A gliding vertical take-off and landing dual-mode flight backpack

Abstract

This invention discloses a gliding vertical takeoff and landing (VTOL) dual-mode flight backpack, belonging to the field of aircraft technology. The gliding VTOL dual-mode flight backpack provided in this application exhibits excellent performance in terms of directional control and endurance, achieving both flexible vertical takeoff and landing and a long flight time. For example, in terms of directional control, the direction can be easily adjusted by transmitting signals from the joystick controlled by the operator through throttle potentiometers, inner nozzle angle potentiometers, left outer nozzle angle potentiometers, and right outer nozzle angle potentiometers, resulting in greater sensitivity. Regarding endurance, this product can reach 30 minutes, which is more durable compared to other VTOL flight backpacks on the market.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, and in particular relates to a gliding vertical take-off and landing dual-mode flight backpack. Background Technology

[0002] Traditional vertical takeoff and landing (VTOL) jetpacks excel in directional control but have limited endurance; while glider jetpacks offer long endurance but lack directional control agility. For example, Jetpack's VTOL jetpack is highly maneuverable but only has an 8-minute flight time, while Jetman's glider jetpack boasts a 40-minute flight time but lacks maneuverability in confined spaces. Therefore, designing a jetpack that combines the advantages of both has become a research topic for those skilled in the art. Summary of the Invention

[0003] This application provides a gliding vertical takeoff and landing dual-mode flight backpack to solve the above-mentioned technical problems.

[0004] To achieve the above-mentioned objectives, the technical solution adopted in this application is as follows:

[0005] This application provides a gliding vertical takeoff and landing dual-mode flight backpack, including a fuselage, wings, power unit, and control stick;

[0006] The fuselage includes a tilting connection device, which includes:

[0007] The tilting connector includes a tilting shaft and a tilting connecting sleeve. One end of the tilting shaft is fixedly connected to the tilting connecting sleeve, and the other end is rotatably connected to the central support.

[0008] The tilting pipe rack includes horizontal pipes and vertical pipes, which are connected at an obtuse angle. The horizontal pipes are coaxially fitted with the tilting connecting sleeve and are located inside the tilting connecting sleeve. The vertical pipes have two locking holes.

[0009] The wing includes the wing shell, torsion spring hinge, locking pin, and locking handle;

[0010] The tilting tube frame and locking pin are both embedded in the groove of the wing shell. The groove of the tilting tube frame has a built-in torsion spring hinge, which is fixed to the tilting tube frame, giving the wing shell a tendency to rotate away from the pilot.

[0011] The locking handle is connected to the locking pin, which is used to control the insertion or withdrawal of the locking pin from the locking hole;

[0012] Specifically, when the locking pin is inserted into one of the two locking holes, the wing shell is in a folded state, and the gliding vertical takeoff and landing dual-mode flight backpack is in vertical takeoff and landing mode; when the locking pin is inserted into the other of the two locking holes, the wing shell is in an unfolded state, and the gliding vertical takeoff and landing dual-mode flight backpack is in gliding mode.

[0013] Optionally, the fuselage also includes an electronic control system, which includes a battery, a receiver, and a controller. The receiver and controller are connected, and the battery powers the receiver and controller.

[0014] Optionally, the fuselage also includes a winch restraint device, which includes a continuously rotating servo motor, a winch, and a pull cable.

[0015] Optionally, the wing also includes a torsion spring pin, the rightmost ring of which is fitted onto the bottom of the locking handle, the torsion spring pin passing through a through hole on the locking handle, and the torsion spring pin being fitted with a first spring.

[0016] Optionally, the power unit includes: an oil pump, an oil-electricity line, an engine, an inner nozzle, an inner rocker arm, an inner connecting rod, an inner crank, an inner servo, an outer nozzle, an outer rocker arm, an outer connecting rod, an outer crank, and an outer servo.

[0017] The oil pump runs through the oil and electricity lines. The inner and outer servos are mounted on the wings. The oil and electricity lines pass through the inside of the wings and are connected to the inner servo. The inner servo is connected to the inner crank, and the inner crank is connected to the inner connecting rod. The inner connecting rod is connected to the inner nozzle through the inner rocker arm. The inner nozzle is mounted on the engine and can rotate around an axis perpendicular to the plane of the wing. The engine is mounted on the wing.

[0018] The oil and electricity lines are also connected to the outer servo, which is connected to the outer crank. The outer rocker arm is connected to the outer crank via the outer connecting rod. The outer rocker arm is connected to the outer nozzle, which is mounted on the engine. The outer nozzle can rotate around an axis parallel to the trailing edge of the wing.

[0019] The oil and electricity lines are connected to the fuel tank, and after passing through the inner and outer servo motors, they are connected to the engine.

[0020] Optionally, there are two control levers, each of which includes a button, a throttle, a middle sleeve, a locking sleeve, a second spring, and a locking pin, which is fixed to the mounting groove of the wing shell.

[0021] The locking pin on the right control lever is connected to the right outer nozzle angle potentiometer, and the locking pin on the left control lever is connected to the left outer nozzle angle potentiometer; the inner nozzle angle potentiometer is fixed to the outside of the middle sleeve on the left control lever, and the throttle potentiometer is fixed to the outside of the middle sleeve on the right control lever.

[0022] For any control stick, the center sleeve is hinged to the wing shell via a locking pin, the throttle is mounted on the outside of the center sleeve and can rotate relative to the center sleeve, and the locking sleeve is mounted on the inside of the center sleeve; for the right control stick, the locking sleeve can slide relative to the center sleeve and the right outer nozzle angle potentiometer; for the left control stick, the locking sleeve can slide relative to the center sleeve and the left outer nozzle angle potentiometer.

[0023] For the control lever on either side, the bottom end of the button is installed inside the upper end of the locking sleeve, and the second spring is installed inside the locking sleeve; for the right control lever, the two ends of the second spring are fixedly connected to the button base and the upper end of the right outer nozzle angle potentiometer, respectively; for the left control lever, the two ends of the second spring are fixedly connected to the button base and the upper end of the left outer nozzle angle potentiometer, respectively.

[0024] Optionally, for the control lever on either side, the locking sleeve is provided with a rotating hole, a sleeve groove, and a limiting hole, and the locking pin is provided with a pin groove and a fixing hole;

[0025] In its natural state, the lever is controlled by the second spring, and the sleeve groove on the locking sleeve is nested with the pin groove on the locking pin. At this time, the lever cannot rotate around the locking pin. When the button is pressed, the rotating hole on the locking sleeve is coaxial with the locking pin, and the lever can rotate around the locking pin.

[0026] Optionally, when the gliding vertical takeoff and landing dual-mode flight backpack is in vertical takeoff and landing mode, the flight maneuvers of the gliding vertical takeoff and landing dual-mode flight backpack include: ascent and descent, forward and backward movement, left and right translation, and left and right turning.

[0027] When the gliding vertical takeoff and landing dual-mode flight backpack is in gliding mode, the flight maneuvers of the gliding vertical takeoff and landing dual-mode flight backpack include pitch, roll, and yaw.

[0028] Alternatively, the method for switching from vertical takeoff and landing mode to gliding mode is as follows:

[0029] First, adjust the position of all nozzles to ensure they are all vertical.

[0030] When the preset height is reached, pinch the locking handles on both sides, and the wings on both sides will unfold under the action of the torsion spring hinges.

[0031] Next, press the button on the control stick and push both control sticks forward. The nozzles on the outer sides of the wings deflect towards the trailing edge of the wings, and the angle of the entire fuselage gradually changes from perpendicular to the ground to parallel to the ground, thus switching to gliding mode.

[0032] Alternatively, the method for switching from gliding mode to vertical takeoff and landing mode is as follows:

[0033] First, fly upwards until you are perpendicular to the ground;

[0034] Then, pinch the locking handles on both wings and pull both wings toward one side of your body. When the locking pins slide into the locking holes of the tilting tube rack, release the locking handles to switch to vertical takeoff and landing mode.

[0035] Compared with the prior art, the beneficial effects of the embodiments of this application are:

[0036] This application provides a gliding vertical takeoff and landing (VTOL) dual-mode flight backpack that excels in directional control and endurance, achieving both flexible vertical takeoff and landing and long flight time. For example, in terms of directional control, signals from the operator-controlled joystick are transmitted via throttle potentiometers, inner nozzle angle potentiometers, left outer nozzle angle potentiometers, and right outer nozzle angle potentiometers, allowing for easy and more sensitive directional adjustments. Regarding endurance, this product can reach 30 minutes, which is significantly longer than other VTOL flight backpacks on the market. Attached Figure Description

[0037] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0038] Figure 1 This illustration shows a structural diagram of a gliding vertical takeoff and landing dual-mode flight backpack in gliding mode, according to an embodiment of this application.

[0039] Figure 2 This illustration shows a structural diagram of a gliding vertical takeoff and landing dual-mode flight backpack in vertical takeoff and landing mode, according to an embodiment of this application.

[0040] Figure 3 A schematic diagram of the fuselage structure provided in an embodiment of this application is shown;

[0041] Figure 4 A schematic diagram of the tilting tube rack provided in an embodiment of this application is shown;

[0042] Figure 5 A schematic diagram of the structure of the wing provided in an embodiment of this application is shown;

[0043] Figure 6 A schematic diagram of the power unit provided in an embodiment of this application is shown;

[0044] Figure 7 This paper shows a schematic diagram of the left-side joystick provided in an embodiment of this application;

[0045] Figure 8 It shows Figure 7 A magnified view of a section at point A in the middle;

[0046] Figure 9 This paper shows a schematic diagram of the structure of the right-side joystick provided in an embodiment of this application;

[0047] Figure 10 It shows Figure 9 A magnified view of a section at point B in the middle;

[0048] Figure 11 A schematic diagram of the locking sleeve and locking pin provided in an embodiment of this application is shown.

[0049] Illustration:

[0050] 1. Fuselage; 2. Wings; 3. Powerplant; 4. Control stick;

[0051] 11. Head unit; 12. Fuel tank; 13. Central support; 14. Tilting connector; 141. Tilting shaft; 142. Tilting connecting sleeve; 15. Tilting tube rack; 151. Horizontal tube; 152. Vertical tube; 153. Locking hole; 16. Cushion; 17. Safety belt; 18. Battery; 19. Receiver; 110. Controller; 111. Continuous rotation servo motor; 112. Winch; 113. Guy cable;

[0052] 21. Wing shell; 22. Torsion spring hinge; 23. Locking pin; 24. Locking handle; 25. Torsion spring pin;

[0053] 31. Oil pump; 32. Oil and electricity lines; 33. Engine; 34. Inner nozzle; 35. Inner rocker arm; 36. Inner connecting rod; 37. Inner crank; 38. Inner servo; 39. Outer nozzle; 310. Outer rocker arm; 311. Outer connecting rod; 312. Outer crank; 313. Outer servo;

[0054] 41. Button; 42. Throttle; 43. Throttle potentiometer; 44. Middle sleeve; 45. Locking sleeve; 451. Rotating hole; 452. Sleeve groove; 453. Limiting hole; 46. Second spring; 47. Locking pin; 471. Pin groove; 472. Fixing hole; 48. Inner nozzle angle potentiometer; 49. Right outer nozzle angle potentiometer; 410. Left outer nozzle angle potentiometer. Detailed Implementation

[0055] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0056] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0057] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0058] In the field of aircraft technology, traditional aircraft require relatively open spaces and long runways for takeoff and landing, placing high demands on the site and subjecting them to significant limitations. In contrast, aircraft capable of vertical takeoff and landing offer operational versatility, such as rapid takeoff during combat, resulting in higher efficiency and maneuverability.

[0059] Most vertical takeoff and landing (VTOL) manned flight backpacks currently on the market are electrically powered, which results in low speed and short flight time. Using an engine as a power source requires solving the problem of engine ignition in a vertical position. The gliding VTOL dual-mode flight backpack provided in this application uses an engine capable of vertical ignition.

[0060] However, prolonged vertical flight presents challenges such as high power requirements, reduced payload, and significant performance degradation.

[0061] In view of this, the present application provides a gliding vertical take-off and landing dual-mode flight backpack, which is a dual-mode aircraft that combines vertical take-off and landing performance with gliding level flight capability, and can significantly improve endurance and load capacity.

[0062] To illustrate the technical solution described in this application, specific embodiments are provided below.

[0063] Please see Figure 1 and Figure 2 As shown in the embodiment of this application, a gliding vertical takeoff and landing dual-mode flight backpack includes: fuselage 1, wings 2, power unit 3, and control stick 4.

[0064] For example, in Figure 1 In the gliding vertical takeoff and landing dual-mode flight backpack shown, the wings 2 are deployed, and the gliding vertical takeoff and landing dual-mode flight backpack is in gliding mode.

[0065] For example, in Figure 2 In the gliding vertical takeoff and landing dual-mode flight backpack shown, the wings are folded, and the gliding vertical takeoff and landing dual-mode flight backpack is in vertical takeoff and landing mode.

[0066] In some embodiments, such as Figure 3 and Figure 4 As shown, the fuselage 1 includes an electronic control system, a tilting connection device, and a winch restraint device.

[0067] The electronic control system includes a battery 18, a receiver 19, and a controller 110, all located inside the fuselage 1. For example, the receiver 19 receives remote control signals sent by a remote terminal and transmits them to the controller 110, which automatically controls the operation of the gliding vertical takeoff and landing dual-mode flight backpack based on the remote control signals. The battery 18 supplies power to the electronic control system.

[0068] The tilting connection device includes a tilting connector 14 and a tilting tube support 15. The tilting connector 14 includes a tilting shaft 141 and a tilting connecting sleeve 142.

[0069] One end of the tilting shaft 141 is fixedly connected to the tilting connecting sleeve 142, and the other end is rotatably connected to the central support 13. The tilting tube frame 15 is sleeved with the tilting connecting sleeve 142. In this way, the tilting connecting device can rotate around the central support 13 as a whole through the tilting shaft 141.

[0070] Specifically, such as Figure 4 As shown, the tilting tube frame 15 includes a horizontal tube 151 in the middle and vertical tubes 152 on both sides. The horizontal tube 151 and the vertical tube 152 are connected at an obtuse angle. The horizontal tube 151 is coaxially fitted with the tilting connecting sleeve 142 and is located inside the tilting connecting sleeve 142. Two locking holes 153 are opened on the vertical tube 152.

[0071] The winch restraint device includes a continuously rotating servo motor 111, a winch 112, and a pull cable 113. The winch 112 is connected below the continuously rotating servo motor 111, and the pull cable 113 is wound around the winch 112. The winch restraint device is embedded in the central support 13. The continuously rotating servo motor 111 is covered by a cushion 16, and the winch 112 and pull cable 113 are visible at the lower part of the central support 13.

[0072] In some embodiments, such as Figure 5 As shown, the wing 2 includes a wing shell 21, a torsion spring hinge 22, a locking pin 23, a locking handle 24, and a torsion spring pin 25.

[0073] The tilting tube frame 15 and the locking pin 23 are both embedded in the groove of the wing shell 21. The vertical tube 152 in the tilting tube frame 15 has two locking holes 153. The locking pin 23 is used to insert into the locking holes 153 and cooperate with the tilting tube frame 15 to lock the wing shell 21 in the tilting tube frame 15, so that the wing shell 21 will no longer rotate around the tilting tube frame 15. In addition, the groove of the tilting tube frame 15 has a built-in torsion spring hinge 22, which is fixed on the tilting tube frame 15, so that the wing shell 21 has a tendency to rotate away from the pilot.

[0074] Specifically, the locking handle 24 is connected to the locking pin 23, which is used to control the locking pin 23 to be inserted into or removed from the locking hole 153.

[0075] Specifically, when the locking pin 23 is inserted into one of the two locking holes 153, the wing shell 21 of the wing 2 is in a folded state, and the flight backpack is in vertical takeoff and landing mode. When the locking pin 23 is inserted into the other locking hole 153, the wing shell 21 of the wing 2 is in an unfolded state, and the flight backpack is in gliding mode.

[0076] In some embodiments, the rightmost annular part of the locking pin 23 is fitted onto the bottom of the locking handle 24, and the torsion spring pin 25 passes through the through hole on the locking handle 24, and the torsion spring pin 25 is equipped with a first spring (not shown in the figure). When the operator squeezes the locking handle 24, the locking handle 24 rotates around the torsion spring pin 25, and then the locking handle 24 drives the locking pin 23 to move along the groove until the locking pin 23 moves out of one of the two locking holes 153. At this time, the wing shell 21 can rotate around the tilting tube frame 15, so that the wing shell 21 is adjusted to another position. At this time, the locking pin 23 can be inserted into the other locking hole 153 of the two locking holes 153 to fix the wing shell 21.

[0077] In some embodiments, such as Figure 6 As shown, the power unit 3 includes an oil pump 31, an oil and electricity line 32, an engine 33, an inner nozzle 34, an inner rocker arm 35, an inner connecting rod 36, an inner crank 37, an inner servo motor 38, an outer nozzle 39, an outer rocker arm 310, an outer connecting rod 311, an outer crank 312, and an outer servo motor 313.

[0078] The oil pump 31 runs through the oil and electricity line 32. The inner servo 38 and the outer servo 313 are mounted on the wing 2. The oil and electricity line 32 passes through the inside of the wing 2 and is connected to the inner servo 38. The inner servo 38 is connected to the inner crank 37, and the inner crank 37 is connected to the inner connecting rod 36. The inner connecting rod 36 is connected to the inner nozzle 34 through the inner rocker arm 35. The inner nozzle 34 is mounted on the engine 33 and can rotate around an axis perpendicular to the plane of the wing 2. The engine 33 is mounted on the wing 2. Meanwhile, the fuel and electrical line 32 passes through the interior of wing 2 and connects to the outer servo 313. The outer servo 313 is connected to the outer crank 312, and the outer rocker arm 310 is connected to the outer crank 312 via the outer connecting rod 311. The outer rocker arm 310 is connected to the outer nozzle 39, which is mounted on the engine 33 and can rotate around an axis parallel to the trailing edge of wing 2. The fuel and electrical line 32 is connected to the fuel tank 12. After passing through the inner servo 38 and the outer servo 313, the fuel and electrical line 32 connects to the engine 33.

[0079] The oil in the fuel tank 12 will flow into the oil-electric line 32. Under the action of the oil pump 31, the oil flowing into the oil-electric line 32 will be pumped into the inner servo 38 and the outer servo 313 along the oil-electric line 32. Then, along the oil-electric line 32 that connects the inner servo 32 and the outer servo 313 to the engine 33, it will flow into the engine 33.

[0080] In some embodiments, such as Figures 7 to 10 As shown, both the left and right control levers 4 include a button 41, a throttle 42, a middle sleeve 44, a locking sleeve 45, a second spring 46, and a locking pin 47. The locking pin 47 is fixed to the mounting slot of the wing housing 21.

[0081] The locking pin 47 on the right control lever 4 is connected to the right outer nozzle angle potentiometer 49, and the locking pin 47 on the left control lever 4 is connected to the left outer nozzle angle potentiometer 410.

[0082] An inner nozzle angle potentiometer 48 is fixed to the outer side of the middle sleeve 44 on the left control lever 4, and a throttle potentiometer 43 is fixed to the outer side of the middle sleeve 44 on the right control lever 4. For example, the two inner nozzles 34 share the same inner nozzle angle potentiometer 48.

[0083] For any one of the control sticks 4, the central sleeve 44 is hinged to the wing shell 21 via a locking pin 47. A throttle 42 is mounted on the outside of the central sleeve 44 and can rotate relative to the central sleeve 44. A locking sleeve 45 is mounted on the inside of the central sleeve 44. For the right-hand control stick 4, the locking sleeve 45 can slide relative to the central sleeve 44 and the right outer nozzle angle potentiometer 49. For the left-hand control stick 4, the locking sleeve 45 can slide relative to the central sleeve 44 and the left outer nozzle angle potentiometer 410.

[0084] For any one of the levers 4, the bottom end of the button 41 is mounted on the inner side of the upper end of the locking sleeve 45, and the second spring 46 is mounted on the inner side of the locking sleeve 45. For the right lever 4, the two ends of the second spring 46 are fixedly connected to the base of the button 41 and the upper end of the right outer nozzle angle potentiometer 49, respectively. For the left lever 4, the two ends of the second spring 46 are fixedly connected to the base of the button 41 and the upper end of the left outer nozzle angle potentiometer 410, respectively.

[0085] In some embodiments, such as Figure 11 As shown, for any one side of the control lever 4, the locking sleeve 45 is provided with a rotating hole 451, a sleeve groove 452, and a limiting hole 453. The locking pin 47 is provided with a pin groove 471 and a fixing hole 472.

[0086] In its natural state, the lever 4 on either side is acted upon by the second spring 46, causing the sleeve groove 452 on the locking sleeve 45 to nest with the pin groove 471 on the locking pin 47. At this time, the lever 4 cannot rotate around the locking pin 47. When the button 41 is pressed, the rotation hole 451 on the locking sleeve 45 becomes coaxial with the locking pin 472, allowing the lever 4 to rotate around the locking pin 47.

[0087] In summary, the gliding vertical takeoff and landing dual-mode flight backpack provided in this application embodiment has a vertical takeoff and landing mode and a gliding mode, and its working principle is as follows:

[0088] I. Vertical Take-off and Landing Mode

[0089] 1. Structural form: The overall structure of the skid vertical takeoff and landing mode is as follows: Figure 2 As shown.

[0090] The following explanations of left and right are all from the perspective of the pilot with his backpack on.

[0091] (1) The throttle 42 on the left wing 2 controls the direction of the two inner nozzles 34 on the left and right sides.

[0092] For example, when the left throttle 42 is turned counterclockwise, the nozzle of the inner nozzle 34 on the left wing 2 deflects towards the wingtip, while the nozzle of the inner nozzle 34 on the right wing 2 deflects towards the wing root, and vice versa.

[0093] (2) The throttle is controlled by the throttle lever 42 on the right wing 2. For example, the throttle of all four engines 33 can be increased or decreased simultaneously.

[0094] (3) The control stick 4 on the left wing 2 controls the direction of the nozzle 39 on the outer side of the left wing 2.

[0095] (4) The control stick 4 on the right wing 2 controls the direction of the nozzle 39 on the outer side of the right wing 2.

[0096] For example, when the left or right control stick 4 is pushed to one side of the body, the outer nozzle 39 deflects toward the trailing edge of the wing 2, and vice versa.

[0097] 2. Flight maneuvers: ascent and descent, forward and backward movement, left and right lateral movement, left and right turning.

[0098] Ascent and Descent: Rotate the throttle 42 on the right wing 2 to control the throttle, which in turn controls the thrust of the engine 33. When the thrust increases, the flight pack ascends; when the thrust decreases, the flight pack descends.

[0099] Forward and backward movement: The left wing 2 and the right wing 2 rotate around the tilting tube frame 15. When moving forward, both wings 2 need to rotate slightly backward, and when moving backward, both wings 2 need to rotate slightly forward.

[0100] Lateral translation: The left wing 2 and the right wing 2 swing around the tilt axis 141. When translating to the left, the left wing 2 is depressed and the right wing 2 is raised; when translating to the right, the left wing 2 is raised and the right wing 2 is depressed.

[0101] Left and right turns: Rotate the throttle 42 on the left wing 2. When the left throttle 42 is rotated counterclockwise, the nozzle of the inner nozzle 34 on the left wing 2 deflects towards the wingtip, while the nozzle of the inner nozzle 34 on the right wing 2 deflects towards the wing root, and the whole turns to the left. The reverse is also true.

[0102] 3. Transitional flight maneuvers: vertical takeoff and landing transitions into gliding mode.

[0103] 4. Modality switching method:

[0104] First, adjust the nozzle position to ensure they are all vertical. When a certain height is reached, pinch the locking handles 24 on both sides. The wings 2 on both sides will unfold under the action of the torsion spring hinges 22. Then, press the button 41 on the control stick 4 and push the control stick 4 forward. The nozzles 39 on the outer sides of the wings 2 will deflect towards the trailing edge of the wings. The angle of the entire fuselage 1 will gradually change from perpendicular to the ground to parallel to the ground, thus switching to gliding mode.

[0105] II. Gliding Mode

[0106] 1. Structural morphology: The overall structure of the gliding mode is as follows: Figure 1 As shown.

[0107] 2. Flight maneuvers: pitch, roll, yaw.

[0108] (1) Pitch: When diving, move the control stick 4 forward to adjust the nozzles of the outer nozzles 39 on both wings 2 to deflect towards the trailing edge of the wing 2; when pitching up, move the control stick 4 backward to adjust the nozzles of the outer nozzles 39 on both wings 2 to deflect away from the trailing edge of the wing 2.

[0109] (2) Roll: Roll to the left. At this time, adjust the left control stick 4 to move it backward, so that the nozzle of the outer nozzle 39 on the left wing 2 deflects away from the trailing edge of the wing 2. At the same time, adjust the right control stick 4 to move it forward, so that the nozzle of the outer nozzle 39 on the right wing 2 deflects towards the trailing edge of the wing 2. The opposite is true.

[0110] (3) Yaw: including yaw to the left and yaw to the right.

[0111] Yawing to the left is a combination of left roll and pitching up, while yawing to the right is a combination of right roll and pitching up.

[0112] For example, a left roll + dive = avoids an obstacle to the left and then returns to the original course; for example, a right roll + dive = avoids an obstacle to the right and then returns to the original course.

[0113] 3. Transitional flight maneuver: The gliding mode is changed to the vertical take-off and landing mode.

[0114] 4. Modality switching method:

[0115] First, fly up to a position perpendicular to the ground, then pinch the locking handles 24 on both wings 2 and pull both wings 2 towards one side of the body. When the locking pin 23 slides into the locking hole 153 of the tilting tube frame 15, release the locking handle 24 to switch to vertical take-off and landing mode.

[0116] The above-described embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application, and should all be included within the protection scope of this application.

Claims

1. A gliding vertical takeoff and landing dual-mode flight backpack, comprising a fuselage, wings, a power unit, and a control stick, characterized in that: The fuselage includes a tilting connection device, which comprises: A tilting connector, comprising a tilting shaft and a tilting connecting sleeve, wherein one end of the tilting shaft is fixedly connected to the tilting connecting sleeve, and the other end is rotatably connected to a central support; A tilting pipe rack, comprising a horizontal pipe and a vertical pipe, wherein the horizontal pipe and the vertical pipe are connected at an obtuse angle, the horizontal pipe is coaxially fitted with the tilting connecting sleeve and located inside the tilting connecting sleeve, and the vertical pipe has two locking holes. The wing includes a wing shell, a torsion spring hinge, a locking pin, and a locking handle; The tilting tube frame and the locking pin are both embedded in the groove of the wing shell. The torsion spring hinge is built into the groove of the tilting tube frame. The torsion spring hinge is fixed on the tilting tube frame, so that the wing shell has a tendency to rotate away from the pilot. The locking handle is connected to the locking pin and is used to control the locking pin to insert into or retract from the locking hole; Specifically, when the locking pin is inserted into one of the two locking holes, the wing shell is in a folded state and the gliding vertical takeoff and landing dual-mode flight backpack is in vertical takeoff and landing mode; when the locking pin is inserted into the other of the two locking holes, the wing shell is in an unfolded state and the gliding vertical takeoff and landing dual-mode flight backpack is in gliding mode. The power unit includes an inner nozzle and an outer nozzle; The number of control levers is two, and each control lever includes a button, a throttle, a middle sleeve, a locking sleeve, a second spring, and a locking pin, which is fixed to the mounting groove of the wing shell; The locking pin on the right control lever is connected to the right outer nozzle angle potentiometer, and the locking pin on the left control lever is connected to the left outer nozzle angle potentiometer; the inner nozzle angle potentiometer is fixed to the outer side of the middle sleeve on the left control lever, and the throttle potentiometer is fixed to the outer side of the middle sleeve on the right control lever. For any one of the control sticks, the middle sleeve is hinged to the wing shell via the locking pin, the throttle is mounted on the outside of the middle sleeve and can rotate relative to the middle sleeve, and the locking sleeve is mounted on the inside of the middle sleeve; for the right control stick, the locking sleeve can slide relative to the middle sleeve and the right outer nozzle angle potentiometer; for the left control stick, the locking sleeve can slide relative to the middle sleeve and the left outer nozzle angle potentiometer. For the control lever on either side, the bottom end of the button is installed inside the upper end of the locking sleeve, and the second spring is installed inside the locking sleeve; for the right control lever, the two ends of the second spring are fixedly connected to the button base and the upper end of the right outer nozzle angle potentiometer, respectively; for the left control lever, the two ends of the second spring are fixedly connected to the button base and the upper end of the left outer nozzle angle potentiometer, respectively. For the control lever on either side, the locking sleeve is provided with a rotating hole, a sleeve groove, and a limiting hole, and the locking pin is provided with a pin groove and a fixing hole; In its natural state, under the action of the second spring, the sleeve groove on the locking sleeve is nested with the pin groove on the locking pin, and the operating lever cannot rotate around the locking pin. When the button is pressed, the rotating hole on the locking sleeve is coaxial with the locking pin, and the operating lever can rotate around the locking pin.

2. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 1, characterized in that, The fuselage also includes an electronic control system, which includes a battery, a receiver, and a controller. The receiver and the controller are connected, and the battery is used to power the receiver and the controller.

3. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 2, characterized in that, The fuselage also includes a winch restraint device, which includes a continuously rotating servo motor, a winch, and a pull cable.

4. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 3, characterized in that, The wing also includes a torsion spring pin, the rightmost annular part of which is fitted onto the bottom of the locking handle. The torsion spring pin passes through a through hole on the locking handle and is equipped with a first spring.

5. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 4, characterized in that, The power unit also includes: an oil pump, an oil and electricity pipeline, an engine, an inner rocker arm, an inner connecting rod, an inner crank, an inner servo motor, an outer rocker arm, an outer connecting rod, an outer crank, and an outer servo motor; The oil pump passes through the oil and electricity line. The inner servo and the outer servo are mounted on the wing. The oil and electricity line passes through the inside of the wing and is connected to the inner servo. The inner servo is connected to the inner crank. The inner crank is connected to the inner connecting rod. The inner connecting rod is connected to the inner nozzle through the inner rocker arm. The inner nozzle is mounted on the engine. The inner nozzle can rotate around an axis perpendicular to the plane of the wing. The engine is mounted on the wing. The oil and electricity line is also connected to the outer servo, the outer servo is connected to the outer crank, the outer rocker arm is connected to the outer crank via the outer connecting rod, the outer rocker arm is connected to the outer nozzle, the outer nozzle is mounted on the engine, and the outer nozzle can rotate about an axis parallel to the trailing edge of the wing. The oil and electricity line is connected to the fuel tank, and after passing through the inner servo and the outer servo, the oil and electricity line is connected to the engine.

6. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 1, characterized in that: When the gliding vertical takeoff and landing dual-mode flight backpack is in the vertical takeoff and landing mode, the flight actions of the gliding vertical takeoff and landing dual-mode flight backpack include: ascent and descent, forward and backward movement, left and right translation, and left and right turning. When the gliding vertical takeoff and landing dual-mode flight backpack is in the gliding mode, the flight maneuvers of the gliding vertical takeoff and landing dual-mode flight backpack include: pitch, roll, and yaw.

7. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 1, characterized in that, The method for switching from the vertical takeoff and landing mode to the gliding mode is as follows: First, adjust the position of all nozzles to ensure they are all vertical. When the preset height is reached, pinch the locking handles on both sides, and the wings on both sides will unfold under the action of the torsion spring hinges; Next, press the button on the control stick and push the control sticks on both sides forward. The outer nozzles on the wings on both sides deflect towards the trailing edge of the wings, and the angle of the entire fuselage gradually changes from perpendicular to the ground to parallel to the ground, thereby switching to the gliding mode.

8. The gliding vertical takeoff and landing dual-mode flight backpack according to claim 1, characterized in that, The method for switching from the gliding mode to the vertical takeoff and landing mode is as follows: First, fly upwards until you are perpendicular to the ground; Then, pinch the locking handles on both wings and pull both wings toward one side of the body. When the locking pin slides into the locking hole of the tilting tube frame, release the locking handle to switch to the vertical take-off and landing mode.

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