Flight backpack for low-altitude single aircraft

Abstract

The invention discloses a flying backpack for a low-altitude single aircraft, 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. An oil supply system is installed in a shell, an electrical system is installed on the upper end face of the shell, and a backpack micro turbine engine is installed on the lower portion of the shell. The shell comprises a back plate and a flying back covering part, the back plate is a plate body, a plurality of lightening holes are formed in the upper portion of the back plate, the back plate is made of aluminum alloy, penetrating holes are formed in the periphery of the back plate, and the middle of the safety belt is fixedly installed in the middle of the back plate through bolts and olecranon hooks. A strap of the safety belt penetrates through the penetrating-connecting hole and then is connected with the body of the pilot, the flying back covering part is a shell cover and covers the back plate, and a filiform net is arranged on the lower portion of the flying back covering part. 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 flying backpack used for a low-altitude single-person aircraft. Background Art

[0002] The future intelligent transportation system will require more flexible means of transportation, the emergency rescue field will require a mobile method that can quickly reach the disaster site, the logistics industry will need more efficient means of transportation, and the rescue environment will require a fast, concealed, and flexible flying system.

[0003] With the development of the low-altitude economy, people's demand for new modes of transportation is increasing. Low-altitude single-person aircraft driven by micro-turbojet engines, with their 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.

[0004] 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.

[0005] 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.

[0006] 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

[0007] 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 flight backpack for low-altitude single-person aircraft.

[0008] The technical solution of the present invention is:

[0009] A flying backpack used in a low-altitude single-person aircraft comprises 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; the shell comprises a back plate and a flying back cover, wherein the back plate is a plate body, wherein a plurality of weight-reducing holes are provided at the upper part of the back plate, and the back plate is made of aluminum alloy, and through holes are provided around the back plate, wherein the middle part of the safety belt is fixedly installed at the middle part of the back plate by bolts and hawkbill hooks, and the shoulder straps of the safety belt are connected to the pilot's body after passing through the through holes, and the flying back cover is a shell cover, which is covered on the back plate, and a filamentary net is provided at the lower part of the flying back cover.

[0010] 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.

[0011] Furthermore, the shell also includes an EVA board, and the EVA board is wrapped on the fabric layer.

[0012] 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.

[0013] 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.

[0014] 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.

[0015] 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.

[0016] Preferably, the shape of the oil through hole is a circular hole, a rectangular hole, a conical hole or an elongated hole.

[0017] 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.

[0018] Furthermore, a host computer interface is provided on the flight attitude controller.

[0019] Furthermore, the number of the transverse flow stabilizing and wave-breaking plates is three.

[0020] Furthermore, the front and rear flow-stabilizing and wave-breaking plates are installed in the box body symmetrically with the longitudinal flow-stabilizing and wave-breaking plate as the center.

[0021] Compared with the prior art, the present invention has the following effects:

[0022] 1. The present invention provides a flight backpack for a low-altitude single-person aircraft. Compared with the prior art, the backpack has good integrity by opening a weight-reducing hole on the back plate and using lightweight materials for one-piece CNC processing, which greatly reduces the weight of the back plate. 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 plate.

[0023] 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.

[0024] 3. The present invention adopts a modular electrical system to realize the posture and control during flight, with high integration. It is simple 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. At the same time, it is equipped with a flight attitude controller using a deep reinforcement learning controller to assist the pilot in flying.

[0025] 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall effect of the present invention worn by a pilot.

[0027] Figure 2 It is a schematic diagram of the overall structure of the flying backpack of the present invention.

[0028] Figure 3 It is an overall schematic diagram of the oil supply system applied to the backpack and the arm thruster A of the present invention.

[0029] Figure 4 It is a structural schematic diagram of the oil tank of the present invention.

[0030] Figure 5 It is a schematic diagram of the layout of the electrical system.

[0031] Figure 6 It is a signal transmission diagram of the electrical system.

[0032] Figure 7 It is a schematic diagram of the structure of the backplane.

[0033] Figure 8 It is a schematic diagram of the structure of a seat belt.

[0034] Fig. 9 It is a schematic diagram of the three-dimensional structure of the flight back cover.

[0035] Fig.10 This is a physical picture of the present invention after removing the flight back cover, fuel supply system and electrical system.

[0036] Fig.11 yes Fig.10 Side view of.

[0037] Fig.12 yes Fig.10 Rear view of.

[0038] Fig.13 It is a physical diagram of the electrical system.

[0039] Fig.14 It is a schematic diagram of the upper computer interface.

[0040] Fig.15 It is a structural diagram of the oil supply system.

[0041] Fig.16 It is a schematic diagram of the overall structure of the exterior of the fuel tank of the present invention.

[0042] In the figure:

[0043] 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 anti-wave plate, 3- 7-3, longitudinal flow stabilizer and wave breakers, 3-7-4, front and rear flow stabilizer and wave breakers, 3-7-5, oil through 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. DETAILED DESCRIPTION

[0044] Specific implementation method 1: Combination Figures 1 to 16 The present embodiment is described. The present embodiment includes a safety belt 1, which also includes 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; the shell 2 includes a back plate 2-1 and a flight back cover 2-2, the back plate 2-1 is a plate body, wherein a plurality of weight reduction holes 2-3 are provided on the upper part 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, the middle part of the safety belt 1 is fixedly installed on the middle part of the back plate 2-1 by bolts and eagle hooks, and the shoulder strap of the safety belt 1 is connected to the pilot's body after passing through the through hole 2-4, 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 mesh 2-5 is provided on the lower part of the flight back cover 2-2.

[0045] 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] Specific implementation method three: Combination Figure 7 To illustrate this embodiment, the shell 2 of this embodiment further includes an EVA board, and the EVA board is wrapped on the fabric layer 2-6.

[0051] 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.

[0052] 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.

[0053] Specific implementation method four: Combination Figure 3 , Figure 4 and Fig.15To 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.

[0054] 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 .

[0055] 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.

[0056] 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.

[0057] 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.

[0058] Specific implementation method six: Combination Figure 4 to Figure 2To 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.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] 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.

[0064] 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.

[0065] 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.

[0066] 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.

[0067] 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.

[0068] 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).

[0069] The other components and connection relationships are the same as any one of the specific implementation modes 1 to 8.

[0070] 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.

[0071] 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.

[0072] 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 .

[0073] The other components and connection relationships are the same as any one of the specific implementation modes 1 to 8.

[0074] Combination Figures 1 to 16 The working principle of the present invention is described:

[0075] 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.

[0076] 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. 9shown (cover not shown).

[0077] 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.

[0078] 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.

[0079] 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.

[0080] 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 flying backpack for use with a low-altitude single-person aircraft, comprising a safety belt (1), characterized in that: It also includes a housing (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 housing (2), the electrical system (4) is installed on the upper end surface of the housing (2), and the backpack micro-turbine engine (5) is installed on the lower part of the housing (2); The shell (2) comprises 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 part 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 part of the safety belt (1) is fixedly installed on the middle part of the back plate (2-1) by bolts and hawk-beak 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). The flying back cover (2-2) is a shell cover, and the flying back cover (2-2) is covered on the back plate (2-1). The lower part of the flying back cover (2-2) is provided with a filamentary net (2-5).

2. The flying backpack for a low-altitude single-person aircraft 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 flying backpack for a low-altitude single-person aircraft 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. The flying backpack for a low-altitude single-person aircraft according to claim 3, 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. The flying backpack for a low-altitude single-person aircraft 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. The flying backpack for a low-altitude single-person aircraft 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. The flying backpack for a low-altitude single-person aircraft 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 flying backpack for a low-altitude single-person aircraft 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. The flying backpack for a low-altitude single-person aircraft according to claim 8, characterized in that: The number of transverse flow stabilizing and wave-breaking plates (3-7-2) is 3.

10. A flying backpack for a low-altitude single-person aircraft according to claim 9, characterized in that: The front and rear flow stabilizing and wave-breaking plates (3-7-4) are installed in the box body (3-7-1) symmetrically with the longitudinal flow stabilizing and wave-breaking plate (3-7-3) as the center.

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