology

[0002] An autogyro is a rotorcraft that uses the relative airflow during forward flight to rotate its rotor and generate lift. The power for forward flight comes from a propeller at the rear of the aircraft, which is connected to the engine. Its rotation pushes air backward, propelling the aircraft forward. Furthermore, autogyros have a tail fin, which is used to control their direction of flight. Because of this, compared to traditional helicopters, autogyros are much simpler to operate, giving them certain advantages.

[0003] Traditional gyroplanes, with most of their main structures made of stainless steel, have a large empty weight and a rotor pre-rotation speed limited to 200-220 RPM. This results in long takeoff distances, typically exceeding 100 meters, making them highly dependent on runway length and causing numerous inconveniences in spaces with limited space. Furthermore, existing gyroplanes are often structurally complex, have high maintenance costs, and are difficult to operate, requiring highly skilled pilots and presenting significant challenges for single-person operation. Therefore, designing a full-cabin single-seat autogyro capable of short takeoff, with a simple and reliable structure and convenient operation, is an urgent problem to be solved. This application provides a short-takeoff full-cabin single-seat autogyro to meet these requirements. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a full-cabin single-seat autogyro capable of short-takeoff.

[0005] To achieve the above objectives, this application provides the following technical solution: a full-cabin single-seat autogyro capable of short takeoff, the autogyro comprising:

[0006] The airframe constitutes the main load-bearing structure of the autogyro and forms the cockpit space for the operators.

[0007] The rotor system, located above the fuselage, is used to rotate under the influence of airflow to generate lift, thereby enabling the autogyro to fly.

[0008] The tail fin, located at the rear of the fuselage, is used to provide directional stability and control torque during flight.

[0009] The landing structure is installed below the fuselage and is used to support the autogyro for parking and takeoff and landing on the ground.

[0010] The power system is located at the rear of the fuselage, and the forward thrust generated by the power system provides forward propulsion for the autogyro.

[0011] The control system is connected to the rotor system and the tail drive, and is used to control the flight attitude, heading and speed of the autogyro.

[0012] Furthermore, the machine body includes a frame and a housing. The frame is composed of a frame beam and a frame mast fixed on the frame beam. The housing is located at the front of the frame beam, and the frame mast is located at the rear of the housing.

[0013] Furthermore, the rotor system includes a movable rotor head, a rotor adapted to the rotor head, a drive motor mounted on the frame mast, a reducer adapted to the drive motor, and a transmission shaft mounted on the output end of the reducer. The movable rotor head is fixed to the top of the frame mast, and the transmission shaft is connected to the rotor head through a transmission structure.

[0014] Furthermore, the tail fin is mounted at the rear of the frame beam and consists of a stabilizer and a rudder. The stabilizer, serving as the lateral and longitudinal stabilizing surface of the rotorcraft, is fixed. The rudder is mounted behind the stabilizer, and its deflection controls the rotorcraft's left and right direction.

[0015] Furthermore, the landing structure includes a rotatable front landing gear, a front wheel mounted to the front landing gear, a rear landing gear support rod symmetrically distributed on both sides of the frame mast, a rear landing gear diagonal brace connected to the rear landing gear support rod, and a main wheel mounted at the tail end of the rear landing gear diagonal brace. The rear landing gear support rod is mounted on the frame mast via a clamp, and the rear landing gear diagonal brace is mounted on the frame crossbeam.

[0016] Furthermore, the control system includes a control stick mounted on the frame beam, a connecting rod connected to the control stick, a rocker arm pulled by the connecting rod, and a push-pull rod connecting the rocker arm to the rotor head. The control stick can adjust the angle of the rotor lifting surface.

[0017] Furthermore, the control system also includes a pair of foot pedals mounted on the frame beam, a linkage connecting the pair of foot pedals to the nose landing gear, and a steel cable connecting the pair of foot pedals to the rudder. Controlling the foot pedals can simultaneously control the steering operation of the nose landing gear and the rudder.

[0018] Furthermore, the power system includes a rear-push propeller that provides forward thrust for the rotorcraft's flight, an engine for driving the rear-push propeller to rotate, and a fuel tank adapted to the engine. Both the engine and the fuel tank are fixed to the frame mast by mounting brackets.

[0019] In summary, the technical effects and advantages of this invention are as follows:

[0020] This invention enables short-distance takeoff, greatly enhancing its applicability in confined spaces. Furthermore, the interconnected design of the control system makes adjustments to flight attitude, heading, and speed more intuitive and convenient, significantly lowering the skill requirements for pilots and making it more suitable for single-person operation. Moreover, the efficient coordination between the power system and rotor system further enhances flight stability and safety. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0023] Figure 2 This is a schematic diagram of the second perspective structure of the present invention.

[0024] Figure 3 This is a schematic diagram of the body structure of the present invention.

[0025] Figure 4 This is a schematic diagram of the third-view structure of the present invention.

[0026] Figure 5 For the present invention Figure 4 Enlarged structural diagram at point A in the middle.

[0027] Figure 6 This is a schematic diagram of the landing gear structure of the present invention.

[0028] Figure 7 This is a schematic diagram of the control system structure of the present invention.

[0029] Figure 8 This is a schematic diagram of the power system structure of the present invention.

[0030] In the diagram: 1. Airframe; 2. Rotor system; 3. Tail; 4. Landing structure; 5. Control system; 6. Power system; 11. Frame beam; 12. Frame mast; 13. Fuselage; 21. Rotor head; 22. Rotor; 23. Drive motor; 24. Reducer; 25. Drive shaft; 31. Stabilizer; 32. Rudder; 41. Front landing gear; 42. Nose wheel; 43. Rear landing gear support rod; 44. Main wheel; 45. Rear landing gear diagonal brace; 46. Clamping plate; 51. Control stick; 52. Linkage; 53. Rocker arm; 54. Push-pull rod; 55. Foot pedal; 56. Combined linkage; 57. Steel cable; 61. Rear-pull propeller; 62. Engine; 63. Fuel tank. Detailed Implementation

[0031] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] Example: Reference Figure 1 , Figure 2 The illustration shows a single-seat, full-cabin autogyro capable of short takeoff, comprising:

[0033] Airframe 1 constitutes the main load-bearing structure of the autogyro and forms the cockpit space for the operators.

[0034] Rotor system 2 is located above fuselage 1 and is used to rotate under the action of airflow to generate lift, thereby enabling the autogyro to fly.

[0035] Tail fin 3 is located at the tail of fuselage 1 and is used to provide directional stability and control torque during flight.

[0036] The landing structure 4 is installed below the fuselage 1 and is used to support the autogyro for parking and take-off and landing on the ground.

[0037] The power system 6 is located at the rear of the fuselage 1. The forward thrust generated by the power system 6 provides forward propulsion for the autogyro.

[0038] The control system 5 is connected to the rotor system 2 and the tail fin 3 respectively, and is used to control the flight attitude, heading and speed of the autogyro.

[0039] This autogyro employs an avionics system integrated within the airframe to monitor and control flight parameters, ensuring flight safety and stability. The avionics system comprises an instrument panel, sensor array, and data processing unit. The instrument panel provides the pilot with real-time flight information such as speed, altitude, and attitude. The sensor array collects various data during flight, including airflow speed, rotor speed, and airframe tilt angle. The data processing unit analyzes and processes this data to generate command signals for the control system.

[0040] In the actual operation of this autogyro, the fuselage 1 includes a frame and a shell 13. The frame consists of a frame beam 11 and a frame mast 12 fixed on the frame beam 11. The frame is made of titanium alloy, which can reduce the weight by 40% compared to stainless steel. The shell 13 is made of carbon fiber composite material. The shell 13 is located at the front of the frame beam 11, and the frame mast 12 is located at the rear of the shell 13.

[0041] The rotor system 2 includes a movable rotor head 21, a rotor 22 adapted to the rotor head 21, a drive motor 23 mounted on the frame mast 12, a reducer 24 adapted to the drive motor 23, and a drive shaft 25 mounted on the output end of the reducer 24. The movable rotor head 21 is fixed to the top of the frame mast 12, and the drive shaft 25 is connected to the rotor head 21 through a transmission structure. The rotor 22 has a diameter of 7.5m, an angle of attack of 2°, a dihedral angle of 2°, and an airfoil of NACA-8H12 to increase the diameter of the rotor 22 and improve lift.

[0042] During flight, the rotor head 21 and rotor 22 in rotor system 2 rotate rapidly under the influence of airflow, generating sufficient lift to lift the autogyro off the ground. Furthermore, during flight, the operator precisely controls rotor system 2 through control system 5 to adjust the flight attitude.

[0043] It is worth mentioning that, in order to shorten the takeoff run distance of the gyroplane, an electric pre-rotation mode is provided in this invention. By design, the drive motor 23 is controlled to run before takeoff. Under the transmission action of the reducer 24, the transmission shaft 25 and the transmission structure, the rotor 22 is pre-rotated to more than 280 RPM. By adopting this scheme, the takeoff run distance of the gyroplane can be kept below 50m.

[0044] The tail section 3 is mounted at the rear of the frame beam 11 and consists of a stabilizer 31 and a rudder 32. The stabilizer 31, serving as the lateral and longitudinal stabilizing surface of the rotorcraft, is fixed. The rudder 32 is mounted behind the stabilizer 31. Both the stabilizer 31 and the rudder 32 are made of carbon fiber composite material. The stabilizer 31 and the rudder 32 work together to ensure lateral and longitudinal stability during flight. The operator can control the deflection of the rudder 32 through the control system 5 to achieve directional control of the rotorcraft.

[0045] The landing gear structure 4 includes a rotatable nose landing gear 41, a nose wheel 42 mounted to the nose landing gear 41, a rear landing gear support rod 43 symmetrically distributed on both sides of the frame mast 12, a rear landing gear diagonal brace 45 connected to the rear landing gear support rod 43, and a main wheel 44 mounted at the tail end of the rear landing gear diagonal brace 45. The rear landing gear support rod 43 is mounted on the frame mast 12 via a clamp 46, the height of which can be adjusted to meet the vibration damping requirements of the landing gear for different weights of the rotorcraft. The rear landing gear diagonal brace 45 is mounted on the frame crossbeam 11. The nose landing gear 41 and the rear landing gear support rod 43 work together to ensure the stability of the aircraft 1 when moving on the ground. Especially during short takeoffs, the design of the landing gear structure 4 can effectively reduce the takeoff distance and improve takeoff and landing efficiency.

[0046] The control system 5 includes a control stick 51 mounted on the frame beam 11, a connecting rod 52 connected to the control stick 51, a rocker arm 53 pulled by the connecting rod 52, and a push-pull rod 54 connecting the rocker arm 53 to the rotor head 21. The transmission link composed of the control stick 51, the connecting rod 52, the rocker arm 53 and the push-pull rod 54 transmits the operation command to the rotor head 21, thereby adjusting the angle of the rotor lifting surface.

[0047] The control system 5 also includes a pair of foot pedals 55 mounted on the frame beam 11, a linkage 56 connecting the pair of foot pedals 55 to the nose landing gear 41, and a steel cable 57 connecting the pair of foot pedals 55 to the rudder 32. Controlling the foot pedals 55 can simultaneously control the steering operation of the nose landing gear 41 and the rudder 32. The foot pedals 55, through the linkage 56 and the steel cable 57, link the nose landing gear 41 and the rudder 32, providing additional operational convenience when steering or attitude adjustment is required.

[0048] The power system 6 includes a pusher propeller 61 that provides forward thrust for the gyroplane's flight, an engine 62 that drives the pusher propeller 61, and a fuel tank 63 adapted to the engine 62. Both the engine 62 and the fuel tank 63 are fixed to the frame mast 12 via mounting brackets. During the gyroplane's flight, the engine 62 drives the pusher propeller 61 to rotate at high speed, providing strong forward thrust to help the gyroplane accelerate and maintain its flight speed, while the fuel tank 63 continuously provides fuel to the engine 62.

[0049] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A single-seat, full-cabin autogyro capable of short takeoff, characterized in that, This autogyro includes: Airframe (1), which constitutes the main load-bearing structure of the autogyro and forms a cabin space for the operator to sit in; Rotor system (2), the rotor system (2) is located above the fuselage (1) and is used to rotate under the action of airflow to generate lift and realize the flight of the autogyro. Tail fin (3), which is located at the tail of the fuselage (1) and is used to provide directional stability and control torque during flight; The landing structure (4) is installed below the fuselage (1) and is used to support the autogyro for parking and take-off and landing on the ground. The power system (6) is located at the rear of the fuselage (1), and the forward thrust generated by the power system (6) provides forward power for the autogyro. The control system (5) is connected to the rotor system (2) and the tail fin (3) respectively, and is used to control the flight attitude, heading and speed of the autogyro.

2. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 1, characterized in that: The body (1) includes a frame and a housing (13). The frame is composed of a frame beam (11) and a frame mast (12) fixed on the frame beam (11). The housing (13) is located in front of the frame beam (11), and the frame mast (12) is located behind the housing (13).

3. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 2, characterized in that: The rotor system (2) includes a movable rotor head (21), a rotor (22) adapted to the rotor head (21), a drive motor (23) mounted on the frame mast (12), a reducer (24) adapted to the drive motor (23), and a transmission shaft (25) mounted on the output end of the reducer (24). The movable rotor head (21) is fixed on the top of the frame mast (12), and the transmission shaft (25) is connected to the rotor head (21) through a transmission structure.

4. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 3, characterized in that: The tail fin (3) is installed at the rear of the frame beam (11) and consists of a stabilizer (31) and a rudder (32). The stabilizer (31) serves as the lateral and longitudinal stabilizing surface of the rotorcraft and is in a fixed state. The rudder (32) is installed behind the stabilizer (31) and the deflection of the rudder (32) can control the left and right directions of the rotorcraft.

5. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 2, characterized in that: The landing structure (4) includes a rotatable front landing gear (41), a front wheel (42) mounted to the front landing gear (41), a rear landing gear support rod (43) symmetrically distributed on both sides of the frame mast (12), a rear landing gear diagonal brace (45) connected to the rear landing gear support rod (43), and a main wheel (44) mounted at the tail end of the rear landing gear diagonal brace (45). The rear landing gear support rod (43) is mounted on the frame mast (12) through a clamp (46), and the rear landing gear diagonal brace (45) is mounted on the frame crossbeam (11).

6. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 5, characterized in that: The control system (5) includes a control stick (51) mounted on the frame beam (11), a connecting rod (52) connected to the control stick (51), a rocker arm (53) pulled by the connecting rod (52), and a push-pull rod (54) connecting the rocker arm (53) to the rotor head (21). The control stick (51) can adjust the angle of the lifting surface of the rotor (22).

7. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 6, characterized in that: The control system (5) also includes a pair of foot pedals (55) mounted on the frame beam (11), a combination linkage (56) connecting the pair of foot pedals (55) to the front landing gear (41), and a steel cable (57) connecting the pair of foot pedals (55) to the rudder (32). The foot pedals (55) can simultaneously control the steering operation of the front landing gear (41) and the rudder (32).

8. The short-takeoff, full-cabin, single-seat autogyro aircraft according to claim 2, characterized in that: The power system (6) includes a rear-push propeller (61) that provides forward thrust for the rotorcraft, an engine (62) for driving the rear-push propeller (61) to rotate, and a fuel tank (63) adapted to the engine (62). The engine (62) and the fuel tank (63) are both fixed to the frame mast (12) by mounting brackets.

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