Power system of single-person jet aircraft

Abstract

The invention provides a power system of a single-person jet aircraft, the power system comprises a plurality of fixed engines and a plurality of tilting engines, the fixed engines are fixedly arranged on a force bearing frame, and the tilting engines are rotatably arranged on the force bearing frame; the fixed engine nozzle is obliquely arranged outwards relative to the Z axis of the body axis coordinate system of the aircraft; a nozzle of the tilting engine in a neutral state is obliquely arranged relative to a Z axis of a body axis coordinate system of the aircraft, and component forces of thrust of the tilting engine relative to all directions of the aircraft are changed by changing a tilting angle of the tilting engine relative to the aircraft, so that the attitude of the aircraft is adjusted; therefore, the rolling, pitching and yawing three-axis angular motion and the vertical axis total thrust of the aircraft can be controlled without adjusting the speed / thrust of the tilting engine, and then the aircraft can be controlled to move along the three axes; when the attitude of the aircraft is changed, the phenomenon of falling down or decelerating is avoided.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of manned aircraft, in particular to a power system of a single-person jet aircraft. BACKGROUND

[0002] The existing single-person aircraft includes jet flight suits, jet flight backpacks and flight skateboards. The three single-person aircrafts all provide thrust through jet engines. The jet flight suit requires the passenger's limbs to participate in force bearing and control through the cooperation of the engine on the back and the handheld engine, which is difficult to operate. The jet flight backpack class removes the requirement for the passenger's limb bearing capacity by configuring a bearing frame, but the platform is heavy. The flight skateboard installs the jet engine on the platform below the passenger's feet, but when taking off and landing, the engine is too close to the ground, which makes the engine unable to work stably, and a special hollow landing platform needs to be equipped, which seriously limits the application scenario. The total thrust, height and speed of the existing three single-person aircrafts need to rely on engine speed regulation / push force regulation to achieve freedom control, which requires high engine dynamic characteristics and is difficult to achieve.

[0003] As disclosed in the patent literature with Chinese patent number 202510077667.X, published on April 25, 2025, a low-altitude single-person aircraft powered by a miniature turbojet engine includes a flight backpack and two arm propulsion devices; an engine is arranged on the flight backpack and the arm propulsion device; the aircraft controls the attitude of the aircraft by adjusting the thrust of the engine, which is prone to operation errors. At the same time, due to the slow response of the turbojet engine speed and thrust regulation, the engine speed / thrust change has hysteresis, which further limits the control margin of the aircraft. At the same time, the engine of the aircraft is fixedly arranged, and the propulsion direction of the engine nozzle is fixed; when adjusting the engine thrust to change the attitude of the aircraft, the change of the engine thrust causes the change of the total vertical thrust of the aircraft, and the aircraft will appear to drop height / slow down. SUMMARY

[0004] Therefore, the purpose of the present application is to provide a power system of a single-person jet aircraft, which can change the attitude of the aircraft by changing the tilt angle of the tilt engine relative to the aircraft and changing the component force of the thrust of the tilt engine relative to each direction of the aircraft, without adjusting the speed / thrust of the tilt engine, so as to control the roll, pitch and yaw three-axis angular motion and the vertical axis total thrust of the aircraft, and then control the movement of the aircraft along the three-axis line, and the aircraft will not appear to drop height / slow down when changing the attitude of the aircraft.

[0005] In order to solve the above technical problems, the technical solution used by the present application is:

[0006] The power system of the single-person jet aircraft comprises multiple fixed engines and multiple tilting engines, the fixed engines are fixedly arranged on a load-bearing frame, and the tilting engines are rotatably arranged on the load-bearing frame; the jet nozzles of the fixed engines are outwardly inclined relative to the Z-axis of the aircraft body-axis coordinate system; and the jet nozzles of the tilting engines in the neutral state are inclined relative to the Z-axis of the aircraft body-axis coordinate system.

[0007] Preferably, the angle between the thrust direction of the fixed engine and the Z-axis of the aircraft body-axis coordinate system is θ; θ>0°.

[0008] Preferably, the angle between the thrust direction of the tilting engine and the Z-axis of the aircraft body-axis coordinate system is δ.

[0009] Preferably, δ is continuously adjustable within the range of 0°-90°.

[0010] Preferably, the angle between the line connecting the thrust point of the tilting engine and the geometric center of the aircraft and the X-axis of the aircraft body-axis coordinate system is α; the angle between the tilting axis of the tilting engine and the X-axis of the aircraft body-axis coordinate system is β; and α+β≠90°.

[0011] Preferably, the tilting engines are distributed at the two ends of the load-bearing frame, the tilting engines are arranged around the fixed engines, and the tilting engines and the fixed engines are arranged on the same horizontal plane to form a distributed power array.

[0012] The power system of the single-person jet aircraft has the following beneficial effects compared with the prior art:

[0013] The tilting engines are arranged, the tilt angle of the tilting engines relative to the aircraft is changed, the component forces of the thrust of the tilting engines relative to each direction of the aircraft are changed, and thus the attitude of the aircraft is adjusted; in this way, the roll, pitch and yaw attitude angles of the aircraft can be adjusted without adjusting the speed and thrust of the tilting engines, and thus the movement control of the aircraft along the three axes can be realized.

[0014] The fixed engines are arranged in an inclined manner, and the jet directions are radially outwardly inclined, which is beneficial to the diffusion of the exhaust gas and greatly improves the problem of heat aggregation at the center of the aircraft during take-off and landing and the problem of unstable operation caused by the intake of exhaust gas by the engines. The combination of the included angle α and the included angle β ensures the heading control effect of the aircraft. By arranging the outwardly inclined fixed engines and the outwardly inclined tilting engines in the neutral state, the overall vertical component force of the aircraft is unchanged during the adjustment of the attitude of the aircraft, the attitude control and the vertical total thrust control are decoupled, multiple tilting engines are cooperatively rotated, the tilt angle of part of the tilting engines relative to the aircraft is reduced to increase the vertical component force, the tilt angle of part of the tilting engines relative to the aircraft is increased to reduce the vertical component force, and the overall vertical component force is unchanged. When the attitude of the aircraft is changed, the phenomenon of falling height / speed reduction does not occur. Attached Figure Description

[0015] The above and other objects, features, and advantages of the invention will become clearer through a more detailed description of the preferred embodiments illustrated in the accompanying drawings. The same reference numerals denote the same parts throughout the drawings, and the drawings are not intentionally drawn to scale with actual dimensions; the focus is on illustrating the gist of the invention.

[0016] Figure 1 This is a three-dimensional schematic diagram of the application of the present invention in an aircraft.

[0017] Figure 2 This is a schematic diagram showing the connection between the control system and the load-bearing frame in this aircraft.

[0018] Figure 3 This is a topology diagram of the installation of the fixed engine and the tilting engine of the present invention.

[0019] Figure 4 This is a topological diagram of the tilt engine of the present invention in the Z-axis of the aircraft body axis coordinate system.

[0020] Figure 5 This is a schematic diagram of the tilting engine of the present invention in a neutral state.

[0021] Figure 6 This is a schematic diagram of the horizontal inward thrust of the tilting engine of the present invention.

[0022] Figure 7 This is another schematic diagram showing the horizontal inward thrust of the tilting engine of the present invention.

[0023] Figure 8 This is a schematic diagram of the tilting engine of the present invention, showing the thrust vertically upward.

[0024] Explanation of icon numbers:

[0025] 1. Load-bearing frame; 11. Back plate; 12. Boom; 121. Longitudinal truss; 122. Transverse partition; 123. Hand support; 13. Transverse truss.

[0026] Power system 2, stationary engine 21, tilting engine 22

[0027] Control system 3, drive motor 31, control joystick 32, display 33, rotary switch 34.

[0028] Oil supply system 4.

[0029] 5. Multi-point seat belt.

[0030] Install clamps 6. Detailed Implementation

[0031] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments, so that those skilled in the art can better understand the present invention and implement it. However, the embodiments are not intended to limit the present invention. In this embodiment, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention 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. Therefore, they should not be construed as limiting the present invention.

[0032] It should be noted that when one element is considered to be "connected" to another element, it can be directly connected to and integrated with the other element, or there may be an intervening element present. The terms "mounted," "one end," "the other end," and similar expressions used in this invention are for illustrative purposes only.

[0033] like Figures 1-7 As shown, a power system for a single-person jet aircraft is applied to the aircraft; the aircraft includes a load-bearing frame 1, a control system 3, and a fuel supply system 4; the power system 2, control system 3, and fuel supply system 4 are installed on the load-bearing frame 1.

[0034] The power system 2 includes multiple stationary engines and multiple tilting engines. The stationary engines are fixedly mounted on the load-bearing frame 1, while the tilting engines are rotatably mounted on the load-bearing frame 1. Preferably, the load-bearing frame 1 is equipped with mounting clamps 6. The mounting clamp 6 corresponding to the stationary engine 21 is fixed to the boom 12, and the mounting clamp 6 corresponding to the tilting engine 22 is hinged to the boom 12. The control system 3 is connected to the mounting clamp 6 corresponding to the tilting engine 22. The control system 3 drives the tilting engine 22 to rotate, thereby adjusting the tilt angle of the tilting engine 22 relative to the aircraft. The fuel supply system 4 is connected to the engine control units of the stationary engine 21 and the tilting engine 22.

[0035] By setting up a tilt engine 22, the tilt angle of the tilt engine 22 relative to the aircraft is changed, thereby changing the thrust of the tilt engine 22 nozzle relative to the aircraft in each direction and thus adjusting the attitude of the aircraft. In this way, without adjusting the speed / thrust of the tilt engine 22, the roll, pitch and yaw attitude angles of the aircraft can be adjusted, thereby achieving the motion control of the aircraft along the three axes.

[0036] The tilting engines 22 are distributed at both ends of the load-bearing frame 1, and are arranged around the fixed engines 21. The tilting engines 22 and the fixed engines 21 are arranged on the same horizontal plane to form a distributed power array.

[0037] Referring to Figure 1 As shown in the figure, in the present embodiment, two fixed engines 21 are provided, and four tilting engines 22 are provided.

[0038] In the direction of the Z-axis of the aircraft body-axis coordinate system, the nozzles of the fixed engines 21 are arranged outwardly inclined relative to the Z-axis of the aircraft body-axis coordinate system. The fixed engines 21 are arranged inclined, and the jet directions are radially outwardly inclined, which is conducive to the diffusion of the exhaust gas discharged outwardly, and greatly improves the problem of heat aggregation at the center of the aircraft during take-off and landing and the instability of operation caused by the intake of exhaust gas by the engine. Preferably, the angle between the thrust direction of the fixed engine 21 and the Z-axis of the aircraft body-axis coordinate system is θ; θ > 0°. In an embodiment, θ is 8°.

[0039] Referring to Figures 3-8 As shown in the figure, the center of gravity of the tilting engine 22 is located on the tilting axis, and the tilting range of the tilting engine 22 is 0°-90° relative to the vertical direction (referring to Figures 5-8 The dashed line). The neutral state of the tilting engine 22 is arranged inclined. Referring to Figure 6 and 7 As shown in the figure, the tilting engine is tilted to the maximum angle; referring to Figure 8 As shown in the figure, the tilting engine is tilted to the minimum angle. By arranging the outwardly inclined fixed engine 21 and the outwardly inclined tilting engine 22 in the neutral state, when adjusting the attitude of the aircraft, the overall vertical component force of the aircraft remains unchanged, ensuring that the attitude control and the vertical total thrust control are decoupled; specifically, the control system 3 drives the plurality of tilting engines 22 to rotate cooperatively, and the decrease of the tilting angle of part of the tilting engines 22 relative to the aircraft increases the vertical component force, and the increase of the tilting angle of part of the tilting engines 22 relative to the aircraft decreases the vertical component force, and the overall vertical component force remains unchanged.

[0040] The mounting state of the fixed engine 21 and the neutral state of the tilting engine 22 are both non-vertical upward thrust, which avoids the phenomenon that when adjusting the tilting state of the tilting engine 22, only the increase of the tilting angle of the tilting engine 22 relative to the aircraft decreases the vertical component force, which leads to the decrease of the overall vertical component force of the aircraft, and further leads to the decrease of the vertical total thrust of the aircraft, resulting in the phenomenon of falling height / speed reduction.

[0041] Referring to Figure 7 As shown in the figure, the center of gravity of the aircraft is located near the envelope center of the mounting positions of the tilting engines 22 and the fixed engines 21, and the envelope of the mounting positions of the engines has a horizontal half-axis length L lat , a longitudinal half-axis length L lon ; the thrust direction of the tilting engine 22 is the thrust axis of the tilting engine 22; and the tilting axis of the thrust direction of the tilting engine 22 is Ai, i = 1, 3, 4, 6, respectively corresponding to the four tilting engines 22.

[0042] The angle between the line connecting the thrust point of the tilt engine 22 (i.e. the midpoint of the tilt axis) and the geometric center of the aircraft and the X axis of the aircraft body axis coordinate system is α; the angle between the tilt axis of the tilt engine 22 and the X axis of the aircraft body axis coordinate system is β; α+β≠90°. The angle between the projection of the thrust line of the tilt engine 22 in the horizontal plane and the line connecting the thrust point (i.e. the midpoint of the tilt axis) and the geometric center of the aircraft is γ. By setting the combination of the angles α and β, the heading control effect of the aircraft is ensured.

[0043] Heading control moment

[0044]

[0045] From the geometric relationship, γ=α+β-90°; when α+β=90°, γ=0°, the heading control fails. Therefore, α+β≠90°. In a preferred embodiment

[0046] The angle between the thrust direction of the tilt engine 22 and the Z axis of the aircraft body axis coordinate system is δ, which is the tilt range of the tilt engine 22. δ is continuously adjustable in the range of 0°-90°. When the tilt engine 22 is in the neutral state, δ is set in the range of 10°-50°, and in a preferred embodiment

[0047] The load-bearing frame 1 includes a back plate 11 and an arm support 12, which is symmetrically arranged on both sides of the back plate 11, and the back plate 11 is connected with the two arm supports 12; the fixed engine 21 and the tilt engine 22 are arranged on the arm support 12, and in an embodiment, a transverse girder 13 is connected between the two arm supports 12.

[0048] The arm support 12 includes a plurality of transverse partitions 122 and longitudinal girders 121; the longitudinal girders 121 are arranged in the transverse partitions 122 and are detachably connected with the transverse partitions 122; the longitudinal girders 121 are made of light thin-walled pipes, and the transverse partitions 122 are provided with large-area weight-reducing hollows to reduce the weight of the arm support 12.

[0049] Preferably, the corner end points of the transverse partitions 122 are provided with connecting sleeves, corresponding holes are provided on the longitudinal girders 121 and the connecting sleeves, and light detachable rivets are connected through the holes of the longitudinal girders 121 and the connecting sleeves.

[0050] A plurality of multi-point safety belts 5 are arranged on the back plate 11, and the multi-point safety belts 5 are used for fixing the passengers and the aircraft; preferably, the multi-point safety belts 5 adopt quick-release devices with safety belts, and the passengers can be quickly released from the restraint of the aircraft. The fuel tank 41 is arranged on the back plate 11, and the fuel tank 41 is located between the two arm supports 12, so that the load-bearing frame 1 plays a roll cage role, and when an accident occurs, the two arm supports 12 protect the fuel tank 41 and the passengers.

[0051] Preferably, a palm rest 123 is arranged at the end of the armrest 12, and the palm rest 123 is used for assisting the support of the hand of the passenger.

[0052] The control system 3 comprises a driving motor 31, a remote control lever 32, a display 33 and a rotary switch 34. The driving motor 31 is connected with the mounting clamp corresponding to the tilt engine 22, and the remote control lever 32, the display 33 and the rotary switch 34 are arranged on the palm rest of the armrest 12.

[0053] In the present specification, unless explicitly specified and limited, a first feature is "on", "above" or "under" a second feature can be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature is "above", "over" and "on" the second feature can be that the first feature is directly above or obliquely above the second feature, or only means that the horizontal height of the first feature is higher than that of the second feature. The first feature is "below", "under" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or only means that the horizontal height of the first feature is less than that of the second feature.

[0054] In the description of the present specification, the description of the terms "preferred embodiment", "further embodiment", "other embodiment" or "specific example" means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, the different embodiments or examples described in the present specification and the features of the different embodiments or examples can be combined and combined by those skilled in the art without contradiction.

[0055] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above embodiments within the scope of the present application.

Claims

1. A power system for a single person jet vehicle, characterized by: The fixed engine is fixedly arranged on the load-bearing frame, and the tilting engine is rotatably arranged on the load-bearing frame; the fixed engine nozzle is outwardly inclined relative to the Z-axis of the aircraft body axis coordinate system; and the tilting engine nozzle is inclined relative to the Z-axis of the aircraft body axis coordinate system in the neutral state.

2. The single person jet aircraft power system of claim 1, wherein: The angle between the thrust direction of the fixed engine and the Z-axis of the aircraft body axis coordinate system is θ; θ>0°.

3. The single person jet aircraft power system of claim 1, wherein: The angle between the thrust direction of the tilting engine and the Z-axis of the aircraft body axis coordinate system is δ.

4. The single person jet aircraft power system of claim 3, wherein: The angle δ is continuously adjustable in the range of 0°-90°.

5. The single person jet aircraft power system of claim 3, wherein: The angle between the line connecting the thrust point of the tilting engine and the geometric center of the aircraft and the X-axis of the aircraft body axis coordinate system is α; the angle between the tilting axis of the tilting engine and the X-axis of the aircraft body axis coordinate system is β; and α+β≠90°.

6. The single person jet aircraft power system of claim 1, wherein: The tilting engines are distributed at both ends of the load-bearing frame, the tilting engines are arranged around the fixed engine, and the tilting engines and the fixed engine are arranged on the same horizontal plane to form a distributed power array.

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