JPH04191195A - Flying object - Google Patents

Abstract

PURPOSE:To enable a cylindrical body which is suspended by a top cover to stable fly by disposing a propeller which allows air to flow from the suction port to the discharge port of the cylindrical body and a rudder. CONSTITUTION:After a square parachute 1 is stretched toward the discharge port 5 of a cylindrical body 2 and is held, when an engine 25 is started, contra- rotating propellers 6 are rotated in opposite directions, and air flows through the cylindrical body 2 from its suction port 4 to its discharge port 5, and the air stream flowing out from the discharge port 5 enters into the inside of the parachute through a plurality of air inflow ports 20 at the leading edge of the parachute 1 so that the parachute 1 is stretched in a wing-like shape. Then, the rotational speed of the engine 25 is gradually increased to increase the thrust force in association with the rotation of the propellers 6. Accordingly, the cylindrical body 2 takes off by a buoyancy of the parachute through the intermediary of wires 3. Cargo is also loaded in the inside of the cylindrical body 2. The engine 25 and the rudder 7 are remotely controlled by control servo mechanisms 26, 25. Accordingly, it enables the cylindrical body 2 to fly in a stabilized condition.

Description

DETAILED DESCRIPTION OF THE INVENTION Field of Industrial Application The present invention particularly relates to a flying vehicle that is most suitable for unmanned outdoor advertising, aerial photography, surveying for civil engineering works, spraying of chemicals, and the like.

Conventional technology Conventionally, the system consists of a sheet that impregnates the wind, a number of ropes attached to the periphery of the seat, and a suspension frame attached to the other end of the rope, and a power propulsion device and the seat are attached to the suspension frame. An integrally fixed flying parachute was developed in 1980-1984.
It has been proposed as Publication No. 400.

Problems to be Solved by the Invention However, the device described in Japanese Utility Model Application Publication No. 60-84400 cannot fly in a stable state because the mounting part and the power propulsion device are directly affected by the wind from the outside. difficult,
It was difficult to load luggage.

An object of the present invention is to solve the above-mentioned problems and to move the cylinder forward by the propulsion force of the propulsion device by circulating air from the suction port of the cylinder toward the discharge port, and to move the cylinder forward toward the canopy. Lift is generated as the cylinder moves forward, and the cylinder takes off while suspended by the lifting force of the canopy.The direction of rotation of the cylinder is adjusted by the rudder to fly the cylinder. In addition to being securely protected by the body, by loading cargo inside the cylinder, the cargo, propulsion unit, and rudder are not directly affected by air from outside, making it possible to fly the cylinder in a stable state. The objective is to provide a flying vehicle.

Means for Solving the Problems The flying object of the present invention has a cylindrical body suspended by a canopy, an inlet at one end of the cylindrical body, an outlet at the other end, and inside the cylindrical body: The structure is characterized in that a propulsion device and a rudder are respectively disposed for circulating air from the suction port toward the discharge port.

When the propulsion device installed inside the working cylinder circulates air from the suction port provided at one end of the cylinder toward the discharge port provided at the other end, a propulsive force is generated in the propulsion device, and the cylinder body moves forward due to the propulsion force of the propulsion aircraft, lift force is generated on the canopy as the cylinder moves forward, and the cylinder takes off with the cylinder suspended by the lift of the canopy.
A rudder placed inside the cylinder adjusts the direction of rotation of the cylinder.

Embodiments Hereinafter, embodiments of the present invention will be described in detail based on the drawings.

In FIG. 1, l is a square parachute serving as a canopy, and a cylindrical body consisting of a cylindrical body 2 is provided at the bottom of the square parachute 1 via a plurality of cables 3.
The fuselage 2 is suspended by a square parachute 1.

As shown in FIG. 2, one end 2a of the body 2 is provided with an air inlet 4 that is open, and the other end 2b of the body 2 is provided with an air suction port 4, as shown in FIG.
An air discharge port 5 is opened at the top of the fuselage 2, and near one end 2a inside the fuselage 2 there is a propulsion machine consisting of a contra-rotating propeller 6.6 that circulates air from the suction port 4 toward the discharge port 5. A rudder 7 is disposed inside the fuselage 2 near the other end 2b so as to be swingable in the vertical direction.

Inside the fuselage 2, a first annular frame 8 of the same shape is provided at intervals. Second annular frame9. Third annular frame 1
0. Fourth annular frame 11 and fifth annular frame 1
2 are respectively arranged, a cabin 13 is formed between the third annular frame 10 and the fourth annular frame 11 inside the fuselage 2, and the first annular frame 8. Second annular frame 9, third annular frame 10. The fourth annular frame 11 and the fifth annular frame 12 are sequentially arranged on the central axis of the body 2 from one end 2a to the other end 2b.

Also, the first annular frame 8. Second annular frame9.
Third annular frame 10. The upper parts of the fourth annular frame 11 and the fifth annular frame 12 are connected by a connecting rod 14 parallel to the central axis of the body 2, and the upper parts of the first annular frame 8. Second annular frame9. Third annular frame 1
0. Fourth annular frame 11 and fifth annular frame 1
The lower portions of the first annular frame 8.2 are connected by a connecting rod 15 parallel to the connecting rod 14. Second annular frame 9, third annular frame 10. Both sides of the fourth annular frame 11 and the fifth annular frame 12 are connected by two parallel connecting rods 16, 16.

Furthermore, a first annular frame 8. Second annular frame 9
．． Third annular frame 10. The inner peripheral surface of a cylindrical body is fixed to the outer peripheral surface of the fourth annular frame 11 and the fifth annular frame 12, and the first annular frame 8. Second annular frame9. Third annular frame 10. Fourth annular frame 1
The first and fifth annular frames 12 are covered by a cylindrical body to constitute the body 2.

As shown in FIG. 1, the square parachute 1 has a plurality of partition walls 1 spaced apart from each other at regular intervals in the width direction of each sheet between a rectangular upper sheet 17 and a lower sheet 18 that are long in the left and right directions.
A plurality of air inlets 20 opening toward the front are formed at the front edge of the square parachute 1, respectively, and a rear edge of the square parachute 1 is closed.

A plurality of protrusions 21 that protrude outward are provided on the outer peripheral surface of the fuselage 2, and a plurality of cables 3 are provided on the front and rear edges and both side edges of the lower sheet 18 of the square parachute 1.
The upper ends of the cables 3 are connected to each other, and the lower ends of the cables 3 are connected to the protrusion 21, respectively.

The square parachute 1 is made of various natural fiber sheets, synthetic fiber sheets such as nylon, synthetic resin films, synthetic rubber sheets, or other foldable flexible sheets.

On the front side of the second annular frame 9, as shown in FIG.
As shown in FIG. A see-through window 23a is provided in the fuel tank 2.
At the top of 3 there is a support arm 24. between the columns 22.22.
Two engines 25. act as prime movers via 24. 25
is installed.

Engine 25. On the top of 25 is an engine control servo mechanism 2 that controls the rotation speed of the engine 25.
A propeller shaft 27 of a propeller 6 is connected to the tip of the rotating shaft of the engine 25, and the propeller 6 is arranged between the first annular frame 8 and the second annular frame 9. . .

An axle 28 is provided below the fuel tank 23 so as to be rotatable in the horizontal direction, and front wheels 29 and 29 are provided at both ends of the axle 28, respectively.

The front connecting rod 14 of the third annular frame 10 and the connecting rod 1
A holding rod 30 is provided vertically between the connecting rods 16 and 16, and a holding rod 31 is provided horizontally intersecting the holding rod 30 between the connecting rods 16 and 16.

The rear connecting rod 14 of the fourth annular frame 11 and the connecting rod 1
A support rod 32 is provided in the vertical direction between the fourth annular frame 11 and the fifth annular frame 12, and a support rod 32 is provided between the connection rod 14 and the connection rod 15 near the middle of the fourth annular frame 11 and the fifth annular frame 12.
A support rod 33 parallel to the rudder 2 is provided, a receiver 34 is provided between the support rod 32 and the support rod 33, and the receiver 34 is provided with a rudder control servo mechanism 35 for controlling the direction of the rudder 7. It is being

The fuel tank 23 and the receiver 34 are respectively installed inside the fuselage 2 so as not to obstruct the flow of air from the suction port 4 to the discharge port 5 as the propeller 6.degree. 6 rotates.

A rudder 7 is arranged between the support rod 33 and the fifth annular frame 12, a movable holder 36 is provided at the lower part of the rudder 7, and the rudder 7 and the movable holder 36 are supported parallel to the support rod 33. They are each fixed to a shaft 37, and the support shaft 37 is connected to a servo mechanism 35 for rudder control.

The engine control servo mechanism 26 and the rudder control servo mechanism 35 are each remotely controlled via a receiver 34 by a remote control device (not shown) from the ground.

The upper end of an inclined support leg 38 is connected to the movable holder 36, and a rear wheel 39 is rotatably provided at the lower end of the support leg 38.

40 is a damper for damping vibrations of the fuselage 2 during landing.

Next, the operation of this embodiment will be explained.

First, after holding the square parachute 1 in an expanded state behind the exhaust port 5 of the fuselage 2, when the engine 25.25 is started, the contra-rotating propeller 6.6
．． 25 rotate in opposite directions, and air flows through the interior of the fuselage 2 through the suction port 4 due to the rotation of the propeller 6.
The air flow flows from the air outlet 5 toward the outlet 5 and flows out from the outlet 5 of the fuselage 2, and flows into the inside of the square parachute 1 through the plurality of air inlets 20 at the leading edge of the square parachute 1. It expands into a swollen wing shape.

Next, when the rotation speed of the engine 25.25 is gradually increased, the fuselage 2 moves forward while accelerating through the front wheels 29.29 and the rear wheels 39 due to the propulsive force generated by the rotation of the propeller 6.6, and the body 2 moves forward toward the square parachute 1. A lift force is generated, and the cable 3 is put under tension against the fuselage 2 by the square parachute 1, and the fuselage 2 is attached to the square parachute 1 via the cable 3.
The aircraft takes off due to the lift of the aircraft.

The cabin 13 inside the fuselage 2 also carries cargo.

Further, when the receiver 34 receives a control signal for controlling the rotation speed of the engine 25.25 from a remote control device on the ground, the engine control servo mechanism 2
6 is the engine 25.・Controls the rotation speed of 25,
By increasing the rotation speed of the engine 25.25, the propulsive force accompanying the rotation of the propeller 6.6 increases, the fuselage 2 rises together with the square parachute 1, and the engine 25.25
By lowering the rotation speed of the propeller 6.6, the propulsive force accompanying the rotation of the propeller 6.6 is weakened, and the fuselage 2
The parachute 1 moves the fuselage 2 upward and downward by a remote control device from the ground.

Further, when the receiver 34 receives a control signal for controlling the direction of the rudder 7 from a remote control device on the ground, the rudder control servo mechanism 35 rotates the support shaft 37, and the rudder 7 swings together with the support shaft 37. The direction of the rudder 7 is controlled by a rudder control servo mechanism 35, and the turning direction of the square parachute 1 of the fuselage 2 is remotely controlled by a remote control device from the ground.

Moreover, when the rudder control servo mechanism 35 rotates the support shaft 37 when the front wheels 29, 29 and the rear wheels 39 travel due to the propulsive force generated by the rotation of the propeller 6.6 of the fuselage 2, the movable holding body 36 supports the rudder control servo mechanism 35. It swings together with the rudder 7 via a shaft 37, the direction of the movable holding body 36 is controlled by a rudder control servo mechanism 35, and the direction in which the body 2 travels is controlled by rear wheels 39.

Also, when the operation of the engine 25.25 is stopped by a remote control device from the ground, the engine 25 of the propeller 6.6
．． The propulsive force accompanying the rotation by 25 disappears, the lift of square parachute 1 disappears, and square parachute 1
The fuselage 2 is exposed to air resistance when falling due to the gravity of the fuselage 2 and each device installed inside the fuselage 2, and the fuselage 2
The body 2 slowly descends together with the square parachute 1 while being suspended from the lower part of the body, and the fuselage 2 lands via the front wheels 29, 29 and the rear wheels 39. ``After the fuselage 2 is landed with the square parachute 1, the cables 3 are removed from the protrusion 21 of the fuselage 2, and the square parachute 1 is folded and stored.

Note that the protruding body 21, which is the attachment part of the cable 3 of the square parachute 1, is not provided separately in the axial direction of the fuselage 2;
It may be provided at a position above the center of gravity on the intersection line of the vertical plane containing the center of gravity of the fuselage 2 and the center of gravity of the fuselage 2, and a part of the cable 3 is pulled by remote control from the ground for controlling the turning direction. If a servo mechanism is provided, it is also possible to control the turning direction of the fuselage 2 by the square parachute 1 using the servo mechanism for controlling the turning direction, and it is also possible to use an electric motor as the prime mover for driving the propulsion machine. A single propeller may be used for the propulsion device.

Effects of the Invention As described above, according to the flying object of the present invention, the propulsion device circulates air from the suction port of the cylinder toward the discharge port, so that the cylinder can be moved forward by the propulsive force of the propulsion device. The canopy generates lift as the cylinder moves forward, allowing the cylinder to take off while suspended by the lifting force of the canopy.The direction of rotation of the cylinder can be adjusted using the rudder to move the cylinder forward. The propeller and rudder are reliably protected by the cylinder, and cargo can be loaded inside the cylinder, and the cargo, propulsion unit, and rudder are not directly affected by air from outside. You can fly with your body in a stable state.

Additionally, displaying advertisements or the like on the outer circumferential surface of the barrel can attract pedestrians' interest, and if the barrel is equipped with a photographing device, a surveying device, or a chemical spraying device, it can be used for photographing. Aerial photography using the device, aerial surveying of civil engineering work using a surveying device, and aerial spraying of chemicals using a chemical spraying device can be performed.

[Brief explanation of the drawing]

FIG. 1 is a front view of an aircraft according to an embodiment of the present invention, FIG. 2 is a side view of FIG. 1, FIG. 3 is a front view of main parts of FIG. 1, and FIG. FIG. 1... Square parachute, 2... Body, 2a.
...One end, 2b...Other end, 3...Cable, 4...Suction port, 5...Exhaust port, 6...Propeller, 7...Rudder, 8...First annular frame, 9... second annular frame, 10... third annular frame, 11...
- Fourth annular frame, 12... Fifth annular frame, 13... Cabin, 14... Connection rod, 15...
Connecting rod, 16... Connecting rod, 17... Upper sheet, 1
8... Lower sheet, 19... Partition wall, 20... Air inlet, 21... Projection, 22... Support column, 23...
- Fuel tank, 23a... See-through window, 24... Support arm, 25... Engine, 26... Servo mechanism for engine control, 27... Propeller shaft, 2
8... Axle, 29... Front wheel, 30... Holding rod, 3
DESCRIPTION OF SYMBOLS 1... Holding rod, 32... Supporting rod, 33... Supporting rod, 34... Receiver, 35... Servo mechanism for rudder control, 36... Movable holding body, 37... Support shaft, 38... Support leg, 39... Rear wheel, 40...
・Damper.

Claims (1)

[Claims] A cylindrical body is suspended by a canopy, an inlet is provided at one end of the cylindrical body, and an outlet is provided at the other end, and air is circulated through the interior of the cylindrical body from the inlet to the outlet. A flying object characterized by being equipped with a plane and a rudder.