Flying object

Abstract

The invention relates to a flying body. A flying body capable of flying horizontally at a high speed and flying for a long distance is obtained by providing propellers for vertical rising and falling and horizontal flying, and wings for horizontal flying.

Description

[0001] This application is a divisional application of an invention patent application entitled “High-speed UAVs and other aircraft”, with an international application date of March 22, 2019, an international application number of PCT / JP2019 / 012261, and a national application number of 201980033909.8. Technical Field

[0002] The present invention relates to a flying object such as a new type of unmanned aerial vehicle that can take off and land vertically and can fly horizontally at high speed. Background Art

[0003] Normally, an airplane glides on a taxiway until it reaches a speed that allows it to take off. On the other hand, when landing, the airplane glides from landing to stopping, so a taxiway is also required. The general distance required is about 1.5km to 3km. Therefore, a VTOL (vertical take-off and landing) is required.

[0004] As such aircraft, helicopters, Ospreys, drones, etc. are known. Figure 1 As shown, a helicopter uses one propeller for each of the following maneuvers: hovering, ascending, descending, and level flight. Figure 1 In the figure, reference numeral 1 is a body, reference numeral 3 is a tail rotor, and reference numeral 32 is a motor for rotating a propeller.

[0005] Since helicopters have a slow horizontal speed, the Osprey aircraft with a faster horizontal speed was developed. Figure 2 The Osprey aircraft was invented by the inventor in 1953 and taught to Lawrence Bell, CEO of Bell Aircraft. Bell Aircraft finally put it into practical use in recent years.

[0006] There are propellers that can be tilted at both ends of the main wing. By controlling the tilt angle of the propeller, the hovering function and horizontal flight can be achieved. In order to perform ascent and forward movement, the propeller tilt angle is changed from 0 degrees to 90 degrees. However, many accidents occur when the rotor is switched from horizontal to vertical.

[0007] exist Figure 2 In the figure, reference numeral 1 is the fuselage, reference numeral 34 is the propeller for the Osprey aircraft to ascend, descend and advance, reference numeral 4 is the horizontal tail, reference numeral 5 is the rotating shaft for the Osprey aircraft engine, and reference numeral 33 is the engine for the Osprey aircraft propeller, which has finally become popular in recent years.

[0008] Figure 3 The well-known drone, which was also invented by the inventor in 1940, has finally become popular in recent years. Figure 3In the figure, reference numeral 6 is a drone propeller, reference numeral 7 is a motor for ascending and descending the drone, reference numeral 8 is a drone propeller protection part, and reference numeral 9 is a receiving device, a camera, etc. Summary of the invention

[0009] Problems to be solved by the invention

[0010] As mentioned above, in places without taxiways, airplanes cannot take off and land. Conventional airplanes have the following disadvantages: they do not have vertical take-off and landing and hovering functions. In order to solve this problem, a flying object with vertical take-off and landing and hovering functions is considered. A helicopter is a flying object with vertical take-off and landing and hovering functions, and plays a role in saving lives in marine accidents, mountain accidents, etc. However, due to the slow horizontal flight speed, short cruising range, and small cargo capacity, a flying object is required to replace the helicopter.

[0011] In the case of an Osprey type aircraft, the wind from the propeller hitting the wing during vertical takeoff and landing is aerodynamically inefficient.

[0012] In addition, if Figure 3 Drones are well known, but they have a slow horizontal flight speed, cannot fly long distances, can be overturned by crosswinds, and are not all-weather capable. Therefore, although Amazon and others are planning to use them, they are not suitable for cargo delivery or rapid transportation.

[0013] Means for solving problems

[0014] The present invention for solving the above-mentioned problems is constituted by providing a propeller for vertical ascent and descent and a stabilizer wing for horizontal flight. It is a device different from an automatic rotorcraft that cannot vertically ascend and descend.

[0015] Effects of the Invention

[0016] According to the present invention, a vertical take-off and landing high-speed, long-distance safe aircraft can be provided which can deliver mail-order goods over long distances at a high speed and reliably with high energy efficiency. It has a high horizontal speed, can fly long distances with less energy, has a larger cargo capacity, is an all-weather type, has safe and stable vertical take-off and landing and hovering functions, has no wing force loss due to propeller wind hitting the wings during take-off and ascent, does not require tilt-rotors, and the control structure becomes simpler. In addition, accidents are eliminated, and it is easy and low-cost to manufacture. It is a groundbreaking invention that saves time and produces various effects in the industry. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a side view of a known helicopter.

[0018] Figure 2 It is a side view of a well-known tilt-rotor type (Osprey aircraft).

[0019] Figure 3 is a top view of a known UAV.

[0020] Figure 4 It is a top view showing an embodiment of a drone according to the present invention.

[0021] Figure 5 1 is a top view of a tailless UAV according to a second embodiment of the present invention.

[0022] Figure 6 It is a top view of a canard-type (Japanese: tail-forward wing) type of a third embodiment of the present invention.

[0023] Figure 7 1 is a top view of a string machine according to a fourth embodiment of the present invention.

[0024] Figure 8 4 is a top view of a fifth embodiment of the present invention.

[0025] Fig. 9 FIG. 1 is a diagram of a solar powered airplane according to a sixth embodiment of the present invention.

[0026] Fig.10 is a diagram of a seventh embodiment of the present invention.

[0027] Fig.11 It is a diagram of a twin-engine type according to an eighth embodiment of the present invention.

[0028] Fig.12 It is a side view of the ninth embodiment (actual machine) of the present invention.

[0029] Fig.13 This is a top view showing a tenth embodiment of the present invention in which the wings are horizontally arranged.

[0030] Fig.14 It is the front side view of the same as above.

[0031] Fig.15 It is a side elevation view of the same as above.

[0032] Fig.16 This is a top view showing a tenth embodiment of the present invention in which the wings are made vertical.

[0033] Fig.17 It is the front side view of the same as above.

[0034] Fig.18 It is a side elevation view of the same as above.

[0035] Fig.19 This is a side view of the drive mechanism in which the wing rotating motor is provided as one.

[0036] Fig. 20This is a conceptual diagram of the present invention in which the blade of the present invention is rotated using a bevel gear.

[0037] Fig.21 This is a diagram of the ascending and descending embodiment of the present invention in which the rear propeller is not affected by the follow-up of the front propeller.

[0038] Fig. 22 It is the same picture of the horizontal plane as above.

[0039] Fig.23 It is a side view of an embodiment of the present invention of a single tilt main rotor type.

[0040] Fig.24 This is the top view of the same. DETAILED DESCRIPTION

[0041] The present invention is a newly invented aircraft made in view of such a problem, and its purpose is to provide a new vertical take-off and landing aircraft (new VTOL), which is equipped with a propeller for ascent and descent, a propeller for forward movement, and a rotating or non-rotating wing for horizontal flight, and of course can take off and land vertically or hover, and has a high horizontal flight speed, less energy loss, can fly long distances, is an all-weather type, and can perform stable flight even in bad weather.

[0042] It should be noted that the present invention is a concept different from previous drones, helicopters, osprey aircraft, and autogyro aircraft.

[0043] Figure 4 1 is a top view of the first embodiment of the aircraft of the present invention. In the figure, reference numeral 13 is a horizontal tail, reference numeral 14 is a vertical tail, and reference numeral 10 is a propeller for forward movement. Reference numeral 12 is a main wing for horizontal flight, which is supported by a propeller protection member 8 for ascending and a main wing spar 15. Reference numeral 6 is a propeller for ascending and descending and hovering.

[0044] The pair of main wings 12 and the main spar 15 are provided on the left and right of the propeller guard 8 .

[0045] Reference numeral 14 is a horizontal tail provided at the rear of the propeller guard 8, and reference numeral 13 is a steering vertical tail supported by the propeller guard 8. Reference numeral 7 is a motor for rotating the hovering propeller 6. Reference numeral 9 is a camera for photographing, an electronic circuit, a battery, and the like.

[0046] The aircraft of the present invention is a first embodiment of the present invention that is structured using a propeller guard 8 to support and share the forward propeller 10, the rotating motor 11, the main wing 12, the tail wing 13, and the forward propeller 10 without hindering the upward propeller, and can increase the horizontal flight speed.

[0047] Figure 51 is a top view of a tailless UAV according to a second embodiment of the present invention. 1 is a top view of a tailless UAV according to a second embodiment of the present invention, which is provided with a wing spar 15, a main wing 20, an elevator 16, a wing end vertical direction arm 17, and a propeller 18 and a drive motor 19 at the rear. Figure 4 As described.

[0048] Figure 6 It is an embodiment of the canard wing of the present invention, and is composed of a canard wing beam 22 supported by a propeller protection member 13, a canard wing 21 supported by a propeller protection member 8, a propeller motor 11, a pulling propeller (Japanese: プルプロペラ) 10, a main wing beam 35 supported by the propeller protection member 8, a main wing 31, a driving motor 19 for a pushing propeller 18 supported by the propeller protection member 8, and a vertical tail 30 at the end of the main wing.

[0049] Figure 7 This is the fourth embodiment of the present invention, which is an invention in which the propeller guard 13 is not provided and the two main wings 36 and 37 are used as propeller guards. It is a tandem aircraft in which the front wing 36 and the rear wing 37 are set to the same size. That is, it is an invention in which the propeller 6 and the motor 7 for ascending and descending are provided between the two wings, and the main wings 36 and 37 protect the rotation of the propeller 6. The reference numeral 38 is a support beam for the ascending and descending propeller motor 7 provided outside the wing. Of course, even if the number of propellers is increased or decreased, it is also included in the present invention.

[0050] Figure 8 This is the fifth embodiment of the present invention, in which all four rotation tracks 39 of the upper and lower propellers are inscribed, and no propeller protection is provided, but the four main wings 24, the canard wings 28 and the tail wing 29 are used as propeller protection. Reference numeral 40 is a beam connecting the four propeller motors 7.

[0051] Fig. 9 This is the sixth embodiment of the present invention. The propeller motor 7 and the main wing 42 are installed on the quadrilateral frame 41. Figure 8 The same, but it is an embodiment in which the four main wings are set as solar panels 42, and it can also use solar energy to fly permanently, and can use microwaves to transport energy on the ground.

[0052] Fig.10 This is the seventh embodiment of the present invention, in which the upper and lower propellers 6 and the motor 7 are provided on the outer sides of the main wings 43 and 44, and the main wing structure is simplified.

[0053] like Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 , Fig.10The operation of the aircraft having the structure shown is described as follows.

[0054] In this case, first, when the controller turns on switch 1 (not shown) using the remote controller, the ascending motor 7 and the ascending propeller 6 of the drone start rotating wirelessly, and the drone rises to a predetermined height. Next, when the controller turns on switch 2 (not shown) using the remote controller, the forward propeller 7 and the push propeller 18 rotate using the rotational force of the motors 11 and 19.

[0055] The body starts to move forward, and the buoyancy is Figure 4 The main wing 12 and the tail wing 13, Figure 5 20. Figure 6 21 and 31, Figure 7 36 and 37, Figure 8 24, 28, Fig. 9 42. Fig.10 43 and 44 share the load, during which the propeller 6 and the motor 9 are idled for ascending. In addition, since the drone can reach the destination at a higher speed than the known drone, it is superior to the known drone in product sales or remote photography.

[0056] Next, the operation at the time of landing will be described. At the time of landing, the controller increases the rotation of all the vertical propellers 6 and stops the rotation of the forward propeller 10. In this state, the controller lands while controlling the rotation of the vertical propellers 6.

[0057] According to the present invention, no propeller tilt angle control is required during landing (refer to Figure 1 The invention can control the rotation speed of the multiple horizontal propellers of the UAV, and the circuit or instruction of the rotation speed of the multiple horizontal propellers of the UAV is simple in structure, cost is reduced, and operation is simple, so that the landing action can be performed safely and reliably. In addition, since the horizontal propeller uses fixed wings, it can fly at high speed. In addition, since the propeller guard can be used as a wing, the structure is simple and lightweight.

[0058] Fig.12 It is a top view of the ninth embodiment of the invention of the present application with twin engines. It is equipped with twin-engine propellers 10 for horizontal flight, and can fly at high speed and move long distances. Four propellers 6 are provided for vertical ascent and descent. Reference numeral 21 is a beam provided between the engines 11, reference numeral 53 is a beam connecting the engines 11 and the mechanism 54, and reference numeral 55 is a beam connecting the mechanism 54. Fig.12 As shown, the present invention can also be used as an aircraft that carries many people.

[0059] The above is a drone. Fig.11This is the eighth embodiment of the present invention, which is a real machine for people to ride in and shows its side view. It is equipped with a forward engine 46 and its propeller 47, and an ascending and descending engine 25 and a rotor 48 are provided on the fuselage 1 at the center of gravity. Reference numeral 51 is a vertical tail, reference numeral 50 is a horizontal tail, and reference numeral 26 is a driver's seat. The case where a jet engine or a rocket engine 27 is provided at the rear to replace the forward propeller 47 and the engine 46 is also included in the present invention. In addition, the case where the ascending and descending rotor 48 and its engine 32 are provided at the wing tip 8 is of course also included in the present invention. For the sake of caution, there is an aircraft called an automatic rotorcraft, but it does not have an ascending and descending engine, which is completely different from the present invention.

[0060] Fig.13 , 14 , 15, 16, 17, and 18 are the tenth embodiments of the present invention.

[0061] This embodiment is fundamentally different from the embodiments up to the ninth embodiment.

[0062] Specifically, in the ninth embodiment, the wings are fixed and the propeller for advancement is independently provided, but in the tenth embodiment, the wings are rotated and the propeller for advancement is not provided.

[0063] In the ninth embodiment, in order to prevent the rear flow of the propeller for ascending and descending from being turbulent, no wing is arranged in the rear flow of the propeller. And the wing is fixed. In addition, the propeller for advancing and the propeller for ascending and descending are independently arranged. This tenth embodiment is an embodiment of a completely different concept from the ninth embodiment, and is an embodiment that makes the present invention more efficient.

[0064] Specifically, in order to rationalize the structure, a propeller for ascent and descent is installed on the wing. In order to improve the propeller efficiency and prevent the propeller's afterflow from being disturbed by the wing, the wing is arranged at right angles to the propeller. If the axial direction of the propeller changes, the wing direction also rotates accordingly, so that the propeller afterflow becomes the same as the surface direction of the wing, and the propeller afterflow is never disturbed by the wing.

[0065] In order to use the propeller for both ascent and descent and not to provide a propeller for advancement, the blade is rotated about 90 degrees as described above, the direction of the propeller is rotated about 90 degrees, and the propeller is used as the propeller for advancement.

[0066] This may be misunderstood as being the same as the Osprey, but this invention is fundamentally different from the Osprey. The Osprey is an aircraft in which the wings are fixed, and an engine and a propeller are provided at the front end of the wings to rotate in the direction, and the wings do not rotate even if the propeller rotates in the direction. In contrast, the present invention fixes the propeller with the engine to the wing, and the wing is not fixed but rotates together with the wing rotating in the direction of the propeller.

[0067] In this way, it is different from the Osprey. In the case of the Osprey, the propeller backflow collides with the wing, and the propeller efficiency decreases. In contrast, in the present invention, since the propeller and the wing are always at right angles and when the propeller is tilted, the wing is tilted at the same angle, the propeller backflow does not collide with the wing, so it is an invention that significantly improves the propeller backflow.

[0068] In addition, since the engine and propeller of the Osprey aircraft rotate at the wing tip, vibration or strength failures may occur in the structure, but since the engine and propeller of the present invention are firmly fixed to the wing, no failure will occur in the structure. In addition, since the Osprey aircraft is provided with a rotating engine and propeller at the front end of the wing, it is necessary to make the wing spar strong, so the weight increases and the aerodynamic performance decreases.

[0069] In contrast, the present invention has a lighter wing spar than the Osprey aircraft, so the aerodynamic performance is improved. Since the Osprey aircraft has an engine and a propeller at the wing end, resonance caused by a longer span will occur, vibration will be greater, and vertical center retention will be poor, and finally a crash accident caused by vibration will occur.

[0070] In contrast, in the present invention, since the engine and propeller are not located at the front end of the wing but are located in the central part with a strong structure, resonance will not occur and the vertical center maintenance performance is also good.

[0071] use Fig.13 The following figures illustrate this situation.

[0072] Fig.13 This is a top view of an example of the tenth embodiment. The fuselage 53 is provided with a motor 55 for rotating the wing 57, a motor 56 for rotating the wing 58, a battery 54 for driving the motors 55 and 56, a vertical tail 14, a front main wing 57, and a rear main wing 58. The front main wing 57 is equipped with a propeller motor 7 and a propeller 6, and the rear main wing 58 is equipped with a propeller 6' driving motor 7' and a propeller 6'.

[0073] Fig.14 This is a picture obtained by observing it from the front.

[0074] Fig.15 This is a picture obtained by observing it from the side.

[0075] Reference numeral 59 denotes a take-off and landing device and a cargo holding unit. A camera or cargo 60 is carried on CG68 of the aircraft, and a method is employed to enable the aircraft to always fly horizontally regardless of the weight of the cargo.

[0076] It is important here that the motor 7 for the propeller 6 is mounted on the front wing 57 so that the wing 57 has an angle of attack α62 with respect to the thrust line of the propeller 6 .

[0077] Similarly, the motor 7 ′ for the propeller 6 ′ is mounted so that the rear wing 58 also has an angle of attack β.

[0078] α and β are of course different angles.

[0079] Fig.16 This is a top view obtained by rotating the front main wing 57 and the rear main wing 58 and the propeller 6, the propeller 6 motor 7, the propeller 6', and the propeller 6' motor 7' mounted thereon by 90 degrees using the rotating shaft 67 of the motor 55 and the rotating shaft 70 of the motor 56.

[0080] Fig.17 This is a picture obtained by observing it from the front.

[0081] Fig.18 Observed from the side Fig.16 The obtained figure.

[0082] In this state, the aircraft of the present invention uses the motor 7 to rotate the propeller 6 and uses the motor 7 ′ to rotate the propeller 6 ′, thereby taking off vertically.

[0083] It is ensured that the wings 57, 58 do not completely block the rear flow of the propellers 6, 6' at this time.

[0084] Next, the motors 55 and 56 are gradually rotated to rotate the propellers 6 and 6', the wings 57 and 58 around the rotating shafts 69 and 70. Fig.18 location.

[0085] Thus, the body is floated by wings 57 and 58, and the thrust of propellers 6 and 6' is used to fly horizontally at high speed. If necessary, the camera 60 is used to take pictures.

[0086] When the destination is reached, the motors 55 and 56 are rotated in the opposite direction to the above, so that the wings 57, 58 and the propellers 6, 6' gradually turn upward and vertically descend around the rotating shafts 60, 76. Since the wings do not hinder the propeller backflow at this time, the propeller efficiency is improved.

[0087] Fig.19 Not used Figures 13 to 18 According to an embodiment of the present invention, the wings 57 and 58 are rotated by only one motor 55 instead of two motors 55 and 56, thereby making it possible to reduce the weight of the aircraft.

[0088] The motor is preferably a stepper motor.

[0089] The rotation force 66 of the motor 55 is converted into a rotation force 67 by the rod 61 , the pivot 62 , and the connecting beam 63 via the pivot 64 and the rod 65 , and the shaft 70 is rotated.

[0090] Fig. 20 is with Fig.19Different embodiments of the present invention utilize the non-reversible nature of the bevel gear 68 to rotate the wings 57 , 58 .

[0091] Fig.21 , Fig. 22 Other embodiments of the present invention include Fig.16 , 17 In the embodiment of 18, due to the backflow of the front propeller 6, the efficiency of the rear propeller 6' becomes poor. Fig.21 , Fig. 22 This is a diagram of another embodiment of the present invention obtained by improving the above-mentioned embodiment. In this embodiment, since the afterflow of the front propeller 6 is outside the rotation range of the rear propeller 6', the efficiency of the rear propeller 6' does not decrease. Fig.21 It is a graph when rising or falling. Fig. 22 This is a picture of horizontal flight.

[0092] Fig.23 , Fig.24 This figure is also another embodiment of the present invention, and is composed of a single tilting main rotor 69, a torque correction tail rotor (Japanese: Torque is positive tail rotor) 70, a fixed main wing 57 and a fixed tail wing 58.

[0093] The present invention is applicable not only to drones but also to real machines. In this case, the propeller is rotated by an engine. In addition, the present invention also includes the case where a jet engine or a rocket is used instead of a propeller.

[0094] Industrial Applicability

[0095] The present invention is a new type of aircraft that is safe and has a high horizontal speed compared to known unmanned aerial vehicles, known tilt-rotor aircraft such as Osprey aircraft, helicopters and other vertical take-off and landing aircraft. Current unmanned aerial vehicles are not suitable for high-speed transportation for long-distance goods transportation and logistics such as mail order due to their slow speed, inability to fly long distances, and high energy consumption. However, when the present invention is applied to unmanned aerial vehicles, goods can be transported at high speed and long-distance photography can be performed. In addition, when the present invention is applied to a manned aircraft, it can play a role in rapid mountain rescue, maritime rescue, etc. in remote locations, and therefore has great potential for industrial use.

[0096] In addition, since the aircraft of the present invention does not require pitch control compared to a helicopter, it is not only simple to turn and low-cost, but also has a fast horizontal speed and a long cruising range. In addition, there is no accident caused by the tilting of the Osprey aircraft, so it is safe and has a wider range of use. In addition, if the size of its body is increased, it can carry many people, and it can reach islands without airports, which can make up for the inconvenience of transportation for residents on the islands, and has great applicability in defense and industry.

[0097] In addition, if the present invention is flown near the stratosphere, the solar energy received by the wings can be converted into microwaves and transmitted to the ground, where it can be used as electricity. This will supply precious energy to our country, which has no resources, and can also replace reconnaissance satellites. It has great applicability in defense and industry.

[0098] Description of Reference Numerals

[0099] 1 Body

[0100] 2 Main rotor

[0101] 3 Tail rotor

[0102] 4 Horizontal tail

[0103] 5 Rotating shaft for Osprey aircraft engine

[0104] 6 drone propellers

[0105] 6' Same as above (back)

[0106] 7 UAV ascending and descending motor

[0107] 7' Same as above (back)

[0108] 8 UAV propeller protection parts

[0109] 9Receiving device, camera, etc.

[0110] 10 Forward propeller

[0111] 11 Forward propeller motor

[0112] 12 main wing

[0113] 13 Horizontal tail

[0114] 14 Vertical tail

[0115] 15 Main spar

[0116] 16 Elevator rudder

[0117] 17 Wing end vertical elevator

[0118] 18 Pushing propeller

[0119] 19 Push propeller drive motor

[0120] 20 Tailless main wing

[0121] 21 Canard

[0122] 22 Canard spar

[0123] 23 canard main wing

[0124] 24 Propeller protection and main wing

[0125] 25 Ascending and descending propeller engine

[0126] 26 Cab

[0127] 27 Jet or rocket engine

[0128] 28 propellers 6 protection and canard wing

[0129] 29 propellers 6 protection and tail

[0130] 30 wing end vertical tail

[0131] 31 canard main wing

[0132] 32 Propeller rotation motor

[0133] 33 Osprey aircraft propeller engine

[0134] 34 Osprey aircraft ascending, descending, and moving forward with propellers

[0135] 35 canard wing main spar

[0136] 36 propellers 6 protection and tandem main wing front wing

[0137] 37 propeller 6 protection and tandem main wing rear wing

[0138] 38 is set on the upper and lower propeller motor support beams of the tandem machine

[0139] 39 Up and down propeller rotation track

[0140] 40 connect the four upper and lower beams with the propeller motor 7

[0141] 41 A quadrilateral beam connecting the four propeller motors 7

[0142] 42 Solar panels

[0143] 43 tandem main wing (with wingtip propeller) front wing

[0144] 44 tandem main wing (with wingtip propeller) rear wing

[0145] 45 Fuselage beam

[0146] 46 Actual forward propeller engine

[0147] 47 Actual forward propeller

[0148] 48 Actual aircraft ascent and descent dedicated rotor

[0149] 49 Real level flight dedicated main wing

[0150] 50 real level flight dedicated horizontal tail

[0151] 51 real machine horizontal flight dedicated vertical tail

[0152] 52 Actual aircraft ascending and descending dedicated rotor engine

[0153] 53 body

[0154] 54Batteries, electronic circuits, etc.

[0155] 55 front wing rotation motor (stepping motor)

[0156] 56 rear wing rotation motor (stepping motor)

[0157] 57 Front wing

[0158] 58 rear wing

[0159] 59 Cargo loading and landing device

[0160] 60 Cargo

[0161] 61 Rotation transmission rod of motor 55

[0162] 62 Pivot of motor 55

[0163] 63 Motor 55 rear wing rotation connecting beam

[0164] 64 Pivot of motor 55

[0165] 65 motor 55 rod

[0166] 66 Front wing rotation motor rotation direction

[0167] 67 Rear wing rotation motor rotation direction

[0168] 68 Wing Rotary Bevel Gear

[0169] 69 Tilt main rotor

[0170] 70 Torque correction tail rotor

Claims

1. A flying object, characterized in that: include: a rotatable front wing for horizontal and vertical flight, comprising a first set of propellers for vertical takeoff, vertical landing, and horizontal flight propulsion; as well as A rotatable rear wing for horizontal and vertical flight, including a second set of propellers for vertical takeoff, vertical landing and horizontal flight propulsion, wherein the positioning of the second set of propellers relative to the first set of propellers prevents interference with the leading flow from the second set of propellers and prevents overlapping of the trailing flow from the first set of propellers in the same plane during ascending and level flight, The rotatable front wing and the rotatable rear wing are located in the same horizontal plane on the fuselage of the flying object, When viewed from above and along the same horizontal plane on the fuselage of the flying body, the second set of propellers included in the rotatable rear wing are located outside the first set of propellers included in the rotatable front wing, so that the wake of the second set of propellers is located outside the rotation range of the first set of propellers during horizontal and vertical flight, Wherein, the flying body consists of only two wings, each of which is fully rotatable, and the two wings include the rotatable front wing and the rotatable rear wing, and the length of the rotatable front wing is different from the length of the rotatable rear wing to avoid interference between the propeller wakes of the first group of propellers and the second group of propellers.

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