Portable single-person low-altitude vector jet aircraft with folding wing structure

Abstract

The invention relates to the field of aircrafts, in particular to a portable single-person low-altitude vector jet aircraft with a folding wing structure, the portable single-person low-altitude vector jet aircraft comprises a rack part, a power part and a load part, the power part is arranged below the rack part, and the load part is arranged below the power part; according to the portable single-person low-altitude vector jet aircraft with the folding wing structure, through the design of the telescopic framework of a multi-connecting-rod structure, the aircraft can be easily folded when not used, the occupied space is small, carrying and storage are convenient, and the problems that a traditional single-person aircraft is large in size and difficult to carry are solved; the applicability and convenience of the aircraft are improved; meanwhile, the structural strength of the wings in the unfolded state is ensured through the multi-point supporting design of the telescopic framework, the stability and safety of the aircraft are improved, the air resistance of the aircraft is reduced through the design of the wing skin, the protective cover, the conical cover, the wind tunnel and the fairing, the aerodynamic performance is effectively improved, and the aircraft is more efficient in the flight process.

Description

Technical Field

[0001] The invention belongs to the field of aircraft, and in particular relates to a portable single-person low-altitude vector jet aircraft with a folding wing structure. Background Art

[0002] A single-person aircraft is a flying device that is built by humans and can take off from the ground and fly in space while being controlled by an individual. The origins of this type of technology can be traced back to early flying dreamers and inventors, such as Leonardo da Vinci, who envisioned the possibility of human flight. However, it was not until the mid-20th century, with significant advances in aviation technology, that the concept of a single-person aircraft gradually became a reality.

[0003] With the popularization of aircraft, personal aircraft will inevitably be the future development direction. Personal aircraft can not only provide a fast and convenient way of air travel, but also play an important role in specific occasions such as emergency rescue and military reconnaissance. Traditional personal aircraft mainly include rocket backpacks, jet backpacks, powered hang gliders, etc.

[0004] In the prior art, single-person aircraft generally have the characteristic of being bulky. Most personal aircraft are large in size due to their structural design, and are difficult to carry and store conveniently. They require a huge space to carry and store, which limits their application in daily life. The large size makes these aircraft very inconvenient to transport and use. Therefore, how to overcome the above-mentioned technical problems and defects has become a key issue to be solved. Summary of the invention

[0005] The purpose of the invention is to overcome the defects described in the background technology, so as to realize a portable single-person low-altitude vector jet aircraft with a folding wing structure, so as to solve the problems of the single-person aircraft in the prior art having a large structure, being difficult to carry and store conveniently, occupying a large space, affecting applicability, and being inconvenient during use.

[0006] In order to achieve the above-mentioned object of the invention, the technical solution of the present invention is:

[0007] A portable single-person low-altitude vector jet aircraft with a folding wing structure comprises a frame part, a power part and a load part. The power part is arranged below the frame part, and the load part is arranged below the power part.

[0008] Specifically, the frame part includes a wing mid-frame, a telescopic frame and a wing skin, the power part is arranged below the wing mid-frame, and the load part is arranged below the power part. The telescopic frame is symmetrically arranged on both sides of the upper part of the wing mid-frame, and the wing skin is fixedly wrapped and laid on the outside of the telescopic frame.

[0009] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the wing mid-frame is T-shaped when viewed from above, and a positioning beam is arranged on the top of the front end cross beam. A hanger is integrally arranged on the side and bottom of the middle position of the bottom of the T-shaped wing mid-frame, and the power unit is hoisted at the bottom of the hanger.

[0010] At the same time, the telescopic frame is symmetrically arranged on both sides of the wing mid-frame, and the telescopic frame is a multi-link structure, including a rocker arm A, a rocker arm B, a rocker arm C, a connecting rod A, a connecting rod B and an active rocker.

[0011] Specifically, the front end of the rocker arm A is hinged to the positioning beam, and the rear end is hinged to the middle part of the connecting rod A; the right side of the middle part of the rocker arm A is hinged to the front end of the active rocker, and the rear end of the active rocker is displaceably and fixedly arranged at the tail of the T-shaped wing center frame, the middle part of the active rocker is hinged to the end of the connecting rod A through the rocker arm B, and the other end of the connecting rod A is hinged to the middle part of the rocker arm C; the left side of the middle part of the rocker arm A is hinged to the end of the connecting rod B, and the other end of the connecting rod B is hinged to the front end of the rocker arm C; the hinge point of the active rocker and the rocker arm A is close to the front end of the rocker arm A, and the hinge point of the connecting rod B and the rocker arm A is close to the rear end of the rocker arm A.

[0012] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, a telescopic drive unit is arranged on the wing mid-frame, and the telescopic drive unit includes a telescopic motor, a screw, a threaded hinge sleeve and a screw bracket. The front end, the tail end and the middle part of the screw are rotatably connected with the screw bracket, and the screw bracket is fixedly arranged on the wing mid-frame in an integrated or separate manner.

[0013] Specifically, the telescopic motor is on the side of the screw bracket at the front end of the screw and is driven to connect the front end of the screw. The threaded articulated sleeve is threadedly arranged on the screw between the middle part of the screw and the screw bracket at the tail end. Both sides of the threaded articulated sleeve are hingedly connected to the rear end of the active rocker.

[0014] In addition, a protective cover is provided on the upper part of the telescopic drive unit, and the top shape of the protective cover is a transitional curved surface that rises and slowly descends from front to back, and the protective cover is provided with a recess at the rear end corresponding to the active rocker.

[0015] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, when the telescopic frame is fully unfolded, the threaded articulated sleeve is located at the screw bracket in the middle of the screw, and when the telescopic frame is fully folded, the threaded articulated sleeve is located at the screw bracket at the tail end of the screw.

[0016] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the front end of the rocker arm C is connected to the end of the positioning beam through a pull rope, and the rear end of the rocker arm C is connected to the tail of the wing mid-frame through a pull rope.

[0017] Preferably, the swing rod C and the pull rope are hingedly connected, and the pull rope is made of steel wire rope.

[0018] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the power unit includes a fuel tank, an engine, a transmission unit and a power output unit. The fuel tank is arranged at the middle position of the lower front end of the wing mid-frame, and the engine is arranged at the bottom of the hanger. The hanger is located at the side and bottom of the wing mid-frame behind the fuel tank. The power output unit is symmetrically arranged on both sides of the engine. The fuel tank is connected to the engine through an oil circuit, and the engine is driven by the transmission unit and fixedly connected to the power output unit.

[0019] At the same time, the engine is connected with a right control handle through a control line.

[0020] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, a narrowed portion is provided at the front of the fuel tank, and its front end is rounded. The fuel filling port of the fuel tank is provided at the upper end of the fuel tank, and the fuel filling port is lower than the highest point of the wing mid-frame.

[0021] Preferably, a detachable fairing is provided at the oil filling port on the top of the oil tank.

[0022] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the transmission unit is arranged at the front end of the engine, and the transmission unit includes a truss, a driving wheel, a passive wheel and a transmission belt. The truss is fixedly arranged laterally at the front end of the engine, and the driving wheel, the passive wheel and the transmission belt are all arranged inside the truss. A driving wheel is arranged after the power output shaft of the engine passes through the truss, and the passive wheel is arranged on the rotating shaft of the power output unit. The driving wheel and the passive wheel are connected by the transmission belt.

[0023] Preferably, a plurality of wind tunnels are arranged on the truss, and the front and rear edges of the wind tunnels are chamfered and rounded.

[0024] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the power output unit includes a duct cylinder, a connecting frame, front propeller blades, rear propeller blades and a coaxial reversal gearbox. After the truss passes through the duct cylinder, a coaxial reversal gearbox is integrally provided at its end. A bracket is provided at the place where the truss passes through the duct cylinder. Front propeller blades and rear propeller blades are respectively provided on the power output shafts at the front and rear ends of the coaxial reversal gearbox, and the driven wheel is provided on the power output shaft of the coaxial reversal gearbox. The coaxial reversal gearbox is located at the center of the duct cylinder, and connecting frames are provided at the top, bottom and sides. The coaxial reversal gearbox is fixedly supported and connected to the inner wall of the duct cylinder by the connecting frames at the top, bottom and sides.

[0025] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, a protective cover is also provided at the front end of the duct cylinder, and a conical cover is provided at the rear end thereof. A pull rope is provided on the outside of the conical cover, and the other end of the pull rope is connected to the rear end of the rocker arm C and / or the outermost tip of the wing skin. The tail end of the conical cover is an open design, and a vector adjustment unit is provided at the tail end.

[0026] Specifically, the vector adjustment unit includes a tail jet steering cover, a guide plate, a side adjustment motor and an upper adjustment motor. The tail jet steering cover is sleeved on the tail opening of the conical cover. The top and bottom of the tail jet steering cover are hingedly connected to the tail opening of the conical cover. Arc grooves are provided on the left and right sides of the tail jet steering cover to prevent the tail jet steering cover and the conical cover opening from interfering with each other when turning left or right.

[0027] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, there are multiple guide plates, and the multiple guide plates are arranged inside the rear end of the tail jet steering cover. The middle part of the guide plate is hingedly connected to the side wall of the tail jet steering cover through a hinge shaft. A linkage vertical plate is provided at the front end of the guide plate, and the linkage vertical plate is hingedly connected to the front ends of multiple guide plates arranged in a row. Limiting slide grooves are provided on the inner wall of the tail jet steering cover at the upper and lower ends of the linkage vertical plate, and the top and bottom ends of the linkage vertical plate are slidably arranged in the limiting slide grooves.

[0028] Specifically, the upper adjusting motor is fixedly embedded at the top of the tail jet steering cover above the linkage vertical plate, and a threaded rod is arranged on the output shaft of the upper adjusting motor, and the threaded rod is threadedly connected to the top of the linkage vertical plate.

[0029] At the same time, the side adjustment motor is symmetrically arranged at the arc-shaped grooves on the left and right sides of the tail jet steering cover, and the side adjustment motor is arranged at the tail opening of the conical cover through a motor bracket. A threaded rod is also arranged on the output shaft of the side adjustment motor, and a motor bracket is also arranged at the arc-shaped groove of the tail jet steering cover. The threaded rod is threadedly connected to and passes through the motor bracket at the arc-shaped groove of the tail jet steering cover.

[0030] Preferably, the outside of the threaded rod between the linkage vertical plate and the upper adjustment motor, and the outside of the threaded rod between the motor bracket of the side adjustment motor and the motor bracket at the arc-shaped groove of the tail spray steering cover are both sleeved with return springs, and the end of the threaded rod is provided with a stop block.

[0031] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the upper adjustment motor and the side adjustment motor are both reversible motors, and the upper adjustment motor and the side adjustment motor are both connected to the left control handle through a control line.

[0032] In the above-mentioned portable single-person low-altitude vector jet aircraft with a folding wing structure, the load-bearing part includes a download frame and a shoulder strap. The download frame is fixedly arranged at the lower part of the engine, and the shoulder strap is fixedly arranged at the bottom of the download frame.

[0033] Preferably, the shoulder strap is a five-point safety shoulder strap, and the shoulder strap is an adjustable shoulder strap with a safety buckle.

[0034] Compared with the prior art, the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention has at least the following beneficial effects:

[0035] 1. The portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention can be easily folded up when not in use through the telescopic frame design of the multi-link structure, occupying less space and convenient to carry and store. It solves the problem that traditional single-person aircraft are large in size and difficult to carry, and improves the applicability and convenience of the aircraft.

[0036] 2. At the same time, the multi-point support design of the telescopic frame ensures the structural strength of the wing in the unfolded state, improves the stability and safety of the aircraft, and the design of the wing skin, protective cover, cone cover, wind tunnel and fairing reduces the air resistance of the aircraft and improves the aerodynamic performance.

[0037] It makes the aircraft more efficient during flight, extends the endurance and increases the flight speed. The streamlined design of the fuel tank and the cooling function of the wind tunnel optimize the operating environment of the power system and improve the engine's operating efficiency.

[0038] 3. The design of the five-point safety harness and escape backpack provides comprehensive safety protection, ensuring that the user can quickly detach from the aircraft in an emergency. The design of the electromagnet and emergency detachment handle makes the detachment process fast and reliable, improving the safety of the user; at the same time, the design of the electromagnet and the plug-in column ensures the stable connection of the detachment frame during normal flight, reducing the risk of mechanical failure.

[0039] 4. The telescopic drive unit and vector adjustment unit improve the degree of automation of the aircraft, allowing users to adjust the flight attitude more conveniently. Operation through the control handle ensures user comfort and convenience of operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a three-dimensional structural schematic diagram of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0041] Figure 2 It is a front view structural schematic diagram of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0042] Figure 3 It is a schematic diagram of the three-dimensional structure of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention after the wing skin is removed;

[0043] Figure 4 It is a top view structural schematic diagram of a telescopic frame of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0044] Figure 5 It is a three-dimensional structural schematic diagram of a telescopic frame of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0045] Figure 6 It is a schematic diagram of the installation position of the protective cover of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0046] Figure 7 It is a schematic diagram of the three-dimensional structure of the power output unit of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention after removing the protective cover;

[0047] Figure 8 It is a cross-sectional structural schematic diagram of a power output unit of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0048] Fig. 9 It is a schematic diagram of the installation position of the vector adjustment unit of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0049] Fig.10 It is a cross-sectional structural schematic diagram of a vector adjustment unit of a portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0050] Fig.11 It is a three-dimensional structural schematic diagram of the load portion of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention;

[0051] Fig.12 is a schematic diagram of the three-dimensional structure of the load portion in Example 9;

[0052] Fig.13 yes Fig.12 Schematic diagram of the three-dimensional structure after the middle load part is separated.

[0053] In the figure:

[0054] 1- Frame part:

[0055] 101-wing center frame, 111-positioning beam, 112-hanging bracket;

[0056] 102-telescopic frame, 121-rocker A, 122-rocker B, 123-rocker C, 124-connecting rod A, 125-connecting rod B, 126-active rocker, 127-pull rope;

[0057] 103- wing skin;

[0058] 104- telescopic drive unit, 141- telescopic motor, 142- screw rod, 143- threaded hinge sleeve, 144- screw rod bracket, 145- protective cover;

[0059] 2- Power Department:

[0060] 201-fuel tank; 202-engine;

[0061] 203-transmission unit, 231-frame, 232-driving wheel, 233-passive wheel, 234-transmission belt, 235-bracket, 236-wind tunnel;

[0062] 204-power output unit, 241-duct body, 242-connecting frame, 243-front propeller blade, 244-rear propeller blade, 245-coaxial reverse gear box, 246-protective cover, 247-conical cover;

[0063] 205- vector adjustment unit, 251- tail jet steering cover, 252- guide plate, 253- side adjustment motor, 254- upper adjustment motor, 255- arc groove, 256- motor bracket, 257- limit slide groove, 258- threaded rod, 259- return spring;

[0064] 3- Loading part:

[0065] 301-downloading frame, 311-micro vertical roller;

[0066] 302- Straps;

[0067] 303-detachment frame, 331-insertion column;

[0068] 304-electromagnet;

[0069] 305-disengagement mechanism, 351-pin shaft, 352-pulley block, 353-emergency disengagement handle, 354-pulley frame, 355-disengagement rope;

[0070] 4-right control handle; 5-left control handle. DETAILED DESCRIPTION

[0071] The portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention is described in more detail below with reference to the accompanying drawings and through specific embodiments.

[0072] In the description of the present invention, it is necessary to understand that the terms "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0073] Example 1

[0074] This embodiment discloses a portable single-person low-altitude vector jet aircraft with a folding wing structure to solve the problems of the single-person aircraft in the prior art being large in size, difficult to carry and store, occupying a large space, affecting applicability, and being inconvenient during use. Figure 1 , Figure 2 , including a frame part 1, a power part 2 and a load part 3, wherein the power part 2 is arranged below the frame part 1, and the load part 3 is arranged below the power part 2. The frame part 1, the power part 2 and the load part 3 can be lifted into the air by the operation of the power part 2 in coordination with the frame part 1. See the following for details.

[0075] To support the mold, see Figure 1 , Figure 3 The frame part 1 includes a wing middle frame 101, a telescopic frame 102 and a wing skin 103. The power part 2 is arranged below the wing middle frame 101, and the load part 3 is arranged below the power part 2. The power part 2 operates in coordination with the wing middle frame 101, the telescopic frame 102 and the wing skin 103 of the frame part, thereby completing the lift-off.

[0076] For details, see Figure 6 The telescopic frame 102 is symmetrically arranged on both sides of the upper part of the wing mid-frame 101 , and the wing skin 103 is fixedly wrapped and laid on the outside of the telescopic frame 102 .

[0077] The telescopic frame 102 is telescoped to reduce the occupied space of the aircraft.

[0078] To install the telescopic frame 103, see Figure 4 The wing mid-frame 101 is T-shaped when viewed from above, and a positioning beam 111 is provided at the top of the front crossbeam. In addition, to facilitate the installation of the engine, see Figure 5 A hanger 112 is integrally provided on the side and bottom of the middle position of the bottom of the T-shaped wing mid-frame 101 , and the power unit 2 is hoisted at the bottom of the hanger 112 .

[0079] In order to make the overall structure of the frame part 1 reasonable, it can be lifted into the air under the drive of the power part, see Figure 3 , Figure 4 The telescopic frame 102 is symmetrically arranged on both sides of the wing mid-frame 101.

[0080] To achieve the extension and retraction of the telescopic frame and reduce the occupied space, see Figure 4 , Figure 5 , the telescopic skeleton 102 is a multi-link structure.

[0081] To achieve the scalability of its multi-link structure, see Figure 4 , Figure 5 The telescopic skeleton 102 includes a rocker arm A121, a rocker arm B122, a rocker arm C123, a connecting rod A124, a connecting rod B125 and an active rocker arm 126.

[0082] Specifically, the front end of the rocker bar A121 is hingedly connected to the positioning beam 111, and the rear end is hingedly connected to the middle part of the connecting rod A124. The right side of the middle part of the rocker bar A121 is hingedly connected to the front end of the active rocker 126, and the rear end of the active rocker 126 is displaceable and fixedly arranged at the tail of the T-shaped wing mid-frame 101. The middle part of the active rocker 126 is hingedly connected to the end of the connecting rod A124 through the rocker bar B122, and the other end of the connecting rod A124 is hingedly connected to the middle part of the rocker bar C123.

[0083] At the same time, the left side of the middle of the swing rod A121 is hinged to the end of the connecting rod B125, and the other end of the connecting rod B125 is hinged to the front end of the swing rod C123. The hinge point of the active rocker 126 and the swing rod A121 is close to the front end of the swing rod A121, and the hinge point of the connecting rod B125 and the swing rod A121 is close to the rear end of the swing rod A121.

[0084] Through the above structure, the rear end of the active rocker 126 moves forward, and the front end of the active rocker 126 also moves accordingly. When the front end of the active rocker 126 moves, the middle part of the rocker rod A121 is pushed forward through the hinge point. The front end of the rocker rod A121 is fixed on the positioning beam 111, so the rocker rod A121 will rotate around the positioning beam 111 and gradually unfold.

[0085] When the middle part of the rocker arm A121 moves forward, the front ends of the connecting rods A124 and B125 are pushed outward through the hinge point. The expansion of the connecting rods A124 and B125 pushes the front end of the rocker arm C123 to move outward. The above telescopic frame drives the wing skin 103 to expand while expanding. When the telescopic frame supports the wing skin to be fully expanded, the active rocker is fixed to the wing center frame, thereby completing the extension of the wing.

[0086] Through the rapid deployment and folding of the multi-link structure, the aircraft can be easily folded when not in use, taking up less space and convenient to carry and store. At the same time, the design of the multi-link structure ensures the stability and reliability of the wing during deployment and folding, reducing the risk of mechanical failure. The multi-point support design of the multi-link structure ensures the structural strength of the wing in the deployed state, improving the stability and safety of the aircraft.

[0087] In this embodiment, the active rocker can be fixed to the wing mid-frame by pinning, and can also be fixed to the wing mid-frame by other means, as long as the structure can achieve the active rocker being fixed to the wing mid-frame after the sliding extension and sliding contraction process.

[0088] In order to provide the energy and power required for flight, in this embodiment, the power unit 2 includes a fuel tank 201, an engine 202, a transmission unit 203 and a power output unit 204. The fuel tank 201 is arranged at the middle position of the lower front end of the wing mid-frame 101, the engine 202 is arranged at the bottom of the hanger 112, and the hanger 112 is located at the side and bottom of the wing mid-frame 101 behind the fuel tank 201. The power output unit 204 is symmetrically arranged on both sides of the engine 202. The fuel tank 201 is connected to the engine 202 through an oil circuit, and the engine 202 is driven by the transmission unit 203 and fixedly connected to the power output unit 204. The engine 202 is connected to the right control handle 4 through a control line.

[0089] In this embodiment, the fuel tank 201 is used to store fuel and provide fuel for the engine 202. At the same time, the fuel tank 201 is located at the front lower part of the wing center frame 101, which can optimize the center of gravity distribution of the aircraft and improve the flight stability and controllability.

[0090] The engine 202 generates high-temperature and high-pressure gas by burning fuel, driving a propeller or other propulsion device to provide thrust and lift required for flight. The engine 202 is connected to the right control handle 4 through a control line, and the user can adjust the power and thrust of the engine through the control handle to achieve speed control of the aircraft.

[0091] To achieve the transmission of the engine to the power output unit, see Figure 7 , Figure 8 The transmission unit 203 is arranged at the front end of the engine 202, and the transmission unit 203 includes a frame 231, a driving wheel 232, a driven wheel 233 and a transmission belt 234.

[0092] For details, see Figure 7 The truss 231 is fixedly and laterally arranged at the front end of the engine 202, the driving wheel 232, the passive wheel 233 and the transmission belt 234 are all arranged inside the truss 231, and the power output shaft of the engine 202 passes through the truss 231 and is provided with a driving wheel 232, the passive wheel 233 is arranged on the rotating shaft of the power output unit 204, and the driving wheel 232 and the passive wheel 233 are connected by the transmission belt 234.

[0093] The truss 231 is fixedly disposed transversely at the front end of the engine 202, providing a sturdy installation frame to ensure that various components of the transmission unit 203 and the power output unit 204 can be stably installed and operated.

[0094] When the engine 202 is running, the driving wheel 232 can drive the transmission belt 234 to drive the driven wheel 233 to run, thereby driving the power output unit to run.

[0095] It should be noted that in actual implementation, the structures such as the driving wheel 232, the driven wheel 233 and the transmission belt 234 can be replaced with other transmission structures according to the actual installation situation, including but not limited to gear transmission structure, toothed belt transmission structure, bevel gear transmission structure, etc., as long as the structure can realize the engine transmission power output unit.

[0096] To achieve engine power output, see Figure 7 , Figure 8 The power output unit 204 includes a duct body 241, a connecting frame 242, a front propeller blade 243, a rear propeller blade 244 and a coaxial reverse gear box 245.

[0097] Specifically, after the truss 231 passes through the duct body 241, a coaxial reverse gear box 245 is integrally provided at its end, and a front propeller blade 243 and a rear propeller blade 244 are respectively provided on the power output shafts at the front and rear ends of the coaxial reverse gear box 245, and the driven wheel 233 is arranged on the power output shaft of the coaxial reverse gear box 245; the coaxial reverse gear box 245 is located at the center of the duct body 241, and connecting frames 242 are provided on the top, bottom and sides thereof, and the coaxial reverse gear box 245 is fixedly supported and connected to the inner wall of the duct body 241 through the connecting frames 242 at the top, bottom and sides thereof.

[0098] Through the above structure, the coaxial reverse gearbox 245 distributes the power from the engine 202 to the front propeller blades 243 and the rear propeller blades 244, realizes reverse rotation, offsets the reverse torque generated by the propeller, and improves the stability and controllability of the flight. In addition, the coaxial reverse gearbox 245 is fixedly supported and connected to the inner wall of the duct body 241 through the connecting frames 242 at the top, bottom, and side thereof, and the duct body 241, the coaxial reverse gearbox 245, and the truss 231 are connected as a whole, ensuring the stability and reliability of the duct body 241 during high and low speed flight and the front propeller blades 243 and the rear propeller blades 244 during high speed rotation. The front propeller blades 243 and the rear propeller blades 244 provide the thrust and lift required for flight through reverse rotation, and improve the stability and controllability of the flight. The duct body 241 provides protection and guidance, reduces air resistance, and improves flight efficiency.

[0099] In order to further enhance the connectivity between the truss and the duct body, a bracket 235 is provided at the place where the truss 231 passes through the duct body 241. The bracket 235 is provided at the place where the truss 231 passes through the duct body 241, further enhancing the connectivity between the truss 231 and the duct body 241, ensuring the structural stability and reliability of the truss 231 and the duct body 241 under high-speed rotation and high-load conditions. In addition, the design of the bracket 235 can evenly distribute the stress at the connection between the truss 231 and the duct body 241, reduce local stress concentration, and extend the service life of the system.

[0100] The front end of the duct body 241 is also provided with a protective cover 246, and the rear end thereof is provided with a conical cover 247. The tail end of the conical cover 247 is an open design, and the tail end thereof is provided with a vector adjustment unit 205. The protective cover 246 can effectively protect the front propeller blades 243 and prevent external objects (such as debris, birds, etc.) from entering the duct body 241 and causing damage or accidents. The design of the conical cover 247 can smooth the air flow at the rear end, so that the air can flow through the duct body 241 more smoothly, reduce resistance, and improve the aerodynamic performance of the aircraft. At the same time, the conical cover 247 is provided at the rear end of the duct body 241, which can effectively protect the rear propeller blades 244, prevent external objects from entering the duct body 241, and reduce the risk of damage.

[0101] To adjust the direction and attitude of the aircraft more flexibly in the air and improve the flexibility and stability of flight, see Fig. 9 , Fig.10 The vector adjustment unit 205 includes a tail jet steering cover 251, a guide plate 252, a side adjustment motor 253 and an upper adjustment motor 254.

[0102] The tail jet steering cover 251 is sleeved on the tail opening of the conical cover 247. The top and bottom of the tail jet steering cover 251 are hingedly connected to the tail opening of the conical cover 247. The tail jet steering cover 251 can swing left and right around the hinge point to change the tail jet direction and realize the left and right tilt attitude control of the aircraft. The left and right sides of the tail jet steering cover 251 are provided with arc grooves 255 to prevent the tail jet steering cover 251 and the opening of the conical cover 247 from interfering with each other when turning left and right.

[0103] There are multiple deflectors 252, which are arranged in an array inside the rear end of the tail jet steering cover 251. The deflectors 252 can guide the direction of the tail jet flow, further improving the controllability and stability of the aircraft. The middle part of the deflector 252 is hingedly connected to the side wall of the tail jet steering cover 251 through a hinge shaft, and a linkage vertical plate 256 is arranged at the front end of the deflector 252. The linkage vertical plate 256 is hingedly connected to the front ends of multiple deflectors 252 arranged in a row. The inner wall of the tail jet steering cover 251 at the upper and lower ends of the linkage vertical plate 256 is provided with a limited slide groove 257, and the top and bottom ends of the linkage vertical plate 256 are slidably arranged in the limited slide groove 257. The linkage vertical plate 256 is hingedly connected to the front ends of multiple guide plates 252 arranged in a row. Limiting slide grooves 257 are provided on the inner walls of the tail jet steering cover 251 at the upper and lower ends of the linkage vertical plate 256. The top and bottom ends of the linkage vertical plate 256 are slidably arranged in the limiting slide grooves 257 to ensure the synchronous movement of the guide plates 252.

[0104] The upper adjustment motor 254 is fixedly embedded at the top of the tail jet steering cover 251 above the linkage vertical plate 256 , and a threaded rod 258 is provided on the output shaft of the upper adjustment motor 254 , and the threaded rod 258 is threadedly connected to the top of the linkage vertical plate 256 .

[0105] The side adjustment motor 253 is symmetrically arranged at the arc-shaped grooves 255 on the left and right sides of the tail jet steering cover 251. The side adjustment motor 253 is arranged at the tail opening of the conical cover 247 through a motor bracket 256. A threaded rod 258 is also arranged on the output shaft of the side adjustment motor 253. A motor bracket 256 is also arranged at the arc-shaped groove 255 of the tail jet steering cover 251. The threaded rod 258 is threadedly connected and passes through the motor bracket 256 at the arc-shaped groove 255 of the tail jet steering cover 251.

[0106] The upper adjustment motor 254 and the side adjustment motor 253 are both forward and reverse motors, and the upper adjustment motor 254 and the side adjustment motor 253 are both connected to the left control handle 5 through a control line.

[0107] Through the above structure, the upper adjustment motor 254 is controlled to rotate forward and reversely through the left control handle 5, and the upper adjustment motor 254 drives the threaded rod 258 to operate, driving the threaded rod 258 to move up and down. The up and down movement of the threaded rod 258 drives the linkage vertical plate 256 to slide up and down in the limit slide groove 257 through the threaded connection. The up and down movement of the linkage vertical plate 256 drives the multiple guide plates 252 to swing up and down along the hinge axis in the middle thereof through the hinge connection, thereby changing the direction of the tail jet flow and realizing the pitch control of the aircraft.

[0108] The side adjustment motor 253 is controlled to rotate forward and reversely by the left control handle 5, and the side adjustment motor 253 drives the threaded rod 258 on its output shaft to rotate. The rotation of the threaded rod 258 drives the motor bracket 256 at the arc groove of the tail jet steering cover 251 to move under the action of the thread, thereby driving the tail jet steering cover to swing left and right along the hinge points at the top, bottom and the tail opening of the conical cover 247, changing the direction of the tail jet, and realizing the yaw and left and right tilt attitude control of the aircraft.

[0109] For manned flight, see Figure 2 , Fig.11 The load unit 3 includes a download frame 301 and a shoulder strap 302. The download frame 301 is fixedly arranged at the lower part of the engine 202, and the shoulder strap 302 is fixedly arranged at the bottom of the download frame 301. The download frame 301 is fixedly arranged at the lower part of the engine 202, providing a sturdy frame to ensure that the shoulder strap 302 can be firmly fixed on the aircraft.

[0110] In this embodiment, the harness 302 is a five-point safety harness 302, and the harness 302 is an adjustable harness 302 with a safety buckle. The five-point safety harness can fix the user in all directions to ensure that the user will not fall off the aircraft during flight. At the same time, the adjustable design can be adjusted according to the user's body shape and needs to ensure comfortable wearing and reduce fatigue during long-term flight.

[0111] Example 2

[0112] The same points as the above embodiment will not be repeated here, but the difference is that:

[0113] To ensure the stability and strength of the rocker C123 during the unfolding and folding process, see Figure 2 The front end of the swing rod C123 is connected to the end of the positioning beam 111 through a pull rope 127, and the rear end of the swing rod C123 is connected to the tail of the wing mid-frame 101 through a pull rope 127. Through the above structure, the pull rope can ensure the flatness and stability of the wing in the unfolded state, reduce air resistance, and improve flight efficiency.

[0114] The swing rod C123 is hingedly connected to the pull rope 127, and the pull rope 127 is made of steel wire rope.

[0115] The steel wire rope material is high-strength and durable, and can withstand large tension, ensuring the reliability and safety of the aircraft under various working conditions.

[0116] In addition, a drawstring 127 is provided on the outside of the conical cover 247, and the other end of the drawstring 127 is connected to the rear end of the rocker C123 and / or the outermost tip of the wing skin 103. The multi-point connection design can enhance the structural stability of the wing, ensure reliability and safety in high-speed flight and complex environments, and the connection method of the drawstring 127 can evenly distribute the load on the wing, reduce local stress concentration, and extend the service life of the wing.

[0117] Example 3

[0118] The similarities with the above embodiments and their combinations are not repeated here, and the differences are as follows:

[0119] In this embodiment, in order to optimize the center of gravity distribution of the aircraft and reduce the air resistance during flight, see Figure 1 , Figure 7 The front part of the oil tank 201 is provided with a narrowing part, and the front end thereof is rounded. The oil filling port of the oil tank 201 is provided at the upper end of the oil tank 201, and the oil filling port is lower than the highest point of the wing mid-frame 101.

[0120] The front of the fuel tank 201 adopts a streamlined, rounded narrowing part, which can reduce air resistance during flight and improve flight efficiency. The fuel filling port of the fuel tank 201 is set at the upper end of the fuel tank 201, and the fuel filling port is lower than the highest point of the wing center frame 101, which is convenient for refueling operation and avoids fuel leakage.

[0121] Example 4

[0122] The similarities with the above embodiments and their combinations are not repeated here, and the differences are as follows:

[0123] See also Figure 2 , Figure 8 A plurality of wind tunnels 236 are arranged on the truss 231, and the front and rear edges of the wind tunnels are chamfered and rounded. The design of the wind tunnel 236 can reduce the air resistance of the truss 231 during flight and improve the aerodynamic performance of the aircraft. At the same time, the wind tunnel 236 can introduce external air to help cool the engine 202 behind the wind tunnel and the transmission unit 203 in the truss, ensuring that these components operate normally in a high temperature environment.

[0124] In addition, the rounded chamfering can reduce turbulence and eddy currents at the edge of the wind tunnel 236, further reduce air resistance, and improve the aerodynamic performance of the aircraft. It can also reduce stress concentration at the edge of the wind tunnel 236 during flight, and improve the durability and reliability of the truss 231.

[0125] By opening a wind tunnel, the use of materials is reduced, the weight of the truss 231 is reduced, and the load capacity and endurance of the aircraft are improved.

[0126] Example 5

[0127] The similarities with the above embodiments and their combinations are not repeated here, and the differences are as follows:

[0128] In order to realize the automatic contraction and extension of the telescopic frame during the flight of the aircraft, before and after the flight, enhance its automation and make it easier to adjust the flight attitude, see Figure 4 , Figure 5 The wing midframe 101 is provided with a telescopic drive unit 104. The telescopic drive unit 104 can control the posture of the telescopic frame and the wing skin to unfold in real time.

[0129] Specifically, the telescopic drive unit 104 includes a telescopic motor 141, a screw 142, a threaded hinge sleeve 143 and a screw bracket 144. The front end, tail end and middle part of the screw 142 are rotatably connected to the screw bracket 144, and the screw bracket 144 is fixedly arranged on the wing mid-frame 101 in an integral or separate manner.

[0130] The telescopic motor 141 is on the side of the screw bracket 144 at the front end of the screw 142, and is driven to be connected to the front end of the screw 142. The threaded articulated sleeve 143 is threadedly arranged on the screw 142 between the middle part of the screw 142 and the screw bracket 144 at the tail end. Both sides of the threaded articulated sleeve 143 are hingedly connected to the rear end of the active rocker 126.

[0131] Through the above structure, after the telescopic motor 141 is started, it can drive the screw rod 142 to rotate. When the screw rod 142 rotates, the threaded structure drives the threaded hinge sleeve 143 to move forward or backward along the screw rod 142. The movement of the threaded hinge sleeve 143 drives the rear end of the active rocker 126 to move forward or backward, thereby driving the telescopic frame to extend or retract.

[0132] It should be noted that in this embodiment, in order to prevent the active rocker from moving too far and limit its travel, when the telescopic frame 102 is fully extended, the threaded articulated sleeve 143 is located at the screw support 144 in the middle of the screw 142. When the telescopic frame 102 is fully retracted, the threaded articulated sleeve 143 is located at the screw support 144 at the tail end of the screw 142.

[0133] Example 6

[0134] The same points as the above embodiments and their combinations are not described in detail, but the difference is that:

[0135] To ensure the aircraft is more stable during flight, refer to Figure 6 A protective cover 145 is provided on the upper portion of the telescopic driving unit 104, and the top shape of the protective cover 145 is a transitional curved surface that rises and slowly descends and is integrally provided from front to back.

[0136] The top shape of the protective cover 145 is designed to be an ascending and descending transitional curved surface that is integrally arranged from front to back. This shape can effectively reduce air resistance. During flight, air can flow smoothly over the surface of the protective cover 145, reducing the formation of turbulence and eddies, thereby reducing the resistance of the aircraft and improving flight efficiency. Reducing air resistance means that the aircraft can fly faster or farther at the same power, or maintain the same flight speed at lower power, thereby extending the flight time and improving flight performance. In addition, the protective cover 145 can effectively protect the internal components of the telescopic drive unit 104, prevent dust, rain and other debris from entering, and extend the service life of the mechanical components.

[0137] In this embodiment, the protective cover is detachable, and its internal structure can be maintained by disassembly.

[0138] To prevent the protective cover from interfering with the active rocker movement, see Figure 6The protective cover 145 has a notch at the rear end corresponding to the active rocker 126 .

[0139] In addition, in order to further reduce air resistance during flight, in this embodiment, a detachable fairing is provided at the oil filling port on the top of the oil tank 201. The front part of the fairing fits the top of the oil tank, and the rear part fits the front end of the protective cover.

[0140] The fairing is designed to smooth the air flow around the top of the fuel tank and the fuel filling port, reducing the formation of turbulence and eddies, thereby reducing the aircraft's air resistance. When flying at high speeds, it can improve the efficiency and performance of the aircraft. At the same time, the front of the fairing fits the top of the fuel tank and the rear fits the front of the protective cover, forming a smooth transition and enhancing the overall beauty of the aircraft.

[0141] Example 7

[0142] The same points as the above embodiments and their combinations are not described in detail, but the difference is that:

[0143] See also Fig. 9 , Fig.10 The outer portion of the threaded rod 258 between the linkage vertical plate 256 and the upper adjustment motor 254, and the outer portion of the threaded rod 258 between the motor bracket 256 of the side adjustment motor 253 and the motor bracket 256 at the arc groove 255 of the tail jet steering cover 251 are sleeved with a return spring 259. The ends of the threaded rod 258 are provided with stop blocks.

[0144] The return spring 259 disposed outside the threaded rod 258 between the linkage vertical plate 256 and the upper adjustment motor 254 can make the linkage vertical plate 256 and the tail jet steering cover 251 respond faster when the upper adjustment motor 254 and the side adjustment motor 253 are reversed, thereby improving the stability and agility when adjusting the direction and posture. In addition, a stop block is disposed at the end of the threaded rod to prevent the threaded rod 258 from detaching during the movement, thereby ensuring the safety and reliability of the system.

[0145] Example 8

[0146] The same points as the above embodiments and their combinations are not described in detail, but the difference is that:

[0147] See also Fig.12 , Fig.13In this embodiment, the load unit 3 includes a download frame 301, a detachment frame 303 and an escape backpack. The download frame 301 is fixedly arranged at the lower part of the engine 202, and the detachment frame 303 is detachably arranged at the bottom of the download frame 301. The escape backpack is arranged between the download frame 301 and the detachment frame 303, and the shoulder strap of the escape backpack is passed around the detachment frame 303 for the user to carry it. An electromagnet 304 is arranged on the download frame 301 at the connection between the download frame 301 and the detachment frame 303. In this embodiment, the escape backpack is a parachute bag.

[0148] The electromagnet 304 can firmly fix the detachment frame 303 on the download frame 301 when powered on. In this embodiment, when the user encounters an emergency or failure, the electromagnet 304 can be quickly unlocked when powered off to achieve rapid separation of the detachment frame 303. The user, the detachment frame 303 and the escape backpack are detached from the download frame 301 at the same time, achieving human-machine separation, thereby ensuring the safety of the user.

[0149] Example 9

[0150] The same points as the above embodiments and their combinations are not described in detail, but the difference is that:

[0151] See also Fig.12 , Fig.13 , a plug-in column 331 is provided at the connection between the detachment frame 303 and the download frame 301, and the detachment frame 303 is plugged and arranged at the bottom of the download frame 301 through the plug-in column 331. The plug-in column allows the detachment frame to be quickly plugged into the bottom of the download frame, ensuring convenient loading and unloading in non-emergency situations. When the detachment frame is plugged and arranged at the bottom of the download frame through the plug-in column, a pin is inserted at the download frame and the plug-in column to ensure a stable connection of the detachment frame. The design of the pin ensures that the detachment frame will not be accidentally separated during normal flight, thereby improving safety.

[0152] The load unit further includes a detachment mechanism 305 , which is symmetrically disposed on the download frame 301 , and the download frame 301 is connected to the detachment frame 303 via the detachment mechanism 305 .

[0153] The disengagement mechanism 305 includes a pin 351, a pulley block 352 and an emergency disengagement handle 353. When the disengagement frame 303 is plugged and arranged at the bottom of the download frame 301 through the plug-in column 331, the pin 351 is inserted between the download frame 301 and the plug-in column 331; the pulley block 352 is arranged at the long side of the download frame 301 through the pulley frame 354, and a disengagement rope 355 is arranged at the tail of the pin 351. The disengagement rope 355 at the tail of the pin 351 passes around the pulley block 352 and then connects to the upper end of the emergency disengagement handle 353. The middle part of the emergency disengagement handle 353 is arranged at the front end of the download frame 301 through a hinge frame for the user to pull in an emergency.

[0154] The pulley block is set at the long side of the download frame through the pulley frame to guide the movement of the wire rope and reduce friction and resistance. The design of the pulley block ensures the smooth movement of the wire rope and improves the response speed and reliability of the disengagement mechanism. Through the above structure, when the user pulls the emergency disengagement handle in an emergency, the wire rope transmits force through the pulley block, so that the pin shaft is pulled out from the download frame and the plug-in column, realizing the rapid separation of the disengagement frame.

[0155] The purely mechanical design can prevent separation failure due to aircraft failure, has strong reliability, and can achieve rapid separation of man and machine.

[0156] Example 10

[0157] The same points as the above embodiments and their combinations are not described in detail, but the difference is that:

[0158] The download frame 301 is provided with a miniature vertical roller 311, and the miniature vertical roller 311 is arranged at the support foot of the download frame 301 where the steel wire rope passes.

[0159] The download frame is equipped with micro rollers, which are set at the feet of the download frame where the wire rope passes. The micro rollers can reduce the friction of the wire rope during movement, ensure the smooth movement of the wire rope, and improve the response speed and reliability of the disengagement mechanism. At the same time, the micro rollers can protect the wire rope, reduce wear and extend the service life of the wire rope.

[0160] The working principle of the portable single-person low-altitude vector jet aircraft with a folding wing structure of the present invention is as follows:

[0161] When the present invention is in use, the user starts the engine 202 through the right control handle 4, and the fuel tank 201 supplies fuel to the engine 202 through the oil circuit. The operation of the engine drives the driving wheel 232 to rotate. The driving wheel 232 drives the driven wheel 233 to rotate through the transmission belt 234, thereby driving the coaxial reverse gear box 245 in the power output unit 204, and the front propeller blade 243 and the rear propeller blade 244 are driven to rotate through the coaxial reverse gear box 245.

[0162] The user starts the telescopic drive unit 104 by controlling the handle, and the telescopic motor 141 drives the screw 142 to rotate. The screw 142 drives the threaded hinge sleeve 143 to move forward along the screw 142 through the threaded structure, and the movement of the threaded hinge sleeve 143 drives the rear end of the active rocker 126 to move forward, thereby driving the multi-link structure to extend. Finally, the telescopic frame 102 is fully extended, driving the wing skin 103 to extend, and the wing is extended.

[0163] The user adjusts the power and thrust of the engine 202 through the right control handle 4 to achieve speed control during takeoff and flight of the aircraft. When it is necessary to adjust the flight attitude or jet angle, the upper adjustment motor 254 and the side adjustment motor 253 are controlled through the left control handle 5 to achieve pitch and yaw control of the aircraft.

[0164] During flight, the wind tunnel 236 introduces external air to help cool the engine 202 and the transmission unit 203, ensuring that these components operate normally in a high temperature environment.

[0165] In an emergency, the user pulls the emergency detachment handle 353, and the steel wire 355 transmits force through the pulley block 352, so that the pin 351 is pulled out from the download frame 301 and the plug-in column 331, and the detachment frame 303 is quickly separated. The user, the detachment frame 303 and the escape backpack are detached from the download frame 301 at the same time, realizing the separation of man and machine, ensuring the safety of the user. The electromagnet 304 is quickly unlocked after power failure, further ensuring the reliability of emergency detachment.

[0166] After the flight, the user starts the telescopic drive unit 104 through the control handle, the telescopic motor 141 drives the screw 142 to rotate in the opposite direction, the threaded hinge sleeve 143 moves backward along the screw 142, driving the rear end of the active rocker 126 to move backward, and the telescopic frame 102 is folded, completing the contraction of the telescopic frame 102 and the wing skin.

[0167] It should be noted that, when the device is implemented, the structure described in the drawings of this specification is not a fixed and unchanging implementation method. In addition, the drawings of this specification and the drawings of the abstract are only schematic diagrams and do not represent the specific structure and actual quantity of the specific implementation.

[0168] Unless otherwise defined, the technical or scientific terms used herein shall have the ordinary meaning understood by a person of ordinary skill in the field to which the invention belongs. The use of "one" or "an" and other similar words in the specification and claims of this application does not necessarily indicate a quantitative limitation. "Include" or "comprises" and other similar words mean that the elements or components appearing before the word include the elements or components listed after the word and their equivalents, without excluding other elements or components. "Connect" or "connected" and other similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect.

[0169] The exemplary implementation modes of the present invention are described in detail above with reference to the preferred embodiments. However, it can be understood by those skilled in the art that, without departing from the concept of the present invention, various modifications and variations can be made to the above-mentioned specific embodiments, and various combinations of the technical features and structures proposed in the present invention can be made without exceeding the protection scope of the present invention.

Claims

1. A portable single-person low-altitude vector jet aircraft with a folding wing structure, characterized in that: It comprises a frame part, a power part and a load part, wherein the power part is arranged below the frame part, and the load part is arranged below the power part; The frame part includes a wing middle frame, a telescopic frame and a wing skin, the power part is arranged below the wing middle frame, and the load part is arranged below the power part; The telescopic frame is symmetrically arranged on both sides of the upper part of the wing center frame, and the wing skin is fixedly wrapped and laid on the outside of the telescopic frame.

2. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 1, characterized in that: The wing mid-frame is T-shaped when viewed from above, and a positioning beam is provided at the top of the front end cross beam. A hanger is integrally provided at the side and bottom of the middle position of the bottom of the T-shaped wing mid-frame, and the power unit is hoisted at the bottom of the hanger; The telescopic frame is symmetrically arranged on both sides of the wing mid-frame, and the telescopic frame is a multi-link structure, including a rocker A, a rocker B, a rocker C, a connecting rod A, a connecting rod B and an active rocker; The front end of the swing rod A is hingedly connected to the positioning beam, and the rear end is hingedly connected to the middle part of the connecting rod A; The right side of the middle part of the rocker A is hingedly connected to the front end of the active rocker, the rear end of the active rocker is displaceable and can be fixedly arranged at the tail of the T-shaped wing center frame, the middle part of the active rocker is hingedly connected to the end of the connecting rod A through the rocker B, and the other end of the connecting rod A is hingedly connected to the middle part of the rocker C; The left side of the middle part of the swing rod A is hingedly connected to the end of the connecting rod B, and the other end of the connecting rod B is hingedly connected to the front end of the swing rod C; The hinge point between the active rocker and the rocker rod A is close to the front end of the rocker rod A, and the hinge point between the connecting rod B and the rocker rod A is close to the rear end of the rocker rod A.

3. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 2, characterized in that: The wing mid-frame is provided with a telescopic drive unit, which includes a telescopic motor, a screw, a threaded hinge sleeve and a screw bracket. The front end, the tail end and the middle part of the screw are rotatably connected with the screw bracket, and the screw bracket is fixedly arranged on the wing mid-frame in one piece or in a split manner; The telescopic motor is on the side of the screw bracket at the front end of the screw and is drivingly connected to the front end of the screw. The threaded hinge sleeve is threadedly arranged on the screw between the middle part of the screw and the screw bracket at the tail end. Both sides of the threaded hinge sleeve are hingedly connected to the rear end of the active rocker. A protective cover is provided on the upper part of the telescopic drive unit, the top of the protective cover is an integrally arranged transitional curved surface that rises and slowly descends from front to back, and a notch is provided on the protective cover corresponding to the rear end of the active rocker; When the telescopic frame is fully extended, the threaded articulated sleeve is located at the screw support in the middle of the screw, and when the telescopic frame is fully retracted, the threaded articulated sleeve is located at the screw support at the rear end of the screw.

4. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 2, characterized in that: The front end of the swing rod C is connected to the end of the positioning beam through a pull rope, and the rear end of the swing rod C is connected to the tail of the wing mid-frame through a pull rope; The swing rod C is hingedly connected to the pull rope, and the pull rope is made of steel wire rope.

5. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 2, characterized in that: The power unit includes a fuel tank, an engine, a transmission unit and a power output unit. The fuel tank is arranged at the middle position of the lower front end of the wing mid-frame, the engine is arranged at the bottom of the hanger, and the hanger is located at the side and bottom of the wing mid-frame behind the fuel tank. The power output unit is symmetrically arranged on both sides of the engine. The fuel tank is connected to the engine through an oil circuit, and the engine is driven by the transmission unit and fixedly connected to the power output unit. The engine is connected with a right control handle via a control line.

6. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 5, characterized in that: The front part of the fuel tank is provided with a narrowing part, the front end of which is rounded, and the fuel filling port of the fuel tank is provided at the upper end of the fuel tank, and the fuel filling port is lower than the highest point of the wing mid-frame; A detachable fairing is arranged at the oil filling port on the top of the oil tank.

7. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 6, characterized in that: The transmission unit is arranged at the front end of the engine, and the transmission unit includes a truss, a driving wheel, a driven wheel and a transmission belt. The truss is fixedly arranged horizontally at the front end of the engine, and the driving wheel, the driven wheel and the transmission belt are all arranged inside the truss. The power output shaft of the engine is provided with a driving wheel after passing through the truss, and the driven wheel is arranged on the rotating shaft of the power output unit. The driving wheel and the driven wheel are connected by the transmission belt. A plurality of wind tunnels are arranged on the truss, and the front and rear side edges of the wind tunnels are chamfered and rounded.

8. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 7, characterized in that: The power output unit includes a duct cylinder, a connecting frame, front propeller blades, rear propeller blades and a coaxial reverse gearbox. After the truss passes through the duct cylinder, a coaxial reverse gearbox is integrally provided at its end. A bracket is provided at the place where the truss passes through the duct cylinder. Front propeller blades and rear propeller blades are respectively provided on the power output shafts at the front and rear ends of the coaxial reverse gearbox, and the driven wheel is provided on the power output shaft of the coaxial reverse gearbox. The coaxial reverse gearbox is located at the center of the duct cylinder, and connecting frames are provided on the top, bottom and sides of the duct cylinder. The coaxial reverse gearbox is fixedly supported and connected to the inner wall of the duct cylinder by the connecting frames at the top, bottom and sides.

9. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 8, characterized in that: The front end of the duct body is also provided with a protective cover, and the rear end thereof is provided with a conical cover, a pull rope is provided on the outside of the conical cover, and the other end of the pull rope is connected to the rear end of the rocker C and / or the outermost tip of the wing skin, and the tail end of the conical cover is an open design, and a vector adjustment unit is provided at the tail end; The vector adjustment unit includes a tail jet steering cover, a guide plate, a side adjustment motor and an upper adjustment motor. The tail jet steering cover is sleeved on the tail opening of the conical cover. The top and bottom of the tail jet steering cover are hingedly connected to the tail opening of the conical cover. The left and right sides of the tail jet steering cover are provided with arc grooves to prevent the tail jet steering cover and the conical cover opening from interfering with each other when the tail jet steering cover rotates left and right. The deflector is provided with a plurality of deflectors, which are arranged in an array inside the rear end of the tail jet steering cover, the middle portion of the deflector is hingedly connected to the side wall of the tail jet steering cover through a hinge shaft, the front end of the deflector is provided with a linkage vertical plate, the linkage vertical plate is hingedly connected to the front ends of the plurality of deflectors arranged in a row, and the inner wall of the tail jet steering cover at the upper and lower ends of the linkage vertical plate is provided with a limited sliding groove, and the top and bottom ends of the linkage vertical plate are slidably arranged in the limited sliding groove; The upper adjustment motor is fixedly arranged at the top of the tail jet steering cover above the linkage vertical plate in an embedded manner, and a threaded rod is arranged on the output shaft of the upper adjustment motor, and the threaded rod is threadedly connected to the top of the linkage vertical plate; The side adjustment motor is symmetrically arranged at the arc-shaped grooves on the left and right sides of the tail jet steering cover, and the side adjustment motor is arranged at the tail opening of the conical cover through a motor bracket, and a threaded rod is also arranged on the output shaft of the side adjustment motor, and a motor bracket is also arranged at the arc-shaped groove of the tail jet steering cover, and the threaded rod is threadedly connected and passes through the motor bracket at the arc-shaped groove of the tail jet steering cover; The outer part of the threaded rod between the linkage vertical plate and the upper adjustment motor, and the outer part of the threaded rod between the motor bracket of the side adjustment motor and the motor bracket at the arc-shaped groove of the tail spray steering cover are sleeved with a return spring, and the end of the threaded rod is provided with a stop block; The upper regulating motor and the side regulating motor are both forward and reverse motors, and are connected to the left control handle via a control line.

10. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 9, characterized in that: The load-bearing part includes a download frame and a shoulder strap, wherein the download frame is fixedly arranged at the lower part of the engine, and the shoulder strap is fixedly arranged at the bottom of the download frame; The shoulder strap is a five-point safety shoulder strap, and the shoulder strap is an adjustable shoulder strap with a safety buckle.

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