A manned aircraft

Abstract

The application discloses a manned aircraft and relates to the technical field of aircraft equipment, and comprises a mounting frame, a first engine, a second engine and a third engine, wherein the first engine, the second engine and the third engine are arranged on the mounting frame, and the output directions of the first engine, the second engine and the third engine are the same; one first engine is arranged at the middle position of the mounting frame, four second engines are arranged at equal intervals in a circle on the periphery of the first engine, and two third engines are symmetrically arranged on the two sides of the four second engines; the axes of the first engine and the two third engines are in the same plane, and the jet ends of the first engine, the second engine and the third engine are respectively provided with an adjusting nozzle, so that the flight attitude control after the manned aircraft is realized.

Description

Technical Field

[0001] This invention relates to the field of aircraft equipment technology, specifically to a manned aircraft. Background Technology

[0002] With the advancement of technology, there are already manned aircraft capable of carrying a single person. These aircraft can carry a single person and operate them from the aircraft. They are powered by multiple high-power-density micro turbojet engines and can carry a simulated payload of 30 kg, achieving vertical take-off and landing, automatic hovering, and high-speed flight. However, existing aircraft still suffer from flight instability and difficulty in controlling flight attitude. Therefore, there is a need for a manned aircraft that can achieve more stable flight and maintain flight attitude. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of existing technologies by providing a manned aircraft.

[0004] It includes a mounting bracket, a first engine, a second engine, and a third engine. The first engine, the second engine, and the third engine are all mounted on the mounting bracket, and the first engine, the second engine, and the third engine have the same output direction.

[0005] One first engine is provided, located in the middle of the mounting bracket. Four second engines are provided, arranged at equal intervals around the first engine. Two third engines are provided, symmetrically arranged on both sides of the four second engines. The axes of the first engine and the two third engines are on the same plane. Each of the first, second, and third engines has an adjustable nozzle at its jet end.

[0006] Furthermore, the first engine, the second engine, and the third engine are all micro turbojet engines.

[0007] Furthermore, the output power of the first engine and the second engine is 20kg to 40kg; the output power of the third engine is 15kg to 35kg.

[0008] Furthermore, the output power of the first and second engines is 20kg, 21kg, 22kg, 23kg, 24kg, 25kg, 26kg, 27kg, 28kg, 29kg, 30kg, 31kg, 32kg, 33kg, 34kg, 35kg, 36kg, 37kg, 38kg, 39kg, or 40kg; the output power of the third engine is 15kg, 16kg, 17kg, 18kg, 19kg, 20kg, 21kg, 22kg, 23kg, 24kg, 25kg, 26kg, 27kg, 28kg, 29kg, 30kg, 31kg, 32kg, 33kg, 34kg, or 35kg.

[0009] Furthermore, the mounting bracket includes a main mounting plate, mounting legs, and a secondary mounting plate. The mounting legs are fixedly mounted on the lower end face of the main mounting plate. The first engine, the second engine, and the third engine are all vertically mounted on the main mounting plate. The first engine and four second engines are arranged interlaced on the main mounting plate, and two third engines are symmetrically arranged on both sides of the main mounting plate. The jet ends of the first engine, the second engine, and the third engine face towards the side closest to the mounting legs. The secondary mounting plate is rectangular and is mounted on the upper end face of the main mounting plate. The first engine and four second engines are all fixedly connected to the secondary mounting plate.

[0010] Furthermore, a frame is fixedly provided on the upper surface of the sub-mounting plate.

[0011] Furthermore, the main mounting plate is symmetrically provided with wearable shoes.

[0012] Furthermore, the adjusting nozzles on the first, second, and third engines are all capable of bidirectional adjustment and swinging. The hinge axes of the adjusting nozzles on the first engine and the two third engines are on the same straight line, the hinge axes of the adjusting nozzles on the four second engines are set at a 45° angle, and the extension lines of the hinge axes on the four adjusting nozzles pass through the first engine.

[0013] Furthermore, the regulating nozzle on the first engine can be adjusted and oscillated in four directions, and the regulating nozzles on the second and third engines can be adjusted and oscillated in two directions. The regulating nozzle on the first engine can be adjusted and oscillated in four directions: forward, backward, left, and right. The hinge axes of the four regulating nozzles on the second engines are set at a 45° angle, and the extension lines of the hinge axes on the four regulating nozzles pass through the first engine. The hinge axes of the two regulating nozzles on the third engines are on the same straight line, and the extension lines of the hinge axes on the two regulating nozzles pass through the first engine.

[0014] The advantages of this invention compared to the prior art are:

[0015] In this scheme, a first engine is set up to assist in control, four second engines are set up to handle the mixed control of forward and backward movement plus left and right movement, and two third engines are used for heading control. The scheme adopts a "5+2" configuration, that is, five engines provide elevator and roll power, and the engines on both sides are responsible for yaw and roll control. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of the scheme. Figure 1 ;

[0017] Figure 2 This is a schematic diagram of the overall structure of the scheme. Figure 2 ;

[0018] Figure 3 One method for adjusting the nozzle.

[0019] Reference numerals: 1. Mounting bracket; 2. First engine; 3. Second engine; 4. Third engine; 5. Adjusting nozzle; 6. Main mounting plate; 7. Mounting leg; 8. Secondary mounting plate; 9. Frame; 10. Wearing shoe. Detailed Implementation

[0020] Combined with appendix Figure 1-3 As shown, a manned aircraft includes a mounting frame 1, a first engine 2, a second engine 3 and a third engine 4. The first engine 2, the second engine 3 and the third engine 4 are all mounted on the mounting frame 1, and the output directions of the first engine 2, the second engine 3 and the third engine 4 are the same. The thrust generated by the first engine 2, the second engine 3 and the third engine 4 is used to lift and raise the personnel on the mounting frame 1.

[0021] One first engine 2 is provided, located in the middle of the mounting frame 1. Four second engines 3 are provided, arranged at equal intervals around the first engine 2. Two third engines 4 are provided, symmetrically arranged on both sides of the four second engines 3. The axes of the first engine 2 and the two third engines 4 are on the same plane. Each of the first engine 2, second engine 3 and third engine 4 has an adjustable nozzle 5 at its jet end. The thrust direction of each engine can be finely adjusted through the adjustable nozzles 5, thereby ensuring that the aircraft can move flexibly and maintain balance.

[0022] Preferably, the first engine 2, the second engine 3, and the third engine 4 are all micro turbojet engines, and the thrust generated by the micro turbojet engines is used to propel the user into flight.

[0023] This plan uses seven engines to propel the user into flight. Therefore, the thrust generated must be greater than the weight of the equipment plus the weight of the fuel and the weight of the human body. Based on the engines selected above, the number of engines required under normal load can be calculated.

[0024] Using a person's weight of 75kg and the weight of the load carried by the person of 30kg as design inputs, the effective load Fext is calculated as follows:

[0025] F ext =G 人 +G 携带负重 =75Kg + 30Kg = 105Kg 1

[0026] Based on the overall weight of the scaled-down prototype, the estimated weight of the manned skateboard structure, excluding the engine and electronic control unit, is Fst = 10 kg.

[0027] Meanwhile, the estimated weight of the electronic control system including the battery is Fel = 2Kg.

[0028] Therefore, we can derive the following formula:

[0029] N×F mo ×0.85≥A×(F ext +F st +F el +M+N×G mo )2

[0030] in:

[0031] N: Number of engines;

[0032] Fmo: Maximum thrust of a single engine;

[0033] A: Safety factor, set to 1.1;

[0034] M: Fuel weight carried;

[0035] Gmo: Weight of each turbojet engine.

[0036] Formula 2 calculates the number of engines required for safe flight for 5 minutes at 85% maximum throttle. The fuel consumption per minute per turbojet engine at 85% throttle is calculated to be 0.85 kg.

[0037] Therefore, the following formula can be derived to calculate m:

[0038] m = 0.85 × N × 5 3

[0039] Solving equations 2 and 3 simultaneously yields the following result:

[0040]

[0041] The design of the propulsion system requires extensive ground testing to obtain firsthand technical data. Based on takeoff weight requirements, the Xuanyun 40daN micro turbojet engine has been selected, with the following parameters: thrust 400N, single-engine weight 4kg, thrust-to-weight ratio 10, and maximum fuel consumption 1kg / min. Based on this, and estimating fuel consumption, a 10-minute loiter time would require 56kg of fuel. Considering the engine's thrust margin, fuel load, and loiter time requirements, and assuming the aircraft is at sea level and can hover at 80% throttle, 80% throttle is selected as the engine's primary operating state.

[0042] Therefore, the output power of the first engine 2 and the second engine 3 can be 20kg to 40kg; the output power of the third engine 4 can be 15kg to 35kg. The output power of the first engine 2 and the second engine 3 can be 20kg, 21kg, 22kg, 23kg, 24kg, 25kg, 26kg, 27kg, 28kg, 29kg, 30kg, 31kg, 32kg, 33kg, 34kg, 35kg, 36kg, 37kg, 38kg, 39kg or 40kg; the output power of the third engine 4 can be 15kg, 16kg, 17kg, 18kg, 19kg, 20kg, 21kg, 22kg, 23kg, 24kg, 25kg, 26kg, 27kg, 28kg, 29kg, 30kg, 31kg, 32kg, 33kg, 34kg or 35kg.

[0043] Preferably, the mounting bracket 1 includes a main mounting plate 6, mounting legs 7, and a secondary mounting plate 8. The mounting legs 7 are fixedly mounted on the lower end face of the main mounting plate 6. The first engine 2, the second engine 3, and the third engine 4 are all vertically mounted on the main mounting plate 6, and the main mounting plate 6 fixes the first engine 2, the second engine 3, and the third engine 4. The first engine 2 and the four second engines 3 are arranged interlaced on the main mounting plate 6, and the two third engines 4 are symmetrically arranged on both sides of the main mounting plate 6. Arranging the two third engines 4 on both sides of the main mounting plate 6 facilitates the lateral displacement of the aircraft. The thrust angle at the time increases the flight stability of the aircraft. The jet ends of the first engine 2, the second engine 3 and the third engine 4 face the side closer to the mounting leg 7. The mounting leg 7 can support the entire equipment when the aircraft is stationary, thereby ensuring that the user can stand stably on the aircraft when it is stationary. The auxiliary mounting plate 8 is rectangular and is mounted on the upper surface of the main mounting plate 6. The first engine 2 and the four second engines 3 are all fixedly connected to the auxiliary mounting plate 8. The auxiliary mounting plate 8 further fixes the first engine 2 and the second engine 3, thereby improving the stability of the mounting frame 1.

[0044] Preferably, a frame 9 is fixedly provided on the upper end surface of the auxiliary mounting plate 8. The frame 9 can increase the connection strength of the auxiliary mounting plate 8, and at the same time can make way for the air intake of the first engine 2 and the second engine 3. Placing objects that block the air intake of the first engine 2 and the second engine 3 may cause some engines to malfunction and pose a potential hazard.

[0045] Preferably, the main mounting plate 6 is symmetrically provided with wearable shoes 10, which are fixed to the main mounting plate 6. When using the shoes, the user fixes their feet in the wearable shoes 10 to ensure the user's stability in the air.

[0046] Implementation method 1 for adjusting nozzle 5: The adjusting nozzles 5 on the first engine 2, the second engine 3, and the third engine 4 can all be adjusted and oscillated in both directions. The hinge axes of the adjusting nozzles 5 on the first engine 2 and the two third engines 4 are on the same straight line. The hinge axes of the adjusting nozzles 5 on the four second engines 3 are set at a 45° angle, and the extension lines of the hinge axes on the four adjusting nozzles 5 pass through the first engine 2. In this implementation method, the first engine 2 assists in forward and backward control, the cooperation of the four second engines 3 achieves mixed forward and backward + left and right control, and the two third engines 4 are responsible for heading control, thereby ensuring the stable flight of the aircraft.

[0047] Implementation method two for adjusting nozzle 5: The adjusting nozzle 5 on the first engine 2 can be adjusted and swung in four directions. The adjusting nozzles 5 on the second engine 3 and the third engine 4 can be adjusted and swung in two directions. The adjusting nozzle 5 on the first engine 2 can be adjusted and swung in four directions: forward, backward, left, and right. The hinge axes of the four adjusting nozzles 5 on the second engine 3 are set at a 45° angle, and the extension lines of the hinge axes on the four adjusting nozzles 5 pass through the first engine 2. The hinge axes of the two adjusting nozzles 5 on the third engine 4 are on the same straight line, and the extension lines of the hinge axes on the two adjusting nozzles 5 pass through the first engine 2. In this implementation method, compared with the first implementation method, the first engine 2 is set to four-way control. The two swing axes of the first engine 2 are the same as the xb and yb axes of the aircraft coordinate system. The positive and negative ranges of the swing angle of the adjusting nozzles 5 of each engine are the same, and the rotation direction of the rotor of each engine is clockwise.

[0048] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0049] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0050] In the description of this invention, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0051] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A manned aircraft, characterized in that, It includes a mounting bracket (1), a first engine (2), a second engine (3) and a third engine (4), the first engine (2), the second engine (3) and the third engine (4) are all mounted on the mounting bracket (1), and the output directions of the first engine (2), the second engine (3) and the third engine (4) are the same; One first engine (2) is provided, and the first engine (2) is located in the middle of the mounting bracket (1). Four second engines (3) are provided, and the four second engines (3) are arranged in a circle at equal intervals around the first engine (2). Two third engines (4) are provided, and the two third engines (4) are symmetrically arranged on both sides of the four second engines (3). The axes of the first engine (2) and the two third engines (4) are on the same plane. The jet end of the first engine (2), the second engine (3) and the third engine (4) are respectively provided with an adjusting nozzle (5). The mounting bracket (1) includes a main mounting plate (6), mounting legs (7) and a secondary mounting plate (8). The mounting legs (7) are fixedly mounted on the lower end face of the main mounting plate (6). The first engine (2), the second engine (3) and the third engine (4) are all vertically mounted on the main mounting plate (6). The first engine (2) and the four second engines (3) are arranged interlaced on the main mounting plate (6). The two third engines (4) are symmetrically arranged on both sides of the main mounting plate (6). The jet ends of the first engine (2), the second engine (3) and the third engine (4) face the side closer to the mounting legs (7). The secondary mounting plate (8) is rectangular and is mounted on the upper end face of the main mounting plate (6). The first engine (2) and the four second engines (3) are all fixedly connected to the secondary mounting plate (8). The regulating nozzle (5) on the first engine (2) can be adjusted and swung in four directions. The regulating nozzles (5) on the second engine (3) and the third engine (4) can be adjusted and swung in two directions. The regulating nozzle (5) on the first engine (2) can be adjusted and swung in four directions: front, back, left, and right. The hinge axes of the four regulating nozzles (5) on the second engine (3) are set at a 45° angle, and the extension lines of the hinge axes on the four regulating nozzles (5) pass through the first engine (2). The hinge axes of the two regulating nozzles (5) on the third engine (4) are on the same straight line, and the extension lines of the hinge axes on the two regulating nozzles (5) pass through the first engine (2).

2. A manned aircraft according to claim 1, characterized in that, The first engine (2), the second engine (3) and the third engine (4) are all micro turbojet engines.

3. A manned aircraft according to claim 1, characterized in that, A frame (9) is fixedly installed on the upper surface of the sub-mounting plate (8).

4. A manned aircraft according to claim 3, characterized in that, Wearing shoes (10) are symmetrically arranged on the main mounting plate (6).

5. A manned aircraft according to claim 1, characterized in that, The regulating nozzles (5) on the first engine (2), the second engine (3) and the third engine (4) can all be adjusted and swung in both directions. The hinge axes of the regulating nozzles (5) on the first engine (2) and the two third engines (4) are on the same straight line. The hinge axes of the regulating nozzles (5) on the four second engines (3) are set at a 45° angle, and the extension lines of the hinge axes on the four regulating nozzles (5) pass through the first engine (2).

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