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

Abstract

The utility model relates to the field of aircrafts, in particular to a portable single-person low-altitude vector jet aircraft with a folding wing structure, which 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 and is convenient to carry and store when not used, the problems that a traditional single-person aircraft is large in size and difficult to carry are solved, and 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 improved, and the aircraft is more efficient in the flight process.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of aircraft, concretely relates to a portable single-person low-altitude vector jet aircraft with folding wing structure. BACKGROUND

[0002] Single-person aircraft refers to the flying equipment that is manufactured by human, can fly off the ground and fly in space, and is controlled by a person.

[0003] The personal aircraft not only can provide the quick and convenient air travel mode, but also can play an important role in specific occasions such as emergency rescue, military reconnaissance and the like.

[0004] In the prior art, the single-person aircraft generally has the characteristics of large size, most of the personal aircrafts are large in size due to the structural design, are difficult to conveniently carry and store, need to occupy a large space in carrying and storing, limit the application range in daily life, and the large size makes the aircrafts very inconvenient in the process of transportation and use. UTILITY MODEL CONTENTS

[0005] The utility model aims at overcoming the defects described in the background art, and realizes a portable single-person low-altitude vector jet aircraft with folding wing structure, so as to solve the problems of large structure size of the single-person aircraft in the prior art, difficult to conveniently carry and store, large space occupation, influence on applicability, and inconvenience in the process of use.

[0006] To realize the utility model purpose, the technical scheme of the utility model is as follows:

[0007] A portable single-person low-altitude vector jet aircraft with folding wing structure, comprising 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 comprises a wing middle frame, an extension skeleton 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 extension skeleton is symmetrically arranged on both sides of the upper part of the wing middle frame, and the wing skin is fixedly wrapped and laid outside the extension skeleton.

[0009] In the portable single-person low-altitude vector jet aircraft with folding wing structure, the wing middle frame is T-shaped when viewed from above, a positioning beam is arranged at the top of the front end beam of the T-shaped wing middle frame, a suspension bracket is integrally arranged at the side of the middle position of the bottom of the T-shaped wing middle frame and the bottom, and the power part is suspended at the bottom of the suspension bracket.

[0010] Meanwhile, the telescopic frame is symmetrically arranged on both sides of the wing middle frame, and the telescopic frame is a multi-link structure, including a swing rod A, a swing rod B, a swing rod C, a connecting rod A, a connecting rod B and a driving rocker.

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

[0012] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, a telescopic driving unit is arranged on the wing middle frame, the telescopic driving unit includes a telescopic motor, a screw rod, a threaded hinged sleeve and a screw rod support, the front end, the tail end and the middle part of the screw rod are rotatably connected with the screw rod support, and the screw rod support is integrally or separately fixedly arranged on the wing middle frame.

[0013] Specifically, the telescopic motor is arranged on the side of the screw rod support of the front end of the screw rod and drives the front end of the screw rod, the threaded hinged sleeve is threadedly arranged on the screw rod between the screw rod support of the middle part and the tail end of the screw rod, and the threaded hinged sleeve is hingedly connected to the rear end of the driving rocker on both sides.

[0014] In addition, a protective cover is arranged on the upper part of the telescopic driving unit, the top of the protective cover is in the shape of a transition curved surface that rises and then gently descends, and a notch is arranged on the protective cover corresponding to the rear end of the driving rocker.

[0015] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, when the telescopic frame is fully unfolded, the threaded hinged sleeve is located at the screw rod support of the middle part of the screw rod, and when the telescopic frame is fully folded, the threaded hinged sleeve is located at the screw rod support of the tail end of the screw rod.

[0016] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, 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 middle frame through the pull rope.

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

[0018] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, the power unit comprises an oil tank, an engine, a transmission unit and a power output unit, the oil tank is arranged at the middle position of the lower part of the front end of the wing, the engine is arranged at the bottom of the suspension bracket, the suspension bracket is arranged at the wing suspension bracket side and the bottom of the rear side of the oil tank, the power output unit is symmetrically arranged on both sides of the engine, the oil tank is connected with the engine through an oil line, and the engine drives and fixedly connects the power output unit through the transmission unit.

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

[0020] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, the front part of the oil tank is provided with a narrowing part, the front end of the oil tank is smoothly processed, and the oil inlet of the oil tank is arranged at the upper end of the oil tank and is lower than the highest position of the wing suspension bracket.

[0021] Preferably, the oil inlet at the top of the oil tank is provided with a detachable fairing.

[0022] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, the transmission unit is arranged at the front end of the engine, the transmission unit comprises a diverging frame, a driving wheel, a driven wheel and a transmission belt, the diverging frame is fixedly arranged at the front end of the engine in a transverse direction, the driving wheel, the driven wheel and the transmission belt are arranged in the diverging frame, the power output shaft of the engine penetrates the diverging frame and is provided with the driving wheel at the rear end, the driven wheel is arranged on the rotating shaft of the power output unit, and the driving wheel and the driven wheel are connected through the transmission belt.

[0023] Preferably, a plurality of wind tunnels are arranged on the diverging frame, and the front and rear side edges of the wind tunnels are smoothly processed through chamfering.

[0024] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, the power output unit comprises a duct cylinder, a connecting frame, a front propeller blade, a rear propeller blade and a coaxial reverse gear box, the diverging frame penetrates the duct cylinder and is integrally provided with the coaxial reverse gear box at the end thereof, the diverging frame is provided with a support at the position penetrating the duct cylinder, the power output shafts at the front end and the rear end of the coaxial reverse gear box are respectively provided with the front propeller blade and the rear propeller blade, and the driven wheel is arranged on the power output shaft of the coaxial reverse gear box; the coaxial reverse gear box is located at the center position of the duct cylinder, and the top, the bottom and the side of the coaxial reverse gear box are provided with the connecting frame, and the coaxial reverse gear box is fixedly and supportively connected with the inner wall of the duct cylinder through the connecting frames at the top, the bottom and the side thereof.

[0025] In the portable single-person low-altitude vector jet aircraft with the folding wing structure, the front end of the duct barrel is further provided with a protective cover, and the rear end is provided with a conical cover. A pull rope is arranged outside the conical cover. The other end of the pull rope is connected to the rear end of the swing rod C and / or the tip of the outermost wing skin. The tail of the conical cover is designed as an open end. A vector adjusting unit is arranged at the tail of the conical cover.

[0026] Specifically, the vector adjusting unit comprises a tail jet deflection cover, a guide plate, a side adjusting motor and an upper adjusting motor. The tail jet deflection cover is sleeved at the tail opening of the conical cover. The top and bottom of the tail jet deflection cover are hingedly connected to the tail opening of the conical cover. Arc-shaped grooves are formed in the left and right sides of the tail jet deflection cover to prevent the tail jet deflection cover from interfering with the tail opening of the conical cover when the tail jet deflection cover is turned left or right.

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

[0028] Specifically, the upper adjusting motor is fixedly arranged in the tail jet deflection cover above the linkage vertical plate. A threaded rod is arranged on the output shaft of the upper adjusting motor. The threaded rod is threadedly connected to the top of the linkage vertical plate.

[0029] Meanwhile, the side adjusting motor is symmetrically arranged at the arc-shaped grooves on the left and right sides of the tail jet deflection cover. The side adjusting motor is arranged at the tail opening of the conical cover through a motor support. A threaded rod is also arranged on the output shaft of the side adjusting motor. A motor support is also arranged at the arc-shaped groove of the tail jet deflection cover. The threaded rod is threadedly connected to and penetrates through the motor support at the arc-shaped groove of the tail jet deflection cover.

[0030] Preferably, a reset spring is sleeved outside the threaded rod between the linkage vertical plate and the upper adjusting motor, and outside the threaded rod between the motor support of the side adjusting motor and the motor support at the arc-shaped groove of the tail jet deflection cover. A stop block is arranged at the end of the threaded rod.

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

[0032] The load part comprises a load rack and a shoulder strap, the load rack is fixedly arranged at the lower part of the engine, and the shoulder strap is fixedly arranged at the bottom of the load rack.

[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 the folding wing structure has at least the following beneficial effects:

[0035] 1. The portable single-person low-altitude vector jet aircraft with the folding wing structure has the advantages that the telescopic framework with the multi-link structure design can be easily folded when the aircraft is not used, the aircraft occupies a small space, and the aircraft is convenient to carry and store.

[0036] 2. Meanwhile, the multi-point support design of the telescopic framework 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, the protective cover, the conical cover, the wind tunnel and the fairing reduces the air resistance of the aircraft and improves the aerodynamic performance.

[0037] The aircraft is more efficient during flight, the endurance time is prolonged, the flight speed is improved, the streamlined design of the fuel tank and the cooling function of the wind tunnel optimize the operating environment of the power system, and the working efficiency of the engine is improved.

[0038] 3. The five-point safety shoulder strap and the escape backpack provide comprehensive safety protection, ensuring that the user can quickly escape from the aircraft in an emergency.

[0039] 4. The telescopic drive unit and the vector adjustment unit improve the automation degree of the aircraft, so that the user can more conveniently adjust the flight attitude. BRIEF DESCRIPTION OF DRAWINGS

[0040] Figure 1 is a perspective structural schematic view of the portable single-person low-altitude vector jet aircraft with the folding wing structure of the utility model;

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

[0042] Figure 3 is the three-dimensional structural schematic diagram of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure after removing the wing skin;

[0043] Figure 4 is the overhead structural schematic diagram of the telescopic framework of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure;

[0044] Figure 5 is the three-dimensional structural schematic diagram of the telescopic framework of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure;

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

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

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

[0048] Figure 9 is the installation position schematic diagram of the vector adjusting unit of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure;

[0049] Figure 10 is the sectional structural schematic diagram of the vector adjusting unit of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure;

[0050] Figure 11 is the three-dimensional structural schematic diagram of the load part of the portable single-person low-altitude vector jet aircraft of the utility model with folding wing structure;

[0051] Figure 12 is the three-dimensional structural schematic diagram of the load part in example 9;

[0052] Figure 13 is Figure 12 the three-dimensional structural schematic diagram of the load part after separation.

[0053] In the figure:

[0054] 1-frame part:

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

[0056] 102-Telescopic skeleton, 121- Swing lever A, 122- Swing lever B, 123- Swing lever C, 124- Connecting rod A, 125- Connecting rod B, 126- Main driving rocker, 127- Pulling rope;

[0057] 103- Wing skin;

[0058] 104- Telescopic driving unit, 141- Telescopic motor, 142- Screw rod, 143- Threaded articulated sleeve, 144- Screw rod support, 145- Protective cover;

[0059] 2- Power part:

[0060] 201- Fuel tank; 202- Engine;

[0061] 203- Transmission unit, 231- Yoke, 232- Driving wheel, 233- Driven wheel, 234- Transmission belt, 235- Support, 236- Wind tunnel;

[0062] 204- Power output unit, 241- Duct cylinder, 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 adjusting unit, 251- Tail jet steering cover, 252- Guide plate, 253- Side adjusting motor, 254- Upper adjusting motor, 255- Arc-shaped groove, 256- Motor support, 257- Limiting sliding groove, 258- Threaded rod, 259- Reset spring;

[0064] 3- Load part:

[0065] 301- Download frame, 311- Mini vertical roller;

[0066] 302- Back strap;

[0067] 303- Detaching frame, 331- Inserted vertical column;

[0068] 304- Electromagnet;

[0069] 305- Detaching mechanism, 351- Pin shaft, 352- Pulley block, 353- Emergency detaching handle, 354- Pulley frame, 355- Detaching rope;

[0070] 4- Right control handle; 5- Left control handle. DETAILED DESCRIPTION

[0071] The portable single-person low-altitude vector jet aircraft with the folding wing structure will be described in more detail in combination with the drawings and through specific embodiments.

[0072] In the description of the utility model, it is understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the utility model.

[0073] Embodiment 1

[0074] The embodiment discloses a portable single-person low-altitude vector jet aircraft with a folding wing structure, so as to solve the problems in the prior art that the single-person aircraft structure is large in size, is difficult to conveniently carry and store, occupies a large space, affects applicability, and is inconvenient to use, and the like. Figure 1 、 Figure 2 , including a frame part 1, a power part 2 and a load part 3, 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 by the cooperation of the power part 2 and the frame part 1. For details, see the following content.

[0075] In order to support the mold part, referring to Figure 1 、 Figure 3 , the frame part 1 comprises a wing middle frame 101, a telescopic skeleton 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 wing middle frame 101, the telescopic skeleton 102 and the wing skin 103 of the frame part are cooperated by the power part 2, so that the lifting is completed.

[0076] Specifically, referring to Figure 6 , the telescopic skeleton 102 is symmetrically arranged on both sides of the upper part of the wing middle frame 101, and the wing skin 103 is fixedly wrapped and laid outside the telescopic skeleton 102.

[0077] The telescopic skeleton 102 is telescoped, so that the occupied space of the aircraft is reduced.

[0078] In order to install the telescopic skeleton 103, referring to Figure 4 , the wing middle frame 101 is T-shaped when viewed from above, and a positioning beam 111 is arranged at the top of the front end beam. In addition, in order to facilitate the installation of the engine, referring to Figure 5 , the T-shaped wing middle frame 101 is integrally provided with a hanger 112 at the side of the middle position of the bottom and the bottom, and the power part 2 is hung on the bottom of the hanger 112.

[0079] In order to make the overall structure of the frame part 1 reasonable and lift under the drive of the power part, referring toFigure 3 、 Figure 4 , the telescopic skeleton 102 is symmetrically arranged on both sides of the wing middle frame 101.

[0080] In order to realize the telescopic function of the telescopic skeleton and reduce the occupied space, referring to Figure 4 、 Figure 5 , the telescopic skeleton 102 is a multi-link structure.

[0081] In order to realize the telescopic function of the multi-link structure, referring to Figure 4 、 Figure 5 , the telescopic skeleton 102 includes a swing rod A 121, a swing rod B 122, a swing rod C 123, a connecting rod A 124, a connecting rod B 125 and a driving rocker 126.

[0082] Specifically, the swing rod A 121 is hingedly connected to the front end of the positioning beam 111 and the middle part of the connecting rod A 124. The middle part of the swing rod A 121 is hingedly connected to the front end of the driving rocker 126, and the rear end of the driving rocker 126 is displaceable and fixable on the tail of the T-shaped wing middle frame 101. The middle part of the driving rocker 126 is hingedly connected to the end of the connecting rod A 124 through the swing rod B 122, and the other end of the connecting rod A 124 is hingedly connected to the middle part of the swing rod C 123.

[0083] Meanwhile, the middle part of the swing rod A 121 is hingedly connected to the end of the connecting rod B 125, and the other end of the connecting rod B 125 is hingedly connected to the front end of the swing rod C 123. The hinged point of the driving rocker 126 and the swing rod A 121 is close to the front end of the swing rod A 121, and the hinged point of the connecting rod B 125 and the swing rod A 121 is close to the rear end of the swing rod A 121.

[0084] Through the above structure, when the rear end of the driving rocker 126 moves forward, the front end of the driving rocker 126 also moves, and when the front end of the driving rocker 126 moves, the middle part of the swing rod A 121 is pushed forward through the hinged point, and the front end of the swing rod A 121 is fixed on the positioning beam 111, so that the swing rod A 121 rotates around the positioning beam 111 and gradually unfolds.

[0085] When the middle part of the swing rod A 121 moves forward, the front ends of the connecting rod A 124 and the connecting rod B 125 are pushed outward through the hinged point. The unfolding of the connecting rod A 124 and the connecting rod B 125 pushes the front end of the swing rod C 123 to move outward. The above telescopic skeleton drives the wing skin 103 to unfold at the same time. When the telescopic skeleton supports the wing skin to completely unfold, the driving rocker is fixed on the wing middle frame, thereby completing the unfolding of the wing.

[0086] The aircraft can be easily folded when not in use, occupying less space and being convenient to carry and store. At the same time, the stability and reliability of the wing during the unfolding and folding process are ensured through the design of the multi-link structure, 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 unfolded state, improving the stability and safety of the aircraft.

[0087] In this embodiment, the active rocker can be fixed to the wing truss by pinning, or by other means, as long as it can be fixed to the wing truss after sliding expansion and sliding contraction.

[0088] 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 part of the front end of the wing truss 101, the engine 202 is arranged at the bottom of the suspension 112, the suspension 112 is located at the side and bottom of the wing truss 101 on the rear side of 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 line, the engine 202 drives and fixedly connects the power output unit 204 through the transmission unit 203. 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 end of the lower part of the wing truss 101, which can optimize the center of gravity distribution of the aircraft and improve the stability and maneuverability of the flight.

[0090] The engine 202 generates high-temperature and high-pressure gas by burning fuel, drives the propeller or other propulsion devices, and provides the required thrust and lift 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 control the speed of the aircraft.

[0091] To realize the transmission of the engine to the power output unit, refer to 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 yoke 231, a driving wheel 232, a driven wheel 233, and a transmission belt 234.

[0092] Specifically, refer to Figure 7The bracket 231 is fixed transversely at the front end of the engine 202, the driving wheel 232, the driven wheel 233 and the transmission belt 234 are arranged inside the bracket 231, the power output shaft of the engine 202 penetrates the bracket 231 and is provided with the driving wheel 232, the driven wheel 233 is arranged on the rotating shaft of the power output unit 204, and the driving wheel 232 and the driven wheel 233 are connected through the transmission belt 234.

[0093] The bracket 231 is fixed transversely at the front end of the engine 202, which provides a solid mounting frame and ensures that each component of the transmission unit 203 and the power output unit 204 can be stably mounted and operated.

[0094] When the engine 202 operates, the driving wheel 232 drives the transmission belt 234 to drive the driven wheel 233 to operate, thereby driving the power output unit to operate.

[0095] It should be noted that in actual implementation, the driving wheel 232, the driven wheel 233 and the transmission belt 234 can be replaced by other transmission structures, 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 transmission of the engine to the power output unit.

[0096] To realize the engine power output, refer to Figure 7 , Figure 8 The power output unit 204 includes a duct cylinder 241, a connecting bracket 242, a front propeller blade 243, a rear propeller blade 244 and a coaxial reverse gear box 245.

[0097] Specifically, the bracket 231 penetrates the duct cylinder 241, and the end portion of the bracket 231 is integrally provided with the coaxial reverse gear box 245, the front end and the rear end of the coaxial reverse gear box 245 are respectively provided with the front propeller blade 243 and the rear propeller blade 244, 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 cylinder 241, and the top, bottom and side of the coaxial reverse gear box 245 are provided with the connecting bracket 242, and the coaxial reverse gear box 245 is fixedly connected to the inner wall of the duct cylinder 241 through the connecting bracket 242 on the top, bottom and side thereof.

[0098] Through the above structure, the coaxial reverse gear box 245 distributes the power from the engine 202 to the front propeller blade 243 and the rear propeller blade 244 to realize reverse rotation, offset the counter torque generated by the propeller, and improve the stability and maneuverability of flight. In addition, the coaxial reverse gear box 245 is fixed and supported by the connecting frame 242 on the top, bottom and side of the coaxial reverse gear box 245 to fix the inner wall of the duct cylinder 241, so as to connect the duct cylinder 241, the coaxial reverse gear box 245 and the outrigger 231 into one body, and ensure the stability and reliability of the duct cylinder 241 in high and low speed flight and the front propeller blade 243 and the rear propeller blade 244 in high speed rotation. The front propeller blade 243 and the rear propeller blade 244 provide the required thrust and lift for flight through reverse rotation, and improve the stability and maneuverability of flight. The duct cylinder 241 provides protection and guidance, reduces air resistance, and improves flight efficiency.

[0099] To further enhance the connectivity of the outrigger and the duct cylinder, the outrigger 231 is provided with a support 235 at the position penetrating the duct cylinder 241. The support 235 is arranged at the position where the outrigger 231 penetrates the duct cylinder 241, which further enhances the connectivity of the outrigger 231 and the duct cylinder 241, and ensures the structural stability and reliability of the outrigger 231 and the duct cylinder 241 under high speed rotation and high load conditions. In addition, the design of the support 235 can uniformly distribute the stress at the connection between the outrigger 231 and the duct cylinder 241, reduce local stress concentration, and prolong the service life of the system.

[0100] The duct cylinder 241 is further provided with a protective cover 246 at the front end and a conical cover 247 at the rear end. The conical cover 247 is designed as an open tail, and a vector adjusting unit 205 is arranged at the tail. The protective cover 246 can effectively protect the front propeller blade 243 and prevent external objects (such as debris, birds, etc.) from entering the duct cylinder 241 to cause 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 more smoothly through the duct cylinder 241, reducing resistance and improving the aerodynamic performance of the aircraft. At the same time, the conical cover 247 is arranged at the rear end of the duct cylinder 241, which can effectively protect the rear propeller blade 244 and prevent external objects from entering the duct cylinder 241, reducing the risk of damage.

[0101] To realize more flexible adjustment of the direction and attitude of the aircraft in the air, improve the flexibility and stability of flight, and improve the flexibility and stability of flight, refer to Figure 9 , Figure 10 The vector adjusting unit 205 includes a tail jet turning cover 251, a guide plate 252, a side adjusting motor 253 and an upper adjusting motor 254.

[0102] The tail jet deflection cover 251 is sleeved at the tail opening of the conical cover 247, the top and bottom of the tail jet deflection cover 251 are hingedly connected to the tail opening of the conical cover 247, the tail jet deflection cover 251 can swing left and right around the hinge point, change the direction of the tail jet, and realize the left and right attitude control of the aircraft. The arc-shaped grooves 255 are formed on the left side and the right side of the tail jet deflection cover 251 to prevent the tail jet deflection cover 251 from interfering with the opening of the conical cover 247 when turning left and right.

[0103] The guide plates 252 are arranged in multiple, and the multiple guide plates 252 are arranged in an array inside the rear end of the tail jet deflection cover 251, the guide plates 252 can guide the direction of the tail jet flow, and further improve the controllability and stability of the aircraft. The middle part of the guide plate 252 is hingedly connected to the side wall of the tail jet deflection cover 251, the front end of the guide plate 252 is provided with a linkage vertical plate 256, the linkage vertical plate 256 is hingedly connected to the front ends of the multiple guide plates 252 arranged in an array, the inner wall of the tail jet deflection cover 251 at the upper end and the lower end of the linkage vertical plate 256 is provided with a limiting sliding groove 257, and the top end and the bottom end of the linkage vertical plate 256 are slidingly arranged in the limiting sliding groove 257. The linkage vertical plate 256 is hingedly connected to the front ends of the multiple guide plates 252 arranged in an array, the inner wall of the tail jet deflection cover 251 at the upper end and the lower end of the linkage vertical plate 256 is provided with a limiting sliding groove 257, and the top end and the bottom end of the linkage vertical plate 256 are slidingly arranged in the limiting sliding groove 257, to ensure the synchronous action of the guide plates 252.

[0104] The upper adjusting motor 254 is embeddedly and fixedly arranged above the linkage vertical plate 256 on the top of the tail jet deflection cover 251, a threaded rod 258 is arranged on the output shaft of the upper adjusting motor 254, and the threaded rod 258 is threadedly connected to the top of the linkage vertical plate 256.

[0105] The side adjusting motors 253 are symmetrically arranged at the arc-shaped grooves 255 on the left side and the right side of the tail jet deflection cover 251, the side adjusting motors 253 are arranged at the tail opening of the conical cover 247 through motor supports 256, threaded rods 258 are arranged on the output shafts of the side adjusting motors 253, motor supports 256 are also arranged at the arc-shaped grooves 255 of the tail jet deflection cover 251, and the threaded rods 258 are threadedly connected and penetrate the motor supports 256 at the arc-shaped grooves 255 of the tail jet deflection cover 251.

[0106] The upper adjusting motor 254 and the side adjusting motor 253 are reversible motors, and the upper adjusting motor 254 and the side adjusting motor 253 are connected to the left control handle 5 through a control circuit.

[0107] With the above structure, the left control handle 5 controls the forward and reverse rotation of the upper adjustment motor 254. The upper adjustment motor 254 drives the threaded rod 258 to move, causing the threaded rod 258 to move up and down. The up and down movement of the threaded rod 258 causes the linkage plate 256 to slide up and down within the limiting slide groove 257 through a threaded connection. The up and down movement of the linkage plate 256 causes multiple guide plates 252 to swing up and down along the hinge axis in the middle through a hinge connection, changing the direction of the exhaust jet and realizing the pitch control of the aircraft.

[0108] The left control handle 5 controls the forward and reverse rotation of the side adjustment motor 253, which in turn drives the threaded rod 258 on its output shaft to rotate. The rotation of the threaded rod 258, under the action of the thread, drives the motor bracket 256 at the arc-shaped groove of the tail nozzle steering shield 251 to move, thereby causing the tail nozzle steering shield to swing left and right along the hinge point at the top, bottom and tail opening of the conical shield 247, changing the direction of the tail nozzle and realizing the yaw and left and right attitude control of the aircraft.

[0109] To achieve manned flight, see Figure 2 , Figure 11 The load unit 3 includes a loading rack 301 and a shoulder strap 302. The loading rack 301 is fixedly disposed on the lower part of the engine 202, and the shoulder strap 302 is fixedly disposed on the bottom of the loading rack 301. The loading rack 301 is fixedly disposed on the lower part of the engine 202, providing a sturdy frame to ensure that the shoulder strap 302 can be securely fixed to the aircraft.

[0110] In this embodiment, the harness 302 is a five-point safety harness 302, which is an adjustable harness 302 with safety buckles. The five-point safety harness can secure the user from all directions, ensuring 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, ensuring comfortable wearing and reducing fatigue during long flights.

[0111] Example 2

[0112] The similarities to the above embodiments will not be repeated, the differences are as follows:

[0113] To ensure the stability and strength of the lever C123 during deployment and retraction, see [reference needed]. Figure 2 The front end of the swing arm C123 is connected to the end of the positioning beam 111 via a pull rope 127, and the rear end of the swing arm C123 is connected to the tail of the wing center frame 101 via a pull rope 127. Through this structure, the pull rope ensures the flatness and stability of the wing in its deployed state, reduces air resistance, and improves flight efficiency.

[0114] The swing arm C123 is hinged to the pull rope 127, and the pull rope 127 is made of steel wire rope.

[0115] The steel wire rope material has high strength and durability, can bear large tension, and ensures the reliability and safety of the aircraft in various working conditions.

[0116] In addition, the conical cover 247 is provided with a pull rope 127, the other end of the pull rope 127 is connected to the rear end of the swing rod 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 the reliability and safety in high-speed flight and complex environment, and the connection mode of the pull rope 127 can uniformly distribute the load on the wing, reduce local stress concentration, and prolong the service life of the wing.

[0117] Embodiment 3

[0118] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0119] In this embodiment, in order to optimize the center of gravity distribution of the aircraft and reduce air resistance during flight, referring to Figure 1 、 Figure 7 , the front of the oil tank 201 is provided with a narrowing part, the front end of which is smoothly treated, and the oil inlet of the oil tank 201 is arranged at the upper end of the oil tank 201, which is lower than the highest part of the wing middle frame 101.

[0120] The narrowing part of the front of the oil tank 201 is streamlined and smoothly treated, which can reduce air resistance during flight and improve flight efficiency. The oil inlet of the oil tank 201 is arranged at the upper end of the oil tank 201, which is lower than the highest part of the wing middle frame 101, which is convenient for oiling operation and avoids fuel leakage.

[0121] Embodiment 4

[0122] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0123] Referring to Figure 2 、 Figure 8 , a plurality of wind tunnels 236 are arranged on the outrigger 231, and the front and rear edges of the wind tunnels are chamfered and smoothly treated. The design of the wind tunnel 236 can reduce the air resistance of the outrigger 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 and the transmission unit 203 in the outrigger, and ensure the normal operation of these components in high temperature environment.

[0124] In addition, the chamfering can reduce the turbulence and vortex at the edge of the wind tunnel 236, further reduce the air resistance, and improve the aerodynamic performance of the aircraft. In flight, it can also reduce the stress concentration at the edge of the wind tunnel 236, improve the durability and reliability of the spreader 231.

[0125] By opening the wind tunnel, the use of materials is reduced, the weight of the spreader 231 is reduced, and the carrying capacity and endurance time of the aircraft are improved.

[0126] Embodiment 5

[0127] The same as the above embodiments and their combinations will not be repeated, and the differences are as follows:

[0128] In order to realize the automatic contraction and expansion of the telescopic skeleton during the flight of the aircraft and before and after the flight, enhance the automation degree, and make it more convenient to adjust the flight attitude, referring to Figure 4 、 Figure 5 , the telescopic drive unit 104 is arranged on the wing frame 101. The posture of the telescopic skeleton and the wing skin can be controlled in real time by the telescopic drive unit 104.

[0129] Specifically, the telescopic drive unit 104 includes a telescopic motor 141, a screw rod 142, a threaded hinge sleeve 143, and a screw rod support 144. The front end, the tail end, and the middle part of the screw rod 142 are rotatably connected with the screw rod support 144, and the screw rod support 144 is integrally or separately fixed on the wing frame 101.

[0130] The telescopic motor 141 is arranged on the side of the screw rod support 144 at the front end of the screw rod 142 and drives the front end of the screw rod 142. The threaded hinge sleeve 143 is threadedly arranged on the screw rod 142 between the screw rod supports 144 at the middle part and the tail end of the screw rod 142. The threaded hinge sleeve 143 is hingedly connected to the rear end of the driving rocker 126 on both sides.

[0131] Through the above structure, the telescopic motor 141 can drive the screw rod 142 to rotate after starting. When the screw rod 142 rotates, the threaded hinge sleeve 143 is driven to move forward or backward along the screw rod 142 through the threaded structure. The movement of the threaded hinge sleeve 143 drives the rear end of the driving rocker 126 to move forward or backward. Thus, the telescopic skeleton is driven to expand or contract.

[0132] It should be noted that in this embodiment, in order to prevent the driving rocker from moving too far, the stroke is limited. When the telescopic skeleton 102 is fully expanded, the threaded hinge sleeve 143 is located at the screw rod support 144 at the middle part of the screw rod 142. When the telescopic skeleton 102 is fully contracted, the threaded hinge sleeve 143 is located at the screw rod support 144 at the tail end of the screw rod 142.

[0133] Embodiment 6

[0134] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0135] To ensure that the aircraft is more stable during flight, see Figure 6 The upper part of the telescopic drive unit 104 is provided with a protective cover 145, and the top of the protective cover 145 is shaped as a transition curve from front to back, which is rising and gently descending.

[0136] The top of the protective cover 145 is designed as a transition curve from front to back, which is rising and gently descending. 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 vortex, thereby reducing the drag of the aircraft and improving flight efficiency. Reducing air resistance means that the aircraft can fly faster or farther under the same power, or maintain the same flight speed at lower power, thereby prolonging the endurance time and improving the 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 prolong the service life of mechanical parts.

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

[0138] To prevent the protective cover from interfering with the displacement of the active rocker, see Figure 6 The protective cover 145 is provided with a notch corresponding to the rear end of the active rocker 126.

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

[0140] The design of the fairing can smooth the air flow around the top of the oil tank and the oil filler port, reducing the formation of turbulence and vortex, thereby reducing the air resistance of the aircraft. During high-speed flight, the efficiency and performance of the aircraft can be improved. At the same time, the front of the fairing is attached to the top of the oil tank, and the rear is attached to the front end of the protective cover, forming a smooth transition and enhancing the overall aesthetics of the aircraft.

[0141] Embodiment 7

[0142] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0143] See Figure 9 , Figure 10The reset spring 259 is arranged outside the threaded rod 258 between the linkage vertical plate 256 and the upper adjusting motor 254. The threaded rod 258 is provided with a stop block at the end.

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

[0145] Embodiment 8

[0146] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0147] Referring to Figure 12 , Figure 13 In the embodiment, the load part 3 includes a download frame 301, a separation frame 303 and an escape backpack. The download frame 301 is fixedly arranged at the lower part of the engine 202, and the separation 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 separation frame 303, and the shoulder straps of the escape backpack pass through the separation frame 303 for the user to carry. An electromagnet 304 is arranged on the download frame 301 at the connection between the download frame 301 and the separation frame 303. In the embodiment, the escape backpack is a parachute backpack.

[0148] The electromagnet 304 can firmly fix the separation frame 303 on the download frame 301 when powered on. In the embodiment, the user can quickly unlock and realize the rapid separation of the separation frame 303 by powering off the electromagnet 304 when encountering an emergency or failure. The user, the separation frame 303 and the escape backpack are simultaneously separated from the download frame 301, realizing the separation of man and machine, thereby ensuring the safety of the user.

[0149] Embodiment 9

[0150] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

[0151] Referring to Figure 12 , Figure 13The disengagement frame 303 is provided with a plug-in column 331 at the connection with the download frame 301, and the disengagement frame 303 is plugged into the bottom of the download frame 301 through the plug-in column 331. The plug-in column allows the disengagement frame to be quickly plugged into the bottom of the download frame, ensuring convenient loading and unloading in non-emergency situations. When the disengagement frame is plugged into the bottom of the download frame through the plug-in column, the pin shaft is inserted at the download frame and the plug-in column, ensuring the stable connection of the disengagement frame. The design of the pin shaft ensures that the disengagement frame will not accidentally separate during normal flight, improving safety.

[0152] The load part also includes a disengagement mechanism 305, which is symmetrically arranged on the download frame 301, and the download frame 301 connects the disengagement frame 303 through the disengagement mechanism 305.

[0153] The disengagement mechanism 305 includes a pin shaft 351, a pulley block 352, and an emergency disengagement handle 353. When the disengagement frame 303 is plugged into the bottom of the download frame 301 through the plug-in column 331, the pin shaft 351 is inserted at 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 a pulley frame 354. The tail of the pin shaft 351 is provided with a disengagement rope 355, which is connected to the upper end of the emergency disengagement handle 353 after passing through the pulley block 352. 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 situation.

[0154] The pulley block is arranged at the long side of the download frame through the pulley frame, which is used to guide the movement of the steel wire rope, reduce friction and resistance, and ensure smooth movement of the steel wire rope, improve the response speed and reliability of the disengagement mechanism. Through the above structure, the user pulls the emergency disengagement handle in an emergency situation, the steel wire rope transmits force through the pulley block, the pin shaft is pulled out from the download frame and the plug-in column, and the disengagement frame is quickly separated.

[0155] Through the pure mechanical design, the failure of the aircraft can be prevented due to the failure of the separation, which has strong reliability and can realize the quick separation of man and machine.

[0156] Embodiment 10

[0157] The same as the above embodiments and their combinations will not be repeated, and the difference is that:

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

[0159] The micro vertical roller is arranged at the foot of the download frame through which the steel wire rope passes, and can reduce the friction of the steel wire rope during movement, ensure smooth movement of the steel wire rope, and improve the response speed and reliability of the disengagement mechanism.

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

[0161] In use, the user starts the engine 202 through the right control handle 4, and the oil tank 201 supplies fuel to the engine 202 through an oil circuit. 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 driving the front and rear propeller blades 243 and 244 to rotate through the coaxial reverse gear box 245.

[0162] The user starts the telescopic driving unit 104 through the control handle, and the telescopic motor 141 drives the screw rod 142 to rotate. The screw rod 142 drives the threaded hinge sleeve 143 to move forward along the screw rod 142 through the threaded structure, and the movement of the threaded hinge sleeve 143 drives the rear end of the driving rocker 126 to move forward, thereby driving the multi-link structure to expand. Finally, the telescopic framework 102 is completely unfolded, driving the wing skin 103 to unfold, and completing the expansion of the wing.

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

[0164] At the same time of flight, the wind tunnel 236 introduces external air to help cool the engine 202 and the transmission unit 203, and ensure the normal operation of these components in a high temperature environment.

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

[0166] After the flight, the user starts the telescopic drive unit 104 through the control handle, the telescopic motor 141 drives the screw rod 142 to rotate reversely, the screw joint sleeve 143 moves backward along the screw rod 142, and the rear end of the driving rocker 126 is driven to move backward, the telescopic framework 102 is folded, and the contraction of the telescopic framework 102 and the wing skin is completed.

[0167] It should be noted that the structure expressed in the drawings of the present application is not fixed and unchangeable in the specific implementation. In addition, the drawings and the abstract drawings of the present application are only schematic diagrams and do not represent the specific structure and actual quantity in the specific implementation.

[0168] Unless otherwise defined, technical terms or scientific terms used herein should be understood as the usual meaning understood by a person skilled in the art to which the present application belongs. The similar words such as "one" or "a" used in the specification and claims of the present application do not necessarily mean the quantity limitation. The similar words such as "include" or "contain" mean that the elements or components before the words cover the elements or components listed after the words and their equivalents, and do not exclude other elements or components. The similar words such as "connect" or "connected" are not limited to physical or mechanical connection, but can include electrical connection, whether direct or indirect.

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

Claims

1. A portable, single-person, low-altitude vector jet aircraft with a folding wing structure, characterized in that: It includes a frame section, a power section, and a load section, wherein the power section is disposed below the frame section and the load section is disposed below the power section; The frame section includes a wing center frame, a telescopic frame, and a wing skin; the power unit is located below the wing center frame; and the load unit is located below the power unit. 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: When viewed from above, the wing midframe is T-shaped. A positioning beam is provided at the top of the front crossbeam. A suspender is integrally provided on the side and bottom of the T-shaped wing midframe at the middle position of the bottom. The power unit is suspended at the bottom of the suspender. The telescopic frame is symmetrically arranged on both sides of the wing center frame. The telescopic frame is a multi-link structure, including swing arm A, swing arm B, swing arm C, connecting rod A, connecting rod B and active rocker arm; The front end of the swing arm A is hinged to the positioning beam, and the rear end is hinged to the middle of the connecting rod A. The right side of the middle part of the swing arm A is hinged to the front end of the main swing arm. The rear end of the main swing arm is movable and can be fixedly set at the tail of the T-shaped wing frame. The middle part of the main swing arm is hinged to the end of the connecting rod A through the swing arm B. The other end of the connecting rod A is hinged to the middle part of the swing arm C. The left side of the middle part of the swing rod 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 swing rod C. The hinge point between the active rocker and the rocker arm A is close to the front end of the rocker arm A, and the hinge point between the connecting rod B and the rocker arm A is close to the rear end of the rocker arm 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 midframe is equipped with a telescopic drive unit, which includes a telescopic motor, a screw, a threaded hinge sleeve, and a screw bracket. The front end, tail end, and middle part of the screw are rotatably connected to the screw bracket, and the screw bracket is integrally or separately fixedly mounted on the wing midframe. The telescopic motor is located on the side of the screw support at the front end of the screw and is driven to connect to the front end of the screw. The threaded hinge sleeve is threaded on the screw between the screw support at the middle and tail ends of the screw. Both sides of the threaded hinge sleeve are hinged to the rear end of the main rocker arm. The telescopic drive unit is provided with a protective cover on its upper part. The top of the protective cover is a transitional curved surface that rises and falls integrally from front to back. The protective cover has a notch at the rear end of the main rocker arm. When the telescopic frame is fully extended, the threaded hinge sleeve is located at the screw support in the middle of the screw. When the telescopic frame is fully retracted, the threaded hinge sleeve is located at the screw support at the tail 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 arm C is connected to the end of the positioning beam via a pull rope, and the rear end of the swing arm C is connected to the tail of the wing midframe via a pull rope. The swing arm C is hinged 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 located at the middle of the lower front end of the wing center frame. The engine is located at the bottom of the pylon. The pylon is located on the side and bottom of the wing center frame behind the fuel tank. The power output units are symmetrically arranged on both sides of the engine. The fuel tank is connected to the engine through an oil line. The engine is driven by the transmission unit and fixedly connected to the power output unit. The engine is connected to a right control handle via a control circuit.

6. The portable single-person low-altitude vector jet aircraft with a folding wing structure according to claim 5, characterized in that: The front of the fuel tank is provided with a narrow section, and the front end of the tank is rounded. The fuel inlet of the fuel tank is located at the top of the fuel tank, and the fuel inlet is lower than the highest point of the wing center frame. A detachable fairing is provided 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 located at the front end of the engine. The transmission unit includes a frame, a drive wheel, a driven wheel, and a transmission belt. The frame is fixedly and laterally located at the front end of the engine. The drive wheel, driven wheel, and transmission belt are all located inside the frame. The power output shaft of the engine passes through the frame and is connected to the drive wheel. The driven wheel is located on the rotating shaft of the power output unit. The drive wheel and the driven wheel are connected by the transmission belt. Multiple wind tunnels are arranged on the truss, and the front and rear edges of the wind tunnels are all 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 body, a connecting frame, a front propeller blade, a rear propeller blade, and a coaxial reversing gearbox. After the connecting frame passes through the duct body, a coaxial reversing gearbox is integrally provided at its end. A bracket is provided where the connecting frame passes through the duct body. The front and rear power output shafts of the coaxial reversing gearbox are respectively provided with the front propeller blade and the rear propeller blade. The driven wheel is provided on the power output shaft of the coaxial reversing gearbox. The coaxial reversing gearbox is located at the center of the duct body, and connecting frames are provided at its top, bottom, and sides. The coaxial reversing gearbox is fixedly supported and connected to the inner wall of the duct body through the connecting frames at its 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 duct body is also provided with a protective cover at the front end and a conical cover at the rear end. A pull rope is provided on the outside of the conical cover. The other end of the pull rope is connected to the rear end of the swing arm C and / or the tip of the outermost part of the wing skin. The conical cover has an open design at the tail end and a vector adjustment unit is provided at the tail end. The vector adjustment unit includes a tail nozzle steering shield, a guide plate, a side adjustment motor, and an upper adjustment motor. The tail nozzle steering shield is sleeved on the tail opening of the conical shield. The top and bottom of the tail nozzle steering shield are hinged to the tail opening of the conical shield. The tail nozzle steering shield has arc-shaped grooves on the left and right sides to prevent interference between the tail nozzle steering shield and the opening of the conical shield when rotating left and right. Multiple guide vanes are provided and arranged inside the rear end of the tail spray deflector. The middle part of the guide vane is hinged to the side wall of the tail spray deflector via a hinge shaft. A linkage plate is provided at the front end of the guide vane. The linkage plate is hinged to the front end of the multiple guide vanes arranged in a row. Limiting grooves are provided on the inner wall of the tail spray deflector at the upper and lower ends of the linkage plate. The top and bottom ends of the linkage plate are slidably disposed in the limiting grooves. The upper adjustment motor is embedded and fixedly installed on the top of the tail spray steering cover above the linkage plate. The output shaft of the upper adjustment motor is provided with a threaded rod, which is threadedly connected to the top of the linkage plate. The side adjustment motors are symmetrically arranged in the arc-shaped grooves on the left and right sides of the tail spray steering cover. The side adjustment motors are mounted on the tail opening of the conical cover via motor brackets. A threaded rod is also provided on the output shaft of the side adjustment motors. A motor bracket is also provided in the arc-shaped groove of the tail spray steering cover. The threaded rod is threadedly connected to and passes through the motor bracket in the arc-shaped groove of the tail spray steering cover. Return springs are fitted on the outside of the threaded rod between the linkage plate and the upper adjustment motor, and on 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. A stop block is provided at the end of the threaded rod. Both the upper adjustment motor and the side adjustment motor are reversible motors, and both are connected to the left control handle via control lines.

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

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