Low-altitude single-person aircraft taking micro turbojet engine as power

Abstract

The invention discloses a low-altitude single-person aircraft taking a micro turbojet engine as power, and relates to the field of manned aircrafts. The problems that an existing jet-propelled aircraft garment is large in self weight, inconvenient in pose adjustment and prone to hurting pilots are solved. The flying knapsack comprises a flying knapsack body and two arm propelling devices (7). The flying backpack comprises a safety belt (1), a shell (2), an oil supply system (3), an electrical system (4) and a backpack miniature turbine engine (5), the oil supply system (3) is installed in the shell (2), the electrical system (4) is installed on the upper end face of the shell (2), and the backpack miniature turbine engine (5) is installed on the lower portion of the shell (2); the two arm propelling devices (7) are installed on the left side and the right side of the shell (2) of the flying backpack respectively. The flying backpack is the most complex component in a low-altitude single-person aircraft with a micro turbojet engine as power. The invention is used in aircrafts.

Description

Technical Field

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

[0002] Low-altitude single-person aircraft driven by micro-turbojet engines, with its small size and powerful power, provide new possibilities for single-person rapid travel. This type of aircraft not only has a high speed limit and flexibility, but also plays an important role in special scenarios, such as mountain rescue and sea rescue. After wearing the aircraft, rescuers can quickly locate and rescue trapped people and provide emergency rescue services. In addition, low-altitude single-person aircraft are also widely used in the military field. Taking a single-person aircraft of a British company as an example, it has been used by the British Navy in many experiments to prove its superior performance in rapid transfer between warships at sea and beach landing battles.

[0003] Let's take a turbojet-powered single-person aircraft as an example. In the history of research on turbojet-powered single-person aircraft, the three most classic products are the jet suit, the American jet backpack, and the flying skateboard. The design concepts of the three single-person aircraft are completely different, but they all try to place a micro turbojet engine on a certain part of the human body to provide thrust. The jet suit is the aircraft with the best operating performance, and it uses human bones as a support to reduce the external mechanical structure.

[0004] However, current jet suits are mainly driven by jet engines to achieve flight. However, in order to ensure the safety of pilots, existing jet suits have adopted a variety of protective measures, such as protective clothing (rigid backpack frames). Therefore, they have the disadvantages of being heavy and inconvenient to wear. In addition, since the pilot performs posture operations when the turbojet engine is working, there will be vibration and thrust during the operation (it is difficult for the pilot to fully control the posture of the entire aircraft 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 also cause accidental injuries such as burns to the pilot.

[0005] In summary, existing jet suits have the problems of heavy weight, inconvenient posture adjustment and easy to cause 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 flying machine powered by a micro-turbojet engine, comprising a flying backpack and two arm propulsion devices;

[0009] The flying backpack includes: a safety belt, a shell, an oil supply system, an electrical system and a backpack micro-turbine engine, wherein the oil 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 plate and a flight back cover. The back plate is a plate body, wherein a plurality of weight-reducing holes are provided on the upper part of the back plate, and the back plate is made of aluminum alloy. Through holes are provided around the back plate. The middle part of the safety belt is fixedly installed on the middle part of the back plate by bolts and hawk hooks. The back strap of the safety belt is connected to the pilot's body after passing through the through holes. The flight back cover is a shell cover, which is covered on the back plate, and a filamentary net is provided on the lower part of the flight back cover.

[0011] Among them, 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 strip 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 back plate and located on the back plate 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 pipeline, a fuel filling pipeline, a filter, an oil pump and a ball valve. The air pipeline and the fuel filling pipeline 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 the pipeline, and the other end of the ball valve is connected to the backpack micro-turbine engine through the 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, a plurality of transverse flow stabilizing wave breaking plates, a plurality of longitudinal flow stabilizing wave breaking plates and a plurality of front and rear flow stabilizing wave breaking plates, the plurality of transverse flow stabilizing wave breaking plates are arranged horizontally at equal intervals, the longitudinal flow stabilizing wave breaking plates are vertically installed on the plurality of transverse flow stabilizing wave breaking plates, the front and rear flow stabilizing wave breaking plates are longitudinally installed and arranged perpendicularly to the longitudinal flow stabilizing wave breaking plates, the plurality of transverse flow stabilizing wave breaking plates, the longitudinal flow stabilizing wave breaking plates and the front and rear flow stabilizing wave breaking plates constitute a wave breaking plate assembly, and the plurality of 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 through hole is a circular hole, a rectangular hole, a conical 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 back panel. The power battery and the flight attitude controller are installed on the electrical system tray 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, a host computer interface is provided on the flight attitude controller.

[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 prior art, the 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 damage to the pilot during the flight.

[0025] 3. The present invention uses an electrical system to achieve the posture and control during flight, with high integration. It is easy to operate and has high control accuracy. The flight backpack is equipped with a large-capacity fuel tank, a complete oil circuit, an electrical system and a power system, which can provide a maximum thrust of 80KG for a single-person aircraft and maintain a rated endurance of 10 minutes. It also has a flight attitude controller using a deep reinforcement learning controller, which can assist the pilot in flying.

[0026] 4. The main fuel tank of the present invention has a very large capacity and is equipped with crisscross wave-breaking plates. The shape, size and opening size of the wave-breaking plates are determined by the dynamic simulation process, which can effectively reduce the sloshing of fuel during flight and improve the overall stability and controllability of the aircraft.

[0027] 5. The low-altitude single-person aircraft uses six micro-turbojet engines of two models as the power system, and each engine is a black box for researchers. The ECU of the micro-turbojet engine can only use speed control, which is very inconvenient for the overall control, so it is necessary to find a way to achieve overall thrust control. First, a step signal experiment of different amplitudes is carried out on each micro-turbojet engine to obtain a control model of the control signal and the speed, and then a control model between the speed and the thrust is obtained, and finally the thrust control curve of a single engine can be realized to achieve thrust control. The power system of the low-altitude single-person aircraft is generally divided into three parts: two arm propulsion devices and a flight backpack propulsion device. If the two engines in a single propulsion device cannot be synchronized, bending and twisting will occur on the axis of the propulsion device, which is harmful to the stable control of the pilot and the aircraft, so it is necessary to use the underlying control to complete the synchronization of each propulsion device. The flight backpack in the present invention uses system identification and underlying control technology to achieve the synchronization of each group of power devices, so that the overall power output is more stable and controllable, and the power change is 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 we achieve the control effect we want. After completing ground tests and algorithm optimization, test experiments are carried out in more complex environments, such as mountains and lakes, and finally the performance parameters of the low-altitude single-person aircraft are 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 to low altitudes; 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 3It is an overall schematic diagram of the oil supply system applied to the backpack and the arm thruster A of the present invention.

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

[0033] Figure 5 It 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 schematic diagram of the structure of the backplane.

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

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

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

[0039] Fig.11 yes Fig.10 Side view of.

[0040] Fig.12 yes Fig.10 Rear view of.

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

[0042] Fig.14 It is a schematic diagram of the upper computer interface.

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

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

[0045] Fig.17 It is a schematic diagram of the structure of the arm propulsion device.

[0046] Fig.18 It is a schematic diagram of the structure of the grip and trigger.

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

[0048] In the figure:

[0049] 1. Safety belt, 2. Shell, 2-1. Backboard, 2-2. Flight back cover, 2-3. Weight reduction hole, 2-4. Connection hole, 2-5. Wire mesh, 2-6. Fabric layer, 3. Fuel supply system, 3-1. Fuel tank, 3-2. Air pipeline, 3-3. Fuel pipeline, 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 and wave breakers, 3-7-3. Longitudinal flow stabilizer and wave breakers, 3-7-4. Front and rear flow stabilizer and wave breakers, 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 strip. 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 flying 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 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 shell 2 includes a back plate 2-1 and a flying back cover 2-2. 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. Through holes 2-4 are provided around the back plate 2-1. The middle portion of the safety belt 1 is fixedly installed on the middle portion of the back plate 2-1 by bolts and hawkbill hooks. The back strap of the safety belt 1 is connected to the pilot's body after passing through the through hole 2-4. The flying back cover 2-2 is a shell cover. The flying back cover 2-2 is covered on the back plate 2-1, and a filamentary net 2-5 is provided on the lower portion of the flying back cover 2-2.

[0053] Among them, two arm propulsion devices 7 are respectively installed on the left and right sides of the housing 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 strip 14 and two groups of connecting rod assemblies 12. One end of the two groups 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 groups 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 completely composed of: an arm propulsion device, a flying backpack, a flight attitude controller and various electrical equipment. Figure 1 The main design indicators are a flight altitude of 4m, a flight time of about 10min, a rated load of more than 100KG, the ability to hover at any position, and the ability to complete maneuverable flight.

[0056] The flying backpack of the present invention is the most complicated component in the low-altitude single-person flying vehicle which is powered by a micro-turbojet engine.

[0057] The flying backpack uses two 40KG turbojets, i.e. backpack micro-turbine engines 5 used in pairs, and their matching fuel supply systems have been reasonably installed in the backpack through structural design. Fig.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 it is actually used. Figure 3 , the layout of each oil circuit meets the conditions for 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 when the aircraft is balanced, the thrust required by the flight backpack and the angle between the three, and then determines the selection and arrangement of the micro turbojet engine (finally, it is selected to place 2 30KG-thrust engines on the arm propulsion device and 2 40KG-thrust engines on the flight backpack, using a total of 6 micro turbojet engines, and the relevant analysis will be described in the research basis).

[0059] The arm propulsion device in this embodiment is as follows Fig.17 and Fig.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 each head, and β is the angle between the engine axis and the arm propulsion axis. Fig.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 parameter R-β (R=400Mmm, β=20deg) through simulation and experiment, we can now fully design the arm propulsion device. The shape of the hand guard and the grip is designed according to the 50% quantile arm and palm related dimensions of the Chinese adult human body size GB / T10000-2023. Fig.18 As shown. The complex shape of the hand guard can be perfectly reproduced by 3D printing aluminum alloy technology. The opening near the end of the elbow is elastic and can be clamped with an additional clamping tool to fit the user's forearm. The grip has two built-in self-resetting linear sensors. In actual use, two reverse signals can be obtained by applying reverse voltage to them, which not only ensures the accuracy of the signal, but also ensures reliability by using redundant sensors.

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

[0062] In addition, for the contents not described in detail in the present invention regarding the arm propulsion device, 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 explain 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 at a side away from the flying back cover 2-2.

[0064] With such arrangement, the fabric layer 2-6 of this embodiment reduces the weight of the entire housing 2, and the part in contact with the pilot is more comfortable, reducing the discomfort caused by vibration and impact to the pilot's back. Other components and connection relationships are the same as those of the first embodiment.

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

[0066] In this way, the EVA board supports the fabric layer 2-6 and provides a carrier for the fabric layer 2-6 so as to better connect with the back plate. Other components and connection relationships are the same as those in the first or second embodiment.

[0067] Ergonomics requires consideration of the comfort of the backpack, the reliability of the pilot's fixation during flight, and the safety of the backpack when the engine is running. The back panel is a combination of aluminum alloy and EVA. Figure 7 As shown. In order to improve the reliability of the flight backpack, all components except the oil circuit and wiring harness need to be rigidly connected to the aluminum alloy back plate. The aluminum alloy plate has been subjected to a lot of weight reduction treatment using topological optimization, which has resulted in a large gap in the part where the aluminum alloy plate fits the fuel tank. In order to improve safety, we plan to paste some Kevlar fibers in this gap. This fiber has excellent flame retardant and heat insulation capabilities. On the other side of the aluminum alloy plate is a fabric-wrapped EVA protective plate, which together form the flight backpack back plate. The fabric-wrapped EVA protective plate is relatively soft. Air cushions can be pasted on it to further improve the comfort of the driver's back when carrying it.

[0068] Specific implementation method four: Combination Figure 3 , Figure 4 and Fig.15 To illustrate the present embodiment, the fuel supply system 3 of the present embodiment includes a fuel tank 3-1, an air pipeline 3-2, a refueling 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 refueling 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 configuration, 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 (i.e. 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 set inside the fuel tank. The appearance and internal structure of the fuel tank are as follows Figure 4 The other components and connection relationships are the same as any one of the specific embodiments 1 to 3.

[0071] Specific implementation method five: Combination Figure 4 To explain this embodiment, the oil tank 3-1 of this embodiment includes a square box body 3-7 and an oil level sensor 3-8, and 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 Fig.16 The red arrow in the figure shows that the top is designed from low to high to guide the direction of oil and gas to prevent gas accumulation at the top. A larger breather valve (M10) is set at the highest corner. There is an inclined surface on the front side of the fuel tank (in front of the refueling port). Experience shows that this design can reduce the generation of bubbles. The other structures and components are the same as any one of the specific embodiments 1 to 4.

[0073] Specific implementation method six: Combination Figure 4 to Figure 2 To explain 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] A plurality of transverse flow stabilizing wave-breaking plates 3-7-2 are arranged horizontally at equal intervals, a 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, a front and rear flow stabilizing wave-breaking plates 3-7-4 are longitudinally installed and arranged perpendicularly to the longitudinal flow stabilizing wave-breaking plates 3-7-3, a plurality of transverse flow stabilizing wave-breaking plates 3-7-2, a longitudinal flow stabilizing wave-breaking plates 3-7-3 and a front and rear flow stabilizing wave-breaking plates 3-7-4 constitute a wave-breaking plate assembly, and a plurality of wave-breaking plate assemblies are sequentially installed in the box body 3-7-1.

[0075] In this way, the installation method and position design of the wave-breaking plate group can effectively prevent the oil in the oil tank from shaking excessively 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 good in integrity. The number of transverse flow-stabilizing wave-breaking plates 3-7-2 in each group of wave-breaking plate assemblies is preferably 3, and they are arranged at equal intervals up and down.

[0077] Specific implementation method seven: Combination Figure 4 To explain this embodiment, 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 of this embodiment are all provided with oil holes 3-7-5 in a direction perpendicular to the plate body. Such arrangement can limit the height and left and right fluctuations of the oil while ensuring that the oil can pass smoothly, thereby preventing the instability during flight caused by the violent shaking of the oil. The other components and connection relationships are the same as any one of the specific embodiments 1 to 6.

[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 a long strip hole.

[0079] Such an arrangement makes it easy to select oil holes of different sizes according to different use environments, and 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 Fig.13 To explain 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 control signals of the aircraft come from the triggers installed in the arm propulsion devices and the master controller in the flight backpack. The pilot controls the thrust of the two arm propulsion devices by pressing the two triggers, and the thrust of the flight backpack is controlled by the master controller. The master controller controls the thrust of the flight backpack based on the flight backpack posture and other sensor signals such as the two control signals from the triggers. Various control system equipment such as sensors, controllers, and power supplies also need to be reasonably installed in the backpack.

[0083] The arm propulsion device is equipped with a 30KG-class turbojet engine, using the V3ECU (referring to the first electronic control unit 4-2). The flight backpack is equipped with a 40KG-class turbojet engine, using the V4ECU (referring to the second electronic control unit 4-3). Both ECUs provide wireless control and wired control. Using wireless testing during testing is convenient for debugging and very safe. Using wired control in actual applications can ensure 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 implementation modes 1 to 8.

[0085] In this embodiment, the main controller is used in the flying backpack to collect sensor signals, design control systems, 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 endurance of the flying backpack. The electrical system on 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 Fig.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 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 control signals from the grips of the two arm propulsion devices. At the same time, a deep learning controller needs to be established 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-channel IMU posture signals, and 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 backup 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 Fig.14 .

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

[0089] Combination 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 securely 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. The end of the racing safety belt is an eagle hook with a screw, which can be screwed on the back plate. 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 unexpected problems. 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 main body of the flight backpack and the arm thruster device are kept at a safe distance from the ground. When starting, you can ignite the warm-up engine first, so that the six engines can 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 device to achieve low-altitude free flight. After landing, the pilot releases the trigger and places the arm thruster device 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 Fig. 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 is not 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. Covers such as Fig.10 shown.

[0093] Ergonomics needs to consider the comfort of carrying, the reliability of fixing the driver during flight, and the safety of the flight backpack during engine operation. The back panel is a combination of aluminum alloy plate and EVA plate. In order to improve the reliability of the flight backpack, all other components except the oil circuit and wiring harness need to be rigidly connected to the aluminum alloy back panel. The aluminum alloy plate has been subjected to a lot of weight reduction treatment using topological optimization, which has resulted in a large gap in the part where the aluminum alloy plate fits the fuel tank. In order to improve safety, we plan to paste some Kevlar fibers in this gap. This fiber has excellent flame retardant and heat insulation capabilities. On the other side of the aluminum alloy plate is a fabric-wrapped EVA protective plate, which together form the flight backpack back panel. The fabric-wrapped EVA protective plate is relatively soft. You can paste air cushions on it to further improve the comfort of the driver's back when carrying it. The arm thruster bracket and flight backpack bracket are installed on the mount. 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. The actual object is as follows Figure 11 to Figure 12 shown.

[0094] The electrical system of the flight backpack mainly includes: power battery, V3 ECU group, V4 ECU group, flight attitude controller, and power management unit. We selected two high-capacity 10000mAh 4S LiPo power batteries. Without driving the engine starter motor and oil pump, the two power batteries can maintain the normal operation of the electrical system for more than 48 hours. The power management unit is responsible for switching on and off and distributing power, monitoring the voltage status of the power battery, and emergency power cutoff. The function of switching on and off the power is very simple to implement, just install a switch. Emergency power cutoff is also easy to implement, just connect an emergency stop switch in series on the power bus. We have adopted two ways to monitor the power battery voltage. During the test, we can check the indicated voltage or capacity percentage of the voltage measurement module. In the system, the flight attitude controller detects the voltage in real time. When the power supply voltage is low, an error code will be displayed on the display and a buzzer will beep.

[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 the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. 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 embodiments of the present invention.

Claims

1. A low-altitude single-person aircraft powered by a micro-turbojet engine, characterized in that: It includes a flight backpack and two arm propulsion devices (7); The flying 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), wherein 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); The shell (2) comprises 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 covered on the back plate (2-1), and a filamentary 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 housing (2) of the flying backpack; Each arm propulsion device (7) comprises an engine bracket (8), two engines (9), a grip (10), a trigger (11), an arm bracket (13), a baffle strip (14) and two groups of connecting rod assemblies (12), one end of the two groups of connecting rod assemblies (12) are respectively mounted on the left and right sides of the arm bracket (13), the other ends of the two groups of connecting rod assemblies (12) are respectively connected to an engine bracket (8), each engine bracket (8) is mounted with an engine (9), the grip (10) is horizontally mounted in the arm bracket (13), and the trigger (11) is mounted on the arm bracket (13).

2. A low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1, characterized in that: The shell (2) also includes 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 on the fabric layer (2-6).

4. A low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 1, characterized in that: The oil supply system (3) comprises 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 the pipeline; the other end of the ball valve (3-6) is connected to the backpack micro-turbine engine (5) through the pipeline, so as to supply oil to the backpack micro-turbine engine (5).

5. A 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 inside the square box body (3-7).

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

7. A 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. A low-altitude single-person aircraft powered by a micro-turbojet engine according to claim 7, characterized in that: The shape of the oil through 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; 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) at the bottom of the flight attitude controller (4-4).

10. A 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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