阅读说明：本技术 一种飞机转向轮液压定向锁 (Hydraulic directional lock for aircraft steering wheel ) 是由 兰林 张文智 周玉东 于 2021-09-27 设计创作，主要内容包括：本发明公开了一种飞机转向轮液压定向锁,包括壳体,壳体固定在飞机起落架上,壳体内设有活塞且两端均伸出壳体,活塞为阶梯轴状,阶梯轴状活塞中部为大直径段且与壳体内壁紧密接触,活塞一端与起落架上的用于插入轮子安装轴边缘上孔的锁销相连,另一端垂直设有触动片,壳体上设有触头与触动片相对的微动开关,触动片端的壳体由可供活塞通过的螺塞盖合,活塞的大直径段两侧对应的壳体上均设有液压孔,液压孔内设有与液压管相连的接管咀,壳体内活塞的大直径段朝向锁销侧的活塞上套设有弹簧,朝向锁销端的活塞与壳体间、活塞与螺塞间、活塞的大直径段与壳体间、液压孔与接管咀间和螺塞与壳体间均设有密封圈；该定向锁很好的保证飞机安全性及稳定性。(The invention discloses a hydraulic directional lock for an airplane steering wheel, which comprises a shell, wherein the shell is fixed on an airplane undercarriage, a piston is arranged in the shell, two ends of the piston extend out of the shell, the piston is in a stepped shaft shape, the middle part of the stepped shaft-shaped piston is a large-diameter section and is tightly contacted with the inner wall of the shell, one end of the piston is connected with a lock pin which is arranged on the undercarriage and is used for inserting a hole on the edge of a wheel mounting shaft, the other end of the piston is vertically provided with a touch sheet, the shell is provided with a micro switch with a contact opposite to the touch sheet, the shell at the end of the touch sheet is covered by a screw plug through which the piston can pass, the shell corresponding to two sides of the large-diameter section of the piston is provided with hydraulic holes, a nozzle connected with a hydraulic pipe is arranged in each hydraulic hole, a spring is sleeved on the piston of the large-diameter section of the piston in the shell, facing the lock pin end, between the piston and the shell, between the piston and the screw plug, between the large-diameter section of the piston and the shell, Sealing rings are arranged between the hydraulic hole and the pipe connecting nozzle and between the screw plug and the shell; the directional lock well guarantees the safety and stability of the airplane.)

1. A hydraulic directional lock for an aircraft steering wheel is characterized in that: comprises a shell (1), the shell (1) is fixed on an aircraft landing gear, a piston (2) and two ends of the piston (1) extend out of the shell (1), the piston (2) is in a stepped shaft shape, the middle part of the stepped shaft-shaped piston (2) is a large diameter section and is in close contact with the inner wall of the shell (1), one end of the piston (2) is connected with a lock pin which is arranged on the landing gear and used for inserting a hole on the edge of a wheel mounting shaft, the other end of the piston is vertically provided with a touch piece (6), the shell (1) provided with a contact and a micro switch (11) which is opposite to the touch piece (6) is covered by a screw plug (5), the screw plug (5) is provided with a hole for the piston (2) to pass through, the shell (1) corresponding to two sides of the large diameter section of the piston (2) is provided with a hydraulic hole, and a connecting pipe nozzle (9) connected with a hydraulic pipe is arranged in the hydraulic hole, the large-diameter section of the piston (2) in the shell (1) is sleeved with a spring (3) towards the piston (2) on the lock pin side, and sealing rings (4) are arranged between the piston (2) towards the lock pin end and the shell (1), between the piston (2) and the screw plug (5), between the large-diameter section of the piston (2) and the shell (1), between the hydraulic hole and the pipe connecting nozzle (9) and between the screw plug (5) and the shell (1).

2. An aircraft steering wheel hydraulic directional lock according to claim 1, wherein: and sealing rings (12) are respectively arranged between the piston (2) and the shell (1) and between the piston (2) and the screw plug (5) towards the locking pin end, and the sealing rings between the large-diameter section of the piston (2) and the shell (1), between the hydraulic hole and the pipe connecting nozzle (9) and between the screw plug (5) and the shell (1) are standard parts.

3. An aircraft steering wheel hydraulic directional lock according to claim 2, wherein: guide belts (10) are arranged between the piston (2) and the shell (1) and between the piston (2) and the screw plug (5) on the outer sides of the two Stent seal sealing rings (12).

4. An aircraft steering wheel hydraulic directional lock according to claim 2, wherein: and a protective ring for protecting the sealing ring is arranged beside the standard component sealing ring.

5. An aircraft steering wheel hydraulic directional lock according to claim 1, wherein: and screw holes are formed in the screw plug (5) and the corresponding shell (1), and a set screw (8) is arranged in each screw hole.

6. An aircraft steering wheel hydraulic directional lock according to claim 1, wherein: the utility model discloses a piston, including touch piece (6), piston (2), locking nut (7), it is fixed on piston (2) to touch piece (6) and establish through lock nut (7).

7. An aircraft steering wheel hydraulic directional lock according to claim 1, wherein: the spring (3) is a cylindrical spiral compression spring made of carbon steel wires.

Technical Field

The invention relates to the field of aircraft landing gears, in particular to a hydraulic directional lock for an aircraft steering wheel.

Background

When the airplane flies in the air, if the wheels on the landing gear are not fixed, the wheels swing unsteadily along with environmental factors, and the flight safety and the stability of the airplane are influenced. The directional lock can fix the steering wheel at one position when the helicopter flies, so that the steering wheel is fixed, and the steering wheel is opened when the airplane needs ground maneuvering, so as to meet the steering requirement.

Disclosure of Invention

The invention aims to: the hydraulic directional lock for the aircraft steering wheel is provided, the wheels on the undercarriage are well fixed, and the safety and the stability of the aircraft are well guaranteed.

The utility model provides an aircraft directive wheel hydraulic pressure directional lock, includes the casing, the casing is fixed on the aircraft undercarriage, be equipped with piston and both ends in the casing and all stretch out the casing, the piston is the step shaft form, step shaft form piston middle part be big diameter section and with shells inner wall in close contact with, the lockpin that is used for inserting wheel installation axle edge hole on piston one end and the undercarriage links to each other, and the other end is equipped with the touch piece perpendicularly, be equipped with the micro-gap switch that contact and touch piece are relative on the casing, the casing of touch piece is closed by the plug screw lid, be equipped with the hole that supplies the piston to pass on the plug screw, all be equipped with the hydraulic pressure hole on the casing that big diameter section both sides of piston correspond, the downthehole takeover mouth that links to each other with the hydraulic pressure pipe that is equipped with of hydraulic pressure, the piston of big diameter section orientation lockpin side of piston is overlapped on the casing is equipped with the spring, and the casing towards the lockpin end between piston and the casing, Sealing rings are arranged between the piston and the screw plug, between the large-diameter section of the piston and the shell, between the hydraulic hole and the connecting pipe nozzle and between the screw plug and the shell.

Further, the seal rings are evenly sealed between the piston and the shell and between the piston and the screw plug towards the end of the lock pin, and the seal rings between the large-diameter section of the piston and the shell, between the hydraulic hole and the connecting pipe nozzle and between the screw plug and the shell are standard parts.

Furthermore, guide belts are arranged between the piston and the shell and between the piston and the screw plug on the outer sides of the two Stent seal sealing rings.

Furthermore, a protective ring for protecting the sealing ring is arranged beside the standard component sealing ring.

Furthermore, a screw hole is formed in the screw plug and the shell corresponding to the screw plug, and a set screw is arranged in the screw hole.

Furthermore, the touch sheet is fan-shaped, the middle part of the touch sheet is provided with a reinforcing rib, one end of the touch sheet is provided with a hole for the piston to pass through, and the touch sheet is sleeved on the piston through a locking nut and fixed.

Still further, the spring is a cylindrical helical compression spring made of carbon steel wires.

The invention has the beneficial effects that:

according to the hydraulic directional lock for the aircraft steering wheel, the locking and unlocking conditions can be reflected to a pilot through an electric signal by arranging the micro switch, the looseness of the screw plug caused by the collision of the piston and the screw plug during unlocking can be prevented by arranging the set screw, the sealing performance of each part is ensured by arranging the standard part sealing ring, the steckel sealing ring is arranged, the abrasion of the sealing structure can be reduced by utilizing the characteristic of low friction of a slip ring in the steckel sealing while the sealing performance of the product is ensured, the service life is prolonged, the guide belt is arranged outside the sealing structure, the friction generated when the piston slides in the shell and the screw plug hole can be effectively reduced, the abrasion is reduced, the dustproof effect is realized, the product can normally work in a more severe environment, the wheels on the undercarriage can be well fixed, and the safety and the stability of the aircraft can be well ensured.

Drawings

Fig. 1 is a top cross-sectional view of the present invention.

Fig. 2 is a front view of the present invention.

FIG. 3 is an enlarged cross-sectional view of the seal ring.

Detailed Description

The technical solutions in the embodiments of the present invention are clearly and completely described below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.

Referring to fig. 1-3, an aircraft steering wheel hydraulic directional lock comprises a housing 1, the housing 1 is fixed on an aircraft landing gear and fixed on the landing gear by four fixing lugs through bolts, a piston 2 is arranged in the housing 1, two ends of the piston 2 extend out of the housing 1, the piston 2 is in a stepped shaft shape, the middle part of the stepped shaft-shaped piston 2 is a large-diameter section and is tightly contacted with the inner wall of the housing 1, one end of the piston 2 is connected with a lock pin which is arranged on the landing gear and used for inserting a hole on the edge of a wheel mounting shaft, the lock pin is in the prior art, the other end of the piston is vertically provided with a touch piece 6 and is vertically arranged upwards, the housing 1 is provided with a microswitch 11 of which the contact is opposite to the touch piece 6, the housing 1 at the end of the touch piece 6 is covered by a screw plug 5, the screw plug 5 is provided with a hole for the piston 2 to pass through, the housing 1 corresponding to two sides of the large-diameter section of the piston 2 is provided with hydraulic holes, a nozzle 9 connected with a hydraulic pipe is arranged in the hydraulic hole, the large-diameter section of the piston 2 in the shell 1 is sleeved with a spring 3 towards the piston 2 on the lock pin side, and sealing rings 4 are arranged between the piston 2 towards the lock pin end and the shell 1, between the piston 2 and the screw plug 5, between the large-diameter section of the piston 2 and the shell 1, between the hydraulic hole and the connecting nozzle 9 and between the screw plug 5 and the shell 1.

Between piston 2 and casing 1 and between piston 2 and plug screw 5 towards the lockpin end is the seal ring 12 of steckel, and the seal ring between the major diameter section of piston 2 and casing 1, between hydraulic pressure hole and the takeover mouth 9 and between plug screw 5 and casing 1 is the standard component, and the seal ring 12 of steckel utilizes the low characteristics of sliding ring frictional force in the steckel when guaranteeing the product leakproofness, reducible seal structure's wearing and tearing, improve the life-span.

Guide belts 10 are arranged between the piston 2 and the shell 1 and between the piston 2 and the plug screw 5 on the outer sides of the two Stent seal sealing rings 12, the piston 2 can be kept at the centers of holes of the shell 1 and the plug screw 5 by the aid of the guide belts 10, and the phenomenon that the piston 2 is deviated due to external force to contact the shell 1 or the plug screw 5, the Stent seal sealing rings 12 are damaged due to eccentric wear in the working process, and oil leakage of products is caused.

The protection ring for protecting the sealing ring is arranged beside the standard sealing ring, and the standard sealing ring is protected by the protection ring, so that the sealing ring is prevented from being extruded into a gap of a matched part under the action of pressure to be damaged.

The screw plug 5 and the corresponding shell 1 are provided with screw holes, and the screw holes are internally provided with set screws 8, so that the situation that the screw plug 5 is loosened due to the collision of the piston 2 and the screw plug 5 during unlocking can be prevented.

The touch piece 6 is fan-shaped, the middle part is provided with a reinforcing rib, one end of the touch piece 6 is provided with a hole for the piston 2 to pass through, the touch piece 6 is sleeved on the piston 2 through a locking nut 7 and fixed, and the locking nut 7 is used for fixing the touch piece 7 convenient to detach.

The spring 3 is preferably a cylindrical helical compression spring made of carbon steel wire.

The working principle is as follows: when the filler neck 9 positioned on the right side of the large diameter of the piston inputs pressure, the pressure acts on the side surface of the side, away from the spring 3, of the large diameter of the piston 2, the pressure pushes the piston 2 to move along the left direction of the axis of the piston to compress the spring 3, so that the end surface of the piston 2 is limited by the end surface of the shell 1, the piston pushes the lock pin to be inserted into the pin hole in the edge of the wheel mounting shaft, and the wheel is locked; when the unlocking is needed, the pressure of the cavity position on the right side of the large diameter of the piston is released, the cavity position on the left side inputs the pressure through the filler neck 9, and the piston 2 is in an unlocking state when moving along the right direction of the axis under the action of the spring 3 and the unlocking pressure; when the piston 2 is locked or unlocked in the process of moving along the axial direction, the trigger 6 connected with the piston 2 enables the micro switch 11 to be switched off and on to indicate the locked or unlocked state when the piston is locked or unlocked in place.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.