CN214084739U

CN214084739U - Trigger type coordination valve for upper position lock of cabin door

Info

Publication number: CN214084739U
Application number: CN202023029214.1U
Authority: CN
Inventors: 刘崇武; 潘厚有; 牛成奎
Original assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Current assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Priority date: 2020-12-16
Filing date: 2020-12-16
Publication date: 2021-08-31
Anticipated expiration: 2030-12-16

Abstract

The utility model discloses a coordinated valve of formula is triggered to hatch door upper lock, the range of acting in coordination is wide, and the reliability is higher. The utility model discloses a following technical scheme realizes: the oil extraction nozzle supplies pressure, the upper lock is linked with the pressure rod through the pressing mechanism, the valve core return spring is compressed through the stepped shaft, the valve seat is driven to seal the valve core, and the oil nozzle is closed; when the upper lock of the cabin door is completely opened, the upper lock applies pressing force to the pressing rod through the movement track of the pressing mechanism, the pressing rod pushes the valve core, the valve core return spring is compressed, the valve seat of the valve is separated, the valve oil holes distributed on the conical shell of the valve core are triggered, hydraulic oil enters the valve cavity of the rear end cover through the pressure supply oil path of the cabin door actuator cylinder, flows to the cabin door actuator cylinder from the oil outlet pipe nozzle, the actuator cylinder is pushed to open the cabin door, the pressing rod is pressed at the initial position under the action of elastic force of the compression valve core return spring and the valve core return spring, the simultaneous pressure supply of the upper lock and the cabin door actuator cylinder is realized, and the control logic of the sequential movement sequence is completed through the triggered coordination valve.

Description

Trigger type coordination valve for upper position lock of cabin door

Technical Field

The utility model relates to a can simplify control logic's undercarriage hatch door uplock and trigger formula and coordinate valve.

Background

The landing gear retraction system is mainly used for controlling the retraction and extension of the landing gear and controlling the opening and closing of a main landing gear cabin door, a nose landing gear cabin door and the landing gear, is an important system of an airplane, and can directly influence the flight safety if the landing gear retraction system can work normally. Each landing gear bay has a hydraulically actuated door, respectively a forward landing gear bay door and a main landing gear inner bay door. Since the main hydraulic control and actuation elements of the landing gear control system are mounted within the landing gear bay, including the safety isolation valves, landing gear and door selector valves, bypass valves, uplocks and door actuators, etc., each landing gear door has a set of ground door opening mechanisms for ease of maintenance and service of these elements. The bypass valve is mounted on the closing line of the hatch actuator. When the hydraulic oil is normally stored, the hydraulic oil directly passes through the bypass valve. When the ground cabin door opening mechanism is operated to open the cabin door, the ground cabin door opening handle can pull the push-pull steel cable, the push-pull steel cable can pull the control rod along with the push-pull steel cable to further rotate the spline shaft, the spline shaft drives the driving wheel coaxial with the spline shaft, and the slide valve moves leftwards under the driving of the driving wheel, so that hydraulic supply is closed (disconnected) and two cavities of each cabin door actuator are communicated. Simultaneously, can prevent the hydraulic lock effect, the hatch door is opened under the action of gravity. The cabin door uplock release mechanism and the uplock emergency release mechanism have the same working principle, share one release lever, and have the difference that spline shafts which are different and are respectively arranged at two sides of the uplock are used; under the action of high-pressure oil, a piston rod of the lower lock actuating cylinder retracts, and the lower lock is opened. On one hand, the hydraulic control one-way valve is opened to enable oil return of the cabin door actuator cylinder to be communicated, on the other hand, oil enters the retractable actuator cylinder through the flow limiting valve to enable the piston rod to extend out, the undercarriage is retracted, and oil return of the actuator cylinder flows into the oil tank to the valve, the emergency conversion valve, the electro-hydraulic reversing valve and the emergency oil discharge valve. When the undercarriage is folded, the valve is coordinated to be pressed through, and high-pressure oil enters the upper folding cavity of the cabin door actuator cylinder to fold the cabin door. The valve core of the valve enables an oil path from a cavity B (a rear coordination valve cavity) to a cavity A (a front coordination valve cavity) of the coordination valve which is temporarily interrupted originally to be pressed through and flow into a retraction actuator retraction cavity (a rodless cavity) through the speed regulation valve, and the retraction action of a product is finished. At the moment, an upper lock cavity (rodless cavity) of the lower lock actuator cylinder and a lower cavity (rod cavity oil return) of the retractable actuator cylinder are formed, and oil return of the upper lock cavity of the lower lock actuator cylinder flows through the throttle valve, flows through the coordination valve and then flows through the speed regulating valve, and oil return of the lower cavity of the retractable actuator cylinder and then converges into an oil path to flow back to the oil tank. When the actuator cylinder is retracted and released to put down a product (the piston rod is retracted), the retraction action of the piston rod is very slow, the return oil is over-suppressed, no effect is obtained by repeatedly checking the return oil pipeline, adjusting a throttle valve in the return oil pipeline, damping of the actuator cylinder and the like, and then the fault of a coordination valve connected with the actuator cylinder is related through analysis. When the coordination valve soil structure ring folding and unfolding actuating cylinder puts down a product. The hydraulic oil from the electromagnetic valve is divided into two paths, and one path of hydraulic oil flows into the upper lock actuating cylinder to open the upper lock. The other path is divided into two paths, and one path flows through the coordination valve 2. Since the chamber B to the chamber a of the pilot valve 2 is temporarily blocked, the oil circuit is temporarily interrupted. One path of oil flows into a lower cavity (rod cavity) of the retractable actuating cylinder through the speed regulating valve to put down a product, and after the product is put down in place, the cavity B of the coordination valve 2 is pressed to the cavity A, so that the original temporarily interrupted oil path passes through the coordination valve 2 and flows to a lower lock cavity (rodless cavity) of the actuating cylinder to finish the actions of putting down and locking the product. At this time, the return oil of the retraction cavity (rodless cavity) of the retractable actuating cylinder passes through the speed regulating valve and the coordination valve 1 and is opened with the lower lock actuating cylinder. When the product is collected by the retraction actuator cylinder, hydraulic oil from the electromagnetic valve is divided into two paths, one path of hydraulic oil flows into the coordination valve l, and the cavity B of the coordination valve 1 is temporarily blocked from the cavity A. The oil circuit is temporarily interrupted. The other path of oil flows into an unlocking cavity (rod cavity) of the lower lock actuating cylinder through a throttle valve to unlock, and a top rod of the unlocking actuating cylinder presses the top rod after unlocking. When the landing gear retraction handle in the cockpit is arranged at the 'up' position, the hydraulic solenoid valve is switched on, and the piston rod of the main strut guard plate actuator cylinder retracts to enable the strut guard plate to be at the 'up' position. After the main support guard plate is put in place, the undercarriage retraction hydraulic electromagnetic valve is communicated, so that a retraction pipeline of an undercarriage hydraulic system is communicated with a pressure pipeline, a lowering pipeline is communicated with an oil return pipeline, and pressure oil flows to a front undercarriage hydraulic lock and an automatic brake actuating cylinder through a throttle valve to brake the airplane wheel. Meanwhile, pressure oil flows to the main undercarriage hydraulic lock, the uplock unlocking actuator cylinder and the coordination valve, so that the uplock unlocking actuator cylinder is retracted, and when the support is hung on the lock, the uplock is closed. Because of the structural limitation of the coordination valve, oil cannot reach the wheel guard plate actuator cylinder through the coordination valve, and only when the oil from the hydraulic lock enters the upper cavity of the undercarriage retractable actuator cylinder, and the retraction of the undercarriage is finished, the main undercarriage strut presses the ejector rod of the coordination valve, and after the steel ball is ejected by the ejector rod, the oil flows into the upper cavity of the main undercarriage guard plate retractable actuator cylinder through the coordination valve to retract the upper guard plate. When the hydraulic retractable actuating cylinder is retracted, the oil return resistance is large, and the retraction speed is too slow. In order to ensure the reliable opening of the airplane cabin door, the airplane hydraulic system generally supplies pressure to the cabin door upper lock, and supplies pressure to the cabin door actuator cylinder to open the cabin door after the cabin door upper lock is completely unlocked.

One end of the cabin door of the main landing gear is arranged on the engine body structure, the cabin door upper lock is fixed on the upper lock bracket, and when the cabin door is closed, the upper lock hook is locked on the cabin door lock ring. The retraction and release of the landing gear door are realized through electric control and hydraulic drive modes: when an undercarriage down control command is received, the undercarriage control valve is opened, the upper lock actuator cylinder is driven by hydraulic pressure to unlock, the upper lock hook is put down, and the cabin door is opened to the put-down position under the drive of the actuator cylinder. When the door of the main landing gear is folded, the door is closed under the driving of the actuator cylinder, and the tail end of the door drives the lock hook to rotate through the door lock ring, so that locking is realized. When the undercarriage is folded, the valve is coordinated to be pressed through, and high-pressure oil enters the upper folding cavity of the cabin door actuator cylinder to fold the cabin door. It is thus seen that the opening or closing of the landing gear bay doors is closely related to the landing gear retraction and deployment. Due to the fact that the number of the motion mechanisms is large, multiple driving forces are generally coordinated in the system. When the aircraft takes off and lands, the cabin door of the landing gear and the landing gear act according to a certain motion sequence, and the opening and the putting down of the cabin door and the folding and unfolding of the landing gear are realized. Due to the fact that multiple mechanisms are involved to perform coordinated actions, when the retraction of the door of the landing gear is controlled, the phenomenon that the uplock of the door of the landing gear cannot be locked and the door cannot be closed can occur. Usually, the retraction and the release of the landing gear and the cabin door are controlled by a coordination valve and an electromagnetic valve, the cabin door can be firstly put down when the landing gear is put down, then the landing gear is put down, and the coordination valve has the function of a sequence valve, so that the cabin door uplock trigger type coordination valve is a key technology in the coordination installation process of the cabin door. Because the pressure supply control logic on the airplane is relatively complex, the sequential movement sequence exists between the cabin door and the uplock, and if the retraction time and the left and right of the undercarriage are not coordinated, the cabin door of the main undercarriage is abnormal. The main landing gear door is abnormally retracted due to the following two possible reasons: 1) the coordination valve is not sealed, so that the main undercarriage cabin door actuator cylinder is contracted to feed oil in advance, and the steel ball lock is unlocked. Therefore, under the action of the oil return pressure, the door of the main landing gear is abnormally retracted. 2) The one-way valve arranged on the coordinated valve oil return pipeline is not sealed (can not play a one-way role), and the oil leakage pipeline of the coordinated valve is communicated with the main undercarriage cabin door actuator cylinder take-up pipeline under the condition that the coordinated valve is not pressed by the undercarriage take-up and take-down system oil return pipeline. After the handle of the landing gear is pulled back to the neutral position from the 'up' position, the oil ways for retracting and putting down the landing gear are communicated with the oil return way, and the oil return pressure is high when the landing gear falls down, so that the steel ball lock of the actuator cylinder of the cabin door of the main landing gear is abnormally unlocked.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a task is to there is the sequence of successively moving between hatch door and the overhead lock, supply on the aircraft to press the relatively complicated problem of control logic, for the use that simplifies the aircraft and supply to press control logic or reduce sequence valve, make the hatch door have the sequence of successively moving on the aircraft, it is wide to aim at providing a cooperation scope, the higher hatch door overhead lock of reliability triggers formula and coordinates the valve, especially install on the overhead lock of undercarriage hatch door, can accomplish the formula of triggering on the undercarriage hatch door overhead lock of sequence of moving and coordinate the valve.

The utility model provides a technical scheme that its technical problem adopted is: a coordinated overhead door triggered door comprising: the installation interface of installation upper lock has been integrated, and the leading oil feed mouthpiece (1) and the coordinated valve casing of coordinating the valve chamber of leading coordination of radial intercommunication have assembled valve disk seat 6, case 8 in leading coordination valve chamber, have nested depression bar 3 of depression bar reset spring 5, and the system has the end cover 10 of the mouth of pipe that produces oil, its characterized in that: the pressure lever 3 passes through the dust ring 4 and the first sealing ring 2 in sequence, penetrates through the spring seat plate of the valve seat 6 and is assembled on the bearing; the upper lock is linked with a pressure rod 3 through a pressing mechanism, the pressure rod 3 compresses a valve core reset spring 9 through a stepped shaft to drive a valve seat 6, a valve core 8 is sealed, hydraulic oil is controlled to flow out of an oil outlet nozzle, and control logic of sequential movement sequence is completed through a triggered coordination valve.

The utility model discloses compare and have following beneficial effect in prior art:

the utility model discloses an integrated installation superior lock installation interface and system have the coordination valve casing of the oil feed mouthpiece 1 in the leading coordination valve chamber of radial intercommunication, the assembly is at valve disk seat 6 in leading coordination valve chamber, case 8, the depression bar 3 and the rearmounted end cover valve chamber of depression bar reset spring 5 have been suit, compare in traditional valve class control, it is small to coordinate the valve, light in weight, can integrate on other hydraulic products, use superior lock and hatch door as an example, should trigger on valve integration and the superior lock, alright realize the control logic that superior lock and hatch door pressurized cylinder supplied the pressure simultaneously, the weight and the space volume have been reduced when making the last cabin door superior lock hydraulic control of undercarriage on the aircraft obtain simplifying.

The utility model discloses a superior lock exerts the pressing force through pressing mechanism movement track to depression bar 3, depression bar 3 promotes case 8, compression case reset spring 9, separate valve disk seat 6, the valve oilhole that distributes on the 8 conical shell of trigger case, hydraulic fluid passes through hatch door pressurized oil circuit and gets into rearmounted end cover valve chamber, from the export nozzle flow direction hatch door pressurized cylinder, the hatch door is opened to the promotion pressurized cylinder, compression case reset spring 9 and compression case reset spring 5 are under the elastic force effect, press depression bar 3 at initial position, supply pressure simultaneously at realization superior lock and hatch door pressurized cylinder, through installing on the undercarriage hatch door on the lock trigger formula coordinate the valve and accomplish the control logic of precedence motion order. The use of such triggered coordinated flaps simplifies aircraft hydraulic control logic. The coordination valve is triggered by a mechanical structure on the uplock, the triggered coordination valve completes sequential movement sequence, the coordination range is wide, the aircraft pressure supply control logic is simplified or the use of sequence valves is reduced, and the sequential hydraulic pressure and simultaneous pressure supply of the uplock of the landing gear door are realized. And the control reliability is higher than that of the traditional valves.

Drawings

Figure 1 is a cross-sectional view of the landing gear bay door uplock triggered coordinated air flap of the present invention.

Fig. 2 is a schematic diagram of the trigger operating state of fig. 1.

Fig. 3 is a three-dimensional schematic view of fig. 1.

In the figure: 1, 2 first sealing rings of an oil inlet pipe nozzle, 3 pressure rods, 4 dust rings, 5 pressure rod return springs, 6 valve seats, 7 second sealing rings, 8 valve cores, 7 protective rings, 9 valve core return springs, end covers 10, 11 oil outlet pipe nozzles, 12 coordinated valve shells, 13 front coordinated valve cavity nozzles, 14 rear end cover valve cavities, 15 valve oil holes, 16 pressing mechanisms and 17 pressing mechanism movement tracks.

The present invention is further described with reference to the following figures and examples, but the invention is not limited thereby within the scope of the described embodiments. All of these concepts should be considered as within the scope of the present disclosure and the present invention.

Detailed Description

See fig. 1-3. In a preferred embodiment described below, a landing gear door uplock triggered coordinated trap door comprises: the installation interface of installation upper lock has been integrated, and the oil feed mouthpiece 1 and the coordinated valve casing of leading coordinated valve chamber of radial intercommunication assemble at valve disk seat 6, case 8 in leading coordinated valve chamber, the depression bar 3 of having suit depression bar reset spring 5, the system has the end cover 10 of the mouthpiece of producing oil, wherein: and a sealing groove for assembling a second sealing ring 7 is formed outside the valve seat 6, the end cover 10 is butted with the valve seat 6 through the sealing ring, and the second sealing ring 7 is arranged on the excircle of the opening end.

The pressure lever 3 passes through the dust ring 4 and the first sealing ring 2 in sequence, penetrates through the spring seat plate of the valve seat 6 and is assembled on the bearing; the upper lock is linked with the pressure rod 3 through the pressing mechanism under the action of the pressing mechanism 16 by utilizing the action force of the movement track 17 of the pressing mechanism, the oil inlet pipe nozzle 1 supplies pressure, the pressure rod 3 compresses the pressure rod reset spring 5 through the stepped shaft, the valve seat 6 is driven to seal the valve core 8, and the hydraulic oil is controlled to flow from the oil outlet pipe nozzle; when the door upper lock is completely opened, the upper lock applies pressing force to the pressing rod 3 through the movement track of the pressing mechanism, the pressing rod 3 pushes the valve core 8, the valve core return spring 9 is compressed, the valve seat 6 is separated, the valve oil holes distributed on the conical shell of the valve core 8 are triggered, hydraulic oil enters the valve cavity of the rear end cover through the pressure supply oil path of the door actuator cylinder, flows to the door actuator cylinder from the oil outlet pipe nozzle, the actuator cylinder is pushed to open the door, the pressing rod 3 is pressed at the initial position under the action of elastic force of the compression valve core return spring 9 and the valve core return spring 5, the simultaneous pressure supply of the upper lock and the door actuator cylinder is realized, and the control logic of the sequential movement sequence is completed through the triggered coordination valve.

When the oil inlet pipe nozzle 1 is not supplied with pressure, the valve core return spring 9 compresses the valve core 8 and the valve seat 7 tightly, so that the valve seat of the valve and the valve core are prevented from being separated on an airplane due to working conditions such as vibration impact, and the compression bar is pressed at an initial position by the compression bar return spring 5. When the oil inlet pipe nozzle 1 supplies pressure, oil cannot flow out of the oil outlet pipe nozzle due to the sealing effect of the valve seat and the valve core; when the door upper lock is completely opened, the pressure rod 3 is pressed through a mechanical structure on the upper lock, the pressure rod 3 pushes the valve core 8 to be separated from the valve seat 6 of the valve, at the moment, oil in the oil inlet pipe nozzle 1 flows to the door actuator cylinder through the oil outlet pipe nozzle, and the actuator cylinder opens the door.

The scope of the present invention is not limited to the specific embodiments described. Various modifications to these embodiments described above will be readily apparent to those skilled in the art. The general principles defined by the present invention may be implemented in other embodiments without departing from the spirit or scope of the invention. Any technical solutions obtained by performing the same or equivalent replacement on the technical elements in the described specific technical solutions or technical solutions obtained by those skilled in the art without creative efforts based on the described specific technical solutions should be considered to fall within the protection scope of the present invention.

Claims

1. A coordinated overhead door triggered door comprising: the installation interface of installation upper lock has been integrated, and the leading oil feed mouthpiece (1) and the coordinated valve casing of coordinating the valve chamber are coordinated to radial intercommunication, and valve disk seat (6), case (8) of assembly in leading coordinated valve chamber have suit depression bar (3) of depression bar reset spring (5), and the system has end cover (10) of the mouth of pipe of producing oil, its characterized in that: the compression bar (3) penetrates through a spring seat plate of the valve seat (6) through a dustproof ring (4) and a first sealing ring (2) in sequence and is assembled on the bearing; the upper lock is linked with a pressure lever (3) through a pressing mechanism, the pressure lever (3) compresses a valve core reset spring (9) through a stepped shaft to drive a valve seat (6) and seal a valve core (8), hydraulic oil is controlled to flow out from an oil outlet nozzle, and the control logic of the sequence of motion is completed through the triggered coordination valve.

2. The door uplock-triggered coordinated trap as defined in claim 1 wherein: the pressure lever (3) pushes the valve core (8), compresses the valve core reset spring (9) and separates the valve seat (6), hydraulic oil enters the valve cavity of the rear end cover through the valve oil holes distributed on the conical shell and flows to the cabin door actuator cylinder, the actuator cylinder is pushed to open the cabin door, and the control logic of the sequence of motion is completed through the triggered coordination valve.

3. The door uplock-triggered coordinated trap as defined in claim 1 wherein: and a second sealing ring (7) is arranged on the excircle of the opening end of the valve seat (6), and the end cover (10) is butted with the valve seat (6) through the sealing ring.