Aircraft

Abstract

The invention relates to an aircraft. The present invention provides an aircraft capable of flying horizontally at a high speed and flying for a long distance 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 the invention patent application entitled "High-speed UAV 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 new type of aircraft such as a drone that can take off and land vertically and fly horizontally at high speed. Background Art

[0003] Normal aircraft glide on taxiways until they reach a takeoff speed. Conversely, landing aircraft glide from landing to landing, requiring taxiways as well. Typical distances require approximately 1.5 to 3 km, necessitating a VTOL (Vertical Take-Off and Landing) aircraft.

[0004] As such aircraft, helicopters, Ospreys, drones, etc. are known. Figure 1 As shown in the figure, 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 an airframe, reference numeral 3 is a tail rotor, and reference numeral 32 is a propeller rotation motor.

[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 made it practical in recent years.

[0006] The main wings are equipped with tilt-controlled propellers at both ends. By controlling the propeller tilt angle, hovering and horizontal flight are possible. The propeller tilt angle is varied from 0 to 90 degrees for ascent and forward maneuvers. However, switching the rotors between horizontal and vertical positions can often lead to accidents.

[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 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, camera, etc. Summary of the Invention

[0009] Problems to be solved by the invention

[0010] As mentioned above, aircraft cannot take off and land in areas without taxiways. Conventional aircraft have the following disadvantages: they lack vertical take-off and landing (VTOL) or hovering capabilities. To address this issue, consideration has been given to developing aircraft with VTOL and hovering capabilities. Helicopters, which have VTOL and hovering capabilities, play a vital role in rescuing lives in situations such as marine disasters and mountainous areas. However, due to their slow horizontal flight speed, short range, and limited cargo capacity, there is a demand for alternative aircraft.

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

[0012] In addition, if Figure 3 Drones are well known, but they have slow horizontal flight speeds, 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 configured with a propeller for vertical ascent and descent and a stabilizer 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 that can deliver mail-order goods over long distances at 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, and has safe and stable vertical take-off and landing and hovering functions. During take-off and ascent, there is no wing force loss due to propeller wind hitting the wings, and tilt rotors are not required, so the control structure becomes simple. 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 It is a side view of a known helicopter.

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

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

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

[0021] Figure 5 FIG. 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) 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 FIG. 5 is a top view of a fifth embodiment of the present invention.

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

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

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

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

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

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

[0031] Figure 15 It is a side profile view of the same as above.

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

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

[0034] Figure 18 It is a side profile view of the same as above.

[0035] Figure 19 This is a side view of the drive mechanism in which the same wing rotating motor is used as a single one.

[0036] Figure 20This is a conceptual diagram of the present invention in which the blades of the present invention are rotated using bevel gears.

[0037] Figure 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] Figure 22 This is the same picture of a horizontal plane as above.

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

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

[0041] The present invention is a new aircraft invented in view of such problems, and its purpose is to provide a new vertical take-off and landing aircraft (new VTOL), which is equipped with propellers for ascent and descent, propellers for forward movement, and rotating or non-rotating wings for horizontal flight and can of course take off and land vertically or hover. In addition, the horizontal flight speed is fast, the energy loss is small, and it can fly long distances. It 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, Ospreys, and autogyro aircraft.

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

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

[0045] Reference numeral 14 denotes a horizontal tail provided behind the propeller guard 8, and reference numeral 13 denotes a vertical tail for steering supported by the propeller guard 8. Reference numeral 7 denotes a motor for rotating the hovering propeller 6. Reference numeral 9 denotes a camera for filming, electronic circuitry, batteries, and the like.

[0046] The aircraft of the present invention is the first embodiment of the present invention in which the main wing 12, the tail wing 13, and the forward propeller 10 are arranged without hindering the ascending propeller, and the horizontal flight speed can be increased. The forward propeller 10, the rotating motor 11, the main wing 12, the tail wing 13, and the 14 are supported and shared by the propeller guard 8.

[0047] Figure 5This is a top view of a tailless drone according to a second embodiment of the present invention. It is a top view of a second embodiment of the present invention having a spar 15, a main wing 20, an elevator 16, a wingtip 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 airfoil of the present invention, and is composed of a canard wing beam 22 supported by a propeller guard 13, a canard wing 21 supported by a propeller guard 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 guard 8, a main wing 31, a drive motor 19 for a pushing propeller 18 supported by the propeller guard 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 does not include a propeller guard 13 and instead uses both main wings 36 and 37 as propeller guards. This invention is a tandem-type aircraft, with the front wing 36 and rear wing 37 being of equal size. Specifically, the propeller 6 and motor 7 for ascending and descending are located between the two wings, with the main wings 36 and 37 protecting the rotation of the propeller 6. Reference numeral 38 denotes a support beam for the ascending and descending propeller motor 7, located outside the wing. Of course, any increase or decrease in the number of propellers is also encompassed by the present invention.

[0050] Figure 8 This is the fifth embodiment of the present invention. All four rotational paths 39 of the upper and lower propellers are inscribed, and no propeller guard is provided. Instead, the four main wings 24, canards 28, and tail wing 29 serve as propeller guards. Reference numeral 40 denotes a beam connecting the four propeller motors 7.

[0051] Figure 9 This is the sixth embodiment of the present invention, in which a propeller motor 7 and a main wing 42 are installed on a 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 use microwaves to transport energy on the ground.

[0052] Figure 10 This is the seventh embodiment of the present invention, in which upper and lower propellers 6 and motors 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 、 Figure 9 、 Figure 10The operation of the aircraft having the above configuration will be described as follows.

[0054] In this case, first, when the operator uses a remote control to turn on switch 1 (not shown), the drone's ascent motor 7 and ascent propeller 6 begin rotating wirelessly, causing the drone to ascend to a predetermined altitude. Next, when the operator uses a remote control to turn on switch 2 (not shown), the rotational force of motors 11 and 19 rotates forward propeller 7 and push propeller 18.

[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, Figure 9 42, Figure 10 43, 44 share, during which time, the propeller 6 for ascending and the motor 9 are idling. Moreover, since it reaches 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 during landing will be described. During 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 aircraft lands while controlling the rotation of the vertical propellers 6.

[0057] According to the present invention, the propeller pitch angle control is not required during landing (refer to Figure 1 The circuits or commands for controlling the rotational speed of the drone's multiple horizontal propellers are simplified, resulting in lower costs and easier operation, enabling safe and reliable landings. Furthermore, the use of fixed wings for horizontal flight enables high-speed flight. Furthermore, the propeller guards can double as wings, simplifying the structure and reducing weight.

[0058] Figure 12 It is a top view of the ninth embodiment of the invention of the present application with twin engines. The horizontal flight is equipped with twin engine propellers 10, which 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. Figure 12 As shown, the present invention can also be used as an aircraft that carries many people.

[0059] The above is a drone, Figure 11This is the eighth embodiment of the present invention, a real aircraft for passengers, and its side view is shown. It is equipped with a forward engine 46 and its propeller 47. A combined ascending and descending engine 25 and rotors 48 are installed on the fuselage 1 at the center of gravity. Reference numeral 51 denotes the vertical tail, reference numeral 50 denotes the horizontal tail, and reference numeral 26 denotes the pilot's seat. The present invention also encompasses the case where a jet engine or rocket engine 27 is installed at the rear in place of the forward propeller 47 and engine 46. Furthermore, the present invention also encompasses the case where the ascending and descending rotors 48 and their engines 32 are installed at the wingtips 8. For the sake of caution, there are aircraft called autogyroplanes, but these lack ascending and descending engines and are completely different from the present invention.

[0060] Figure 13 、 14 , 15, 16, 17, and 18 are the tenth embodiment 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 no propeller for advancement is provided.

[0063] In the ninth embodiment, to prevent turbulence in the afterflow of the propeller used for ascent and descent, no blades were placed in the propeller afterflow. Instead, the blades were fixed. Furthermore, the propellers used for forward movement and for ascent and descent were provided independently. This tenth embodiment, with a completely different concept from the ninth embodiment, further enhances the efficiency of the present invention.

[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 direction of the wing also rotates accordingly, so that the propeller's afterflow and the surface direction of the wing become the same, and the propeller's 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 propulsion, the blades are rotated approximately 90 degrees as described above, and the direction of the propeller is rotated approximately 90 degrees to use it as a propeller for propulsion.

[0066] This could be misinterpreted as being similar to the Osprey, but this invention is fundamentally different. The Osprey has fixed wings with engines and propellers at the tips of the wings, which rotate in the same direction. Even when the propellers rotate in that direction, the wings do not rotate. In contrast, the present invention has propellers with engines fixed to the wings, and the wings are not fixed, but rotate along with the wings, which rotate in the same direction as the propellers.

[0067] This is different from the Osprey. Furthermore, in the Osprey, the propeller's afterflow collides with the wing, reducing propeller efficiency. In contrast, in the present invention, the propeller and wing are always at right angles, and when the propeller is tilted, the wing tilts at the same angle. Therefore, the propeller's afterflow does not collide with the wing, resulting in a significantly improved propeller afterflow.

[0068] Furthermore, since the Osprey's engine and propeller rotate at the wingtip, structural failures such as vibration and strength may occur. However, the present invention prevents structural failures because the engine and propeller are securely fixed to the wing. Furthermore, since the Osprey has a rotating engine and propeller at the tip of the wing, the wing spar must be made strong, which increases weight and reduces aerodynamic performance.

[0069] In contrast, the present invention improves aerodynamic performance due to its lighter wing spar compared to the Osprey aircraft. Because the Osprey has its engines and propellers at the wingtips, its longer span causes resonance, resulting in greater vibration and poor vertical centering, ultimately leading to crashes caused by vibration.

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

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

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

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

[0074] Figure 15 This is a diagram obtained by observing it from the side.

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

[0076] What is important here is 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] Figure 16 This is a plan view of the front main wing 57 and the rear main wing 58 and the propeller 6, propeller 6 motor 7, propeller 6', and propeller 6' motor 7' mounted thereon, which are rotated 90 degrees by the rotating shaft 67 of the motor 55 and the rotating shaft 70 of the motor 56.

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

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

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

[0083] Try to make sure that the wings 57 and 58 do not completely block the afterflow of the propellers 6 and 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 rotation shafts 69 and 70. Figure 18 location.

[0085] Thus, the aircraft 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 descend vertically around the rotation shafts 60, 76. Since the wings do not interfere with the propeller backflow at this time, the propeller efficiency is improved.

[0087] Figure 19 Is not used Figures 13 to 18 In the embodiment of the present invention, the wings 57 and 58 are rotated by only one motor 55 instead of the two motors 55 and 56, thereby achieving lightweighting of the aircraft.

[0088] The motor is preferably a stepper motor.

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

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

[0091] Figure 21 、 Figure 22 Other embodiments of the present invention include Figure 16 、 17 In the embodiment of 18, the efficiency of the rear propeller 6' is deteriorated due to the backflow of the front propeller 6. Therefore, Figure 21 、 Figure 22 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. Figure 21 Is the graph when rising or falling, Figure 22 This is a picture of horizontal flight.

[0092] Figure 23 、 Figure 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 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 drones, tilt-rotor aircraft such as known Osprey aircraft, and other vertical take-off and landing aircraft such as helicopters. Current drones are not suitable for long-distance item 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 drones, items 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, so it has great potential for industrial use.

[0096] Furthermore, since the aircraft of the present invention does not require pitch control, unlike helicopters, it not only simplifies steering and is inexpensive, but also boasts high horizontal speed and a long range. Furthermore, it is also safe and has a wider range of applications, as it is free from the tilting accidents associated with Osprey aircraft. Furthermore, if its size is increased, it can carry many people and can reach islands without airports, thus alleviating the transportation difficulties faced by island residents. This has significant applicability in defense and industry.

[0097] Furthermore, if this invention were to fly near the stratosphere, the solar energy received by its wings could be converted into microwaves and transmitted to the ground, where it could be used as electricity. This would provide valuable energy to resource-poor Japan and could replace reconnaissance satellites. This would have significant potential for defense and industrial applications.

[0098] Description of Reference Signs

[0099] 1 Body

[0100] 2 Main rotor

[0101] 3 tail rotor

[0102] 4 horizontal tail

[0103] 5Osprey aircraft engine rotating shaft

[0104] 6 drone propellers

[0105] 6' Same as above (back)

[0106] 7 UAV ascent and descent motors

[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 Push propeller

[0119] 19 Propeller drive motor

[0120] 20 tailless main wing

[0121] 21 Canard

[0122] 22 canard spar

[0123] 23 canard main wing

[0124] 24 propeller protection parts also serve as main wings

[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 propellers

[0135] 35 canard wing main spar

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

[0137] 37 propeller 6 protection and tandem main wing and 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 four beams connected by 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-series main wing (with wingtip propeller) rear wing

[0145] 45 Fuselage beam

[0146] 46 Actual forward propeller engine

[0147] 47 Actual aircraft forward propeller

[0148] 48 Actual aircraft dedicated rotor for ascent and descent

[0149] 49 real level flight dedicated main wing

[0150] 50 real-machine horizontal flight dedicated horizontal tail

[0151] 51 real aircraft horizontal flight dedicated vertical tail

[0152] 52 real machine ascent and descent dedicated rotor engine

[0153] 53 fuselage

[0154] 54 Batteries, electronic circuits, etc.

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

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

[0157] 57 front wing

[0158] 58 rear wing

[0159] 59 Cargo loading and landing device

[0160] 60 goods

[0161] 61 Rotation transmission rod of motor 55

[0162] 62 pivot of motor 55

[0163] 63 motor 55 rear wing rotating 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 Rotating Bevel Gear

[0169] 69 Tilt main rotor

[0170] 70 Torque Correction Tail Rotor

Claims

1. An aircraft, characterized in that: include: a first horizontal flight wing having two first propellers fixed thereto, each of the first propellers being located at a central portion of one side of the first horizontal flight wing for ascent, descent, and propulsion, the first horizontal flight wing being configured to rotate vertically for ascent and descent using the first propellers, and to rotate horizontally with an angle of attack for propulsion and horizontal flight using the first propellers; a second horizontal flight wing having two second propellers fixed thereto, each of the second propellers being located at a central portion of one side of the second horizontal flight wing for ascent, descent, and propulsion, the second horizontal flight wing being configured to rotate vertically for ascent and descent using the second propellers, and to rotate horizontally with an angle of attack for propulsion and horizontal flight using the second propellers; and A landing and take-off device and cargo holding unit, the landing and take-off device and cargo holding unit is located near the center of gravity of the aircraft and serves as both a landing and take-off device and a cargo holding unit. The first horizontal flight wing and the second horizontal flight wing are located on the same horizontal plane on the fuselage of the aircraft. The first horizontal flight wing has a first angle of attack when positioned for horizontal flight, and the second horizontal flight wing has a second angle of attack when positioned for horizontal flight, Furthermore, the first angle of attack and the second angle of attack are different angles of attack.

Images