Long-endurance flying backpack based on eddy current hybrid power

Abstract

The invention relates to a long-endurance flight backpack based on eddy current hybrid power. The long-endurance flight backpack comprises a power system, an electric propulsion system, a skeleton part, a manned part and a flight control system, the power system comprises an energy storage part and an energy conversion part. The efficient power utilization rate is achieved, long-endurance flight can be achieved, the optimal flight performance is met through flexible power distribution performance, meanwhile, the advantages of being environmentally friendly, good in economic performance and the like are achieved, low-altitude flight is met, and wide development prospects are achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft and relates to a long-endurance flying backpack based on turbo-electric hybrid power. Background Art

[0002] In recent years, breakthroughs in micro-aerodynamic technology have promoted the iteration and upgrade of individual flight equipment. Countries are accelerating the development of the next generation of highly maneuverable flying vehicles, aiming to break through the mobility limitations of personnel in traditional combat modes and emergency rescue scenarios. However, current individual flight devices generally adopt a pure jet propulsion architecture, and their power systems rely on multiple micro-turbojet engines to work together to achieve flight control through limb adjustment. For example, the "anti-gravity suit" jet flight suit launched by Gravity Industries in the UK uses 5 micro-turbojet engines (not 6), which are placed in the arms, back and waist to provide vertical take-off and landing and high-speed flight capabilities. Limited by fuel capacity and high fuel consumption of turbojet, the endurance time is about 3-5 minutes. The continuous flight time in actual tests is relatively short, and it is mainly used for military and rescue demonstrations. For example, the JB-11 jet backpack developed by Jetpack Aviation in the United States has a theoretical endurance time of 10 minutes, but it is shortened to 5-8 minutes during the actual test flight due to safety redundancy.

[0003] However, this type of design has many defects. Jet power systems have problems such as high fuel consumption rate, insufficient endurance and weak environmental adaptability. The fuel consumption rate of turbojet engines is generally high, resulting in a serious lack of endurance for the flight backpack. Even after optimization, transformation and upgrading, the endurance of existing jet-powered flight backpacks can only last for 3 to 10 minutes at most, which is difficult to meet the needs of long-term flight, thus limiting its performance.

[0004] In addition, the operator needs to maintain flight stability through high-intensity body movements, which causes both hands to be occupied by power control functions throughout the flight, seriously restricting the efficiency of tactical action execution and rescue mission implementation. Especially in complex battlefield environments or high-rise building rescue scenarios, the operator cannot free both hands to operate weapons or transfer trapped personnel, which greatly weakens the actual application value of the equipment. For example, in maritime interception combat scenarios, soldiers lose the ability to fire immediately because they continue to control the flight posture with both hands; in high-rise rescue missions, rescuers cannot directly transfer trapped personnel in a hovering state.

[0005] The existing technical bottlenecks can be summarized into the following core contradictions: on the one hand, the existing systems mostly use a single power source, which has poor energy utilization and lacks backup plans when the power is interrupted, which does not meet aviation-grade safety standards; on the other hand, there is a conflict between the high dependence of the jet propulsion system on limb control and the functional requirements of both hands in task execution. Although some studies have tried to reduce the difficulty of operation by increasing the degree of flight control automation, they have not been able to fundamentally free the operator's hands.

[0006] It is worth noting that the characteristic of jet power is to meet the needs of high-altitude and high-speed flight. However, under the current prospects of low-altitude economic development, propeller-powered aircraft can better meet a wide range of needs. In addition, although the pure electric system has the advantage of low noise, it is limited by the energy density of the battery and is difficult to meet the needs of long-distance or high-load missions.

[0007] Based on the above problems, it is urgent to develop a flying backpack that integrates a new power architecture and an intelligent control system to solve the bottleneck problem of existing technologies, with a theoretical cruising time of nearly 40 minutes, freeing the pilot's hands. Under the premise of ensuring maneuverability, through the coordinated design of the dual-propeller aerodynamic layout and the turbo-electric hybrid system, the strong dependence of existing technologies on the operator's body movements can be broken, while taking into account the requirements of high load capacity and low detectability, providing a disruptive solution for the next generation of individual flying equipment. Summary of the invention

[0008] In view of the shortcomings of the existing technology, the present invention aims to provide a long-endurance flying backpack based on turbo-electric hybrid power, including a power system, an electric propulsion system, a flight control system, an energy management system, a skeleton part, and a manned part. The energy utilization rate is improved by combining the turbine with electricity, and the flight endurance is extended; multiple energy supply methods improve the safety performance of the flying backpack; and the hands are controlled by the joystick and the intelligent system, which greatly frees the hands and meets more combat needs.

[0009] The present invention is achieved through the following technical solutions.

[0010] A long-endurance flying backpack based on turbo-electric hybrid power, including a power system, an electric propulsion system, a skeleton part, a manned part, and a flight control system;

[0011] The power system includes an energy storage part and an energy conversion part, and the energy storage part and the energy conversion part are installed on the skeleton part; the energy storage part includes a fuel tank and an energy storage lithium battery; the energy conversion part includes a turbojet engine, an axially through-type 90° curved vector nozzle, a DC brushless generator, and a transmission shaft. The turbojet engine and the DC brushless generator are connected through a transmission shaft to achieve energy transfer, the axially through-type 90° curved vector nozzle is connected to the turbojet engine turbine, and the axially through-type 90° curved vector nozzle is placed between the turbojet engine and the DC brushless generator. The fuel tank is connected to the turbojet engine through an oil pipeline to supply aviation kerosene to the turbojet engine, the DC brushless generator is electrically connected to the energy storage lithium battery and the electric propulsion system, and the turbojet engine drives the DC brushless generator through the transmission shaft to operate and generate electricity, a part of which is supplied to the electric propulsion system, and a part of which is supplied to the energy storage lithium battery to store electrical energy;

[0012] The electric propulsion system comprises a rotor, a left rotor bracket of a rotor motor, a right rotor bracket, and a control mechanism, wherein the control mechanism comprises a support frame, one end of each of the left rotor bracket and the right rotor bracket is provided with a helical gear and supported by the support frame, the control mechanism is meshed with the helical gears of the left rotor bracket and the right rotor bracket, the other end of the left rotor bracket and the right rotor bracket is fixed with a rotor motor, and the rotor is connected to the rotating shaft of the rotor motor;

[0013] The skeleton part is used to install the power system, electric propulsion system, manned part, and flight control system. The power system is installed at the rear side, the electric propulsion system is installed at the upper end of the skeleton part, and the manned part and flight control system are installed at the front side of the skeleton part;

[0014] The passenger part includes a back cushion and a safety belt, the safety belt is arranged on the back cushion, and the back cushion is installed on the frame part;

[0015] The flight control system includes an electronic display screen, a directional control handle, and a signal collection and processing box. The flight control system is electrically connected to a lithium energy storage battery, which supplies power to the flight control system. The electronic display screen and the directional control handle are mounted on a skeleton portion, corresponding to the position of the pilot's hands. The signal processing box includes a signal receiving interface and a signal output interface, and the signal receiving interface is respectively connected to sensors in the sensor array. The signal collection and processing box processes data and regulates the forward and backward direction control motors and the left and right direction control motors in the electric propulsion system.

[0016] Furthermore, the energy storage lithium battery is placed above the fuel tank and connected via a lithium battery fixing slot. The fuel tank is placed above the mounting substrate embedded in the frame part, in a corresponding fuel tank fixing slot in the mounting substrate, and fixed by a cylindrical fixing plug.

[0017] Furthermore, the control mechanism also includes a first gear, a second gear, a third gear, a fourth gear, a fifth gear, a sixth gear, a front and rear direction control motor, and a left and right direction control motor. The first gear is installed at the end of the rotating shaft of the front and rear direction control motor and meshes with the second gear; the second gear is installed at the end of the left rotor bracket through a bearing, and the two can rotate around the axis independently without interfering with each other; the third gear and the fifth gear are both installed on the concentric bracket in the middle of the gear plate of the second gear through bearings, wherein the third gear cooperates with the rotating shaft of the left and right direction control motor and is driven by the left and right direction control motor, and the fifth gear is an auxiliary gear, has no drive, and plays a role in sharing the force; the fourth gear and the sixth gear are respectively located at the ends of the left rotor bracket and the right rotor bracket, wherein the fourth gear and the sixth gear are both meshed with the third gear and the fifth gear.

[0018] Furthermore, the skeleton part includes a mounting base plate, an energy conversion part structural connecting plate, a manned part structural connecting plate, an electric propulsion part structural connecting plate, and a symmetrically connected tilt tube. The energy conversion part structural connecting plate is arranged on the upper rear side of the mounting base plate, and the energy conversion part structural connecting plate is provided with bolt holes corresponding to the engine clamp and the generator clamp. The energy conversion part structural connecting plate is connected to the engine clamp and the generator clamp by bolts; the manned part connecting plate is arranged on the upper front side of the mounting base plate, and a slide groove is arranged on the manned part connecting plate. The connecting ribs in the manned part are connected to the manned part of the backpack skeleton through the slide groove. The structure is connected by a structural connecting plate, and the connecting ribs are arranged on the cushion; a slot corresponding to the size of the fuel tank is arranged on the installation base plate between the energy conversion part structural connecting plate and the human part connecting plate, and the fuel tank is embedded in the slot; an electric propulsion part structural connecting plate is arranged on the upper ends of the energy conversion part structural connecting plate and the human part connecting plate, and bolt holes corresponding to the support frame of the electric propulsion system are arranged on the electric propulsion part structural connecting plate, and the electric propulsion system is fixed by bolt connection; the symmetrically connected tilt tube is hollow inside, and is connected to the back side of the manned part structural connecting plate by welding, and the connecting tilt tube is used to install an electronic display screen and a direction control handle.

[0019] Furthermore, the manned part also includes a breastplate and connecting ribs, and the cushion includes a head pillow and a lumbar cushion. The head pillow is fixed to the upper end of the lumbar cushion by bottom bolts, and the head pillow is embedded with a high-density memory foam layer to adapt to the curvature of the cervical spine; the breastplate and the lumbar cushion are adjusted by a safety belt and are equipped with a locking mechanism; the safety belt adopts a double-sided slide rail to slide with the T-slot on the side of the lumbar cushion; the connecting ribs are made of carbon fiber reinforced nylon, embedded in the longitudinal groove on the back of the lumbar cushion, and fixed by four-point bolts to form a torsion-resistant support frame, and the connecting ribs are adapted to the slide grooves in the skeleton part.

[0020] Furthermore, the electronic display screen includes a display screen, a display screen shell, and a display screen fixing tube. The display screen is buckled in the display screen shell, and the display screen shell is integrally connected to the display screen fixing tube. The interior of the display screen fixing tube is a hollow structure. The electronic display screen power transmission line is connected to the charging interface on the display screen shell through the display screen fixing tube to charge the electronic display screen.

[0021] Furthermore, the direction control handle includes a grip body, a throttle trigger mechanism, and a handle fixing tube. The interior of the handle fixing tube is a hollow structure. The power transmission line is connected to the control handle through the handle fixing tube for signal transmission and power transmission.

[0022] Compared with the prior art, the advantages of the present invention are: improving energy utilization and extending flight time by combining a turbine with electricity; multiple energy supply methods improve the safety performance of the flying backpack; and the hands are controlled through a joystick and an intelligent system, which frees the hands to a great extent and meets a wider range of combat needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 A perspective view of the present invention;

[0024] Figure 2 Another perspective view of the present invention;

[0025] Figure 3 It is a power system diagram of the present invention;

[0026] Figure 4 This is a diagram of the energy storage part of the power system of the present invention;

[0027] Figure 5 It is a front view of the energy conversion part of the power system of the present invention;

[0028] Figure 6 It is a three-dimensional diagram of the energy conversion part of the power system of the present invention;

[0029] Figure 7 is a diagram of the electric propulsion system of the present invention;

[0030] Figure 8 It is a three-dimensional diagram of the skeleton part of the present invention;

[0031] Fig. 9 It is a three-dimensional view of the skeleton part of the present invention from another perspective;

[0032] Fig.10 A three-dimensional diagram of the manned portion of the present invention;

[0033] Fig.11 It is a three-dimensional diagram of the manned part of the present invention from another perspective;

[0034] Fig.12A three-dimensional diagram of the electronic display screen of the present invention;

[0035] Fig.13 A three-dimensional diagram of a signal collection and processing box of the present invention;

[0036] Fig.14 A three-dimensional diagram of the direction control handle of the present invention;

[0037] Fig.15 A control mechanism diagram of the electric propulsion system of the present invention;

[0038] Fig.16 It is the total power reference curve for level flight;

[0039] In the figure: 1. Power system, 2. Electric propulsion system, 3. Frame part, 4. Manned part, 5. Flight control system;

[0040] 11. Energy storage part, 12. Energy conversion part, 111. Fuel tank, 112. Energy storage lithium battery, 121. Turbojet engine, 122. Axial through-type 90° curved vector nozzle, 123. DC brushless generator, 124. Transmission shaft, 125. Engine clamp, 126. Generator clamp, 131. Main fuel tank, 133. Fuel pump, 134. Cylindrical fixed plug, 135. Lithium battery fixed slot, 136. Fuel inlet, 141. Charging interface, 142 output interface;

[0041] 21. rotor, 22. rotor protection cover, 23. rotor motor, 241. left rotor bracket, 242. right rotor bracket, 25. control mechanism protection cover, 26. electric propulsion control mechanism, 261. first gear, 262. second gear, 263. third gear, 264. fourth gear, 265. fifth gear, 266. sixth gear, 267. forward and backward direction control motor, 268. left and right direction control motor, 269. support frame;

[0042] 31. Installation base plate, 32. Energy conversion part structural connection plate, 33. Manned part structural connection plate, 34. Electric propulsion part structural connection plate, 351. Symmetrically connected tilting tube (right tube), 352. Symmetrically connected tilting tube (left tube);

[0043] 41. Headrest, 42. Breastplate, 43. Waist cushion, 44. Safety belt, 45. Connecting ribs;

[0044] 51. Electronic display screen, 52. Steering control handle, 53. Signal collection and processing box. DETAILED DESCRIPTION

[0045] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0046] like Figure 1 and Figure 2 As shown, a long-endurance flying backpack based on turbo-electric hybrid power includes a power system, an electric propulsion system, a skeleton part, a manned part, a flight control system, and an energy management system.

[0047] 1.1 Powertrain

[0048] like Figure 3 As shown, the power system (1) includes an energy storage part (11) and an energy conversion part (12).

[0049] 1.1.1 Energy storage

[0050] like Figure 4 As shown, the energy storage part (11) includes a fuel tank (111) and an energy storage lithium battery (112).

[0051] The energy storage lithium battery (112) is placed above the fuel tank (111) and connected via a lithium battery fixing slot (135); the fuel tank (111) is placed above a mounting base plate (31) embedded in the skeleton part (3), in a corresponding fuel tank fixing slot (311) in the mounting base plate (31), and fixed via a cylindrical fixing plug (134).

[0052] The fuel tank (111) includes a main fuel tank (131), a fuel pump (133), a cylindrical fixed plug (134), a lithium battery fixed slot (135), and a fuel input port (136). A fuel state sensor is installed inside the main fuel tank (131) to monitor the fuel level, fuel temperature, and fuel pressure; the fuel pump (133) is arranged above the main fuel tank (131) to supply fuel to the turbojet engine (121) through a fuel pipe; the cylindrical fixed plug (134) is arranged below the main fuel tank (131) to fix the fuel tank (111) on the mounting base plate (31) in the skeleton part (3); the fuel input port (136) is arranged on one side of the fuel pump (133), and when the fuel is exhausted, the fuel tank (111) can be refueled.

[0053] The energy storage lithium battery (112) comprises a charging interface (141), an output interface (142)

[0054] 1.1.2 Energy conversion part

[0055] like Figure 5 and Figure 6 As shown, the energy conversion part (12) includes a turbojet engine (121), an axially through-type 90° curved vector nozzle (122), a DC brushless generator (123), a transmission shaft (124), an engine clamp (125) and a generator clamp (126).

[0056] The turbojet engine (121) is connected to the brushless DC generator (123) via a transmission shaft (124), one end of the transmission shaft (124) is connected to the turbine shaft of the turbojet engine (121), and the other end is connected to the motor shaft of the brushless DC generator (123), thereby realizing energy transfer. The axially through-type 90° curved vector nozzle (122) is connected to the turbine of the turbojet engine (121) via a flange, and the axially through-type 90° curved vector nozzle (122) is placed between the turbojet engine (121) and the brushless DC generator (123), thereby ensuring the overall structural balance. The turbojet engine (121) is connected to the energy conversion part structural connection plate (32) in the skeleton part (3) via an engine clamp (125) via bolts, and the brushless DC generator (123) is connected to the energy conversion part structural connection plate (32) in the skeleton part (3) via a generator clamp (126) via bolts.

[0057] A long-endurance flying backpack based on turbo-electric hybrid power, whose energy conversion is achieved in the following way.

[0058] The fuel tank (111) supplies aviation kerosene to the turbojet engine (121). The aviation fuel burns in the combustion chamber of the turbojet engine (121), releasing heat energy that is converted into mechanical energy to drive the turbine to rotate. The turbine of the turbojet engine (121) is connected to the DC brushless generator (123) through a transmission shaft (124). The DC brushless generator (123) converts mechanical energy into electrical energy. A portion of the electrical energy is directly transmitted to the rotor motor (23) of the electric propulsion system (2) through a wiring harness, driving the rotor (21) to rotate and generate thrust, and the other portion is connected to the charging interface (143) of the energy storage lithium battery (112) of the energy storage part (11) through a wire, storing the electrical energy in the energy storage lithium battery (112) to prepare for the subsequent use of the rotor motor (23) of the electric propulsion system (2).

[0059] 1.2 Electric Propulsion System

[0060] like Figure 7 As shown, the electric propulsion system includes a rotor (21), a rotor protection cover (22), a rotor motor (23), a left rotor bracket (241), a right rotor bracket (242), a support frame (269), a control mechanism protection cover (25), and a control mechanism (26).

[0061] The left rotor bracket (241) and the right rotor bracket (242) are both provided with a bevel gear at one end and supported by a support frame (269), and a rotor motor (23) is fixed at the other end, a rotor protection cover (22) is fixed to one end of the rotating shaft of the rotor motor (23), and the rotor (21) is installed at the end of the rotating shaft of the rotor motor (23) and protected by a rotor protection cover (25).

[0062] The control mechanism (26) comprises a first gear (261), a second gear (262), a third gear (263), a fourth gear (264), a fifth gear (265), a sixth gear (266), a front-rear direction control motor (267), a left-right direction control motor (268), and a support frame (269). The first gear (261) is mounted on the end of the rotating shaft of the front-rear direction control motor (267) and meshes with the second gear (262); the second gear (262) is mounted on the end of the left rotor bracket (241) through a bearing, and the two can rotate around the axis independently without interfering with each other; the third gear (263) and the first gear (264) are mounted on the end of the rotating shaft of the left rotor bracket (241) and mesh with each other. The five gears (265) are all mounted on a concentric bracket in the middle of the gear plate of the second gear (262) through bearings, wherein the third gear (263) matches the rotating shaft of the left and right direction control motor (268) and is driven by the left and right direction control motor (268), and the fifth gear (265) is an auxiliary gear, which has no drive and plays a role in sharing the force; the fourth gear (264) and the sixth gear (266) are respectively located at the ends of the left rotor bracket (241) and the right rotor bracket (242), wherein the fourth gear (264) and the sixth gear (266) are meshed with the third gear (263) and the fifth gear (265).

[0063] 1.3 Skeleton

[0064] like Figure 8 and Fig. 9 As shown, the skeleton part (3) includes a mounting base plate (31), an energy conversion part structural connecting plate (32), a manned part structural connecting plate (33), an electric propulsion part structural connecting plate (34), and a symmetrically connected tilting tube (35).

[0065] Each structural connection plate is connected to the mounting substrate (31) and each structural connection plate is connected by means of a slot. The passenger part connection plate (33) is arranged on the front side above the mounting substrate (31), and a slide groove (331) is arranged on the passenger part connection plate (33). The connecting rib (45) in the passenger part (4) is connected to the passenger part structural connection plate (33) of the skeleton part (3) through the slide groove (331); the energy conversion part structural connection plate (32) is arranged on the rear side above the mounting substrate (31), and bolt holes corresponding to the engine clamp (125) and the generator clamp (126) are arranged on the energy conversion part structural connection plate (32), and the energy conversion part structural connection plate (32) is connected to the engine clamp (125) and the generator clamp (126) by bolts; the mounting substrate (31 ) is provided with a slot corresponding to the size of the fuel tank (111) so that the fuel tank is embedded in the safety base plate (31), and the safety base plate (31) is also provided with a fuel tank fixing slot (311) corresponding to the cylindrical plug block (113) on the bottom surface of the fuel tank (111); the electric propulsion part structure connecting plate (34) is provided with bolt holes corresponding to the control mechanism protection cover (25) and the support frame (269) of the electric propulsion system (2), and the electric propulsion system (2) is fixed by bolt connection; the symmetrical connecting tilt tube (35) is hollow inside and is connected to the back of the manned part structure connecting plate (33) by welding, and an opening is provided on the top, and the connecting tilt tube (35) is used to install an electronic display screen (51) and a direction control handle (52).

[0066] 1.4 Manned part

[0067] like Fig.10 and Fig.11 As shown, the manned part (4) is composed of a head pillow (41), a breastplate (42), a waist cushion (43), a safety belt (44) and connecting ribs (45).

[0068] The headrest (41) is fixed to the upper end of the waist cushion (43) by bottom bolts, and a high-density memory foam layer is embedded in it to adapt to the curvature of the cervical spine; the breastplate (42) and the waist cushion (43) are adjusted by the safety belt (44), and a locking mechanism is configured; the safety belt (44) is connected to the T-slot on the side of the waist cushion (43) by double-sided slide rails, and the tightness can be adjusted by ±5cm in the vertical direction; the connecting ribs (45) are made of carbon fiber reinforced nylon, embedded in the longitudinal groove on the back of the waist cushion (43), and fixed by four-point bolts to form a torsion-resistant support frame. Standardized quick-release buckle interfaces are used between the components to achieve modular assembly without tools, and an anti-slip limit pin is provided at the hinge between the breastplate (42) and the waist cushion (43). The overall structure is designed with multi-point mechanical dispersion to evenly distribute the pressure on the shoulder, thorax and lumbar region to meet the requirements of ergonomic adaptation.

[0069] 1.5 Flight Control System

[0070] like Figure 12 to Figure 14 As shown, the flight control system (5) includes an electronic display screen (51), a direction control handle (52), and a signal collection and processing box (53). The flight control system (5) is electrically connected to an energy storage lithium battery (112), and the energy storage lithium battery (112) supplies power to the flight control system (5).

[0071] The electronic display screen (51) comprises a display screen (511), a display screen housing (512), and a display screen fixing tube (513). The display screen (511) is buckled in the display screen housing (512), the display screen housing (512) and the display screen fixing tube (513) are integrally connected, the interior of the display screen fixing tube (513) is a hollow structure, and the power transmission line of the electronic display screen (52) is connected to the charging interface on the display screen housing (512) through the display screen fixing tube (513) to charge the electronic display screen (51).

[0072] The direction control handle (52) comprises a grip body (521), a throttle trigger mechanism (522), and a handle fixing tube (523). The handle fixing tube (523) is hollow in structure, and a power transmission line is connected to the control handle (52) through the handle fixing tube (523) for signal transmission and power transmission.

[0073] The signal processing box (53) includes a signal receiving interface (531) and a signal output interface (532). The signal processing box (53) is fixed above the structural connection plate (32) of the energy conversion part of the skeleton part (6), and is respectively connected to sensors in a sensor array (not shown in the figure). The signal collection processing box (53) processes data and regulates the front and rear direction control motor (267) and the left and right direction control motor (268) in the electric propulsion system (2), thereby controlling the flight attitude.

[0074] The present invention controls the flight attitude by adjusting the operating rod, as follows:

[0075] like Fig.15 As shown, the joystick control device includes a direction joystick (52) and a throttle trigger mechanism (522). When manual operation is required, the driver can operate the joystick (52) to control the flight backpack. The throttle trigger mechanism (522) controls the rotation speed of the two rotor motors. When the driver operates the throttle trigger mechanism (522) to press forward, the rotation speed of the two rotor motors increases, and the thrust provided also increases; when the driver presses the throttle trigger mechanism (522) backward, the rotation speed decreases, and the thrust provided also decreases. In addition, the greater the angle of pressing, the greater the degree of thrust increase or decrease, thereby achieving control of the flight attitude.

[0076] The direction control handle (52) controls the rotation direction and rotation angle of the front and rear direction control motor (267) and the left and right direction control motor (268). Taking the thumb pointing to the center point of the control mechanism (26) as a reference direction and the direction pointed by other fingers in the right-hand rule representing the clockwise direction as an example, when the driver pushes the direction control handle (52) forward by a certain angle, the front and rear direction control motor (267) rotates counterclockwise by a certain angle, thereby driving the first gear (261) to rotate counterclockwise around the axis, and the second gear (262) to rotate clockwise around the axis, and the bracket in the middle of the gear plate of the second gear (262) and the third gear (263) and the fifth gear (265) drive the fourth gear (264) and the left rotor bracket (241) to rotate counterclockwise, and the sixth gear (266) and the right rotor bracket (246) to rotate clockwise, thereby driving the two rotors to flip forward by a certain angle at the same time, and finally generating a backward thrust. At this time, if the driver does not operate the direction control handle (52) or presses the throttle trigger mechanism (522) backward, the upward force component will decrease. When it is less than gravity, it can achieve forward and downward flight; if the driver presses the throttle trigger mechanism (522) forward, both the upward and forward force components increase. When the upward force component is equal to gravity, horizontal forward flight is achieved; when the upward force component is greater than gravity, forward and upward flight is achieved. On the contrary, when the driver pushes the direction control handle (52) backward at a certain angle, the two rotors flip backward at a certain angle to generate forward thrust, and then cooperate with the throttle trigger mechanism (522) to achieve backward and downward flight, horizontal backward direction, and backward and upward flight.

[0077] When the driver manipulates the direction control handle (52) to push to the left by a certain angle, the left and right direction control motor (268) rotates counterclockwise by a certain angle, driving the third gear (263) to rotate counterclockwise, the fourth gear (264) and the right bracket to flip clockwise, and the sixth gear (266) and the left rotor bracket (241) to flip clockwise, generating a torque. At this time, if the driver does not manipulate the direction control handle (52) or presses the throttle trigger mechanism (522) backward, the upward component force will be less than the gravity, and the flying backpack will rotate to the left by a certain angle and fly downward at the same time. If the driver presses the throttle trigger mechanism (522) forward, both the upward and forward component forces increase. When the upward component force is equal to the gravity, the flying backpack will rotate to the left by a certain angle horizontally. When the upward component force is greater than the gravity, the flying backpack will rotate to the left by a certain angle and fly upward at the same time. On the contrary, when the pilot pushes the direction control handle (52) to the right by a certain angle, in conjunction with the throttle trigger mechanism (522), the flying backpack can be rotated to the right by a certain angle while flying downward, rotated to the right by a certain angle horizontally, and rotated to the right by a certain angle while flying upward.

[0078] 2.1 Energy distribution in different flight modes

[0079] According to the adjustment of the flight control system and the energy management system, a long-endurance flying backpack based on turbo-electric hybrid power is controlled in different flight modes, including vertical take-off and landing mode, high-speed cruise mode, emergency hovering mode, and hybrid power climbing mode.

[0080] The total weight of the turbo-electric hybrid flying backpack under this design structure (including the pilot's own weight) is about 148kg, and the gravity is 1450N.

[0081] According to the calculation formula between power and thrust, the vertical hovering thrust power Where ρ = 1.225 is the air density, A is the equivalent rotor area (rotor length 0.5m, each rotor equivalent area 0.79m 2 ), T is the required thrust.

[0082] 1. Climb forward flight mode:

[0083] The hybrid mode is mainly used in fast climbing or load climbing stages. Assuming the climbing acceleration is 0.4g (about 4m / s 2 ), then the thrust in this stage needs to meet high power, T = m(g+a)≈2030.1N.

[0084] In this mode, the flight control system regulates the energy storage part, and the turbojet engine and energy storage lithium battery operate simultaneously, driving the rotor motor to drive the rotor to rotate at high speed to increase the total thrust.

[0085] 2. High-speed cruise mode:

[0086] The high-speed cruise mode is mainly used in the horizontal flight stage. In this stage, flight stability and aircraft endurance must be guaranteed to meet long-term flight requirements. The cruise thrust is about 1.3-1.5 times the vertical thrust. 巡航 =1.3×T 垂直 =2262.7N.

[0087] In this mode, the flight control system regulates the energy storage part, and the energy distribution is 100% turbine drive. At this time, all the energy comes from the turbojet engine, and the turbine runs at a constant speed at the optimal efficiency point, so that the fuel runs in the high-efficiency range. The turbojet engine drives the DC brushless generator to rotate through the transmission shaft to convert the mechanical energy generated by the turbojet engine into electrical energy. A part of it is directly used for the rotor motor to drive the rotor to rotate and generate thrust, and the other part is stored in the energy storage lithium battery to ensure efficient use of fuel. At the same time, the turbojet engine generates a large amount of jet through the combustion of fuel, which is ejected from the axial through-type 90° curved vector nozzle to compensate for the backpack to a certain extent. In this mode, the energy provided by the energy storage lithium battery accounts for a small part of the total power source, which is mainly used to fill the response delay of the turbojet engine and is only used as an energy backup plan.

[0088] 3. Hover mode:

[0089] The emergency hovering mode is mainly used in the stage of hovering in the air to perform tasks during the flight process. The thrust requirement required in this stage is about 1450N of its own gravity.

[0090] In this mode, the flight control system regulates the energy storage part, and the energy distribution is 20% battery drive + 80% turbine drive. Most of the energy supply comes from the turbine, which provides power to the rotor motor for full electric drive to cope with instantaneous power demand, overcome gravity to ensure successful hovering and complete the mission.

[0091] 4. Vertical take-off and landing mode:

[0092] The vertical take-off and landing mode is mainly used in the take-off or landing stage of the flying backpack. In this stage, the thrust needs to meet the short-term high power, plus 10% safety redundancy, T 垂直 =1.2×F G =1740.5N, and low noise and posture stability must be taken into consideration.

[0093] In this mode, the flight control system regulates the energy storage part, and the energy distribution is 100% battery drive + 100% turbine drive. In theory, the main energy comes from the energy storage lithium battery, which provides a large amount of power to the rotor motor to propel the rotor to rotate; the auxiliary energy source comes from the turbojet engine, which performs thrust compensation to reduce the battery load and stabilize the flight attitude.

[0094] The above four flight modes regulate the energy storage part through the flight control system to maximize fuel efficiency and improve fuel economy by more than 40%, so that the long-endurance flying backpack based on turbo-electric hybrid power has the endurance capability to meet various application needs.

[0095] 2.2 Beneficial Effects of the Invention

[0096] The structural design parameters of the present invention are as follows: fuel tank 28kg, battery 10kg, turbojet engine 15kg, generator 4kg, rotor drive motors on both sides totaling 10kg, rotors on both sides totaling 6kg, skeleton part (hollow structure) 8kg, other 2kg, pilot's own weight 65kg, total weight 148kg. Combined with the characteristics of the series turbo-electric hybrid system, the endurance time is estimated by comprehensively considering the fuel energy conversion efficiency, battery auxiliary strategy and flight power requirements.

[0097] 1. Theoretical Calculation

[0098] 1. First, estimate the flight power requirement of the present invention

[0099] According to the rotor propulsion power formula:

[0100]

[0101] Forward flight power: P 前飞 =P 诱导 +P 型阻 +P 废阻

[0102]

[0103] (Where T is the thrust generated by the rotor, ρ is the air density, ρ = 1.225kg / m 3 , A is the equivalent propulsion area, A = 0.79m 2 , C D0 is the blade drag coefficient, σ is the rotor solidity, Ω is the rotor angular velocity, A r is the reference area)

[0104] When in hover mode, at hover power reference,

[0105] Thrust requirement: 148kg total weight requires at least 148kg×9.8m / s 2 =1450N

[0106]

[0107] The total power curve for level flight is roughly as follows Fig.16 As shown:

[0108] According to the total power curve of level flight and the above formula, P 巡航 ≈28.1kW, P 爬升 ≈50.45kW, P 降落 ≈37.4kW

[0109] 2. Based on the above calculations, calculate the endurance time according to the time allocation of a task.

[0110] The flight time distribution is as follows: vertical take-off and landing accounts for about 5% (take-off + landing), high-speed cruising accounts for about 70%, hovering accounts for about 10%, and mixed climbing accounts for about 15%.

[0111] In high-speed cruise mode, the fuel consumption per hour of flight = cruise power × fuel consumption rate per unit time cruise power P 巡航 ≈28.1kW, fuel consumption rate 0.9kg / kWh

[0112] Fuel consumption = 28.1kW × 0.9kg / kWh = 25.29kg / h

[0113] The available fuel in the cruise phase is 28kg x 70% = 19.6kg

[0114] Cruising flight time = 19.6 / 25.29 = 0.77h = 46min

[0115] 2. After the above theoretical calculations, a conservative estimate of the battery life is made in combination with actual limitations. First, when operating at high power continuously, the turbine exhaust temperature needs to be controlled at 800-1000°C, and the battery needs to be liquid-cooled to maintain <40°C, otherwise the system may overheat and shut down (the actual battery life may be reduced by 20-30%). Secondly, to ensure the safety of fuel and batteries, the coexistence of aviation kerosene and lithium batteries requires strict fire isolation; or other structural supplementary designs may cause the weight of the present invention to increase, increasing the weight by about 3-5kg, which may slightly reduce the theoretical battery life. According to actual measurement reference comparison, the existing pure fuel jet backpack (such as JB12, 30kg fuel) has a battery life of 8-10 minutes. The hybrid power system uses electric energy assistance and efficiency optimization to increase the battery life by 3-4 times, which is in line with technical expectations.

[0116] 3. After the above theoretical calculations, the future optimization effect of the present invention is calculated. If components with more advantageous performance are used, such as SiC power electronic devices (efficiency increased to 98%) and high-temperature superconducting motors (efficiency> 95%), the total energy utilization rate can be increased to 35%, and the battery life can be extended to 50 minutes. If the intelligent power distribution is further optimized, when the power demand is low, the turbine generates electricity to charge the battery, and the battery assists the high-power segment, which can further reduce the average power and the battery life can reach 51 minutes. The component materials are designed to be lightweight, using carbon fiber materials or 3D printed components, reducing the weight by 10% (total weight reduced to 136kg), then the hovering power can be further extended.

[0117] 4. Under the condition of the same fuel consumption, the endurance of the present invention and the jet-powered flying backpack is calculated and compared.

[0118] A 28kg fuel tank can store 35L of aviation fuel, and the total fuel volume is 35L (Jet A-1, energy density is about 43MJ / kg). The fuel consumption rate of a typical micro turbojet engine (such as JetCat P400) is 0.5-1.2L / min / unit (depending on the thrust output), and the average fuel consumption per engine is 0.8L / min. Assuming the number of engines is 6 micro turbojets,

[0119] Total fuel consumption: 0.8 liters / minute × 6 = 4.8 liters / minute

[0120]

[0121] Taking into account the high thrust demand during takeoff and the safety limit on the remaining fuel, the actual flight time may be reduced to 5-6 minutes. Theoretical calculations have shown that under the same fuel consumption, the flight time of the present invention is 6 times that of a jet flight backpack, which is much longer than that of a jet-powered flight backpack.

[0122] In summary, under the above structural design, the theoretical endurance of a turbo-electric hybrid long-range flying backpack is about 40-50 minutes. In actual engineering applications, considering limitations such as thermal management and safety redundancy, the practical endurance is expected to be 35-40 minutes, which is significantly better than the current pure fuel or pure electric flying backpacks (the current products generally have an endurance of 5-10 minutes). In the future, through technical optimization, the endurance is expected to exceed 1 hour.

[0123] The above description is only a preferred embodiment of the present invention, and does not limit the implementation mode and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A long-endurance flying backpack based on turbo-electric hybrid power, characterized in that: It includes a power system (1), an electric propulsion system (2), a skeleton part (3), a manned part (4), and a flight control system (5); The power system (1) comprises an energy storage part (11) and an energy conversion part (12), wherein the energy storage part (11) and the energy conversion part (12) are mounted on the skeleton part (3); the energy storage part (11) comprises a fuel tank (111) and an energy storage lithium battery (112); the energy conversion part (12) comprises a turbojet engine (121), an axially through-type 90° curved vector nozzle (122), a DC brushless generator (123), and a transmission shaft (124); the turbojet engine (121) and the DC brushless generator (123) are connected via the transmission shaft (124) to achieve energy transfer; the axially through-type 90° curved vector nozzle (122) (122) is connected to the turbine of the turbojet engine (121); the axial through-type 90° curved vector nozzle (122) is placed between the turbojet engine (121) and the DC brushless generator (123); the fuel tank (111) is connected to the turbojet engine (121) through an oil pipeline to supply aviation kerosene to the turbojet engine (121); the DC brushless generator (123) is electrically connected to the energy storage lithium battery (112) and the electric propulsion system (2); the turbojet engine (121) drives the DC brushless generator (123) to operate and generate electricity through a transmission shaft (124); a part of the electricity is supplied to the electric propulsion system (2); and a part of the electricity is supplied to the energy storage lithium battery (112) to store electric energy; The electric propulsion system (2) comprises a rotor (21), a rotor motor (23), a left rotor bracket (241), a right rotor bracket (242), and a control mechanism (26), wherein the control mechanism (26) comprises a support frame (269), one end of each of the left rotor bracket (241) and the right rotor bracket (242) is provided with a helical gear and supported by the support frame (269), the control mechanism (26) is meshed with the helical gears of the left rotor bracket (241) and the right rotor bracket (242), the other ends of the left rotor bracket (241) and the right rotor bracket (242) are fixed with a rotor motor (23), and the rotor (21) is connected to the rotating shaft of the rotor motor (23); The frame part (3) is used to install a power system (1), an electric propulsion system (2), a manned part (4), and a flight control system (5); the power system (1) is installed at the rear side, the electric propulsion system (2) is installed at the upper end of the frame part (3), and the manned part (4) and the flight control system (5) are installed at the front side of the frame part (3); The passenger part (4) comprises a back cushion and a safety belt (44), wherein the safety belt (44) is arranged on the back cushion, and the back cushion is installed on the frame part (3); The flight control system (5) comprises an electronic display screen (51), a directional control handle (52), and a signal collection and processing box (53). The flight control system (5) is electrically connected to an energy storage lithium battery (112), and the energy storage lithium battery (112) supplies power to the flight control system (5). The electronic display screen (51) and the directional control handle (52) are mounted on the skeleton part (3) and correspond to the position of the pilot's hand. The signal processing box (53) comprises a signal receiving interface (531) and a signal output interface (532). The signal receiving interface (531) is respectively connected to sensors in the sensor array. The signal collection and processing box (53) processes data and regulates the front and rear direction control motor (267) and the left and right direction control motor (268) in the electric propulsion system (2).

2. A long-endurance flying backpack based on turbo-electric hybrid power according to claim 1, characterized in that: The energy storage lithium battery (112) is placed above the fuel tank (111) and connected via a lithium battery fixing slot (135); the fuel tank (111) is placed above a mounting base plate (31) embedded in the skeleton part (3) and in a corresponding fuel tank fixing slot (311) in the mounting base plate (31) and fixed via a cylindrical fixing plug (134).

3. The long-endurance flying backpack based on turbo-electric hybrid power according to claim 1 is characterized in that: The control mechanism (26) further comprises a first gear (261), a second gear (262), a third gear (263), a fourth gear (264), a fifth gear (265), a sixth gear (266), a front-rear direction control motor (267), and a left-right direction control motor (268). The first gear (261) is mounted on the end of the rotating shaft of the front-rear direction control motor (267) and meshes with the second gear (262); the second gear (262) is mounted on the end of the left rotor bracket (241) through a bearing, and the two can rotate independently around the axis without interfering with each other; the third gear (263) and the fifth gear (265) 265) are both mounted on a concentric bracket in the middle of the gear plate of the second gear (262) through bearings, wherein the third gear (263) is matched with the rotating shaft of the left and right direction control motor (268) and is driven by the left and right direction control motor (268), and the fifth gear (265) is an auxiliary gear, which has no drive and plays a role in sharing the force; the fourth gear (264) and the sixth gear (266) are respectively located at the ends of the left rotor bracket (241) and the right rotor bracket (242), wherein the fourth gear (264) and the sixth gear (266) are both meshed with the third gear (263) and the fifth gear (265).

4. The long-endurance flying backpack based on turbo-electric hybrid power according to claim 1 is characterized in that: The skeleton part (3) comprises a mounting base (31), an energy conversion part structural connecting plate (32), a manned part structural connecting plate (33), an electric propulsion part structural connecting plate (34), and a symmetrically connected tilting tube (35); the energy conversion part structural connecting plate (32) is arranged on the upper rear side of the mounting base (31); the energy conversion part structural connecting plate (32) is provided with bolt holes corresponding to the engine clamp (125) and the generator clamp (126); the energy conversion part structural connecting plate (32) is connected to the engine clamp (125) and the generator clamp (126) by bolts; the manned part connecting plate (33) is arranged on the upper front side of the mounting base (31); the manned part connecting plate (33) is provided with a slide groove (331); the connecting ribs (45) in the manned part (4) are connected to the backpack skeleton (34) through the slide groove (331). ) is connected to the manned part structure connecting plate (33), and the connecting rib (45) is arranged on the cushion; a slot corresponding to the size of the fuel tank (111) is arranged on the installation base plate (31) between the energy conversion part structure connecting plate (32) and the manned part connecting plate (33), and the fuel tank (111) is embedded in the slot; an electric propulsion part structure connecting plate (34) is arranged on the upper end of the energy conversion part structure connecting plate (32) and the manned part connecting plate (33), and a bolt hole corresponding to the support frame (269) of the electric propulsion system (2) is arranged on the electric propulsion part structure connecting plate (34), and the electric propulsion system (2) is fixed by bolt connection; the symmetrical connecting tilt tube (35) is hollow inside and is connected to the back of the manned part structure connecting plate (33) by welding, and the connecting tilt tube (35) is used to install an electronic display screen (51) and a direction control handle (52).

5. The long-endurance flying backpack based on turbo-electric hybrid power according to claim 1 is characterized in that: The manned part (4) also includes a breastplate (42) and connecting ribs (45), and the cushion includes a head pillow (41) and a waist cushion (43). The head pillow (41) is fixed to the upper end of the waist cushion (43) by bottom bolts, and the head pillow (41) is embedded with a high-density memory foam layer to adapt to the curvature of the cervical spine; the breastplate (42) and the waist cushion (43) are adjusted by a safety belt (44), and a locking mechanism is configured; the safety belt (44) adopts a double-sided slide rail and a T-slot on the side of the waist cushion (43) for sliding connection; the connecting rib (45) is made of carbon fiber reinforced nylon, embedded in the longitudinal groove on the back of the waist cushion (43), and fixed by four-point bolts to form a torsion-resistant support frame, and the connecting rib (45) is adapted to the slide groove (331) in the skeleton part (3).

6. The long-endurance flying backpack based on turbo-electric hybrid power according to claim 1 is characterized in that: The electronic display screen (51) comprises a display screen (511), a display screen housing (512), and a display screen fixing tube (513); the display screen (511) is buckled in the display screen housing (512); the display screen housing (512) and the display screen fixing tube (513) are integrally connected; the interior of the display screen fixing tube (513) is a hollow structure; a power transmission line of the electronic display screen (52) is connected to a charging interface on the display screen housing (512) through the display screen fixing tube (513) to charge the electronic display screen (51).

7. The long-endurance flying backpack based on turbo-electric hybrid power according to claim 1, characterized in that: The direction control handle (52) comprises a grip body (521), a throttle trigger mechanism (522), and a handle fixing tube (523); the handle fixing tube (523) has a hollow structure inside, and a power transmission line is connected to the control handle (52) through the handle fixing tube (523) for signal transmission and power transmission.

Images