阅读说明：本技术 一种飞机起落架位置指示机构及指示方法 (Aircraft landing gear position indicating mechanism and indicating method ) 是由 魏亮亮 范建博 王雪 于 2019-08-16 设计创作，主要内容包括：一种飞机起落架位置指示装置及指示方法,有一个与起落架支柱联动的引导装置和受引导装置驱动的指示装置,含有一个与起落架支柱同轴的扇形活动件,在起落架支柱上固定有一个与扇形活动件联动的偏心轴,另有一个铰接在飞机机体上止动块,止动块的第一支臂可以与起落架支柱上偏心轴配合,止动块第二支臂与扇形活动件配合,另有一个钢索将扇形活动件与指示装置连接。保证在起落架位置指示系统故障的情况下,能通过扇形活动件与指示装置机械的向飞行员提供起落架放下位置的正确信息。(The position indicating device for airplane landing gear includes a guide device linked with landing gear support and an indicating device driven by the guide device, and has a fan-shaped moving part coaxial with the landing gear support, on the landing gear support an eccentric shaft linked with the fan-shaped moving part is fixed, and another eccentric shaft is hinged on the airplane body, and its first arm can be matched with the eccentric shaft on the landing gear support, and its second arm is matched with the fan-shaped moving part, and another steel cable is used for connecting the fan-shaped moving part with the indicating device. The method ensures that the correct information of the landing gear falling position can be provided for a pilot mechanically through the fan-shaped movable part and the indicating device under the condition that the landing gear position indicating system fails.)

1. An indicating mechanism for the position of landing gear of airplane is composed of a guide unit linked to the supporting column of landing gear, an indicating unit driven by said guide unit, and features that said guide unit has a fan-shaped moving part coaxial with said supporting column of landing gear, an arc slide slot on said moving part, a concave slot at right end of said slide slot, an eccentric axle relative to said slide slot, a Y-shaped stop block linked to said supporting column of landing gear, and two supporting arms at front end of said stop block, the front end of the second support arm of the stop block is tightly attached to the arc-shaped sliding groove of the fan-shaped moving part, the fan-shaped moving part is connected with an indicating device through another steel cable, the indicating device comprises a spring actuating cylinder fixed on an airplane body and an indicating rod coaxial with the spring actuating cylinder, the lower end of the spring actuating cylinder is connected with the steel cable, the lower end of the indicating rod is connected with an actuating surface of the spring actuating cylinder, and the indicating rod can move up and down under the driving of the spring actuating cylinder.

2. An aircraft landing gear position indicating mechanism according to claim 1, wherein an arc-shaped slide rail is arranged below the arc-shaped slide groove of the fan-shaped movable member, the stop block is attached to the arc-shaped slide rail, and a clamping groove is formed at the right end of the arc-shaped slide rail.

3. An aircraft landing gear position indicating method, characterized by comprising the following: 1) the guiding device comprises a fan-shaped moving part which is coaxial with the landing gear support, an arc-shaped sliding groove is arranged on the fan-shaped moving part, a concave clamping groove is arranged at the right end of the arc-shaped sliding groove, an eccentric shaft which corresponds to the arc-shaped sliding groove is fixed on the landing gear support, the eccentric shaft is embedded in the arc-shaped sliding groove and links the fan-shaped moving part with the landing gear support, a stop block with a Y-shaped structure is arranged, the middle part of the stop block is hinged on an airplane body, the front end of the stop block is provided with two support arms, the first support arm is provided with an arc-shaped edge, the end surface of the second support arm is a plane, the other end of the stop block is connected on the airplane body through a tension spring, the first support arm of the stop block can be matched with the eccentric shaft on the landing gear support, and the front end of the second support arm of the stop, the lower end of the spring actuating cylinder is connected with the steel cable, the lower end of the indicating rod is connected with the actuating surface of the spring actuating cylinder, and the indicating rod can move up and down under the driving of the spring actuating cylinder; 2) when the undercarriage is folded, an eccentric shaft on an undercarriage strut is located at the left end of the arc-shaped sliding groove of the fan-shaped moving part, a second support arm of the stop block is clamped in a clamping groove at the right end of the arc-shaped sliding groove, the steel cable traction spring actuating cylinder drives the indicating rod to retract into the outer skin of the airplane, when the undercarriage is put down, the eccentric shaft on the undercarriage strut moves towards the right end along the arc-shaped sliding groove of the fan-shaped moving part, when the eccentric shaft meets a first support arm of the stop block, the first support arm is lifted along the arc-shaped edge of the first support arm, the second support arm is further driven to be separated from the clamping groove, the limit of the stop block on the fan-shaped moving part is relieved, the spring actuating cylinder ejects.

4. An aircraft landing gear position indicating mechanism according to claim 3, wherein an arc-shaped slide rail is arranged below the arc-shaped slide groove of the fan-shaped movable member, the stop block is attached to the arc-shaped slide rail, and a clamping groove is formed at the right end of the arc-shaped slide rail.

Technical Field

The patent relates to an aircraft design technology, in particular to an aircraft landing gear position indicating mechanism and an indicating method.

Background

The landing gear is a take-off and landing device of the airplane, and has the functions of ensuring take-off running and landing sliding of the airplane and absorbing impact and jumping energy generated during landing and ground movement. When an airplane takes off and lands or flies, a pilot needs to timely and accurately acquire the position information of the undercarriage. The position indicating mechanism of the aircraft landing gear triggers the indicating mechanism to act to send out an in-place signal after the rotating angular displacement of the landing gear reaches a set value, and is suitable for indicating the position of the aircraft landing gear and indicating the position of other angular displacements.

The aircraft landing gear position indicating mechanism is arranged in a landing gear cabin and extends to an outer skin of an aircraft, and a pilot observes whether an indicating rod extends out of the skin at a side window of the aircraft to judge whether the landing gear is put down in place. When the airplane is in a flying state, the landing gear indicator rod retracts into the airplane skin; when the aircraft lands, after the pilot carries out the operation of putting down the landing gear, if the normal indication system of the aircraft landing gear fails, the pilot can normally land at the moment if the indication rod extends out of the aircraft skin to indicate that the landing gear is put down in place; if the indication rod does not extend out of the skin of the airplane, indicating that the landing gear is not put down in place, emergency measures should be taken for landing.

In general, a micro-electric door is arranged at the landing gear lowering position, when the landing gear is lowered in place, the electric door is connected, a landing gear lowering indicator lamp positioned in a cockpit is lighted, and a pilot receives the landing gear lowering in-place information. When the plane loses power supply or the micro switch is in fault, the pilot can not judge whether the undercarriage is put down, and can only land according to the command of the airport tower at the moment, however, the tower can not judge whether the undercarriage is in place at the put-down position, and the undercarriage can be compressed and retracted during the landing process when the undercarriage is in place, so that flight accidents are caused. Therefore, a set of standby undercarriage down position mechanical indicating mechanism needs to be designed, and a pilot can effectively judge whether the undercarriage is down to the position or not by observing an indicating rod arranged on an outer skin of the airplane under the emergency condition.

Disclosure of Invention

The invention aims to provide an aircraft landing gear position indicating mechanism and an indicating method, which can realize standby indication of the landing gear down position under the condition that a landing gear normal position indicating system has a fault.

An aircraft landing gear position indicating mechanism comprises a guide device and an indicating device which are linked with a landing gear support, and is characterized in that the guide device comprises a fan-shaped moving part which is coaxial with the landing gear support, an arc-shaped sliding groove is arranged on the fan-shaped moving part, a concave clamping groove is arranged at the right end of the arc-shaped sliding groove, an eccentric shaft which corresponds to the arc-shaped sliding groove is fixed on the landing gear support, the eccentric shaft is embedded in the arc-shaped sliding groove to link the fan-shaped moving part with the landing gear support, a Y-shaped stop block is arranged, the middle part of the stop block is hinged on an aircraft body, two support arms are arranged at the front end of the stop block, wherein the first support arm is provided with an arc-shaped edge, the end surface of the second support arm is a plane, the other end of the stop block is connected on the aircraft body through a, the front end of the second support arm of the stop block is tightly attached to the arc-shaped sliding groove of the fan-shaped movable part, the fan-shaped movable part is connected with an indicating device through another steel cable, the indicating device comprises a spring actuating cylinder fixed on an airplane body and an indicating rod coaxial with the spring actuating cylinder, the lower end of the spring actuating cylinder is connected with the steel cable, the lower end of the indicating rod is connected with the actuating surface of the spring actuating cylinder, and the indicating rod can move up and down under the driving of the spring actuating cylinder.

When the undercarriage is retracted, an eccentric shaft on an undercarriage strut is positioned at the left end of an arc-shaped sliding groove of the fan-shaped moving part and continues to move leftwards to drive the fan-shaped moving part to rotate, so that a second support arm of the stop block is clamped in a clamping groove at the right end of the arc-shaped sliding groove, and the steel cable traction spring actuating cylinder drives the indicating rod to retract into an outer skin of the airplane; when the undercarriage is in a down position, an eccentric shaft on an undercarriage support post moves towards the right end along an arc-shaped sliding groove on the fan-shaped moving part, when the eccentric shaft meets a first support arm of the stop block, the first support arm is lifted along the arc-shaped edge of the first support arm, then the second support arm is driven to be separated from the clamping groove, the stop block is relieved from limiting the fan-shaped moving part, the indicating rod is popped out of the airplane skin by the spring actuating cylinder to indicate that the undercarriage is down, and meanwhile, the spring actuating cylinder drives the steel cable to pull the fan-shaped moving part.

The invention has the beneficial effects that: the mechanism and the method for indicating the position of the undercarriage of the airplane are linked with the undercarriage strut of the airplane, so that the correct information of the landing gear falling position can be provided for a pilot through the fan-shaped moving part and the spring actuator cylinder machinery under the condition that the undercarriage position indicating system fails.

The present application is described in further detail below with reference to the accompanying drawings of embodiments.

Drawings

FIG. 1 is a schematic view of a position indicating mechanism when the landing gear is stowed.

FIG. 2 is a schematic view of the off-center shaft release stop during landing gear lowering.

FIG. 3 is a schematic view of the position indicating mechanism with the landing gear in place.

Figure 4 is a schematic view of a fan-shaped moving part.

FIG. 5 is a schematic view of a stopper structure

The numbering in the figures illustrates: 1. a landing gear strut; 2. an eccentric shaft; 3. a fan-shaped movable part; 4. a stopper block; 5. stretching the spring; 6. a steel cord; 7. a pulley; 8. a spring actuator cylinder; 9. aircraft skin; 10. an indication lever; 11. an arc-shaped chute; 12, a clamping groove; 13. a first support arm; 14. a second support arm; 15 arc-shaped sliding rails.

Detailed Description

Referring to the drawings, the aircraft landing gear position indicating mechanism of the application, as shown in fig. 1 to 5, comprises a guiding device and an indicating device which are linked with a landing gear support column 1, wherein the guiding device comprises a fan-shaped moving part 3 which is coaxial with the landing gear support column, an arc-shaped sliding groove 11 is arranged on the fan-shaped moving part 3, a concave clamping groove 12 is arranged at the right end of the arc-shaped sliding groove 11, an eccentric shaft 2 which corresponds to the arc-shaped sliding groove 11 is fixed on the landing gear support column 1, the eccentric shaft 2 is embedded in the arc-shaped sliding groove 11 to link the fan-shaped moving part 3 with the landing gear support column 1, a stop block 4 with a Y-shaped structure is arranged, the middle part of the stop block 4 is hinged on an aircraft body, the front end of the stop block 4 is provided with two support arms, wherein a first support arm 13 is provided with an arc-shaped edge, the end surface of a, the first arm 13 of the stop block 4 can be matched with the eccentric shaft 2 on the landing gear strut 1, the front end of the second arm 14 on the stop block 4 is tightly attached to the arc-shaped sliding groove 11 of the fan-shaped moving part 3, and a steel cable 6 is arranged to connect the fan-shaped moving part 3 with the indicating device. The indicating device comprises a spring actuating cylinder 8 fixed on an airplane body and an indicating rod 10 coaxial with the spring actuating cylinder 8, wherein the lower end of the spring actuating cylinder 8 is connected with a steel cable 6, the lower end of the indicating rod 10 is connected with an actuating surface of the spring actuating cylinder 8, and the indicating rod 10 can move up and down under the driving of the spring actuating cylinder 8. The guide pulley 7 is fixed to the aircraft body and serves to guide the wire rope 6.

In the implementation, in order to better enable the stop block 4 to exert the stop effect on the fan-shaped moving part 3, an arc-shaped sliding rail 15 is arranged below the arc-shaped sliding groove 11 of the fan-shaped moving part 3, the stop block 4 is attached to the arc-shaped sliding rail 15, and a clamping groove 12 is formed at the right end head of the arc-shaped sliding rail.

When the landing gear is in the down position, the state of the indicating mechanism is shown in figure 3, the indicating rod 10 extends out of the aircraft skin 9, the eccentric shaft 2 on the landing gear strut 1 is positioned at the leftmost end of the arc-shaped sliding groove of the fan-shaped moving part 3, and the stop block 4 is in a loose state relative to the fan-shaped moving part 3. When the landing gear is retracted, the landing gear strut 1 rotates clockwise, the eccentric shaft 2 drives the fan-shaped movable part 3 to rotate clockwise, the fan-shaped movable part 3 drives the steel cable 6 to compress the spring actuating cylinder 8 through the pulley 7, the indicating rod 10 is forced to move towards the spring actuating cylinder 8, and when the landing gear is completely retracted, the indicating rod 10 is retracted into the aircraft skin 9; the arc chute 11 is provided with a concave clamping groove 12 at the extreme position, when the fan-shaped moving part 3 moves to the extreme position, the stop block 4 slides downwards into the clamping groove 12 along the arc slide rail 15 under the action of the tension of the extension spring 5, and the second support arm 14 of the stop block 4 is clamped, so that the fan-shaped moving part 3 is stopped, the indicating rod 10 is kept at the retracted position, and the state of the indicating mechanism is shown in fig. 1 at this time.

The state of the indicator mechanism when the landing gear is in the stowed position is shown in figure 1. When the landing gear needs to be put down, the landing gear support column 1 rotates anticlockwise, the eccentric shaft 2 fixed on the landing gear support column 1 moves anticlockwise along the arc-shaped sliding groove 11 of the fan-shaped movable piece 3, the fan-shaped movable piece 3 still keeps a state of being clamped by the stop block 4 in the whole process, and the indicating rod 10 also keeps a retracted position; when the eccentric shaft 2 continues to move to the position shown in fig. 2, the eccentric shaft 2 presses the arc-shaped edge of the first support arm of the stop block 4, the stop block 4 is lifted and is separated from the clamping groove 12 of the fan-shaped movable part 3, the stop block 4 is separated from the rear fan-shaped movable part 3, the fan-shaped movable part 3 rotates anticlockwise under the action of the spring actuating cylinder 8, the indicating rod 10 extends out of the aircraft skin 9 under the action of the spring actuating cylinder 8, and the state of the indicating mechanism is shown in fig. 3.