KR20070059748A - Vertical landing equipment for radio control multi-aid aircraft and a method thereof - Google Patents

Abstract

A vertical landing apparatus for a radio control multipurpose aircraft and a landing method using the same are provided to safely land the aircraft at a goal spot without damaging the aircraft. A radio control multipurpose aircraft includes a body section(100), wing sections(200), and a landing unit(300). The landing unit includes a parachute. The parachute and the body section are connected to each other by including at least one pair of highly flexible guide cords and at least one pair of non-flexible guide cords. The highly flexible guide cord includes a first guide cord and a second guide cord. The first and second guide cords are connected to an engine cover and a front main blade connecting rod. The non-flexible guide cord is connected to a rear main blade connecting rod.

Description

Vertical Landing Equipment for Radio Control Multi-aid Aircraft and a Method

1 to 8 are views showing the configuration of a radio-controlled multi-purpose aircraft according to the present invention,

1 and 2 are full perspective views.

3 shows a landing gear;

4 is a full side cross-sectional view.

5 and 6 are views showing the landing device is fixed to the body.

7 shows the principle of operation of the landing gear;

8 is a view showing a parachute connected by operating the landing device.

9 to 14 are views sequentially showing the landing operation of the radio-controlled multi-purpose aircraft according to the present invention.

<Description of the symbols for the main parts of the drawings>

100: body 110: fuselage

120: engine cover 130: propeller

140: arrow keys 200: wings

210: main wing 220: secondary wing

230: auxiliary wing linkage 240, 250: main wing connecting rod

300: landing gear 310: cover

320: servomotor 321: rotary blade

330: parachute 331: parachute rope

340: cover groove 350: fuselage groove

360: elastic means 370: projection

380: connection ring 400: connection cord

410: first guide code 420: second guide code

430: third guide code 440: connection code ring

The present invention relates to a landing apparatus for a radio-controlled multipurpose aircraft applied to a wire twisting method in a cable construction work such as a transmission line, a bridge, or a cable car, and more particularly, by vertically descending in the air regardless of the ground conditions of the landing point. The present invention relates to a vertical landing device for a radio-controlled multipurpose aircraft that safely lands at a target point without damage.

In general, in order to wire the power line of the transmission line work, a messenger wire is first connected to a twisted pair section scheduled as a preliminary work, and the work is performed by pulling the power line using the connected wire.

First, in order to connect the wires, by using manpower to stretch the wires with the maneuvering position between the steel towers and the steel towers, connect the wires, and then pull them up to the top of the steel towers using a puller, and use a helicopter. By using a rope (rope) in the air above the tower and the tower or twisted wire method is used to connect the wire directly.

However, due to the fact that most of the progress of the transmission line construction is located in mountainous areas with dense trees, the manned twisted pair construction method inevitably entails massive logging and environmental damage in order to float the twisted wires into the air, avoiding obstacles on the ground surface. The twisted pair method is used.

However, the twisted pair method using a helicopter requires the installation of a main station for takeoff and landing of the helicopter, the movement of auxiliary equipment such as an oil tanker according to the operation of the helicopter, and the construction cost since it must move from the mooring area of the helicopter to the site of the site. This is a cause of the rise, and the noise caused by the operation of the helicopter and the wind generated by the propeller is concerned about civil complaints at the construction site.

In addition, there is a risk of the helicopter falling when the wire or rope is suspended and the operation is limited due to the weather conditions, and the operation is restricted. In the case of the helicopter, the operation is restricted in the no-fly zone, which reduces work efficiency and interferes with the construction. Will result.

In order to solve the above problems, the present applicant considers the work requirements of the construction site of the steel tower in Patent Application No. 10-2003-0060003, a radio-controlled multi-purpose aircraft (fixed wing aircraft) applied to the twisted pair construction method that can take off and land in a narrow space ).

As the above-mentioned radio-controlled multi-purpose aircraft requires a separate ground space for takeoff and landing, its utilization is lower than that of a helicopter.

In order to solve this problem, take off in a narrow space by using a small oscillator suitable for the aircraft to take off, and for landing, by installing a net at the landing point to crash the plane in the net to land or aircraft The rescue parachute is mounted in the air and the parachute is opened and landed in the air.

However, since the landing method of impinging on the net is sensitive to unexpected weather conditions such as a gust, it is difficult to precisely set a target point, and thus the risk of damage is high when the aircraft is incorrectly introduced into the net, and even when the entry into the net is correct. There is a risk of damage to the aircraft, there is a problem in that the installation is complicated and additional costs because it requires the associated devices according to the net installation.

In addition, the method of mounting the parachute is because the parachute unfolds during the descent, the descent speed of the aircraft is rapidly reduced, the energy generated at this time is not absorbed and transferred to the aircraft, the aircraft is not landing stably and turned over or parachute and There is a problem that damage to the aircraft occurs while the posture such as tangling with the rope is not maintained.

The present invention is to solve the above-mentioned conventional problems, the parachute is mounted as a landing device of the aircraft, when the landing to maintain a stable position until the landing by configuring a shock absorber to absorb the energy generated during the parachute itself It is intended to prevent damage to the aircraft which may occur.

In order to achieve the above object, the vertical landing device of the radio-controlled multi-purpose aircraft according to the present invention includes a body portion, a wing portion, and a landing device in the radio-controlled aircraft, the landing device comprises a parachute, One or more pairs of highly elastic guide cords are provided, and one or more pairs of non-elastic guide cords are provided to connect the parachute and the body part.

In addition, the high elastic guide cord is made of a first guide cord and a second guide cord, each of which is connected to the engine cover and the front main rotor connecting rod, the non-elastic guide cord is characterized in that it is connected to the rear main rotor connecting rod. .

In addition, the landing device is a cover detachably configured on the upper surface of the body portion, a fixing portion for mounting and fixing the cover to the body portion, a servo motor acting to act on the fixing portion to separate the cover from the body portion, and It includes a parachute that is accommodated in the inside of the cover, wherein the fixing portion is fixed to the rotating blade of the servo motor is inserted into the groove formed in the front portion of the cover, the protrusion formed on the back of the cover has a structure that serves as a hinge When the cover is separated from the body portion, the lower portion of the cover is characterized in that the elastic means for pushing the cover to the outside of the body portion is provided.

In addition, in the landing method of a radio-controlled multipurpose aircraft according to the present invention, a landing method of a radio-controlled aircraft performing a landing operation using a parachute stored therein, wherein a cover in which a parachute is embedded by radio remote control is installed from a body part. Separated and injected into the rear of the aircraft, the inherent parachute is released, the air pressure is filled inside the parachute, the high-strength rope connecting the parachute and the body is expanded to the maximum, the descending speed of the aircraft sharply reduced, the change in the descending speed It characterized in that it comprises a step of transferring the impact amount generated by the parachute.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

First, the radio-controlled multi-purpose aircraft according to the embodiment of the present invention includes a configuration of a general fixed wing.

1 to 8 is a view showing the configuration of a radio-controlled multi-purpose aircraft according to the present invention, Figures 1 and 2 are an overall perspective view, Figure 3 is a view showing a landing device, Figure 4 is a full side cross-sectional view, 5 and 6 are views showing the landing device fixed to the body, Figure 7 is a view showing the operating principle of the landing device, Figure 8 is a view showing the landing device is connected to the parachute connected.

As shown in Figures 1 and 2, the device wireless adjustment multi-purpose aircraft is coupled to the wing portion 200 on both sides of the body portion 100, the radio remote control of the operator on the upper surface of the body portion 100 Landing device 300 is operated by the configuration.

Body portion 100 is located in the center portion of the fuselage 110, which is coupled to each part of the aircraft and mounted equipment, propeller 130 and is configured on the front of the fuselage 110 and rotated by the engine device, the fuselage Engine cover 120 located at the front of the 110, the rear portion of the fuselage 110 to generate a lift in the direction of the wind in contact with the key surface side sliding or turning movement of the aircraft, or to stop it It comprises a direction key 140 to. In addition, the body part 100 receives and receives an engine device for generating power for operating an aircraft therein, a fuel tank, a battery for supplying necessary power in the aircraft, and a remote control signal transmitted from an operator's wireless remote controller. And a direction key control device for controlling the direction key 140 according to the control of the remote signal reception control unit, and performing a control operation for controlling the aircraft operation and a pilot line drop according to the received signal. The rear of the body portion 100, the line drop device for dropping the pilot line is configured.

The wing unit 200 is attached to the main wing 210, which extends from side to side in the center of the body 110, and the auxiliary wing 220 mainly used when turning left or right outside the rear edge of the main wing 210, the inside The position of the main wing 210 is fixedly supported on both sides of the auxiliary wing linking unit 230 and the body 110 to operate the auxiliary wing 220 in conjunction with a remote signal reception control unit to adjust an angle with the main wing 210. One pair of main wing connecting rods (240, 250) and the like is configured.

Landing device 300 is configured on the upper surface of the body portion 100 and removable from the body portion 100, 310, the fixing portion for mounting and fixing the cover 310 to the body portion 100, It acts to separate the cover 310 from the body portion 100 by acting on the fixed portion and is connected to the servo motor 320 and the body portion 100 and the cover 310 configured inside the body portion 100, the cover It is configured to include a parachute 330 made of a state accommodated inside the (310).

As shown in Figure 3, the cover groove 340 is formed in the front portion of the cover 310, the rotary blade 321 of the servomotor 320 is inserted into the cover groove 340 is fixed It consists of a structure, the lower portion of the cover 310 is provided with an elastic means 360 made of a bungee cord, etc., the elastic means 360 is pressed by the coupling structure of the rotary blade 321 and the cover groove 340 Is fixed.

That is, as shown in FIGS. 4 and 5, the elastic means 360 made of a bungee cord or the like has both left and right ends fixed to the inside of the body portion 100, and the cover 310 is fixedly mounted in FIG. Since the elastic means 360 is pressed as shown, it becomes a structure that can be separated at any time if only the fixing means is removed.

The elastic means 360 may be applied to any material having elasticity such as a spring, a rubber band as well as a bungee cord, and is installed on the body part 100 so that the cover 310 can be easily separated for a landing operation.

As shown in FIG. 7, the fixed landing device 300 is rotated by the remote control of the rotary blade 321 of the servomotor 320, the cover 310 including the parachute 330 is the body portion Landing device 300 is operated while leaving from (100). Here, the projection 310 is formed on the rear of the cover 310 to serve as a hinge, the cover 310 is configured to be separated while rotating around the hinge structure, the inner parachute 330 is connected The connecting ring 380 is provided. In addition, the cover 310 is made of a lightweight FRP (Fiber-glass Reinforced Plastic) product, the parachute 330 accommodated when the departure from the body portion 100 to perform the landing operation easily fall out More preferably, approximately 1/3 of the bottom surface is blocked and 2/3 is open so that it can be released.

The servo motor 320 is interlocked with the remote signal reception control unit inside the body part 100, and when the remote signal reception control unit receives a landing signal from the wireless remote controller, the rotary blade 321 of the servo motor 320 is 90 degrees. By rotating the cover 310 is separated from the body portion 100 to perform a landing operation. In this case, the rotary blade 321 may be configured to enable a repetitive rotation of 90 °, or may be designed to enable 180 ° or 360 ° rotation, as in the embodiment of the present invention. In addition, when the servo motor 320 is accommodated in the fuselage 110, the fuselage groove 350 is configured at the action portion of the servo motor 320 so that the rotary blade 321 may rotate.

When the landing device configured as described above operates to separate the parachute stored therein, the parachute is connected to a plurality of guide cords toward the aircraft. The guide cord consists of a pair of left and right connecting the parachute 330 and the body portion 100, and is provided with one or more high elastic guide cords and non-elastic guide cords, respectively, as shown in FIG. It is preferred to be configured.

As such, when the guide code is composed of three pieces such as the first guide code 410, the second guide code 420, and the third guide code 430, the first guide code 410 is sequentially formed from the front of the aircraft. The second guide cord 420 is coupled to the front main rotor connecting rod 240, and the third guide cord 430 is coupled to the rear main rotor connecting rod 250. In addition, the upper side of the first guide cord 410, the second guide cord 420, and the third guide cord 430 is composed of a connection cord 400, the connection cord 400 is a connection cord ring 440 is connected to the parachute rope 331 of the parachute 330. Here, the first guide cord 410 and the second guide cord 420 is made of a high-stretch guide cord having excellent elasticity, it is generally preferably made of a 500% elongated bungee cord. In addition, the third guide cord 430 is made of a non-stretch guide cord relatively inelastic compared to the high-stretch guide cord, it is preferably made of nylon rope.

A landing operation for guaranteeing a safe landing and preventing damage to the aircraft in preparation for an emergency situation such as a crash of the aircraft configured as described above will be described in more detail with reference to FIGS. 9 to 14.

First, the operator executes the line drop device using the wireless remote controller to perform the line work, and then adjusts the flight posture to the vertically lowered position by reducing the speed of the aircraft above the expected landing point by wireless adjustment and then servomotor. When the operation 320 is performed, as shown in FIG. 9, the cover 310 is separated from the body portion 100. Therefore, the rotary blade 321 of the servomotor 320 fixing the cover 310 of the landing device 300 is released from the cover groove 340 configured in the front of the cover 310, and thus the cover 310 ) Becomes a free state and becomes a state that can be separated from the body portion 100. That is, when the rotor blade 321 exits from the cover groove 340 in a state in which the parachute 330 is embedded in the cover 310, the cover 310 is formed by the elastic means 360 under the cover 310. Is bounced upwards slightly protruded upwards, while the cover 310 is flipped while the rear protrusion 370 serves as a hinge completely separated from the body portion 100.

Subsequently, as shown in FIG. 10 while hitting the cover 310 protruding from the front of the aircraft, the cover 310 is pushed by the wind and propeller 130 wind due to the vertical descent and injected into the rear of the airplane, thereby From the first guide cord 410, the second guide cord 420, the third guide cord 430 is sequentially tensioned while the parachute 330 is released from the cover (310).

Thus, the parachute 330 is connected to the three guide cords as above towards the aircraft. That is, the first guide cord 410 and the second guide cord 420, which are made of high elastic guide cords sequentially from the front of the aircraft, are attached to the engine cover 110 and the front main connecting rod 240, and are made of non-stretchable ropes. Guide cord 430 is coupled to the rear main blade connecting rod (250).

In addition, the cover 310, which is separated by the parachute 330, is connected to one side of the parachute 330 through a connection ring 380 provided therein, and the following landing operation is performed.

As shown in FIG. 11, the parachute 330 escaping from the cover 310 by the tension of the first guide cord 410 is expanded by the wind and the air pressure is filled into the parachute 330 as described above. Highly flexible guides constituting the first guide cord 410 and the second guide cord 420 while being tensioned in order of the first guide cord 410, the second guide cord 420, and the third guide cord 430. The code is extended to the maximum. Therefore, the descending energy of the aircraft is sequentially absorbed by the parachute 330 through the first guide cord 410, the second guide cord 420, and the third guide cord 430, so that the descending speed is drastically reduced.

As the impact amount caused by the change in the descending speed of the aircraft is completely transferred to the parachute 330 through the third guide code 430, as shown in FIG. As the descent of the aircraft stops, the nose of the aircraft is heard, and the flight posture changes to an upward attitude.

Next, the aircraft, which temporarily stopped descending, is performed again because of its weight. At this time, as shown in Figure 13, the parachute 330 is normally located on the upper portion of the aircraft, while the air pressure acting on the parachute bears the weight of the aircraft sufficiently, the aircraft gradually descends to the landing point.

As shown in FIG. 14, the aircraft which has continuously performed the lowering movement lands without impact at the landing point, and the air pressure of the parachute 330 is naturally dissipated while the landing operation is performed, thereby expanding the parachute on the rear of the aircraft. This completes the landing operation without damaging the aircraft.

This landing motion does not require a separate large space for landing and absorbs the descending speed of the aircraft as a parachute using the stretch force of the bungee cord, so the attitude of the aircraft is maintained during the descent movement, which can occur during landing. Damage is prevented.

The present invention is not limited to the above-described embodiments, and technical ideas that can be modified and converted by those skilled in the art to which the present invention pertains without departing from the gist of the present invention also belong to the following claims. Should be seen.

According to the present invention of the above configuration, since the present invention is equipped with a parachute as a landing device of the aircraft does not require a separate large space for landing, the installation of the landing equipment is not complicated and can reduce the cost.

In addition, by constructing a bungee cord with a stretchable guide code connected to the parachute to absorb the falling energy from the parachute, the aircraft maintains a stable attitude until the moment of landing to prevent safety accidents and damage that may occur during landing. .

Claims (4)

In a radio-controlled aircraft comprising a body, a wing, and a landing device, The landing device comprises a parachute, One or more pairs of high elastic guide cords, a pair of non-elastic guide cords are provided with one or more vertical landing apparatus of the multi-purpose aircraft, characterized in that connecting the parachute and the body portion. The method of claim 1, The high elastic guide cord is composed of a first guide cord and a second guide cord, each of which is connected to the engine cover and the front main connecting rod, The non-stretchable guide cord is a vertical landing device for a radio-controlled multi-purpose aircraft, characterized in that connected to the rear main connecting rod. The method of claim 1, The landing device is a cover detachably configured on the upper surface of the body portion, Fixing part for fixing the cover to the body portion, A servo motor acting on the fixing part to separate the cover from the body part, and It is made to include a parachute that is accommodated inside the cover, The fixed part is a rotary blade of the servomotor is fixed to the groove formed in the front portion of the cover, the protrusion formed on the rear of the cover is made of a structure that serves as a hinge, And a lower portion of the cover is provided with elastic means for pushing the cover to the outside of the body portion when the cover is separated from the body portion. In the landing method of a radio-controlled aircraft performing a landing operation using a parachute stored therein, (a) a step in which the parachute embedded with the parachute is separated from the body part by the radio remote control and is ejected to the rear of the aircraft to escape the internal parachute; (b) the high elastic guide cord connecting the parachute and the body part to the maximum as the air pressure is filled into the parachute, and the descending speed of the aircraft sharply decreases, (c) Landing method of the radio-controlled multi-purpose aircraft characterized in that it comprises the step of transferring the impact amount caused by the change in the falling speed to the parachute.

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