A gyrocopter

Abstract

The application discloses a self-rotating rotorcraft, and relates to the technical field of rotorcrafts, which comprises a body structure, a driver seat and two detachable rear seats arranged on the body structure, the rear seats are arranged side by side and staggered in the left and right directions of the body structure, when the two rear seats are detached, a space for installing a load rack is formed, two symmetrically distributed air-drop box throwing frames are installed on the load rack, and air-drop boxes are slidably installed on the inner sides of the air-drop box throwing frames. The load rack can be installed after the rear seats are removed, which is convenient for carrying materials, the air-drop boxes and the air-drop box throwing frames loaded with the materials can help to support the materials. In the process of throwing the materials, the load rack, the air-drop box throwing frames and the air-drop boxes are symmetrically distributed along the gravity center of the body structure. Therefore, in the process of throwing the air-drop boxes, the range of the gravity center envelope of the whole machine changes little.

Description

Technical Field

[0001] This invention relates to the field of rotorcraft technology, and particularly to an autogyro. Background Technology

[0002] In recent years, with the advancement of low-altitude airspace reform, my country's aviation industry has developed rapidly. Compared with other aircraft, autogyros have become a focus of attention and a hot topic in the aviation field due to their advantages such as good low-altitude and low-speed performance, low manufacturing and maintenance costs, and simple operation.

[0003] An autogyro is a rotorcraft that uses its own rotor as a lifting surface and propeller thrust or other power sources for forward propulsion. Unlike helicopters, which rely on engine power to drive their rotors, autogyros rely on the airflow in front of them for rotor rotation, thus the rotor is always spinning. Even if the engine stops operating in the air, the autogyro can still land safely by relying on the rotor's rotation. Employing rotor pre-spinning technology, the rotor is pre-spinned via a transmission mechanism before takeoff, and the transmission link is disconnected by a clutch to achieve takeoff, allowing the autogyro to perform hop takeoffs or ultra-short takeoffs. Furthermore, autogyros do not require a dedicated airport for landing; by tilting the rotor cone backward, they can achieve point landings.

[0004] Existing autogyros have relatively limited functionality and payload capacity. If drop operations are implemented on these autogyros, the resulting descent force can easily affect the fuselage, causing it to sway and compromising stability during flight, thus compromising safety. Therefore, existing autogyros present significant challenges in dropping supplies, requiring heavy loads and compromising safety during the drop process. Summary of the Invention

[0005] To address the aforementioned problems, this application provides an autogyro.

[0006] To achieve the above objectives, this application provides the following technical solution: an autogyro, comprising an airframe structure, on which a pilot's seat and two removable rear seats are arranged. The rear seats are arranged side-by-side and staggered in the left and right directions of the airframe structure. When the two rear seats are removed, a space is formed for installing a payload bay rack. Two symmetrically distributed airdrop box drop racks can be installed on the payload bay rack. An airdrop box that can slide out is installed on the inner side of the airdrop box drop rack. The payload bay rack is located on the central axis of the airframe structure, and the payload bay rack, airdrop box drop racks, and airdrop box are all symmetrically distributed along the center of gravity of the airframe structure.

[0007] Furthermore, the airdrop box throwing frames are all inclined metal frames, and the front and rear ends of the airdrop box throwing frames are equipped with blocking frames to prevent the airdrop boxes from sliding forward and backward.

[0008] The bottom of each airdrop box throwing frame is equipped with a raised baffle to prevent the airdrop box from sliding down. A binding rope is installed on the raised baffle. The binding rope is attached to the surface of the airdrop box and is connected to the load compartment frame by a servo motor.

[0009] Furthermore, the body structure includes a frame-type frame, a streamlined housing mounted on the frame, and an oil tank mounted at the rear of the housing. The rear seats are mounted on the frame with screws. After the rear seats are removed, a load cell can be installed on the frame.

[0010] Furthermore, the interior of the fuel tank is equipped with multiple layered partitions.

[0011] Furthermore, a main propulsion system consisting of a propeller and an engine that controls the propeller's operation is arranged at the rear of the frame, and an auxiliary power system is arranged at the front of the fuselage. The auxiliary power system includes rotor arms symmetrically arranged and installed on the left and right sides of the front end of the fuselage. When the propeller is stationary, the propeller blades are parallel to the rotor arms.

[0012] Furthermore, the frame is equipped with a pre-spinning system and a rotor system controlled by the pre-spinning system. The pre-spinning system consists of a pre-spinning motor mounted on the frame, a reducer adapted to the pre-spinning motor, and a drive shaft mounted on the output end of the reducer. The rotor system consists of two rotor blades and a rotor head connecting the two rotor blades. The rotor head is mounted on the top of the drive shaft.

[0013] Furthermore, a control system is arranged on the frame, which consists of a push-pull rod, a control stick, a rudder, and a transmission rod. The upper and lower ends of the push-pull rod are connected to the rotor head and the rocker arm by spherical bearings, and the middle end of the push-pull rod is connected to the frame. The control stick is mounted on the transmission rod and is installed inside the fuselage and in a forward position. The rudder is mounted at the rear end of the transmission rod and moves under the control of the control stick and the transmission rod.

[0014] Furthermore, landing gear is arranged below the fuselage.

[0015] In summary, the technical effects and advantages of this invention are as follows:

[0016] 1. This invention allows for the installation of a load rack after removing the rear seats, facilitating the carrying of supplies. The airdrop container loaded with supplies, along with the airdrop container launcher, aids in supply support. During the supply launch process, the load rack, airdrop container launcher, and airdrop container are all symmetrically distributed along the aircraft's center of gravity. Therefore, the overall change in the aircraft's center of gravity envelope is minimal during the airdrop container launch process.

[0017] 2. This invention uses a pre-spinning system and a rotor system controlled by the pre-spinning system. The rotor head in the rotor system has an adjustable position and can be flexibly balanced according to different loads, which helps to increase the effective load of the whole aircraft and improve takeoff efficiency.

[0018] 3. This invention, through the main propulsion system and the auxiliary power system for takeoff, increases the power output of the rotorcraft while meeting the requirements of large loads, thereby improving takeoff performance and safety. Attached Figure Description

[0019] 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.

[0020] Figure 1 This is a three-dimensional structural diagram of the present invention.

[0021] Figure 2 This is a schematic diagram of the structure of the housing after disassembly.

[0022] Figure 3 This is a schematic diagram of the structure after the load chamber of the present invention is installed.

[0023] Figure 4 This is a schematic diagram of the structure of the load cell housing after disassembly.

[0024] Figure 5 This is a schematic diagram of the connection structure between the shell load chamber and the throwing frame of the present invention.

[0025] In the diagram: 101, frame; 102, fuselage; 103, fuel tank; 104, rear seat; 105, airdrop container; 106, airdrop container drop rack; 107, servo motor; 108, binding rope; 201, propeller; 202, engine; 203, auxiliary power system; 301, pre-rotating motor; 302, gearbox; 303, drive shaft; 401, push-pull rod; 402, control stick; 403, rudder; 404, transmission rod; 501, rotor blade; 502, rotor head; 601, landing gear. Detailed Implementation

[0026] 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.

[0027] Example: Reference Figure 1 , Figure 3 The illustrated autogyro includes an airframe with a pilot's seat and two removable rear seats 104 arranged side-by-side and staggered on the left and right sides of the airframe. This three-seat autogyro can accommodate up to one pilot and two passengers. The rear seats 104 allow for staggered legroom, increasing space utilization. The left and right orientation helps avoid obstacles in the nose direction, and the placement of one seat on each side of the fuselage and at the front of the airframe increases visibility.

[0028] After the two rear seats 104 are removed, a space is created for installing the load rack. Two symmetrically distributed airdrop box launchers 106 can be installed on the load rack. An airdrop box 105 that can slide out is installed on the inner side of the airdrop box launcher 106. The load rack is located on the central axis of the aircraft structure, and the load rack, airdrop box launchers 106, and airdrop box 105 are all symmetrically distributed along the center of gravity of the aircraft structure. Therefore, during the airdrop box 105's release, the range of the aircraft's center of gravity envelope changes relatively little.

[0029] All airdrop container launchers 106 are inclined metal frames, and both the front and rear ends of the airdrop container launchers 106 are equipped with barriers to prevent the airdrop containers 105 from sliding forward and backward. The bottom of each airdrop container launcher 106 is equipped with a raised baffle to prevent the airdrop containers 105 from sliding downward. A binding rope 108 is installed on the raised baffle. The binding rope 108 is attached to the surface of the airdrop container 105 and is connected to the load compartment frame via a servo motor 107.

[0030] When the airdrop container 105 is dropped, the pilot controls the servo motor 107 through the control panel to loosen the lashing rope 108, thereby causing the raised baffle to unfold. The airdrop container 105, carrying cargo, slides out of the aircraft through the surface rail of the drop rack 106.

[0031] It is worth mentioning that in this application, the size of the drop rack 106 was controlled so that the distance between the raised baffles and the fuselage tires is greater than the distance between the propellers and the tires, ensuring that the drop box 105 is released beyond the distance between the propellers and the tires, and that it will not pose a safety hazard to the flight during the drop and fall process.

[0032] like Figure 2 , Figure 4 As shown, the fuselage structure includes a frame-type frame 101, a streamlined fuselage 102 mounted on the frame 101, and a fuel tank 103 mounted at the rear of the fuselage 102. The frames of the frame 101 are connected by bolts. The fuselage 102 has front and rear doors on both sides. The rear seats 104 are mounted on the frame 101 with screws. After the rear seats 104 are removed, a payload rack can be installed on the frame 101.

[0033] The fuel tank 103 has multiple layered baffles inside. This effectively reduces the impact force of the fuel inside the fuel tank 103 on the fuel tank 103 during flight along with the airframe structure, thereby enhancing the stability of the airframe structure.

[0034] The main propulsion system, consisting of a propeller 201 and an engine 202 that controls the operation of the propeller 201, is arranged at the rear of the frame 101. The auxiliary power system 203 is arranged at the front of the fuselage 102. The auxiliary power system 203 includes rotor arms symmetrically arranged and installed on the left and right sides of the front of the fuselage 102, which provide additional power for takeoff and improve the takeoff performance of the aircraft. When the propeller 201 is stationary, the blades of the propeller 201 are parallel to the rotor arms.

[0035] The frame 101 is equipped with a pre-spinning system and a rotor system controlled by the pre-spinning system. The pre-spinning system consists of a pre-spinning motor 301 mounted on the frame 101, a reducer 302 adapted to the pre-spinning motor 301, and a drive shaft 303 mounted on the output end of the reducer 302. The rotor system consists of two rotor blades 501 and a rotor head 502 connecting the two rotor blades 501. The rotor head 502 is mounted on the top of the drive shaft 303.

[0036] The pre-spin system employs an electric pre-spin system, which improves the efficiency, stability, and controllability of the rotor pre-spin. The rated pre-spin speed is set to ≥200 rpm; the time required to reach the rated pre-spin speed is ≤50 seconds. To reduce the space required for transporting and storing the rotorcraft, rotor blade 501 must be detachable and foldable. Rotor blade 501 uses all-composite material rotor blades, which are high in strength and have a long service life.

[0037] The frame 101 is equipped with a control system, which consists of a push-pull rod 401, a control stick 402, a rudder 403, and a transmission rod 404. The upper and lower ends of the push-pull rod 401 are connected to the rotor head 502 and the rocker arm by means of spherical bearings, and the middle end of the push-pull rod 401 is connected to the frame 101. The control stick 402 is mounted on the transmission rod 404 and is mounted on the inner side of the housing 102 and in a forward position. The rudder 403 is mounted on the rear end of the transmission rod 404 and moves under the control of the control stick 402 and the transmission rod 404.

[0038] The landing gear 601 is located below the fuselage 102. The landing gear 601 system adopts a tricycle layout, wherein the front landing gear includes a front wheel steering mechanism and a shock absorption mechanism, which has the functions of steering and shock absorption on the ground; the two rear main landing gears include a braking and shock absorption mechanism, which has the functions of braking and shock absorption on the ground.

[0039] 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. An autogyro, comprising an organic structure, characterized in that: The aircraft structure is provided with a driver's seat and two removable rear seats (104). The rear seats (104) are arranged side by side and staggered in the left and right directions of the aircraft structure. When the two rear seats (104) are removed, a space is formed for installing a load rack. Two symmetrically distributed airdrop box launchers (106) can be installed on the load rack. An airdrop box (105) that can slide out is installed on the inner side of the airdrop box launcher (106). The load rack is located on the central axis of the aircraft structure, and the load rack, airdrop box launcher (106) and airdrop box (105) are all symmetrically distributed along the center of gravity of the aircraft structure. The airdrop box throwing frame (106) is a metal frame with an inclined distribution, and the front and rear ends of the airdrop box throwing frame (106) are equipped with blocking frames to prevent the airdrop box (105) from sliding out in the front and rear directions. The bottom of each airdrop box throwing frame (106) is equipped with a raised baffle that can prevent the airdrop box (105) from sliding down. A binding rope (108) is installed on the raised baffle. The binding rope (108) is attached to the surface of the airdrop box (105), and the binding rope (108) is connected to the load compartment frame through a servo motor (107). The body structure includes a frame-type frame (101), a streamlined housing (102) mounted on the frame (101), and an oil tank (103) mounted behind the housing (102). The rear seat (104) is mounted on the frame (101) with screws. After the rear seat (104) is removed, a load cell can be installed on the frame (101).

2. The autogyro as described in claim 1, characterized in that: The oil tank (103) has multiple layered partitions inside.

3. The autogyro according to claim 1, characterized in that: The main propulsion system, consisting of a propeller (201) and an engine (202) that controls the operation of the propeller (201), is arranged at the rear of the frame (101). An auxiliary power system (203) is arranged at the front of the housing (102). The auxiliary power system (203) includes rotor arms symmetrically arranged and installed on the left and right sides of the front end of the housing (102). When the propeller (201) is stationary, the blades of the propeller (201) are parallel to the rotor arms.

4. The autogyro as described in claim 1, characterized in that: The frame (101) is equipped with a pre-spinning system and a rotor system controlled by the pre-spinning system. The pre-spinning system consists of a pre-spinning motor (301) mounted on the frame (101), a reducer (302) adapted to the pre-spinning motor (301), and a drive shaft (303) mounted on the output end of the reducer (302). The rotor system consists of two rotor blades (501) and a rotor head (502) connecting the two rotor blades (501). The rotor head (502) is mounted on the top of the drive shaft (303).

5. A gyroplane according to claim 1, characterized in that: The frame (101) is equipped with a control system, which consists of a push-pull rod (401), a control stick (402), a rudder (403), and a transmission rod (404). The upper and lower ends of the push-pull rod (401) are connected to the rotor head (502) and the rocker arm by means of spherical bearings, and the middle end of the push-pull rod (401) is connected to the frame (101). The control stick (402) is mounted on the transmission rod (404) and is mounted on the inner side of the housing (102) and in a forward position. The rudder (403) is mounted on the rear end of the transmission rod (404) and moves under the control of the control stick (402) and the transmission rod (404).

6. The autogyro according to claim 1, characterized in that: The landing gear (601) is arranged below the housing (102).

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