Coaxial unmanned helicopter based on small turboshaft engine

Abstract

The present application discloses a coaxial unmanned helicopter based on a small turboshaft engine, and the coaxial unmanned helicopter based on the small turboshaft engine comprises: a fuselage structure, an avionics system and a battery are fixedly arranged at the upper end of the fuselage structure; a transmission system, a fuel system, a control system and a coaxial rotor system, and the control system and the coaxial rotor system are connected to the transmission system; a fairing is fixedly installed on the outside of the fuselage structure; compared with the single-rotor helicopter in the prior art, the present application has two upper and lower rotors with opposite directions, and the reversal of the double rotors offsets the fuselage anti-torque, so there is no tail rotor, which improves the hovering efficiency and carrying capacity of the helicopter; at the same time, the fuselage of the double-rotor coaxial helicopter is relatively compact and the external dimensions are small. Furthermore, the power mechanism of the present application adopts a small turboshaft engine, which further reduces the helicopter's own weight and reduces the fuel usage cost.

Description

Technical Field

[0001] The present application relates to a coaxial unmanned helicopter based on a small turboshaft engine. Background Art

[0002] Unmanned helicopter systems are one of the main means of unmanned warfare in various countries today. The more common unmanned helicopter platforms are usually powered by piston engines and use gasoline as the main fuel. In contemporary unmanned helicopters, both in terms of model and quantity, due to a long period of development and relatively mature technology, single-rotor unmanned helicopters with tail rotors have an absolute advantage.

[0003] The tail rotor of a single-rotor helicopter is a component that offsets the anti-torque of the main rotor. While consuming a certain amount of engine power and increasing the vibration and noise of the helicopter body, it is also one of the components with the highest accident rate in helicopters.

[0004] That is, the prior art has the following technical problem: the exposed tail rotor of an ordinary helicopter is easily damaged and causes failure. Therefore, in order to solve the above problem, a coaxial unmanned helicopter based on a small turboshaft engine is proposed. Summary of the invention

[0005] In this embodiment, a coaxial unmanned helicopter based on a small turboshaft engine is provided to solve the problem in the prior art that the exposed tail rotor of an ordinary helicopter is easily damaged and causes failure.

[0006] According to one aspect of the present application, a coaxial unmanned helicopter based on a small turboshaft engine is provided, and the coaxial unmanned helicopter based on the small turboshaft engine comprises:

[0007] A fuselage structure, wherein a landing unit is fixedly arranged at the bottom end of the fuselage structure;

[0008] An avionics system and a battery are fixedly arranged at the upper end of the fuselage structure;

[0009] A photoelectric ball is fixedly installed at the front lower end of the fuselage structure, and a power mechanism is fixedly installed at the rear end of the fuselage structure;

[0010] A transmission system, the transmission system being installed at the middle and upper end of the fuselage structure through a reduction gear;

[0011] A fuel system, wherein the fuel system is installed and fixed at the belly position of the fuselage structure;

[0012] A control system and a coaxial rotor system, wherein the control system and the coaxial rotor system are connected to a transmission system;

[0013] A fairing is fixedly installed on the outside of the fuselage structure.

[0014] Furthermore, the power mechanism is a small turboshaft engine, and the fuel system provides fuel for the small turboshaft engine.

[0015] Furthermore, the transmission system includes a primary reducer, a clutch, a coupling, a secondary reducer and a main rotor shaft, and the primary reducer, the clutch, the coupling, the secondary reducer and the main rotor shaft are connected in sequence.

[0016] Furthermore, the output end of the power mechanism is connected to a primary reducer.

[0017] Furthermore, the control system and the coaxial rotor system are mounted on the main rotor shaft of the transmission system, and the coaxial rotor system has two upper and lower rotors with opposite rotation directions.

[0018] Furthermore, the landing unit includes a fixing frame and a support leg. The fixing frame is fixedly arranged at the bottom end of the fuselage structure by bolts, and the support leg is fixedly connected to the bottom end of the fixing frame.

[0019] Furthermore, the lifting and lowering unit includes a fixing frame, a supporting frame, a limiting slider, an adjusting support leg, a connecting frame, an airbag and a fixing tube. The bottom end of the fixing frame is fixedly connected to the supporting frame, and both sides of the supporting frame are hingedly connected to the adjusting support leg.

[0020] Furthermore, a guide slot is provided inside the support frame, a limiting slider is slidably connected in the guide slot of the support frame, one end of the connecting frame is hingedly connected to the bottom surface of the limiting slider, and the other end of the connecting frame extends to the adjusting support foot and is hingedly connected to the adjusting support foot.

[0021] Furthermore, a servo motor is fixedly installed in the guide slot of the support frame, and one end of a threaded rod is fixedly connected to the end of the output shaft of the servo motor. The other end of the threaded rod is rotatably connected to the inner wall of the slot of the support frame, and the threaded rod passes through the limit slider and is threadedly matched with the limit slider.

[0022] Furthermore, a storage cavity is provided inside the adjusting leg, an airbag is fixedly provided in the storage cavity of the adjusting leg, a fixing cylinder is fixedly provided on the upper surface of the fixing frame, a piston is slidably connected in the inner cavity of the fixing cylinder, one end of a push rod is fixedly connected to one side of the piston, the other end of the push rod extends to the outside of the inner cavity wall of the fixing cylinder, a sliding frame is fixedly connected to one end of the push rod, the sliding frame is provided on the upper surface of the supporting frame and slidably cooperates with the supporting frame, the sliding frame is fixedly connected to the limiting slider, one end of a soft pipe is connected to the inner cavity of the fixing cylinder, and the other end of the soft pipe is connected to the inner cavity of the airbag.

[0023] Through the above-mentioned embodiments of the present application, compared with the single-rotor helicopter in the prior art, the present application has two upper and lower rotors with opposite directions. The reverse rotation of the double rotors offsets the anti-torque of the fuselage, so there is no tail rotor, which improves the hovering efficiency and carrying capacity of the helicopter; at the same time, the fuselage of the double-rotor coaxial helicopter is relatively compact and the external dimensions are small. Furthermore, the power mechanism of the present application adopts a small turboshaft engine, which further reduces the helicopter's own weight and reduces the fuel usage cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0025] Figure 1 This is a schematic diagram of a three-dimensional structure of an embodiment of the present application;

[0026] Figure 2 This is a schematic diagram of the internal structure of an embodiment of the present application;

[0027] Figure 3 This is a schematic diagram of the structure of a transmission system according to an embodiment of the present application;

[0028] Figure 4 This is a schematic diagram of the side structure of an embodiment of the present application;

[0029] Figure 5 This is a schematic diagram of the structure of the landing unit of the first embodiment of the present application;

[0030] Figure 6 This is a schematic diagram of the structure of the landing unit of the second embodiment of the present application;

[0031] Figure 7 This is a schematic diagram of the expansion of the adjustment legs of the second embodiment of the present application;

[0032] Figure 8 This is a schematic diagram of the interior of the fixing cylinder of the second embodiment of the present application.

[0033] In the figure: the lifting unit 1, the fixing frame 101, the supporting frame 102, the limiting slider 103, the threaded rod 104, the servo motor 105, the adjusting foot 106, the connecting frame 307, the air bag 108, the fixing cylinder 109, the piston 110, the push rod 111, the sliding frame 112, the foot 113;

[0034] Fairing 2, power mechanism 3, control system 4, coaxial rotor system 5;

[0035] Transmission system 6, primary reducer 601, clutch 602, coupling 603, secondary reducer 604, main rotor shaft 605;

[0036] Fuselage structure 7, avionics system 8, battery 9, fuel system 10, photoelectric bulb 11. DETAILED DESCRIPTION

[0037] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present application.

[0038] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any of their variations are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device comprising a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0039] In the present application, the terms "upper", "lower", "left", "right", "front", "back", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings. These terms are mainly used to better describe the present application and its embodiments, and are not used to limit the indicated devices, elements or components to have a specific orientation, or to be constructed and operated in a specific orientation.

[0040] In addition, some of the above terms may be used to express other meanings in addition to indicating orientation or positional relationship. For example, the term "on" may also be used to express a certain dependency or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0041] In addition, the terms "installed", "set", "provided with", "connected", "connected", and "socketed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, elements, or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0042] See also Figure 1-4 As shown, a coaxial unmanned helicopter based on a small turboshaft engine, the coaxial unmanned helicopter based on a small turboshaft engine comprises:

[0043] A fuselage structure 7, wherein a landing unit 1 is fixedly arranged at the bottom end of the fuselage structure 7;

[0044] An avionics system 8 and a battery 9 are fixedly installed at the upper end of the fuselage structure 7;

[0045] A photoelectric ball 11 is fixedly installed at the front lower end of the fuselage structure 7, and a power mechanism 3 is fixedly installed at the rear end of the fuselage structure 7;

[0046] A transmission system 6, wherein the transmission system 6 is installed at the middle and upper end of the fuselage structure 7 through a reduction gear;

[0047] A fuel system 10, wherein the fuel system 10 is installed and fixed at the belly position of the fuselage structure 7;

[0048] A control system 4 and a coaxial rotor system 5, wherein the control system 4 and the coaxial rotor system 5 are connected to a transmission system 6;

[0049] A fairing 2 is fixedly mounted on the outside of the fuselage structure 7 .

[0050] The power mechanism 3 is a small turboshaft engine, and the fuel system 10 provides fuel for the small turboshaft engine;

[0051] The transmission system 6 includes a primary reducer 601, a clutch 602, a coupling 603, a secondary reducer 604 and a main rotor shaft 605, wherein the primary reducer 601, the clutch 602, the coupling 603, the secondary reducer 604 and the main rotor shaft 605 are connected in sequence;

[0052] The output end of the power mechanism 3 is connected to the primary reducer 601. Through the technical solution, when the helicopter is working, the fuel system 10 provides fuel for the power mechanism 3, and then the power mechanism 3 transmits the power to the primary reducer 601, the clutch 602, the coupling 603 and the secondary reducer 604 in sequence through the output end, so that the high speed and small torque of the engine are converted into low speed and large torque power;

[0053] The control system 4 and the coaxial rotor system 5 are mounted on the main rotor shaft 605 of the transmission system 6. The coaxial rotor system 5 has two upper and lower rotors with opposite directions. Through the above technical solution, the stage reducer adopts a bevel gear, which can make the inner and outer shafts of the main rotor shaft rotate at the same speed and in opposite directions. At the same time, the upper and lower rotors of the rotor system are respectively installed on the inner and outer shafts, thereby realizing the coaxial reversal of the upper and lower rotors. The control system controls the rotor system to realize various flight attitude changes of the helicopter;

[0054] Embodiment 1:

[0055] See also Figure 5 As shown, the landing unit 1 includes a fixing frame 101 and a support leg 113. The fixing frame 101 is fixed to the bottom end of the fuselage structure 7 by bolts. The bottom end of the fixing frame 101 is fixedly connected with the support leg 113. Through this technical solution, it can be used for the landing support function of the device.

[0056] Embodiment 2:

[0057] See also Figure 6-8 As shown, the landing unit 1 includes a fixing frame 101, a supporting frame 102, a limiting slider 103, an adjusting support leg 106, a connecting frame 107, an airbag 108 and a fixing tube 109. The bottom end of the fixing frame 101 is fixedly connected to the supporting frame 102, and both sides of the supporting frame 102 are hingedly connected to the adjusting support leg 106;

[0058] The support frame 102 is provided with a guide slot inside, and a limit slider 103 is slidably connected in the guide slot of the support frame 102. One end of a connecting frame 107 is hingedly connected to the bottom surface of the limit slider 103, and the other end of the connecting frame 107 extends to the adjusting support leg 106 and is hingedly connected to the adjusting support leg 106.

[0059] A servo motor 105 is fixedly installed in the guide slide groove of the support frame 102, and one end of a threaded rod 104 is fixedly connected to the end of the output shaft of the servo motor 105. The other end of the threaded rod 104 is rotatably connected to the inner wall of the slide groove of the support frame 102. The threaded rod 104 penetrates the limit slider 103 and is threadedly matched with the limit slider 103. Through the technical solution, the servo motor 105 can drive the threaded rod 104 to rotate, so that the limit slider 103 can be moved by the rotation of the threaded rod 104, and the connection frame 107 can be driven to rotate angularly through the movement of the limit slider 103, thereby driving the adjustment leg 106 to rotate angularly, so that the adjustment leg 106 is unfolded, and the automatic unfolding function is realized;

[0060] The adjusting foot 106 is provided with a storage cavity inside, and an airbag 108 is fixedly provided in the storage cavity of the adjusting foot 106. A fixing cylinder 109 is fixedly provided on the upper surface of the fixing frame 101, and a piston 110 is slidably connected in the inner cavity of the fixing cylinder 109. One end of a push rod 111 is fixedly connected to one side of the piston 110, and the other end of the push rod 111 extends to the outside of the inner cavity wall of the fixing cylinder 109. A sliding frame 112 is fixedly connected to one end of the push rod 111, and the sliding frame 112 is provided on the upper surface of the support frame 102 and is slidably matched with the support frame 102. The sliding frame 112 is fixedly connected to the limiting slider 103, one end of a soft pipe is connected to the inner cavity of the fixed cylinder 109, and the other end of the soft pipe is connected to the inner cavity of the airbag 108. When the limiting slider 103 moves to expand the adjustment leg 106, it can drive the push rod 111 to move, thereby driving the piston 110 to move. Through the movement of the piston 110, the gas in the inner cavity of the fixed cylinder 109 is transported to the inner cavity of the airbag 108, so that the airbag 108 is expanded, so that it can float on the water surface and realize the function of landing on the water surface.

[0061] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A coaxial unmanned helicopter based on a small turboshaft engine, characterized by: The coaxial unmanned helicopter based on a small turboshaft engine comprises: A fuselage structure (7), wherein a landing unit (1) is fixedly arranged at the bottom end of the fuselage structure (7); An avionics system (8) and a battery (9) are fixedly arranged at the upper end of the fuselage structure (7); A photoelectric ball (11) is fixedly installed at the front lower end of the fuselage structure (7), and a power mechanism (3) is fixedly installed at the rear end of the fuselage structure (7); A transmission system (6), wherein the transmission system (6) is installed at the middle and upper end of the fuselage structure (7) through a reduction gear; A fuel system (10), wherein the fuel system (10) is installed and fixed at the belly position of the fuselage structure (7); A control system (4) and a coaxial rotor system (5), wherein the control system (4) and the coaxial rotor system (5) are connected to a transmission system (6); A fairing (2) is fixedly mounted on the outside of the fuselage structure (7).

2. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The power mechanism (3) is a small turboshaft engine, and the fuel system (10) provides fuel for the small turboshaft engine.

3. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The transmission system (6) comprises a primary reducer (601), a clutch (602), a coupling (603), a secondary reducer (604) and a main rotor shaft (605), wherein the primary reducer (601), the clutch (602), the coupling (603), the secondary reducer (604) and the main rotor shaft (605) are connected in sequence.

4. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The output end of the power mechanism (3) is connected to a primary reducer (601).

5. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The control system (4) and the coaxial rotor system (5) are mounted on the main rotor shaft (605) of the transmission system (6), and the coaxial rotor system (5) has two upper and lower rotors with opposite rotation directions.

6. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The landing unit (1) comprises a fixing frame (101) and a support leg (113); the fixing frame (101) is fixedly arranged at the bottom end of the fuselage structure (7) by means of bolts; and the support leg (113) is fixedly connected to the bottom end of the fixing frame (101).

7. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 1, characterized in that: The lifting and lowering unit (1) comprises a fixing frame (101), a supporting frame (102), a limiting slider (103), an adjusting support leg (106), a connecting frame (107), an air bag (108) and a fixing tube (109); the bottom end of the fixing frame (101) is fixedly connected to the supporting frame (102), and both sides of the supporting frame (102) are hingedly connected to the adjusting support leg (106).

8. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 7, characterized in that: A guide slot is provided inside the support frame (102), a limit slider (103) is slidably connected in the guide slot of the support frame (102), one end of a connecting frame (107) is hingedly connected to the bottom surface of the limit slider (103), and the other end of the connecting frame (107) extends to the adjusting support foot (106) and is hingedly connected to the adjusting support foot (106).

9. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 7, characterized in that: A servo motor (105) is fixedly installed in the guide groove of the support frame (102); one end of a threaded rod (104) is fixedly connected to the end of the output shaft of the servo motor (105); the other end of the threaded rod (104) is rotatably connected to the inner wall of the groove of the support frame (102); the threaded rod (104) passes through the limit slider (103) and is threadedly matched with the limit slider (103).

10. The coaxial unmanned helicopter based on a small turboshaft engine according to claim 7, characterized in that: The adjusting support leg (106) is provided with a storage cavity inside, an air bag (108) is fixedly provided in the storage cavity of the adjusting support leg (106), a fixing cylinder (109) is fixedly provided on the upper surface of the fixing frame (101), a piston (110) is slidably connected in the inner cavity of the fixing cylinder (109), one end of a push rod (111) is fixedly connected to one side of the piston (110), and the other end of the push rod (111) extends to the fixing cylinder (109). 109), a sliding frame (112) is fixedly connected to one end of the push rod (111), the sliding frame (112) is arranged on the upper surface of the support frame (102) and slides with the support frame (102), the sliding frame (112) is fixedly connected to the limiting slider (103), one end of a soft pipe is connected to the inner cavity of the fixed cylinder (109), and the other end of the soft pipe is connected to the inner cavity of the airbag (108).

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