Body-mounted vertical take-off and landing aircraft

Abstract

To provide a body-fixed vertical take-off and landing flying vehicle that can ascend vertically directly from the ground and transition to a horizontal flight state at any speed by operating it at a certain height, and can select altitude, speed, direction, etc. by operating only one control stick. [Solution] The aircraft is composed of right and left wings (200 and 300) arranged on top of the main body (100), jet-type right and left wing engines (210 and 310) fixed near the center of each of the left and right wings (200, 300), right and left wing flaps (220 and 320) arranged on the wings immediately behind each of the engines (210, 310) and controlling the ascent and descent of the main body (100) by their action, a housing (110) arranged midway between the right and left wings (200, 300) and storing fuel for each engine (210, 310), a fixing belt (140) attached to one side of the housing (110) to fix the main body (100) to the human body, fixing the aircraft during takeoff and landing and reducing shock during landing, and a control stick (150).

Description

[Technical Field]

[0001] The present invention relates to a body-fixed vertical take-off and landing aircraft, and in particular to a body-fixed vertical take-off and landing aircraft that can ascend vertically directly from the ground and transition to horizontal flight at any speed by operating at a certain height, and can select altitude, speed, direction, etc. by operating only one control stick. [Background technology]

[0002] For example, there is the jet wingback, developed by Swiss pilot Yves Rossy, known as "Jetman." This is a method in which a jet-powered wing is attached to the back of a human body, which is carried into the sky by an airplane such as a Cessna, descends, ignites the jet, and flies, landing with a parachute (method 1).

[0003] Another well-known flying suit is designed by British entrepreneur Richard Browning, who has miniature jet engines attached to his arms and legs. It uses small jet engines for propulsion. Its name is "Daedalus." It has jet engines attached to its back, jet engines attached to both wrists, various sensors, and the arms and legs control the center of gravity, thereby controlling the direction of flight and stabilizing flight (the second method).

[0004] The commonality between these two is that they use jet engines for propulsion: the first method relies on the power of another aircraft to propel the plane into the air, then separates from the aircraft and uses the jet engine to glide, while the second method uses the jet engine for takeoff and landing. Summary of the Invention [Problem to be solved by the invention]

[0005] However, such jet propulsion aircraft have the following problems: (1) The first method involves being carried into the sky by another aircraft, using a jet engine attached to the body for gliding, and then using a parachute for landing, which poses the problem that even a slight breeze can prevent the aircraft from landing safely at its destination. (2) The second method involves mounting a jet engine on the back and attaching small jet engines to both wrists, and combining the functions of both to adjust direction and speed. However, this requires life-risking training and skill, and there is a problem in that anyone cannot easily fly it after receiving instructions.

[0006] Therefore, the object of the present invention is to provide a body-fixed vertical take-off and landing aircraft that can ascend vertically directly from the ground, and by operating it at a certain height, can transition to horizontal flight at any speed, and can select altitude, speed, direction, etc. by operating only one control stick. [Means for solving the problem]

[0007] In order to achieve the above-mentioned object, the present invention provides a fixed-body vertical take-off and landing aircraft comprising a rudder, a fuselage, and wings, the fixed-body vertical take-off and landing aircraft having a fuselage body, left and right wings arranged on top of the fuselage body and tilting and pivoting vertically or horizontally either independently or integrally, and attachment means for attaching the fuselage body to the body, wherein the left and right wings are each equipped with a propulsion means at the center of the length of the wing, and a flap located immediately aft of the propulsion means and controlling the ascent and descent of the fuselage body, and wherein an electronic equipment storage section for storing a control section that electronically controls the fuselage body, a power supply storage section for storing power sources for electronic devices mounted on the fuselage body, and a fuel storage section for storing fuel for the propulsion means are arranged intermediate the left and right wings, and a control stick is arranged to control the operation of the fuselage body during take-off, navigation, and / or landing.

[0008] In the above configuration, the propulsion means is a jet engine or a propeller engine.

[0009] The propelling means are characterized in that the propelling angles and propelling forces of the respective propelling means can be made different.

[0010] The aircraft is also characterized by being equipped with a shock mitigation device that stabilizes the aircraft during takeoff and landing and reduces shock during landing.

[0011] The control stick is also characterized by being equipped with an information display screen that controls the angles of the left and right wings, the output of the propulsion means, and displays various information.

[0012] The machine body is also characterized by being provided with a device for preventing the machine body from falling over when it is leaned against something.

[0013] The electronic equipment storage section is characterized by storing a gyro sensor, an altimeter, a speedometer, a wind vane, a fuel gauge, a GPS sensor, an emergency signal transmitter, an automatic hovering device in an emergency, an emergency takeoff point return indicator, an automatic return device, a static electricity air dissipation device, an emergency remote control device, a nearby object detection device, and / or a high-voltage power line detection sensor. [Effects of the Invention]

[0014] According to the present invention, a fixed-body type vertical take-off and landing aircraft is provided, which is composed of a rudder, a fuselage, and wings, and has a fuselage body, left and right wings arranged on top of the fuselage body and tilting and pivoting vertically or horizontally independently or integrally, and attachment means for attaching the fuselage body to the body, and the left and right wings are each provided with a propulsion means at the center of the length of the wing, and a flap located immediately behind the propulsion means for controlling the ascent and descent of the fuselage body, and a fuselage control means is provided at an intermediate position between the left and right wings. The aircraft is equipped with an electronics storage section that stores a control section that electronically controls the main body, a power storage section that stores power sources for the electronic devices mounted on the main body of the aircraft, and a fuel storage section that stores fuel for the propulsion means, as well as a control stick that controls the operation of the main body of the aircraft during takeoff, navigation, and / or landing.This makes it possible to provide a body-fixed vertical takeoff and landing aircraft that can rise vertically directly from the ground and, by operating it at a certain height, transition to a horizontal flight state at any speed, and that can select altitude, speed, direction, etc. by operating only a single control stick. [Brief explanation of the drawings]

[0015] [Figure 1] 1 is a front view showing the configuration of a manned body fixed vertical take-off and landing aircraft of the present invention. FIG. [Figure 2] 1 is a rear view schematic diagram showing the configuration of a manned body fixed vertical take-off and landing aircraft of the present invention. [Figure 3] FIG. 2 is a front view of the control stick when it is operated. [Figure 4] FIG. 2 is a schematic rear view of the aircraft when the control stick is operated. [Figure 5] 1 is a side view of a manned-body fixed vertical take-off and landing aircraft of the present invention. FIG. [Figure 6] This is a cross-sectional view from the left side when moving the control stick back and forth. [Figure 7] Schematic cross-sectional view from the left side when flying forward DETAILED DESCRIPTION OF THE INVENTION

[0016] Preferred embodiments of the present invention will now be described with reference to the drawings. 1 and 2 are schematic front and rear views showing the configuration of the human body-fixed vertical take-off and landing aircraft (hereinafter referred to as "aircraft") of the present invention. FIG. 3 is a schematic front view when the control stick 150 is being operated, and FIG. 4 is a rear view at that time. FIG. 5 is a side view of the aircraft. The relative positions and usage states of the aircraft body, wings, engine, control stick, electronic device storage section, and self-standing opening and closing legs are shown. FIG. 6 is a cross-sectional view seen from the side when the control stick is moved back and forth, and FIG. 7 is a side view during forward flight.

[0017] As shown in FIG. 1, this aircraft comprises right and left wings 200 and 300 disposed on top of the fuselage body 100, jet-type right and left wing engines 210 and 310 fixed near the center of each of the left and right wings 200 and 300, right and left wing flaps 220 and 320 disposed on the wings immediately behind each of the engines 210 and 310 and controlling the ascent and descent of the fuselage body 100 by their action, and right and left wing flaps 220 and 320 disposed at intermediate positions between the right and left wings 200 and 300. It is composed of a housing 110 that stores 10,310 of fuel, a headrest 120 that is arranged on the top of the housing 110 and that reduces shock to the head during takeoff and landing or flight, a fixing belt 140 that is arranged on one side of the housing 110 and that fixes the aircraft body 100 to the human body and fixes the aircraft during takeoff and landing and reduces shock during landing, a control stick 150, and a right self-standing opening and closing leg 290 and a left self-standing opening and closing leg 390 that are devices that prevent the aircraft body 100 from tipping over when it is leaned against something.

[0018] Also, as shown in Figure 2, on the back side of the housing 110, which is located at the midpoint between the left wing 300 and the right wing 200, there are provided an electronic device storage section 130 that stores a control section that electronically controls the aircraft main body 100, and a power supply storage section 135 that stores a power supply for the electronic devices mounted on the aircraft main body 100, such as a lithium battery.

[0019] 1 and 2, reference numeral 230 denotes an actuation motor that actuates the right wing flap 220, 250 denotes an actuation motor that actuates the connection between the right wing 200 and the aircraft main body 100, 260 denotes a gear for pivoting the right wing 200, 270 denotes an actuation bar for the right self-standing opening / closing leg, 280 denotes an attachment part between the right self-standing opening / closing leg 290 and the aircraft main body 100, 330 denotes an actuation motor that actuates the left wing flap 320, 350 denotes an actuation motor that actuates the connection part between the left wing 300 and the aircraft main body 100, 360 denotes a gear for pivoting the left wing 300, 370 denotes an actuation bar for the left self-standing opening / closing leg, and 380 denotes an attachment part between the left self-standing opening / closing leg 390 and the aircraft main body 100.

[0020] In the above configuration, the central axis of each engine 210, 310 is arranged so that it can pivot horizontally at an angle of 3 degrees or less relative to the central axis of the fuselage 100. Furthermore, each of the left and right wings 200, 300 is arranged so that it can pivot horizontally at an angle of 75 degrees from a vertical angle of 91 degrees. As described above, each engine 210, 310 can have a different injection force in addition to the difference in injection angle.

[0021] The reason why the engines 210, 310 are provided near the center of the left and right wings 200, 300 is that the center of gravity is concentrated at the center of the aircraft compared to the attachment positions of the wings at the ends, making it easier to balance the up and down movement of the left and right wings. Note that the engines 210, 310 are not limited to jet engines, and may be, for example, propeller engines.

[0022] 2, flaps 220, 320 are disposed immediately aft of the engines 210, 310 disposed on the left and right wings 200, 300. By disposing the flaps 220, 320 immediately aft in this manner, the jet of air from each engine 210, 310 hits the flaps 220, 320, allowing the flaps 220, 320 to act efficiently. That is, the jet of air from each engine is parallel to each wing, and each engine and each flap work together, so that each wing always maintains a state with the least wind resistance, and the jet of air flows to a location where each flap can most easily act.

[0023] The aircraft body 100 is not provided with a rudder because the rudder function can be achieved by operating the control stick 150 and by changing the angle of each engine 210, 310.

[0024] Additionally, an accelerator lever is provided on this control stick 150, and controls the angles of the left wing 300 and right wing 200 and the output and angle of each engine 210, 310. The control stick 150 also has an information display screen (not shown) that displays various information. By operating the control stick 150, the flat surfaces of the left wing 300 and right wing 200 move, which in turn controls the traveling speed of the aircraft 100, and by adjusting the output of each engine 210, 310, which operates independently, the left and right thrust is adjusted, allowing for left and right directional control, directional control such as turning, automatic return control, and straight-line flight even in crosswinds.

[0025] In addition, although not shown, the electronic equipment storage section 130 stores a gyro sensor, an altimeter, a speedometer, a wind vane, a fuel level gauge, a GPS sensor, an emergency signal transmitter, an automatic hovering device in an emergency, an emergency takeoff point return indicator, an automatic return device, a static electricity air dissipation device, an emergency remote control device, a nearby object detection device, and / or a high-voltage power line detection sensor.

[0026] It is desirable that the wing area of ​​each of the left wing 300 and right wing 200 attached to the fuselage body 100 be 9000 cm 3 or more, assuming a pilot weighing 70 kg.

[0027] Furthermore, it is desirable that the power supply (lithium battery) stored in the power supply storage section 135 has an output of 5 kWh or more.

[0028] Furthermore, it is desirable that each engine installed on the machine body 100 be a two-stroke engine with an output of 10 horsepower or more.

[0029] Furthermore, it is desirable that the materials used for the frame, wings, etc. of the fuselage main body 100 be processed carbon fiber, titanium, aluminum, or the like.

[0030] When the aircraft main body 100 configured as described above is attached to a human body in an upright position, vertical takeoff and landing occurs with the flat surfaces of the left wing 300 and right wing 200 in a vertical position, and the aircraft transitions to horizontal flight by gradually tilting the vertical flat surfaces forward within a 75-degree range. By adjusting the angle of the wing, it is possible to perform operations such as hovering and cruising flight with a single control stick 150. In this way, the aircraft with wings is fixed to the human body, and jet engines are attached to the left and right wings. Using these engines as driving force, the aircraft can take off and land under its own power from the ground, and the angle of the left and right wings can be changed to increase or decrease thrust.

[0031] <Summary> 1. According to the present invention, the plane of the wings can move from horizontal to vertical in the range of 91 to 75 degrees, thereby significantly improving horizontal flight speed and enabling safe takeoff and landing even in high wind speeds. The provision of wings provides buoyancy, allowing for a safer descent at a slower speed than a crash, and the use of a jet engine provides high speed, wind stability, and gravity resistance.

[0032] 2. According to this invention, the flying vehicle is secured to the body with a belt, and there is a sense of being fixed to the aircraft even during floating flight. During initial practice, the aircraft can float up to 30cm above the ground, and by moving the control stick slightly left and right, forward and backward, the aircraft also moves slightly. If the aircraft floats up to 30cm, there is no need to worry about serious accidents. Furthermore, by installing floats, it is possible to practice on water, and with the effect of mass production, it will become a means of transportation for people all over the world.

[0033] 3. Conventional aircraft have no wings and no rudders to easily and accurately achieve a flight attitude, but this invention has wide wings that can generate buoyancy, and by changing the angle of the wings with a control stick, it is possible to easily take off and land vertically, transition to horizontal flight, and change flight speed. [Explanation of symbols]

[0034] 100: Aircraft body 110: Housing 120: Headrest 130: Electronic equipment storage area 135: Power supply compartment 140: Body and body fixing belt 150: Control stick 200: Right wing 210: Right wing engine 220: Right wing flap 230: Right wing flap actuation motor 250: Right wing and fuselage connection and actuation motor 260: Right wing pivot gear 270: Right-side self-standing opening and closing leg actuation bar 280: Right side self-standing opening leg and attachment point to the aircraft body 290: Right side independent opening / closing leg 300: Left wing 310: Left wing engine 320: Left wing flap 330: Left wing flap actuation motor 350: Left wing and main body connection and actuation motor 360: Left wing pivot gear 370: Left-side self-standing opening and closing leg operating bar 380: Attachment between the left self-standing opening leg and the aircraft body 390: Left side independent opening / closing leg

Claims

1. A body-fixed flying vehicle having a body, left and right wings disposed on an upper portion of the body and tilting and pivoting independently or integrally in a vertical or horizontal direction, and attachment means for attaching the body to which the left and right wings are attached to a human body, The left and right wings are provided with a propulsion means at the center of each wing in the longitudinal direction, and a flap located immediately behind the propulsion means for controlling the ascent and descent of the fuselage body, an electronic equipment storage section for storing a control section that electronically controls the aircraft body, a power supply storage section for storing power supplies for electronic devices mounted on the aircraft body, and a fuel storage section for storing fuel for the propulsion means are disposed at an intermediate position between the left wing and the right wing; a control stick is provided for controlling the operation of the aircraft body during takeoff, flight, and / or landing; The control stick is equipped with an information display screen that controls the angle of the left and right wings, the output of the propulsion means, and displays various information.

2. A body-fixed vertical take-off and landing aircraft as described in Claim 1, characterized in that the aircraft body is provided with a device to prevent the aircraft body from falling over when it is leaned against something.

3. A body-fixed vertical take-off and landing aircraft as described in Claim 1, characterized in that the aircraft body is equipped with a shock reduction device that fixes the aircraft during take-off and landing and reduces shock during landing.

4. A body-fixed vertical take-off and landing aircraft as described in Claim 1, characterized in that the electronic equipment storage section stores a gyro sensor, an altimeter, a speedometer, a wind vane, a fuel level gauge, a GPS sensor, an emergency signal transmitter, an emergency automatic hovering device, an emergency take-off point return instruction device, an automatic return device, a static electricity air dissipation device, an emergency remote control device, a nearby object detection device and / or a high-voltage power line detection sensor.

5. A body-fixed vertical take-off and landing aircraft as described in claim 1, characterized in that the propulsion means is a jet engine or a propeller engine.

6. A body-fixed vertical take-off and landing aircraft as described in claim 1 or 4, characterized in that the propulsion means are capable of varying the jet angle and jet force of each propulsion means.

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