KR20030009884A - Landing gear door open and close device of aircraft - Google Patents

Abstract

PURPOSE: A device for opening and closing a landing gear door of an airplane is provided to reduce the drag by opening and closing a landing gear door the sliding, to reduce the weight of an airplane by decreasing the structural strength, and to easily remove the support structure of the landing gear door when the opening and closing of the landing gear door are impossible. CONSTITUTION: Driving guide units(10,12) are installed at both inner sides of an airplane body(100). A drive actuator(20) is mounted in one driving guide unit. A ball screw(30) operated by the actuator is installed between the driving guide units. First and second linear motion guides(40,42) are installed at the upper and lower portions of the ball screw. A ball bushing for changing the rotational motion of the ball screw to the linear motion is installed in the ball screw. A first actuator(60) is supported on a first fixing bracket(50). A second fixing bracket(70) is fixed on the upper end of the other driving guide unit. A second actuator(80) is mounted at the lower portion of the second fixing bracket.

Description

LANDING GEAR DOOR OPEN AND CLOSE DEVICE OF AIRCRAFT}

The present invention relates to a landing gear door opening and closing device of an aircraft, and more particularly, to a landing gear door mounted on an aircraft, when the landing gear door is opened so that the area which hinders the flow of air in the direction of the aircraft is minimized. It will be opened and closed by sliding along the way.

In general, the landing gear door mounted on the body of the aircraft is a door that opens and closes to access the landing device through the landing gear door during landing and takeoff of the aircraft, and a device for opening and closing a conventional landing gear door is illustrated in FIGS. As shown in Fig. 2, the pair of landing gear doors 1 opposed to the body are supported by the door hinges 2 and 3 so as to be rotatable and installed to be opened and closed, and one end of the landing gear door 1 is provided. An actuator 4 is installed in the opening and closing operation of the landing gear door 1, and the landing gear door 1 is hinged by the operation of the actuator 4 to the dotted line of FIG. And as shown by a solid line.

However, such a conventional landing gear door opening and closing device is opened by revealing a large area in the direction of the aircraft when the landing gear door 1 is opened, thus increasing the drag force during takeoff and thus requiring a large distance for takeoff. As the fuel consumption increases and air resistance is increased, many problems such as increase of the weight of the fuselage are required due to the large structural strength required for the door hinge 2 and the fuselage mounting portion. there was.

Accordingly, the present invention is to solve the above-mentioned problems, the landing gear door mounted on the aircraft moves along the surface of the aircraft when the landing gear door is opened so that the area that hinders the flow of air in the direction of the aircraft is minimized It provides a landing gear door opening and closing device of the aircraft that can reduce the weight of the aircraft by forming a base for designing low structural strength as well as reducing drag generated during takeoff by opening and closing in a sliding manner. Its purpose is to.

Another object of the present invention is to provide a landing gear door opening and closing device of an aircraft that can easily remove the support structure of the landing gear door by explosives when the opening and closing operation of the landing gear door becomes impossible.

1 is a perspective view showing a conventional landing gear door opening and closing device

Figure 2 is a side view showing a state when the landing gear door of Figure 1 opening and closing

3 is an overall perspective view showing the present invention

Figure 4 is a longitudinal cross-sectional view showing a drive guide portion according to the present invention;

5a to 5c are schematic longitudinal cross-sectional views sequentially showing the operating relationship when the landing gear door is opened in the closed state according to the present invention;

6 is a perspective view of a first actuator according to the present invention;

7 is a perspective view of a second actuator according to the present invention;

8 is a longitudinal cross-sectional view of the main part of FIG.

Explanation of symbols on the main parts of the drawings

10,12; A driving guide part 20; Drive actuator

30; Ball screw 40; 1st linear motion guide

42; Second linear motion guide 44; Ball bushing

50; First fixing bracket 52; 1st support piece

54; Second support piece 56; Third support

60; First actuator 62,82; piston

64; Fixing piece 70; 2nd fixing bracket

80; Second actuator 84; shaft

86; Guiding roller 100; fuselage

200; Landing gear door 210; Fixing member

220; Guide member 222; Guide

In order to achieve the above object, the present invention is a drive guide unit is fixedly installed on both sides of the inside of the fuselage, a drive actuator mounted inside the drive guide portion of the one side to operate when opening and closing the landing gear door, and the drive guide A ball screw which is installed between the parts and rotates by the operation of the drive actuator, the first and second linear motion guides installed on the upper and lower parts of the ball screw between the driving guide part to serve as guide rails, and the first and second parts. A first actuator supported and mounted on a first fixed bracket mounted on one end of the linear motion guide and a ball bushing mounted on the ball screw, and supported and mounted on a lower portion of the second fixed bracket fixed to an upper end of the other driving guide part. And a second actuator, which is mounted to the fuselage and is slid by driving and operation of the first and second actuators. There is provided a landing gear door opening and closing device for an aircraft, characterized in that the landing gear door is opened and closed.

In addition, a second support piece formed at the rear center of the first fixing bracket is fixed to the ball bushing by a clamp, and the first support piece formed at the rear upper end of the first fixing bracket is supported at the top of the first linear motion guide. The third support piece formed on the rear lower end of the first fixing bracket is supported and installed to surround the lower end of the second linear motion guide.

In addition, a fixing piece is installed at a lower end of the piston of the first actuator, and the fixing piece is installed to surround the inside of the fixing member fixed to the landing gear door in the lower portion.

In addition, a guide roller is rotatably installed at both ends of the piston lower end of the second actuator, and the guide roller is fixed to a landing gear door in which the guide roller is in surface contact with the horizontal movement of the second actuator. It characterized in that the guide hole for guiding is installed to wrap inside the guide member formed in the top center.

Hereinafter, with reference to the accompanying drawings, preferred embodiments of the present invention for achieving the above object will be described in detail.

Figure 3 is an overall perspective view showing the present invention, Figure 4 is a longitudinal sectional view showing a drive guide according to the present invention, Figures 5a to 5c is an operating relationship when the landing gear door is opened in a closed state according to the present invention Figure 6 is a schematic longitudinal cross-sectional view showing sequentially, Figure 6 is a perspective view showing a first actuator according to the present invention, Figure 7 is a perspective view showing a second actuator according to the present invention, Figure 8 is a principal longitudinal cross-sectional view of FIG.

According to the present invention, the driving guides 10 and 12 are fixed to both sides of the fuselage 100 of the aircraft, respectively, and the hydraulic pressure when the landing gear door 200 is opened and closed within the driving guide 10 of the one side. , The drive actuator 20 is operated by any one of the power supply of pneumatic or electricity is mounted, and the drive actuator 20 is connected to the drive actuator 20 between the drive guide unit 10, 12 The ball screw 30 is rotated by the operation of the ball screw 30, the first and second linear motion guides 40 which serve as guide rails on the upper and lower portions of the ball screw 30 between the driving guide portion 10 (12). 42 is installed, the ball screw 30 is provided with a ball bushing 44 for converting the rotational movement of the ball screw 30 to a linear movement.

In addition, a first actuator 60 supported by the first fixing bracket 50 is provided at one end of the first and second linear motion guides 40 and 42 and the ball bushing 44 installed at the ball screw 30, respectively. In this case, the second support piece 54 formed at the rear center of the first fixing bracket 50 is fixed to the ball bushing 44 by a clamp 58 or the like, and the first fixing bracket 50 The first support piece 52 formed at the rear upper end of the) is supported at the upper end of the first linear motion guide 40, and the third support piece 56 formed at the rear lower end of the first fixing bracket 50 is It is supported and installed to surround the lower end of the second linear motion guide 42.

In addition, a fixing piece 64 is installed at a lower end of the piston 62 of the first actuator 60, and the fixing piece 64 of the fixing member 210 fixed to the lower landing gear door 200. It is installed to wrap inside.

In addition, a second fixing bracket 70 is fixed to the upper end of the driving guide part 12 on the other side, and a second actuator 80 is mounted to the lower portion of the second fixing bracket 70, and the second actuator is mounted. A guide roller 86 is rotatably installed at both ends of the piston 82 at the lower end of the piston 82 so that the guide roller 86 is in surface contact with the guide roller 86. A guide long hole 222 fixed to the landing gear door 200 to guide the horizontal movement of the second actuator 80 is installed to surround the inside of the guide member 220 formed at the top center thereof.

3 to 8, the present invention configured as described above, when the landing gear door 200 mounted on the fuselage 100 of the aircraft to open in a closed state landing gear door as shown in Figure 5a One end of the first and second linear motion guides 40 and 42 and the ball screw between the driving guide parts 10 and 12 fixedly installed on both sides of the fuselage 100 in the closed state 200. As the first actuator 60 supported and mounted by the first fixing bracket 50 to the ball bushing 44 installed at 30, respectively, operates, the piston 62 of the first actuator 60 is lowered. And a fixing piece 64 installed at a lower end of the piston 62 to surround the inside of the fixing member 210 fixed to the landing gear door 200 at a lower portion of the piston 62. Boosted.

At the same time, the piston 82 of the second actuator 80 as the second actuator 80 mounted on the lower portion of the second fixing bracket 70 fixed to the upper end of the other driving guide portion 12 operates. Simultaneously with this lowering, the lower end of the piston 82 is supported by the shaft 84 and rotatably installed at both ends thereof, so as to surround the inside of the guide member 220 fixed to the landing gear door 200. The installed guide roller 86 pushes the landing gear door 200 downward.

That is, since the first and second actuators 60 and 80 operate simultaneously to push the landing gear door 200 downward, the landing gear door 200 is spaced apart from the fuselage 100 as shown in FIG. 5B. Will be maintained.

At the same time, the driving actuator 20 mounted inside the driving guide part 10 of one side of the driving guide parts 10 and 12 fixedly installed on both sides of the fuselage 100 in the state shown in FIG. As the ball is driven, the ball screw 30 connected to the drive actuator 20 and installed between the drive guides 10 and 12 performs a rotational movement, and is installed at one end of the ball screw 30. The ball bushing 44 for converting the rotational motion of the 30 into a linear motion is horizontally moved along the outer circumferential surface of the ball screw 30 in the right direction on the drawing, and at the same time, the ball bushing 44 is 2 The first actuator 60 supported by the first fixing bracket 50 on which the support piece 54 is fixed by the clamp 58 or the like moves together in the right direction on the drawing.

At the same time, the fixing piece 64 installed on the lower end of the piston 62 of the first actuator 60 is installed to surround the inside of the fixing member 210 fixed to the landing gear door 200 at the lower side. The landing gear door 200 is moved in the right direction.

At the same time, the guide roller 36 supported by the shaft 84 at the lower end of the piston 82 of the second actuator 80 is linked with the movement in the right direction of the landing gear door 200. Since the guide roller 36 rotates while the guide roller 36 rotates in the state of being in contact with the bottom surface, the landing gear door 200 is completely moved to the right direction. As shown in FIG. 5C, the landing gear door 200 may be opened by a sliding method.

In addition, when the landing gear door 200 is to be closed in the open state as shown in FIG. 5C, the landing gear door 200 is operated in the reverse order described above, so that the landing gear door 200 can be closed by a sliding method.

On the other hand, in case the inoperability of the landing gear door opening and closing device of the present invention occurs by installing explosives and the like on the end of the first and second actuators 60 and 80, the first and second actuators 60 in case of emergency. If the end of the 80 is broken, the landing gear door 200 is separated so that the landing gear door 200 can be forcibly separated.

As described above, the present invention opens and closes the landing gear door mounted on the aircraft in a sliding manner that moves along the surface of the aircraft when the landing gear door is opened so that the area that hinders the flow of air in the direction of the aircraft is minimized. It can reduce the drag generated during takeoff, reduce the weight of the aircraft by forming the base to design low structural strength, and when exploding the landing gear door in case of emergency, Since the support structure of the landing gear door can be easily removed, it is a very useful invention that greatly improves the efficiency and reliability of the device.

Although the present invention has been described with reference to one embodiment shown in the drawings, this is merely exemplary, and those skilled in the art will understand that various modifications and equivalent other embodiments are possible therefrom. Therefore, the true technical protection scope of the present invention will be defined by the technical spirit of the appended claims.

Claims (4)

A driving guide part fixedly installed on both sides of the fuselage, A driving actuator mounted inside the driving guide part of the one side and operating when the landing gear door is opened or closed; A ball screw installed between the drive guides and rotating by operation of a drive actuator, First and second linear motion guides installed on upper and lower ball screws between the driving guides and serving as guide rails; A first actuator supported and mounted on a first fixing bracket respectively installed at one end of the first and second linear motion guides and the ball bushing installed in the ball screw; A second actuator supported and mounted on a lower portion of the second fixing bracket fixed to an upper end of the other driving guide part; Landing gear door opening and closing device of the aircraft, characterized in that consisting of a landing gear door which is mounted to the fuselage and is opened and closed by the drive and operation of the first and second actuators. The method of claim 1, wherein the second support piece formed in the rear center of the first fixing bracket is fixed to the ball bushing by a clamp, the first support piece formed on the rear upper end of the first fixing bracket is a first linear motion guide. And a third support piece formed at a rear lower end of the first fixing bracket is supported so as to surround a lower end of a second linear motion guide. 2. The opening and closing of the landing gear door of an aircraft according to claim 1, wherein a fixing piece is provided at a lower end of the piston of the first actuator, and the fixing piece is installed to surround an inside of a fixing member fixed to the landing gear door at the bottom. Device. According to claim 1, wherein the lower end of the piston of the second actuator is supported by a shaft rotatably installed in each of the guide rollers, the guide roller is fixed to the landing gear door that the guide roller is in surface contact with the second Landing gear door opening and closing device of the aircraft, characterized in that the guide hole for guiding the horizontal movement of the actuator is installed so as to surround the inside of the guide member formed in the top center.