A low-altitude single-person aircraft powered by a micro-turbojet engine

Abstract

A low-altitude single-person aircraft powered by a micro-turbojet engine relates to the field of manned aircraft. The invention solves the problems of existing jet aircraft suits, such as heavy weight, inconvenient posture adjustment, and easy injury to the pilot. The invention comprises a flight backpack and two arm propulsion devices (7); the flight backpack comprises: a safety belt (1), a shell (2), an oil supply system (3), an electrical system (4), and a backpack micro-turbine engine (5); the oil supply system (3) is installed inside the shell (2), the electrical system (4) is installed on the upper end surface of the shell (2), and the backpack micro-turbine engine (5) is installed on the lower part of the shell (2); wherein the two arm propulsion devices (7) are respectively installed on the left and right sides of the shell (2) of the flight backpack. The flight backpack of the invention is the most complex component of a low-altitude single-person aircraft powered by a micro-turbojet engine. The invention is used in aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of manned aircraft, and in particular to a low-altitude single-person aircraft powered by a micro-turbojet engine. Background Art

[0002] Low-altitude, single-person aircraft powered by micro-turbojets, with their compact size and powerful power, offer new possibilities for rapid solo travel. These aircraft not only offer high speed limits and flexibility, but also play a vital role in specialized scenarios, such as mountain and maritime rescue. Rescuers equipped with these aircraft can quickly locate and rescue trapped individuals, providing emergency relief. Furthermore, low-altitude, single-person aircraft have extensive military applications. For example, a single-person aircraft developed by a British company has been used in numerous trials by the Royal Navy, demonstrating its superior performance in rapid transfers between warships at sea and in beach landing operations.

[0003] Let's take turbojet-powered single-person aircraft as an example. In the history of turbojet-powered single-person aircraft research, the three most classic products are the jet suit, the American jet pack, and the flying skateboard. While these three single-person aircraft have completely different design concepts, they all attempt to provide thrust by placing a miniature turbojet engine somewhere on the human body. The jet suit offers the best operational performance, and it also uses the human skeleton as a support structure to reduce external mechanical structure.

[0004] However, current jet suits are mainly driven by jet engines to achieve flight. However, since existing jet suits adopt various protective measures to ensure the safety of pilots, such as protective clothing (rigid backpack frames), they have the disadvantages of being heavy and inconvenient to wear. In addition, since the pilot performs posture operations while the turbojet engine is working, there will be vibration and thrust during the operation (it is difficult for the pilot to fully control the entire aircraft posture when operating multiple engines independently at the same time, and it is easy to make mistakes), which makes the operation process easy to get out of control. If the operation is improper, the fluid ejected by the turbojet engine may cause burns and other accidental injuries to the pilot.

[0005] In summary, existing jet suits have the problems of being heavy, difficult to adjust their posture, and prone to causing harm to pilots. Summary of the Invention

[0006] The purpose of the present invention is to solve the problems of existing jet suits, such as heavy weight, inconvenient posture adjustment, and easy harm to the pilot, and to provide a low-altitude single-person aircraft powered by a micro-turbojet engine.

[0007] The technical solution of the present invention is:

[0008] A low-altitude single-person aircraft powered by a micro-turbojet engine, comprising a flight backpack and two arm propulsion devices;

[0009] The flight backpack includes: a safety belt, a shell, a fuel supply system, an electrical system and a backpack micro-turbine engine. The fuel supply system is installed inside the shell, the electrical system is installed on the upper end surface of the shell, and the backpack micro-turbine engine is installed at the lower part of the shell.

[0010] The shell includes a back panel and a flight back cover. The back panel is a plate body, wherein a plurality of weight-reducing holes are opened on the upper portion of the back panel and the back panel is made of aluminum alloy. The back panel is provided with through holes around the periphery. The middle portion of the safety belt is fixed to the middle portion of the back panel by bolts and hawkbill hooks. The seat belt is connected to the pilot's body after passing through the through holes. The flight back cover is a shell cover, which is mounted on the back panel and has a filamentary mesh on the lower portion of the flight back cover.

[0011] Among them, the two arm propulsion devices are respectively installed on the left and right sides of the flying backpack shell;

[0012] Each arm propulsion device includes an engine bracket, two engines, a grip, a trigger, an arm bracket, a baffle bar and two sets of connecting rod assemblies. One end of the two sets of connecting rod assemblies are respectively installed on the left and right sides of the arm bracket, and the other ends of the two sets of connecting rod assemblies are respectively connected to an engine bracket. An engine is installed on each engine bracket. The grip is horizontally installed in the arm bracket, and the trigger is installed on the arm bracket.

[0013] Furthermore, the shell also includes a fabric layer, which is fixedly mounted on the backboard and located on the backboard at a side away from the flying back cover.

[0014] Furthermore, the shell also includes an EVA board, and the EVA board is wrapped on the fabric layer.

[0015] Furthermore, the fuel supply system includes a fuel tank, an air line, a refueling line, a filter, an oil pump and a ball valve. The air line and the refueling line are installed on the fuel tank. The filter, the oil pump and the ball valve are connected in sequence through pipelines. One end of the filter is connected to the inside of the fuel tank through a pipeline, and the other end of the ball valve is connected to the backpack micro-turbine engine through a pipeline to supply fuel to the backpack micro-turbine engine.

[0016] Preferably, the oil tank comprises a square box body and an oil level sensor, and the oil level sensor is vertically and sealedly inserted inside the square box body.

[0017] Preferably, the square box includes a box body, multiple transverse flow stabilizing wave-breaking plates, multiple longitudinal flow stabilizing wave-breaking plates and multiple front and rear flow stabilizing wave-breaking plates, multiple transverse flow stabilizing wave-breaking plates are arranged horizontally at equal intervals, longitudinal flow stabilizing wave-breaking plates are vertically installed on multiple transverse flow stabilizing wave-breaking plates, front and rear flow stabilizing wave-breaking plates are installed longitudinally and arranged perpendicular to the longitudinal flow stabilizing wave-breaking plates, multiple transverse flow stabilizing wave-breaking plates, longitudinal flow stabilizing wave-breaking plates and front and rear flow stabilizing wave-breaking plates constitute a wave-breaking plate assembly, and multiple wave-breaking plate assemblies are sequentially installed in the box body.

[0018] Furthermore, the plurality of transverse flow stabilizing and wave breaking plates, the plurality of longitudinal flow stabilizing and wave breaking plates, and the plurality of front and rear flow stabilizing and wave breaking plates are all provided with oil holes in a direction perpendicular to the plate body.

[0019] Preferably, the shape of the oil hole is a circular hole, a rectangular hole, a tapered hole or an elongated hole.

[0020] Furthermore, the electrical system includes a power battery, a first electronic control unit, a second electronic control unit, a flight attitude controller, a power management unit and an electrical system tray. The electrical system tray is connected to the backplane. The power battery and the flight attitude controller are installed on the electrical system tray in front and back. The first electronic control unit and the second electronic control unit are installed on the left and right sides of the flight attitude controller respectively. The power management unit is installed on the electrical system tray at the bottom of the flight attitude controller.

[0021] Furthermore, the flight attitude controller is provided with a host computer interface.

[0022] Compared with the prior art, the present invention has the following effects:

[0023] 1. The present invention provides a low-altitude single-person aircraft powered by a micro-turbojet engine. Compared with the existing technology, this backpack has good integrity by opening weight-reducing holes on the back panel and using lightweight materials for 3D printing. The weight of the back panel is greatly reduced. When the weight of other components cannot be reduced any further, the weight of the entire backpack is reduced while ensuring the strength of the back panel.

[0024] 2. The present invention is securely bound to the pilot through a safety belt. Since the safety belt is provided with a quick-release device, it can be quickly separated from the flight backpack when encountering danger or special circumstances, thereby avoiding harm to the pilot during the flight.

[0025] 3. This invention utilizes an electrical system to achieve position and control during flight, resulting in a high level of integration. It offers simple operation and high control precision. The flight backpack is equipped with a large-capacity fuel tank, a complete oil circuit, an electrical system, and a power system, providing a maximum thrust of 80 kg for a single-person aircraft and a rated endurance of 10 minutes. It also incorporates a flight attitude controller using a deep reinforcement learning controller to assist the pilot in flight.

[0026] 4. The main fuel tank of this invention has a very large capacity and is equipped with crisscrossing wave-breaking panels. The shape, size, and opening dimensions of the panels are determined through dynamic simulation, effectively reducing fuel sloshing during flight and improving the overall stability and controllability of the aircraft.

[0027] 5. The low-altitude single-person aircraft uses six micro-turbojet engines of two different models as its power system. Each engine is a black box to researchers. The micro-turbojet engine's ECU can only use speed control, which is very inconvenient for overall control. Therefore, a method is needed to achieve overall thrust control. First, step signal experiments of different amplitudes are conducted on each micro-turbojet engine to obtain a control model of the control signal and speed. Then, a control model between speed and thrust is obtained. Ultimately, a thrust control curve for each engine can be achieved, thereby achieving thrust control. The power system of the low-altitude single-person aircraft is generally divided into three parts: two arm propulsion units and a flight backpack propulsion unit. If the two engines in a single propulsion unit cannot be synchronized, bending and torsion will occur on the propulsion unit axis, which is detrimental to both the pilot and the stable control of the aircraft. Therefore, low-level control is required to synchronize each propulsion unit. The flight backpack in this invention uses system identification and low-level control technologies to achieve synchronization of each power unit, making the overall power output more stable and controllable, and the power changes smoother.

[0028] 6. After completing the structural design and algorithm design of the low-altitude single-person aircraft, design and build a test platform that can lift the pilot and equipment, and the lifting height should be adjustable. Complete routine flight tests and high-maneuverability flight tests on this test platform. Use the host computer to collect flight data in real time, establish a data set, and use the new data set to strengthen the deep learning model to obtain a better controller, and repeat this process until the desired control effect is achieved. After completing ground tests and algorithm optimization, test experiments are carried out in more complex environments, such as mountains and lakes, and the performance parameters of the low-altitude single-person aircraft are finally obtained. The flight altitude of the single-person aircraft in the present invention is set to 3-5m, which can ensure that the pilot has unimpeded access in low altitude areas; the flight speed is up to 120KM / h, allowing high-speed flight; the optimized controller ensures hovering stability and maneuverable flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic diagram of the overall effect of the present invention worn by a pilot.

[0030] Figure 2 It is a schematic diagram of the overall structure of the flying backpack of the present invention.

[0031] Figure 3Schematic diagram of the overall oil supply system applied to the backpack and the arm propeller A of the present invention.

[0032] Figure 4 It is a structural schematic diagram of the fuel tank of the present invention.

[0033] Figure 5 This is a schematic diagram of the layout of the electrical system.

[0034] Figure 6 It is a signal transmission diagram of the electrical system.

[0035] Figure 7 It is a structural diagram of the backplane.

[0036] Figure 8 It is a schematic diagram of the structure of a seat belt.

[0037] Figure 9 It is a schematic diagram of the three-dimensional structure of the flight back cover.

[0038] Figure 10 This is a physical picture of the present invention after removing the flight back cover, fuel supply system and electrical system.

[0039] Figure 11 yes Figure 10 side view.

[0040] Figure 12 yes Figure 10 rear view.

[0041] Figure 13 It is a physical diagram of the electrical system.

[0042] Figure 14 It is a schematic diagram of the host computer interface.

[0043] Figure 15 It is a structural diagram of the oil supply system.

[0044] Figure 16 It is a schematic diagram of the overall structure of the exterior of the fuel tank of the present invention.

[0045] Figure 17 It is a structural diagram of the arm propulsion device.

[0046] Figure 18 It is a structural diagram of the grip and trigger.

[0047] Figure 19 It is a parameter diagram of R and β in the arm propulsion device.

[0048] In the picture:

[0049] 1. Safety belt, 2. Shell, 2-1. Backboard, 2-2. Flight back cover, 2-3. Weight reduction holes, 2-4. Connection holes, 2-5. Wire mesh, 2-6. Fabric layer, 3. Fuel supply system, 3-1. Fuel tank, 3-2. Air line, 3-3. Fuel line, 3-4. Filter, 3-5. Fuel pump, 3-6. Ball valve, 3-7. Square box, 3-7-1. Box, 3-7-2. Horizontal flow stabilizer, 3-7-3. Longitudinal flow stabilizer, 3-7-4. Front and rear flow stabilizers, 3-7-5 , oil hole, 3-8, oil level sensor, 4, electrical system, 4-1, power battery, 4-2, first electronic control unit, 4-3, second electronic control unit, 4-4, flight attitude controller, 4-5, power management unit, 4-6, electrical system tray, 4-7, host computer interface, 5, backpack micro turbine engine, 6, bracket, 7, arm propulsion device, 8, engine bracket, 9, two engines, 10, grip, 11, trigger, 12, two sets of connecting rod assemblies, 13, arm bracket, 14, baffle bar. DETAILED DESCRIPTION

[0050] Specific implementation method 1: Combination Figures 1 to 18 To illustrate this embodiment, this embodiment includes a flying backpack and two arm propulsion devices 7;

[0051] The flight backpack includes: a safety belt 1, a shell 2, a fuel supply system 3, an electrical system 4, and a backpack micro-turbine engine 5. The fuel supply system 3 is installed inside the shell 2, the electrical system 4 is installed on the upper end surface of the shell 2, and the backpack micro-turbine engine 5 is installed at the lower part of the shell 2.

[0052] The housing 2 includes a back panel 2-1 and a flight back cover 2-2. The back panel 2-1 is a plate body, wherein a plurality of weight-reducing holes 2-3 are provided on the upper portion of the back panel 2-1. The back panel 2-1 is made of aluminum alloy and is provided with through holes 2-4 around the periphery of the back panel 2-1. The middle portion of the safety belt 1 is fixed to the middle portion of the back panel 2-1 by bolts and hawkbill hooks. The straps of the safety belt 1 pass through the through holes 2-4 and connect to the pilot's body. The flight back cover 2-2 is a housing cover. The flight back cover 2-2 is mounted on the back panel 2-1. A filamentary mesh 2-5 is provided on the lower portion of the flight back cover 2-2.

[0053] Among them, the two arm propulsion devices 7 are respectively installed on the left and right sides of the shell 2 of the flying backpack;

[0054] Each arm propulsion device 7 includes an engine bracket 8, two engines 9, a handle 10, a trigger 11, an arm bracket 13, a baffle bar 14 and two sets of connecting rod assemblies 12. One end of the two sets of connecting rod assemblies 12 are respectively installed on the left and right sides of the arm bracket 13, and the other ends of the two sets of connecting rod assemblies 12 are respectively connected to an engine bracket 8. An engine 9 is installed on each engine bracket 8. The handle 10 is horizontally installed in the arm bracket 13, and the trigger 11 is installed on the arm bracket 13.

[0055] The flying backpack of the present invention is used in conjunction with a low-altitude single-person aircraft. The low-altitude single-person aircraft powered by a micro-turbojet engine is composed of: an arm propulsion device, a flying backpack, a flight attitude controller and various electrical equipment. The overall appearance is as follows Figure 1 The figure shows the safety belt that secures the pilot to the aircraft. The main design specifications are a flight altitude of 4 meters, a flight time of approximately 10 minutes, a rated payload of more than 100 kg, the ability to hover at any position, and the ability to perform maneuverable flight.

[0056] The flying backpack of the present invention is the most complex component of a low-altitude single-person aircraft that uses a micro-turbojet engine as power.

[0057] The flying backpack uses two 40KG turbojets, that is, backpack micro-turbine engines 5 used in pairs, and their supporting fuel supply systems have been reasonably installed in the backpack through structural design. Figure 15 In addition, in order to ensure smooth fuel supply, the fuel tank is installed at a position not lower than the engine. In this flight backpack, the fuel supply system can supply fuel to 6 engines at the same time when actually used. Figure 3 , the layout of each oil circuit meets the conditions of smooth oil supply.

[0058] Before starting the design of each component, the present invention first conducts a force analysis on the entire aircraft to determine the relationship between the thrust required by each arm propulsion device, the thrust required by the flight backpack and the angle between the three when the aircraft is balanced, and then determines the selection and arrangement of the micro turbojet engine (finally, it is selected to place two 30KG thrust engines on the arm propulsion devices and two 40KG thrust engines on the flight backpack, using a total of 6 micro turbojet engines. The relevant analysis will be explained in the research basis).

[0059] The arm propulsion device in this embodiment is as follows Figure 17 and Figure 18 As shown in the figure, there are two key parameters in the arm propulsion device, R and β. R is the distance from the intersection of the two engine axes to the respective heads, and β is the angle between the engine axis and the arm propulsion axis. Figure 19As shown in . R and β are related to the overall size of the arm thruster, the maximum thrust that the arm thruster can produce, and whether the driver's forearm can be guaranteed to be absolutely safe from being burned by the engine exhaust gas.

[0060] After selecting the important design parameters R-β (R = 400mm, β = 20deg) through simulation and experiment, we can now fully design the arm propulsion device. The shape of the hand guard and grip is designed according to the 50% quantile arm and palm dimensions of the Chinese adult human body size GB / T10000-2023. Figure 18 The complex shape of the handguard is perfectly reproduced using 3D printing aluminum alloy. The opening near the elbow is elastic, allowing it to be tightened to the user's forearm using an additional clamping tool. The grip contains two self-resetting linear sensors. In actual use, applying reverse voltage to them produces two opposing signals. This not only ensures signal accuracy but also ensures reliability through redundant sensors.

[0061] The engine mount should be lightweight, not produce too much thermal deformation when the engine is running, and should also be securely clamped to the engine. The temperature of the engine housing should not exceed 130°C when running at full speed, so we chose 6061 aluminum alloy as the material for the engine mount. The inner wall size of the engine mount is an interference fit with the engine housing, and the two mounts are connected by bolts.

[0062] In addition, for details about the arm propulsion device in the present invention that are not described in detail, please refer to the invention patent with announcement number CN118790483A, which will not be repeated here.

[0063] Specific implementation method 2: Combination Figure 7 To illustrate this embodiment, the shell 2 of this embodiment further includes a fabric layer 2-6, which is fixedly mounted on the back plate 2-1 and located on the back plate 2-1 on a side away from the flying back cover 2-2.

[0064] With this arrangement, the fabric layers 2-6 of this embodiment reduce the weight of the entire housing 2 while providing a more comfortable fit in the area in contact with the pilot, alleviating discomfort caused by vibration and impact on the pilot's back. The remaining components and connections are the same as those in the first embodiment.

[0065] Specific implementation method three: Combination Figure 7 To illustrate this embodiment, the housing 2 of this embodiment further includes an EVA board, which is wrapped on the fabric layer 2 - 6 .

[0066] In this way, the EVA board plays a supporting role for the fabric layers 2-6 and also provides a carrier for the connection of the fabric layers 2-6 so as to better connect with the backboard. Other components and connection relationships are the same as those in the first or second embodiment.

[0067] Ergonomics needs to consider the comfort of carrying, the reliability of the pilot's fixation during flight, and the safety of the flight backpack when the engine is running. The back plate is made of a combination of aluminum alloy plate and EVA plate, such as Figure 7 As shown. To improve the reliability of the flight backpack, all components, except for the fuel lines and wiring harnesses, must be rigidly connected to the aluminum alloy backplate. The aluminum alloy plate has undergone significant weight reduction through topological optimization, resulting in a large gap where the plate meets the fuel tank. To improve safety, we plan to apply Kevlar fiber to this gap. This fiber has excellent flame retardancy and heat insulation properties. On the other side of the aluminum alloy plate is a fabric-wrapped EVA protective plate, which together form the flight backpack backplate. The fabric-wrapped EVA protective plate is relatively soft and can be attached with air cushions to further enhance the pilot's back comfort.

[0068] Specific implementation method four: Combination Figure 3 、 Figure 4 and Figure 15 To illustrate this embodiment, the fuel supply system 3 of this embodiment includes a fuel tank 3-1, an air pipeline 3-2, a fuel filling pipeline 3-3, a filter 3-4, an oil pump 3-5 and a ball valve 3-6. The air pipeline 3-2 and the fuel filling pipeline 3-3 are installed on the fuel tank 3-1, and the filter 3-4, the oil pump 3-5 and the ball valve 3-6 are connected in sequence through pipelines. One end of the filter 3-4 is connected to the interior of the fuel tank 3-1 through a pipeline, and the other end of the ball valve 3-6 is connected to the backpack micro-turbine engine 5 through a pipeline to supply fuel to the backpack micro-turbine engine 5.

[0069] With this arrangement, the fuel tank in the fuel supply system is the core of the entire fuel supply system, and the endurance is also mainly related to the size of the fuel tank. When designing a backpack fuel tank, it is necessary to consider the width of the human back, the comfort and stability of the fuel tank. The maximum fuel consumption of the engine used is 5280g / min (the rated thrust is 80% of the maximum thrust, and the fuel consumption can be converted by ×0.83), and the operating time is required to be no less than 5min. The fuel used is aviation kerosene RP-3, with a density of 775~830kg / m at 20°C. 3 .

[0070] Therefore, the required fuel tank capacity is between 0.02640 and 0.02827 cubic meters. To be on the safe side, a slightly larger capacity is selected to ensure sufficient fuel supply. The fuel tank capacity is about 0.029 cubic meters (ie 29 liters). The fuel tank is installed on a highly maneuverable flight backpack. In order to suppress excessive sloshing of fuel during the operation of the aircraft, a wave-breaking plate is installed inside the fuel tank. The shape and internal structure of the fuel tank are as follows Figure 4 The other components and connection relationships are the same as those in any one of the specific embodiments 1 to 3.

[0071] Specific implementation method five: Combination Figure 4 To illustrate this embodiment, the oil tank 3-1 of this embodiment includes a square box body 3-7 and an oil level sensor 3-8. The oil level sensor 3-8 is vertically and sealedly inserted inside the square box body 3-7.

[0072] With this arrangement, the tank is roughly square in shape, but the overall orientation is as shown in the figure. Figure 16 As shown by the red arrow, the top is designed to flow from low to high to guide the flow of fuel and gas and prevent air accumulation at the top. A larger breather valve (M10) is installed at this highest corner. The front of the fuel tank has an inclined surface (in front of the refueling port). Experience has shown that this design can reduce the generation of bubbles. The rest of the structure and components are the same as any of the first to fourth embodiments.

[0073] Specific implementation method six: combination Figure 4 to Figure 2 To illustrate this embodiment, the square box 3-7 of this embodiment includes a box 3-7-1, a plurality of transverse flow stabilizing and wave breaking plates 3-7-2, a plurality of longitudinal flow stabilizing and wave breaking plates 3-7-3, and a plurality of front and rear flow stabilizing and wave breaking plates 3-7-4.

[0074] Multiple transverse flow stabilizing wave-breaking plates 3-7-2 are arranged horizontally at equal intervals, longitudinal flow stabilizing wave-breaking plates 3-7-3 are vertically installed on the multiple transverse flow stabilizing wave-breaking plates 3-7-2, and front and rear flow stabilizing wave-breaking plates 3-7-4 are installed longitudinally and arranged perpendicularly to the longitudinal flow stabilizing wave-breaking plates 3-7-3. Multiple transverse flow stabilizing wave-breaking plates 3-7-2, longitudinal flow stabilizing wave-breaking plates 3-7-3 and front and rear flow stabilizing wave-breaking plates 3-7-4 constitute a wave-breaking plate assembly, and multiple wave-breaking plate assemblies are sequentially installed in the box body 3-7-1.

[0075] This arrangement, through the design of the installation method and position of the wave-breaking plate group, can effectively prevent the oil in the fuel tank from excessively strong shaking during the engine injection process. The other components and connection relationships are the same as any one of the specific embodiments 1 to 5.

[0076] The oil tank in this embodiment is preferably integrally formed, light in weight and with good integrity. The number of the transverse flow-stabilizing wave-breaking plates 3-7-2 in each group of wave-breaking plate assemblies is preferably three, and they are arranged at equal intervals up and down.

[0077] Specific implementation method seven: combination Figure 4 To explain this embodiment, the multiple transverse flow-stabilizing and wave-breaking plates 3-7-2, the multiple longitudinal flow-stabilizing and wave-breaking plates 3-7-3, and the multiple front and rear flow-stabilizing and wave-breaking plates 3-7-4 are each provided with oil holes 3-7-5 perpendicular to the plates. This arrangement ensures smooth oil flow while limiting the oil's vertical and horizontal fluctuations, thereby preventing instability during flight caused by excessive oil sloshing. The remaining components and connections are identical to those of any of the first through sixth embodiments.

[0078] Specific implementation method eight: combination Figure 4 To illustrate this embodiment, the shape of the oil hole 3-7-5 in this embodiment is a circular hole, a rectangular hole, a tapered hole or an elongated hole.

[0079] This arrangement makes it easy to select oil holes of different sizes according to different usage environments. Other components and connection relationships are the same as any one of the specific implementation methods one to seven.

[0080] Specific implementation method nine: combination Figure 5 and Figure 13 To illustrate this embodiment, the electrical system 4 of this embodiment includes a power battery 4-1, a first electronic control unit 4-2, a second electronic control unit 4-3, a flight attitude controller 4-4, a power management unit 4-5 and an electrical system tray 4-6.

[0081] The electrical system tray 4-6 is connected to the back panel 2-1, the power battery 4-1 and the flight attitude controller 4-4 are installed on the electrical system tray 4-6 in front and back, the first electronic control unit 4-2 and the second electronic control unit 4-3 are installed on the left and right sides of the flight attitude controller 4-4 respectively, and the power management unit 4-5 is installed on the electrical system tray 4-6 at the bottom of the flight attitude controller 4-4.

[0082] The aircraft's control signals come from triggers installed in the arm propulsion units and a master controller in the flight backpack. The pilot controls the thrust of the two arm propulsion units by pressing the two triggers, while the flight backpack's thrust is controlled by the master controller. The master controller controls the flight backpack's thrust based on the flight backpack's attitude, the two control signals from the triggers, and other sensor signals. Various control system components, including sensors, controllers, and power supplies, must also be properly installed in the backpack.

[0083] The arm propulsion system is equipped with a 30kg turbojet engine and uses a V3 ECU (referring to the first electronic control unit 4-2). The flight backpack is equipped with a 40kg turbojet engine and uses a V4 ECU (referring to the second electronic control unit 4-3). Both ECUs offer both wireless and wired control. Using wireless testing facilitates debugging and is very safe during testing, while using wired control in actual applications ensures reliability (wireless control can be reserved for remote monitoring).

[0084] The other components and connection relationships are the same as any one of the specific embodiments 1 to 8.

[0085] In this embodiment, the main controller is used in the flying backpack to collect sensor signals, design the control system, and output control signals to uniformly control the six turbojet engines. The power supply uses two 10000mAh 4S power batteries connected in series to ensure the power consumption of the electronic power system and the long flight life of the flying backpack. The electrical system of the flying backpack is mostly installed on the platform above the fuel tank. Except for the main controller and wiring harness, other electrical equipment such as Figure 5 As shown, the line connection is as follows Figure 6 shown.

[0086] Specific implementation method ten: Combination Figure 14 To describe this embodiment, the flight attitude controller 4 - 4 of this embodiment is provided with a host computer interface 4 - 7 .

[0087] The most complex electrical system is undoubtedly the flight attitude controller, which needs to communicate with two groups of ECUs to obtain their operating status in real time, and also needs to capture and filter four-way control signals from the grips of the two arm propulsion devices. At the same time, it needs to establish a deep learning controller to control six micro-turbojet engines in real time and at high frequency. The flight attitude controller circuit board is designed with a high-speed multi-channel ADC measurement module, a dual CAN communication module, a six-channel IMU measurement module, etc. It is designed with two chips, F103 is specifically responsible for collecting V3ECU group status signals, six-way IMU posture signals, grip control signals and transmitting them to F407 through CAN. F407 collects V4ECU group status signals and receives complex messages from F103, and controls the thrust of the six engines based on these sensor information. In addition, F407 has a spare CAN channel, which can use the host computer designed by us to collect information and control the aircraft during the experiment. The host computer interface is as follows Figure 14 .

[0088] The other components and connection relationships are the same as any one of the specific embodiments 1 to 8.

[0089] Combine Figures 1 to 16 The working principle of the present invention is described:

[0090] The straps of the flight backpack can use a six-point racing safety belt, and the end is installed on the flight backpack with an eagle hook and bolts. This kind of strap can bind the backpack firmly to the driver. The straps of the racing safety belt may put a lot of pressure on the driver's shoulders when carrying it, and installing a decompression shoulder strap on the strap can effectively solve this problem. The racing safety belt is very convenient to fix, and the end is an eagle hook with a screw, which can be screwed on the backboard. At the same time, the racing safety belt has a quick release device, and the driver can quickly separate from the flight backpack through the quick release device when encountering an emergency problem. The flight backpack can use the Sino SNK5D01-2 six-point safety belt, such as Figure 8 shown.

[0091] A mounting rack is also required on the flight backpack, on which the arm thruster bracket and the flight backpack bracket are installed. When the single-person aircraft is not started, the equipment should be able to stand steadily on the ground, so that the flight backpack body and the arm thruster device are kept at a safe distance from the ground. When starting, you can first ignite the warm-up engine to allow the six engines to generate a certain thrust to offset the gravity of the flight backpack itself. Then, the pilot wears the single-person aircraft in a half-squatting position. After standing up, the pilot operates the trigger of the arm thruster to achieve low-altitude free flight. After landing, the pilot releases the trigger and places the arm thruster on the arm thruster bracket. At this time, each engine enters the idle state, the pilot unfastens the seat belt and leaves, and the single-person aircraft can still stand steadily on the ground. The mounting rack, arm thruster bracket, and flight backpack bracket are as follows Figure 9 shown (cover not shown).

[0092] The cover is designed to reduce the resistance during flight and protect the electronic / mechanical components in the flight backpack. The flight backpack is large in size, so the cover is also large, which makes the processing cost rise sharply. If it is completely dependent on 3D printing, the processing cost of the cover will not be less than 15,000 yuan, so we use a combination of 3D printed nylon skeleton and nylon plate, with an estimated cost of 1,000 yuan. The cover near the engine installed in the flight backpack is replaced with wire mesh, which can ensure sufficient air intake for the engine and avoid the nylon melting due to radiant temperature heat. Cover such as Figure 10 shown.

[0093] Ergonomic considerations include carrying comfort, pilot securement during flight, and the safety of the flight pack when the engine is running. The backplate is a combination of aluminum alloy and EVA panels. To improve the reliability of the flight pack, all components, except for the fuel lines and wiring harness, must be rigidly connected to the aluminum alloy backplate. The aluminum alloy plate has undergone significant weight reduction through topological optimization, resulting in a large gap where the aluminum alloy plate meets the fuel tank. To improve safety, we plan to apply Kevlar fiber to this gap. This fiber has excellent flame retardancy and heat insulation properties. On the other side of the aluminum alloy plate is a fabric-wrapped EVA protective plate, which together form the flight pack backplate. The fabric-wrapped EVA protective plate is relatively soft. Air cushions can be attached to it to further improve back comfort for the pilot. The arm thruster bracket and flight pack bracket are mounted on the mount. When the single-person aircraft is not powered on, the equipment should be able to stand steadily on the ground, keeping the flight pack body and arm thruster at a safe distance from the ground. (See the actual product.) Figures 11 to 12 shown.

[0094] The flight pack's electrical system primarily consists of a power battery, a V3 ECU, a V4 ECU, a flight attitude controller, and a power management unit. We selected two high-capacity 10,000mAh 4S LiPo batteries. These batteries can maintain normal electrical system operation for over 48 hours without powering the engine starter motor or fuel pump. The power management unit is responsible for switching power on and off, distributing power, monitoring power battery voltage, and performing emergency power cuts. Implementing the power on and off function is simple, requiring only a switch. Implementing an emergency power cut is equally easy, requiring only an emergency stop switch to be connected in series with the power bus. We monitor the power battery voltage in two ways: during testing, we can check the indicated voltage or capacity percentage on the voltage measurement module. In the system, the flight attitude controller monitors the voltage in real time. Low voltage signals are displayed with an error code and a buzzer.

[0095] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A low-altitude single-person aircraft powered by a micro-turbojet engine, characterized by: It includes a flight backpack and two arm propulsion units (7); The flight backpack comprises: a safety belt (1), a shell (2), a fuel supply system (3), an electrical system (4) and a backpack micro-turbine engine (5), wherein the fuel supply system (3) is installed inside the shell (2), the electrical system (4) is installed above the inside of the shell (2), and the backpack micro-turbine engine (5) is installed at the bottom of the shell (2); The shell (2) includes a back plate (2-1) and a flight back cover (2-2), wherein the back plate (2-1) is a plate body, wherein a plurality of weight-reducing holes (2-3) are provided on the upper portion of the back plate (2-1), and the back plate (2-1) is made of aluminum alloy, and through holes (2-4) are provided around the back plate (2-1), and the middle portion of the safety belt (1) is fixedly mounted on the middle portion of the back plate (2-1) by bolts and hawkbill hooks, and the back strap of the safety belt (1) is connected to the pilot's body after passing through the through hole (2-4), and the flight back cover (2-2) is a shell cover, and the flight back cover (2-2) is mounted on the back plate (2-1), and a filamentous net (2-5) is provided on the lower portion of the flight back cover (2-2); Wherein, two arm propulsion devices (7) are respectively installed on the left and right sides of the flying backpack shell (2); Each arm propulsion device (7) includes an engine bracket (8), two engines (9), a grip (10), a trigger (11), an arm bracket (13), a baffle bar (14) and two sets of connecting rod assemblies (12), one end of the two sets of connecting rod assemblies (12) are respectively installed on the left and right sides of the arm bracket (13), and the other ends of the two sets of connecting rod assemblies (12) are respectively connected to an engine bracket (8), each engine bracket (8) is installed with an engine (9), the grip (10) is horizontally installed in the arm bracket (13), and the trigger (11) is installed on the arm bracket (13).

2. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1, characterized in that: The shell (2) further comprises a fabric layer (2-6), which is fixedly mounted on the back plate (2-1) and is located on the back plate (2-1) at a side away from the flying back cover (2-2).

3. A low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1 or 2, characterized in that: The shell (2) also includes an EVA plate, which is wrapped around the fabric layer (2-6).

4. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1, characterized in that: The oil supply system (3) includes an oil tank (3-1), an air pipeline (3-2), an oil filling pipeline (3-3), a filter (3-4), an oil pump (3-5) and a ball valve (3-6). The air pipeline (3-2) and the oil filling pipeline (3-3) are installed on the oil tank (3-1). The filter (3-4), the oil pump (3-5) and the ball valve (3-6) are connected in sequence through pipelines. One end of the filter (3-4) is connected to the inside of the oil tank (3-1) through a pipeline. The other end of the ball valve (3-6) is connected to the backpack micro-turbine engine (5) through a pipeline to supply oil to the backpack micro-turbine engine (5).

5. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 4, characterized in that: The oil tank (3-1) comprises a square box body (3-7) and an oil quantity sensor (3-8), wherein the oil quantity sensor (3-8) is vertically and sealedly inserted into the interior of the square box body (3-7).

6. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 5, characterized in that: The square box (3-7) includes a box (3-7-1), a plurality of transverse flow stabilizing and wave-breaking plates (3-7-2), a plurality of longitudinal flow stabilizing and wave-breaking plates (3-7-3) and a plurality of front and rear flow stabilizing and wave-breaking plates (3-7-4). A plurality of transverse flow-stabilizing wave-breaking plates (3-7-2) are arranged horizontally at equal intervals, longitudinal flow-stabilizing wave-breaking plates (3-7-3) are vertically installed on the plurality of transverse flow-stabilizing wave-breaking plates (3-7-2), and front and rear flow-stabilizing wave-breaking plates (3-7-4) are installed longitudinally and arranged perpendicularly to the longitudinal flow-stabilizing wave-breaking plates (3-7-3). The plurality of transverse flow-stabilizing wave-breaking plates (3-7-2), the longitudinal flow-stabilizing wave-breaking plates (3-7-3) and the front and rear flow-stabilizing wave-breaking plates (3-7-4) constitute a wave-breaking plate assembly, and the plurality of wave-breaking plate assemblies are sequentially installed in the box (3-7-1).

7. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 6, characterized in that: Oil holes (3-7-5) are provided on the plurality of transverse flow stabilizing and wave-breaking plates (3-7-2), the plurality of longitudinal flow stabilizing and wave-breaking plates (3-7-3), and the plurality of front and rear flow stabilizing and wave-breaking plates (3-7-4) in a direction perpendicular to the plate bodies.

8. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 7, characterized in that: The shape of the oil hole (3-7-5) is a circular hole, a rectangular hole, a tapered hole or a long strip hole.

9. A low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1 or 8, characterized in that: The electrical system (4) includes a power battery (4-1), a first electronic control unit (4-2), a second electronic control unit (4-3), a flight attitude controller (4-4), a power management unit (4-5) and an electrical system tray (4-6). The electrical system tray (4-6) is connected to the back panel (2-1), the power battery (4-1) and the flight attitude controller (4-4) are mounted on the electrical system tray (4-6) at the front and rear ends, the first electronic control unit (4-2) and the second electronic control unit (4-3) are mounted on the left and right sides of the flight attitude controller (4-4), respectively, and the power management unit (4-5) is mounted on the electrical system tray (4-6) below the flight attitude controller (4-4).

10. The low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 9, characterized in that: The flight attitude controller (4-4) is provided with a host computer interface (4-7).

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