CN102390526B - Rocker-arm-type bearable lock connecting rod emergency disengagement mechanism, system and method - Google Patents

Abstract

A rocker-type loadable lock link emergency disengagement mechanism, disengagement system and method, belonging to the technical field of landing gear. It mainly includes the upper platform (4) and the lower platform (7) composed of the upper locking link (1), the lower locking link (2), the pull rod (3), the thrust cylindrical roller (6, 9), and the pull rod. The main load-bearing member of the connecting rod; also includes spur gears (10), mixed gears (11), bevel gears (12), torsion springs (15), rocker arms (13) constitute the rotating part of the disengagement mechanism; also include the following Tension spring (14) constitutes the safety device after mechanism disengages; The emergency release system (22) constitutes the blocking device of the rocking arm. The invention effectively solves the problem that the landing gear cannot be put down in an emergency without an auxiliary power source.

Description

Rocker-type loadable lock link emergency disengagement mechanism, disengagement system and method

technical field

The invention belongs to a disengagement mechanism, and in particular relates to a technical field suitable for realizing the disengagement function of a locking link when the landing gear is released in an emergency

technical background

Landing gear is an important part of the aircraft. Due to the complex working environment of the landing gear system and the short air-to-ground cycle of modern aircraft, there are many failures in use. In the whole landing gear system, the retractable system accounts for a relatively high proportion of failures in the entire landing gear system due to the complexity of its own mechanism movement and control system. In order to improve landing safety, airworthiness regulations stipulate that for transport category aircraft, in the event of any reasonable possible failure of the landing gear retraction system or failure of a single hydraulic source, power supply or equivalent energy source, the aircraft should have an emergency release function.

The normal retraction and retraction of the aircraft landing gear depends on the hydraulic retractable actuator j as the power device for retraction and retraction. The emergency release system is a cable transmission, mechanical unlocking, and the bypass valve (or exhaust valve) releases pressure. The landing gear relies on its own gravity and The aerodynamic resistance of the pillar is freely lowered and locked. The specific method is as follows: the pilot first releases the pressure of the actuator to avoid excessive hydraulic damping force to prevent the landing gear from being lowered; then pulls the emergency release handle, and the steel cable pulls upwards i, driving the emergency rocker arm h for unlocking the upper position to rotate, and the rocker arm rotates Until the upper lock is unlocked, the landing gear is lowered by its own gravity and the aerodynamic load of the prop, so as to realize the emergency lowering of the landing gear. The principles are shown in Figures 4, 5, and 6. In order to simplify the control system, many modern models do not have a separate power source for the retraction and retraction of the hatch, and most of them choose the linkage mechanism between the hatch and the landing gear. As shown in Figure 6, the hatch is connected to the strut p of the landing gear through the front lock link l, crossbeam r, and rear lock link k, so as to realize the mechanical linkage between the landing gear and the hatch. However, the aerodynamic load m on the door of the mechanism prevents the landing gear from being lowered, and different flight conditions have a great influence on the emergency deployment of the landing gear.

In actual engineering, some similar models at home and abroad have experienced the situation that the emergency landing gear cannot be put in place due to the excessive aerodynamic resistance of the cabin door, and the emergency landing gear has failed. The failure of the emergency release will seriously affect the safety of the aircraft taking off and landing, and affect the airworthiness certification of the aircraft. In order to solve the problem of emergency discharge failure, military aircraft often adopt two methods:

⑴ Auxiliary power source: When the main power hydraulic source fails, use the stored hydraulic power source to drive the retractable actuator to make the landing gear drop into place smoothly;

⑵ Auxiliary operation: When the landing gear cannot be lowered in an emergency under special flight conditions, an additional emergency handle is provided on the aircraft, and the pilot pulls the handle to forcefully lower the landing gear.

However, the addition of auxiliary hydraulic pressure sources and the addition of pilot operations do not meet the airworthiness requirements of civil aircraft, so the above method is not suitable for civil transport aircraft and large passenger aircraft. The method that can be adopted by civil aircraft is to change the connection method or connection position of the hatch, but due to the structural space layout problem, the above method is often not realized. Another way is to disengage the connecting mechanism that hinders the lowering of the landing gear from the landing gear, but according to airworthiness requirements, the pilot cannot have redundant additional operations and excessive operating force, and at the same time there is no auxiliary power source, so the mechanism is realized mechanically. It is difficult to disengage. At present, there is no specific model that uses a mechanical disengagement mechanism to solve the problem of emergency discharge failure.

Contents of the invention

The purpose of the present invention is to design a set of locking link disengagement mechanism and disengagement system and method under the premise of meeting the linkage and load transmission requirements of the mechanism during normal retraction for some special models, so as to effectively solve the problem of emergency release of the landing gear. The problem of function failure.

A rocker-type loadable locking link emergency disengagement mechanism is characterized in that it includes an upper locking link linked with the cabin door and a lower locking link linked with the landing gear, the upper locking link and the lower locking link There is a tie rod installation cavity at the joint, and a tie rod is installed in the tie rod installation cavity; the above tie rod has an upper platform, and the lower part of the above locking connecting rod has an upper platform cavity matching the upper platform, and the above upper platform is embedded in the upper platform cavity, and the upper platform The upper and lower surfaces of the platform are arranged with thrust cylindrical rollers along the circumferential direction, so that the lower part of the upper lock and the upper part of the tie rod form a thrust cylindrical roller bearing connection; the above-mentioned upper platform is a star-shaped tooth structure, and the lower wall of the upper platform cavity has A star-shaped groove-shaped structure matched with the star-shaped tooth-shaped structure; the above-mentioned pull rod has a lower platform, and the upper part of the above-mentioned lower locking link has a lower platform cavity that cooperates with the lower platform. The above-mentioned lower platform is embedded in the lower platform cavity, and the lower platform The upper and lower surfaces of the platform are arranged with thrust cylindrical rollers along the circumferential direction, so that the upper part of the lower lock link and the lower part of the tie rod form a thrust cylindrical roller bearing connection; the above-mentioned tie rod installation cavity is also equipped with spur gears, mixed gears, bevel gears, Rocker arm and tension spring; the spur gear is coaxially connected with the pull rod, the mixed gear is coaxially connected with a fixed shaft of the lower lock link, the rocker arm is installed on the upper lock link, and one end of the rocker arm is connected to the bevel gear Coaxial and fixedly connected, the other end extends out of the rod installation cavity, the spur gear meshes with the spur gear part of the mixed gear, and the bevel gear meshes with the bevel tooth part of the mixed gear; one end of the tension spring is connected with the lower part of the locking link , the other end is connected with the upper part of the lower lock link; the emergency release mechanism also includes a torsion spring with one end connected with the above-mentioned pull rod and the other end connected with the above-mentioned lower lock link.

The disengagement system using the rocker-arm-type loadable lock-link emergency disengagement mechanism is characterized in that: the disengagement system is composed of an emergency release system, a rocker-arm arresting system, and a rocker-arm-type loadable lock-link emergency disengagement mechanism; The rocker arresting system consists of a head pulley, a transition pulley, an end pulley, a steel cable, and an arresting rod; the head pulley is installed on the rotating part of the emergency release system and rotates with the rotating part; the transition pulley and the end pulley are installed on the lifting The above-mentioned arresting rod is installed on the end pulley, and the axis of the arresting rod is perpendicular to the axis of the end pulley; one end of the steel cable is connected to the head pulley, and the other end is connected to the end pulley around the transition pulley block.

The working method of breaking away from the system is characterized in that it includes the following process:

(a) When the landing gear system is normally retracted, the rocker-type loadable lock link emergency release mechanism acts as a lock link to realize the linkage of the hatch mechanism and the transmission of loads. The specific working process is as follows: the lock link The internal load transmission mode is that the upper locking connecting rod is transmitted to the tie rod through the thrust cylindrical roller bearing structure, and the pulling rod is transmitted to the lower locking connecting rod through the thrust cylindrical roller bearing structure, so as to realize the load transmission; when retracting normally, the arresting rod is retracted , when the lock link moves to the position of the arresting lever, it can pass through smoothly without affecting the normal retraction and retraction of the landing gear;

(b) When the landing gear is in the emergency release state, it is necessary to unload the door load that hinders the lowering of the landing gear, that is, to disengage the locking link; the pilot pulls the emergency handle, which drives the emergency release mechanism to rotate, thereby driving the nose pulley to rotate, and the The steel cable drives the end pulley to rotate accordingly, and the arresting rod is driven by the end pulley to rotate to the lowered state. When the lock connecting rod moves to the position of the arresting rod, the rocker arm hits the arresting rod and starts to rotate, and the rotation of the rocker arm drives the bevel gear, the bevel gear The rotation drives the mixing gear, and the rotation of the mixing gear drives the spur gear, thereby driving the pull rod to rotate. The contact between the pull rod and the upper locking link and the lower locking link is in the form of cylindrical roller bearings, so the friction force is small, and the force required for disengagement is also relatively small. Small; when the teeth of the star-shaped tooth structure on the upper platform of the tie rod are aligned with the grooves of the star-shaped tooth structure on the lower wall of the upper platform chamber, the load of the upper locking link cannot be transmitted to the tie rod, and the upper locking link and the lower lock are connected. The rods are separated to realize the disengagement of the locking rods; after the upper and lower locking rods are disengaged, there are tension springs to restrict their free movement;

(c) Under normal circumstances, the teeth of the star-shaped tooth structure on the upper platform of the tie rod are aligned with the grooves of the star-shaped tooth structure on the lower wall of the upper platform cavity, so as to transmit the load, and the free rotation of the tie rod due to environmental disturbance cannot occur, so For safety and reliability, a torsion spring is connected between the pull rod and the lower lock link to limit the free rotation of the pull rod when the rocker arm is not acting, and the whole mechanism is in a locked state.

The principle of the present invention: the arresting system is directly connected with the emergency release mechanism, that is, the emergency release mechanism moves, and the arresting system also works accordingly. Therefore, the pilot does not need to add additional operations, and only needs to pull the emergency handle once. When the arresting rod works, the rocker arm hits the arresting rod to realize the rotation of the rocker arm, the rotation of the rocker arm drives the bevel gear, the rotation of the bevel gear drives the mixed gear (half bevel half straight tooth), and the rotation of the mixed gear drives the spur gear, thereby driving the pull rod to rotate , when the pull rod is rotated until the teeth of the star-shaped tooth structure on the upper platform are aligned with the grooves of the star-shaped tooth structure on the lower wall of the upper platform chamber, the load of the upper locking link cannot be transmitted to the tie rod, and the upper locking link is connected with the lower lock. The rods are separated to realize the disengagement of the locking rod; the thrust cylindrical roller can effectively bear the axial load, and at the same time, the rolling friction of the roller is small. These two properties effectively solve the problem that the locking rod can bear a large axis At the same time, the friction force on the rotating pull rod is small, that is, the force required for disengagement is small; through the first-stage amplification transmission of the hybrid gear and the spur gear, the load transmitted from the rocker arm force to the pull rod is effectively increased, and at the same time The rotation angle of the rocker arm is also enlarged to the angle of the pull rod, which effectively increases the safety margin of the mechanism function and improves the reliability of the mechanism; the torsion spring is used to limit the free movement of the pull rod when the rocker arm is not acting; the tension spring is used for Restrict the free movement of the upper half of the lock link and the lower half of the lock link after disengagement;

Beneficial effects of the present invention:

(a) This set of disengagement mechanism effectively solves the problem of failure of the emergency release of the landing gear without an auxiliary power source, and disengages the aerodynamic resistance of the door that restricts the lowering of the landing gear from the landing gear.

(b) The realization of the function of this set of detachment mechanism meets the three basic design principles of no additional operation by the pilot, no obvious increase of the pilot's operating force, and no instability or damage to the mechanisms due to uncertain movements after the detachment.

(c) The amplified transmission of the detachment mechanism effectively improves the safety margin of the mechanism function and effectively improves the reliability of the mechanism.

(d) This set of disengagement mechanism can be widely used in civil models that need the function of emergency release landing gear, manned aerospace aircraft in some aerospace fields, and also suitable for some military aircraft that do not have auxiliary retractable power sources type

Description of drawings

Accompanying drawing 1 is a detailed diagram of the internal structure of the load-bearing lock link disengagement mechanism;

Attached Figure 2 is a schematic diagram of the external structure of the load-bearing lock link disengagement mechanism;

Attached Figure 3 Schematic diagram of the structure of the arresting system; a is the retracted position of the rocker arm; b is the lowered position of the rocker arm;

Attached drawing 4 is a schematic diagram of the working principle of the arresting system; c is the direction in which the cable moves after the pilot pulls the handle; d is the emergency rocker used to release the upper lock; e is the link between the locking link and the hatch; f is the The impact position of the rocker arm and the arresting rod; g is the linkage part between the lower lock link and the landing gear;

Accompanying drawing 5 is the schematic diagram of the mixed gear structure of half-bevel and half-straight teeth;

Accompanying drawing 6 is the schematic diagram of the structure of the tie rod assembly;

Attached drawing 7 is a schematic diagram of the retracted state of the landing gear; h is the unlocking position of the emergency rocker arm for unlocking the upper lock; i is the direction in which the steel cable moves after the pilot pulls the handle; j is the retractable actuating cylinder; k is the rear lock link ; l is the front lock link; m is the aerodynamic load direction of the hatch; r is the beam;

Accompanying drawing 8 is the schematic diagram of the landing gear lowered state and the installation position diagram of the disengagement link in the landing gear; n is the emergency release system; k is the rear lock link; l is the front lock link; m is the aerodynamic load direction of the hatch; o is the lock link that needs to be disengaged; p is the landing gear strut; q is the hatch;

Label names in the figure: 1. Locking connecting rod, 2. Lower locking connecting rod, 3. Pull rod, 4. Upper platform, 5. Upper platform cavity, 6. Thrust cylindrical roller, 7. Lower platform, 8. Lower platform Cavity, 9, thrust cylindrical roller, 10, spur gear, 11, mixed gear, 12, bevel gear, 13, rocker arm, 14, tension spring, 15, torsion spring, 16, head end pulley, 17, second Pulley, 18, the third pulley, 19, end pulley, 20, steel cable, 21, arresting rod, 22, emergency release system, C, pull rod installation cavity.

Detailed ways:

The structural details of the rocker-type loadable lock link emergency release mechanism are shown in Figures 1 and 2, and the details of the arresting system mechanism are shown in Figures 3 and 4. Here, the specific implementation of the rocker-type loadable lock link emergency disengagement mechanism and disengagement system will be described.

The specific implementation of the rocker-type loadable lock link emergency release mechanism is as follows:

(a) When the landing gear system is normally retracted, the rocker-type loadable lock link emergency release mechanism acts as a lock link to realize the linkage of the hatch mechanism and the transmission of loads. The specific working process is as follows: the lock link The internal load transmission mode is that the locking connecting rod 1 is transmitted to the tie rod 3 through the thrust cylindrical roller bearing structure, and the tie rod 3 is transmitted to the lower rod 2 through the thrust cylindrical roller bearing structure, so as to realize the load transmission;

During normal retraction and retraction, the arresting rod is retracted at position a (as shown in Figure 3), and when the lock link moves to the position of the arresting rod, it can pass smoothly without affecting the normal retraction and retraction of the landing gear.

(b) When the landing gear is in the emergency release state, it is necessary to unload the door load that prevents the landing gear from being lowered, that is, to disengage the locking link; the pilot pulls the emergency handle to drive the emergency release mechanism to rotate, thereby driving the nose pulley 16 to rotate, The end pulley 19 is driven by the cable to rotate accordingly, and the arresting rod is driven by the end pulley 19 to rotate to position b (as shown in Figure 3). When the lock link moves to the arresting rod position, the rocker arm 13 hits the arresting rod and starts Rotation, the rocker arm 13 rotates to drive the bevel gear 12, the bevel gear 12 rotates to drive the mixing gear 11, the mixing gear 11 rotates to drive the spur gear 10, thereby driving the pull rod 3 to rotate, and the pull rod 3 is in contact with the upper lock link 1 and the lower lock link 2 The method is in the form of cylindrical roller bearings, so the friction force is small, and the force required for disengagement is also small; When they are aligned, the load of the upper locking link 1 cannot be transmitted to the pull rod 3, and the upper locking link 1 and the lower locking link 2 are separated to realize the separation of the locking links; after the upper and lower locking links are separated, there is a tension spring 14 Pulling, restricting its free movement;

(c) Under normal circumstances, the teeth of the star-shaped tooth structure of the upper platform 4 of the tie rod are aligned with the teeth of the star-shaped tooth structure of the lower wall of the upper platform cavity 5, so as to transmit the load, and the free rotation of the tie rod due to environmental disturbances cannot occur. Therefore, for safety and reliability, a torsion spring 15 is connected between the pull rod 3 and the lower locking link 2 to limit the free rotation of the pull rod when the non-rocker arm 13 acts, and the whole mechanism is in a locked state.

Claims (3)

1. lock connecting rod emergency escape mechanism that rocker-arm can carry is characterized in that:

Comprise and the connecting rod of locking (1) of hatch door interlock and the following lock connecting rod (2) that links with alighting gear that the connecting rod of locking has pull bar installation cavity (C) with the junction of locking connecting rod down, and pull bar (3) is installed in the pull bar installation cavity;

Above-mentioned pull bar (3) has upper mounting plate (4), the above-mentioned connecting rod bottom of locking has the upper mounting plate chamber (5) that cooperates with upper mounting plate, above-mentioned upper mounting plate (4) is embedded in the upper mounting plate chamber (5), and there is cylindrical roller thrust (6) on the upper and lower surface of this upper mounting plate (4) along circumferential arrangement, makes lock connecting rod bottom and pull bar top formation thrust roller bearing connection mode; Above-mentioned upper mounting plate (4) is star-like dentalation, and the lower wall surface of upper mounting plate chamber (5) has the star-like groove shape structure that cooperates with this star-like dentalation;

Above-mentioned pull bar has lower platform (7), the above-mentioned connecting rod of lock down top has the lower platform chamber (8) that cooperates with lower platform, above-mentioned lower platform (7) is embedded in the lower platform chamber (8), and there is cylindrical roller thrust (9) on the upper and lower surface of this lower platform (7) along circumferential arrangement, makes down lock connecting rod top and pull bar bottom form the thrust roller bearing connection mode;

Straight gear (10) also is installed in the above-mentioned pull bar installation cavity (C), mixes gear (11), finishing bevel gear cuter (12), rocking arm (13) and extension spring (14); Wherein straight gear (10) is coaxial with pull bar (3) and captive joint, mix gear (11) and coaxial connection of an anchor shaft of lock connecting rod (2) down; rocking arm (13) is installed on the connecting rod of locking; and rocking arm (13) one ends are coaxial with finishing bevel gear cuter (12) and captive joint; and the other end stretches out pull bar installation cavity (C); straight gear (10) partly is meshed with the straight gear of mixing gear (11), and finishing bevel gear cuter (12) is meshed with the bevel gear part of mixing gear (11); Extension spring (14) one ends are connected with the connecting rod of locking (1) lower part, and the other end is connected with following lock connecting rod (2) top;

This emergency escape mechanism comprises that also an end links to each other with above-mentioned pull bar (3), the torsion spring (15) that the other end links to each other with above-mentioned lock connecting rod (2) down.

2. utilize the detachment system of the lock connecting rod emergency escape mechanism that the described rocker-arm of claim 1 can carry, it is characterized in that: this detachment system is made up of the lock connecting rod emergency escape mechanism that emergent place system (22), rocking arm arresting system, rocker-arm can carry;

This rocking arm arresting system by head end pulley (16), transition assembly pulley (17,18), block (19), cable wire (20), block bar (21) and form; Wherein head end pulley (16) is installed on the rotating part of emergent place system (22), and rotates with rotating part; Transition assembly pulley and block (19) are installed on the interior framing member of landing gear compartment; The above-mentioned bar (21) that blocks is installed on the block (19), and blocks axis and the block axis normal of bar (21); Cable wire one end is connected in head end pulley (16), the other end is walked around the transition assembly pulley and is connected with block (19).

3. the method for work of detachment system as claimed in claim 2 is characterized in that comprising following process:

(a), when the normal folding and unfolding of Landing Gear System, the lock connecting rod emergency escape mechanism that this rocker-arm can carry realizes the interlock of hatch door mechanism and the transmission of load as a lock connecting rod, concrete working process is as follows: lock connecting rod internal load transfer mode is passed to pull bar (3) for the connecting rod of locking (1) by the thrust roller bearing structure, pull bar (3) is passed to down lock connecting rod (2) by the thrust roller bearing structure, thereby realizes the transmission of load;

During normal folding and unfolding, block bar and pack up, the lock connecting rod is servo-actuated when blocking the bar position, can pass through smoothly, does not influence the normal folding and unfolding of alighting gear;

(b), when alighting gear is in emergent release position, the hatch door load unloading that hinders gear down need be about to lock connecting rod and break away from; The aviator spurs emergent handle, drive emergent laying mechanism rotation, thereby drive head end pulley (16) rotation, correspondingly drive block (19) rotation by cable wire, block bar by block (19) driven rotary to down state, when the lock connecting rod servo-actuated when blocking the bar position; rocking arm (13) collides and blocks bar and begin to rotate; rocking arm (13) rotating band dynamic bevel gear (12); finishing bevel gear cuter (12) rotation drives combination tooth wheel (11); mix gear (11) rotation and drive straight gear (10); thus drive pull bar (3) rotation; pull bar (3) with lock connecting rod (1) and to lock connecting rod (2) way of contact down be the cylindrical roller bearing form, so friction force is less, it is also less to break away from required application force; When the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate (4) and upper mounting plate chamber (5) lower wall aligns, lock the load transmission of connecting rod (1) less than pull bar (3), the connecting rod (1) of locking is then separated with locking connecting rod (2) down, realizes that the lock connecting rod breaks away from; Locking up and down has extension spring (14) dragging after connecting rod breaks away from, and limits its free motion;

(c) under the normal circumstances, the groove of the star-like dentalation of the tooth of the star-like dentalation of pull bar upper mounting plate (4) and upper mounting plate chamber (5) lower wall aligns, so that transmitted load, can not occur because the situation that the environmental perturbation pull bar freely rotates, therefore for safe and reliable, be connected torsion spring (15) at pull bar (3) with following the lock between connecting rod (2), be used for the restriction pull bar and do freely rotating of time spent at non-rocking arm (13), sleeve mechanism is in the state of being lockable.

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