CN216374981U

CN216374981U - Energy conversion device for multi-medium emergency retraction piston rod

Info

Publication number: CN216374981U
Application number: CN202122771991.1U
Authority: CN
Inventors: 郭智; 匡克焕; 吴通; 金成毅
Original assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Current assignee: SICHUAN LINGFENG AVIATION HYDRAULIC MACHINERY CO Ltd
Priority date: 2021-11-12
Filing date: 2021-11-12
Publication date: 2022-04-26
Anticipated expiration: 2031-11-12

Abstract

The energy conversion device for the multi-medium emergency retraction piston rod can realize redundancy emergency. The utility model is realized by the following technical scheme: the emergency separation component is packaged in a ring groove at the end of the lock pushing sleeve through a sealing ring, the emergency separation component is locked in a lock cavity of the piston rod through a radial lock cap, and the screw rod and screw rod pair drives the piston rod to do linear motion to convert the rotary motion into the linear reciprocating motion of normally retracting the piston rod; under the emergency release state that a transmission mechanism is blocked or the motor cannot normally supply power, a high-pressure emergency medium enters an inner ring cavity formed by the actuating cylinder body and the outer circle of the piston rod from an emergency medium nozzle on a tail pipe of the actuating cylinder body, high-pressure emergency fluid pushes and seals in an emergency release assembly to compress a radial lock cap, the radial lock cap overcomes the outward elasticity of a return spring and is released from the lock cavity of the piston rod, the radial lock cap retracts to release the constraint of the lock cavity, and the high-pressure emergency medium pushes the piston rod to extend rightwards, so that redundancy emergency is realized.

Description

Energy conversion device for multi-medium emergency retraction piston rod

Technical Field

The utility model relates to an emergency release structure applied to an electromechanical actuator, in particular to a structure which can improve the safety of the electromechanical actuator and realize the emergency release of a piston rod by multiple media.

Background

The actuating systems on modern aircraft are four, namely hydraulic, electric, pneumatic and mechanical actuating systems, and the hydraulic transmission device is essentially an energy conversion device. At present, an airborne hydraulic actuating system is widely applied, particularly in the field of flight control, hydraulic pressure is almost completely adopted as power, and a flight control system computer performs telex integrated control to operate control surfaces of an airplane, such as an elevator, a rudder, a flaperon, a horizontal tail and the like, so that control of flight attitude and trajectory is realized, and the performance of the airborne hydraulic actuating system directly influences the overall performance of the airplane, such as maneuverability, safety and reliability and the like. In order to meet the development of the airplane towards high maneuverability, ultrahigh speed and high power in the future, the hydraulic system of the airplane is developing towards high pressure, high power, variable pressure, intellectualization, integration and redundancy. However, the hydraulic actuating system increases the total weight of the flight control system due to the fact that the whole aircraft is fully distributed with hydraulic pipelines, and the efficiency of the traditional aircraft hydraulic system is increasingly highlighted due to high pressure and high power, so that the problems of heat dissipation, reduction of the total fuel efficiency of the aircraft and the like are caused. At present, an airborne hydraulic actuating system becomes a weak link of a flight control system. The cost of the airborne hydraulic actuating system accounts for 42% in the fly-by-wire control system, and the reliability of the airborne hydraulic actuating system becomes a weak link in the fly-by-wire control system, so that a redundancy actuating system has to be adopted, but the redundancy actuating system brings new problems of weight, volume increase and the like. With the development of new materials, motor technologies, control and advanced manufacturing technologies, etc., it is possible to completely eliminate a hydraulic actuation system in an aircraft in the future, and a new type of power Electro-mechanical actuator, such as an Electro-hydrostatic actuator (Electro-hydrostatic actuator) and an Electro-mechanical actuator (EMA), will become a new type of control surface actuator of a flight control system. The electromechanical actuators are not only applied to flight control systems, but also to electric environmental control systems, electric brake systems, electric fuel systems, engine control and other occasions where the aircraft needs to be actuated. After all flight control surfaces of the airplane adopt the integrated electric actuators, fuel oil of the airplane is saved by 5-9% for the passenger plane, meanwhile, 30-50% of ground equipment is reduced, the takeoff weight can be reduced by 600-1000 pounds, and the area of the vulnerable airplane body is reduced by 14%. Research shows that after the flight control surface adopts the integrated electric actuator, the aircraft has a series of advantages because no hydraulic pipeline is distributed over the aircraft body and the integrated actuator easily forms fault-tolerant capability: better reliability, higher viability, better maintainability, higher efficiency and improved airplane performance, and meanwhile, the cost can be greatly saved because fuel oil is reduced and the attendance rate of the airplane is greatly improved. It is with these advantages that the development of power teletype actuators has become necessary. The EHA actuation system comprises a flight control computer, a junction box, an airplane 400Hz power supply (inverter), a power monitoring circuit and an EHA actuator body, wherein the EHA actuator body consists of a motor, a hydraulic pump, a hydraulic oil tank, a detection valve, an oil filter, a release valve, a pipeline and a hydraulic actuator. An EMA actuation system typically includes a flight control computer, a junction box, an aircraft 400Hz power supply, a power control monitoring circuit, and an EMA actuator body. The EMA actuator body is composed of a direct current brushless motor, a ball screw, a microprocessor controller, a position, speed, voltage and current monitoring device and the like. The electromechanical actuator is composed of an electric motor, a hydraulic pump, a hydraulic motor and the like. In addition, some novel actuation principles, such as the linear driving mode of most existing actuating cylinders, can be used for driving the actuating cylinders in a rotating mode by adopting a motor or a hydraulic motor, so that the weight of the system can be reduced and the efficiency can be improved. Ram extension force 59.122 KN-piston rod stroke 57.15mm load 28.134KN load velocity 152.40mm/sec idle velocity l95.58mm/sec dynamic stiffness 49.353. KN/mm response frequency 7Hz (5% load) up to now, flight tests have been carried out with success. The power electro-mechanical actuator is high in reliability, better in maintainability, easier to guarantee and low in life cycle cost compared with a hydraulic actuator used by a current assembly machine, and is proved by a flight test of 10Q0 b. The EHA system has three main components, a triple controller, a dual power platform, and a two-channel actuator. Triple redundant controllers and actuators are integrated, whereas dual redundant power supplies are two separate components. The output mechanism of the system is a two-channel actuator. The neural center of the Ella system architecture "system is a triple redundant controller. In addition, the EACS system adopts a complex Redundancy Management (RM) technology, including redundancy management of hardware and software, wherein the problems to be solved in an important way are operation mode, system reentry and reset, fault identification and reconfiguration and fault recording. In addition, some theoretical problems of the EHA and EMA actuators, such as the problem of fast response control of an EMA closed loop, the problem of control of EHA motor pump integrated design, system simulation and closed loop fast response, the stability certification of the compound regulation of the motor and the hydraulic pump and the fast regulation method, need to be solved, and at present, only the redundant control and system monitoring with one EHA are considered in the EACS which is tried to fly abroad. If all control surfaces of the airplane adopt electric actuators, the tasks of redundant control and system monitoring are more complex, and the public management system of airborne equipment needs to be further researched, and the system structure, the reliability and the comprehensive scheduling management algorithm of electromechanical comprehensive management, flight control comprehensive and comprehensive with an avionics system need to be further researched. With integrated actuators, these functions can be much more complex and difficult to implement than current algorithms using centrally fed hydraulic actuation systems, since each electric actuator is a separate system with redundancy.

The electromechanical actuator is an energy conversion device which is used for realizing the linear reciprocating motion or the swinging motion of less than 360 degrees of a working mechanism and is used as a linear motion executing element. The basic structure of a conventional electric actuator is as follows: the device comprises a motor, a reduction gearbox, a transmission part, a ball screw pair, an outer barrel assembly, a piston rod assembly, a self-locking assembly and the like. An electric actuator cylinder with a self-locking device can prevent the electric actuator cylinder from moving due to external force when stopping moving at a limited position, and is usually locked by a mechanical lock in the actuator cylinder. The mechanical lock is usually in the form of a steel ball lock, and consists of a steel ball, a lock groove, a conical piston, a spring and the like. In some application occasions with higher safety requirements, for example, electromechanical actuators applied to retraction and release of an aircraft landing gear, the actuators are not supported by internal mechanical locks of the actuators, but are supported by heavy loads by external mechanical locks, so that the actuators are required to have certain safety margins, and the landing gear can still be smoothly put down under emergency conditions. The redundancy of a common electromechanical actuator is designed to backup a motor, when a main motor fails, the backup motor works to realize emergency release or retraction of a piston rod, but the structure cannot solve the problem of emergency release or retraction when a screw rod, a gear, a speed reducer and the like are stuck. The conventional dual-redundancy electromechanical actuator still needs to rely on electric power to realize emergency release, and transmission parts such as a lead screw, a gear, a speed reducer and the like cannot work when being blocked.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving the problem that the prior art is difficult to solve the problem that emergency release or retraction is realized when a lead screw, a gear, a speed reducer and the like are stuck, and provides a scheme which is simple in structure and can realize emergency release of a piston rod without depending on electric power so as to solve the problems that the conventional dual-redundancy electromechanical actuator still needs to depend on electric power to realize emergency release and transmission parts such as the lead screw, the gear, the speed reducer and the like cannot work when being stuck, and realize redundancy emergency of different working media.

The technical scheme adopted by the utility model for solving the technical problems is as follows: an energy conversion device for a multi-medium emergency retraction piston rod comprises: connect the screw drive mechanism of redundancy electromechanical actuator motor main shaft, the suit is converted rotary motion into linear reciprocating motion's lead screw 11 in screw-nut 4, makes reciprocating motion's piston rod 10 in actuator cylinder body 2, its characterized in that: the emergency separation component 6 is axially connected in series between the locking and pushing sleeve 3 and a step hole of a hollow piston of the piston rod 10 through sealing rings at two ends, and is packaged in a ring groove at the cylinder end of the locking and pushing sleeve 3 through the sealing rings, the electromechanical actuator is in a normal working state, the emergency separation component 6 is locked in a locking cavity 7 of the piston rod 10 through a radial locking cap 5, and a lead screw 11 and a lead screw pair drive the piston rod 10 to do linear motion through a lead screw nut 4, so that rotary motion is converted into linear reciprocating motion for normally retracting the piston rod 10; under the emergency release state that a transmission mechanism is blocked or the motor cannot normally supply power, a high-pressure emergency medium enters an inner ring cavity formed by the actuating cylinder body 2 and the outer circle of the piston rod 10 from an emergency medium nozzle 1 on a tail pipe of the actuating cylinder body 2, high-pressure emergency fluid pushes and seals in an emergency release assembly 6 to compress a radial lock cap 5, the radial lock cap 5 overcomes the outward elasticity of a return spring 9, the emergency fluid is released from a lock cavity 7 of the piston rod 10, the radial lock cap 5 retracts, the constraint of the lock cavity 7 is removed, the emergency medium is separated to lock the push sleeve 3 and the piston rod 10, and the high-pressure emergency medium pushes the piston rod 10 to extend rightwards, so that redundancy emergency is realized.

Compared with the prior art, the utility model has the following gain effects:

the utility model adopts a screw transmission mechanism connected with a main shaft of a motor, a lead screw 11 sheathed in a lead screw nut 4, a piston rod 10 which reciprocates in an actuating cylinder body 2, the lead screw 11 which drives the piston rod 10 to convert rotary motion into linear reciprocating motion, and an emergency separation component which provides coupling force, and has simple and compact structure.

The utility model adopts high-pressure emergency medium to enter an inner ring cavity formed by the actuating cylinder body 2 and the outer circle of the piston rod 10 from an emergency medium nozzle 1 on a tail pipe of the actuating cylinder body 2, high-pressure emergency fluid pushes a radial lock cap 5 sealed in an emergency separation component 6 to compress the radial lock cap 5, overcomes the outward elasticity of a return spring 9, is separated from a lock cavity 7 of the piston rod 10, the radial lock cap 5 in the emergency separation component 6 retracts to release the constraint of the lock cavity 7, so that the emergency medium is separated from a locking and pushing sleeve 3 and the piston rod 10, the high-pressure emergency medium pushes the piston rod 10 to extend rightwards, therefore, redundancy emergency is realized, the piston rod can be put down in an emergency mode without depending on electric power, and the problem that the conventional dual-redundancy electromechanical actuator still needs to depend on electric power to realize emergency release, and particularly cannot work when transmission parts such as a screw rod, a gear, a speed reducer and the like are stuck.

According to the utility model, the emergency medium unlocking emergency separation component 6 is arranged between the lock push sleeve 3 and the piston rod 10, so that when the electromechanical actuator normally works, the emergency separation component 6 is in a locking state, and the screw nut 4 drives the lock push sleeve 3 in threaded connection with the screw nut to linearly move, so that the piston rod 10 is driven to move. When emergency operation is needed, the emergency medium entering the actuator can push the radial lock cap 5 to be separated from the lock cavity 7, so that unlocking between the piston rod 10 and the lock push sleeve 3 is realized, and the piston rod 10 is pushed out, so that the problem that the conventional electromechanical actuator can only depend on the electromechanical system for emergency operation is solved.

Drawings

FIG. 1 is a structural schematic diagram of an energy conversion device for a multi-medium emergency retraction piston rod in a normal working state;

FIG. 2 is a schematic diagram of the emergency release operating state of FIG. 2;

fig. 3 is an axial cross-sectional view between the emergency disconnect assembly and the piston rod.

In the figure: the emergency hydraulic cylinder comprises an emergency medium nozzle 1, an actuator cylinder body 2, a locking and pushing sleeve 3, a lead screw nut 4, a radial locking cap 5, an emergency disengaging assembly 6, a locking cavity 7, a threaded sleeve 8, a return spring 9, a piston rod 10 and a lead screw 11.

The utility model is further illustrated with reference to the following figures and examples, without thereby limiting the scope of the utility model to the described examples. All such concepts are intended to be within the scope of the present disclosure and the present invention.

Detailed Description

Refer to fig. 1 and 2. In a preferred embodiment described below, a multimedia energy conversion device for emergency retraction of a piston rod comprises: the screw transmission mechanism is connected with a main shaft of a motor of the redundancy electromechanical actuator, a lead screw 11 which is sleeved in the lead screw nut 4 and converts rotary motion into linear reciprocating motion, and a piston rod 10 which reciprocates in the cylinder body 2 of the actuating cylinder. The emergency separation component 6 is axially connected in series between the locking and pushing sleeve 3 and a step hole of a hollow piston of the piston rod 10 through sealing rings at two ends, and is packaged in a ring groove at the cylinder end of the locking and pushing sleeve 3 through the sealing rings, the electromechanical actuator is in a normal working state, the emergency separation component 6 is locked in a locking cavity 7 of the piston rod 10 through a radial locking cap 5, and a lead screw 11 and a lead screw pair drive the piston rod 10 to do linear motion through a lead screw nut 4, so that rotary motion is converted into linear reciprocating motion for normally retracting the piston rod 10; under the emergency release state that a transmission mechanism is blocked or the motor cannot normally supply power, a high-pressure emergency medium enters an inner ring cavity formed by the actuating cylinder body 2 and the outer circle of the piston rod 10 from an emergency medium nozzle 1 on a tail pipe of the actuating cylinder body 2, high-pressure emergency fluid pushes and seals in an emergency release assembly 6 to compress a radial lock cap 5, the radial lock cap 5 overcomes the outward elasticity of a return spring 9, the emergency fluid is released from a lock cavity 7 of the piston rod 10, the radial lock cap 5 retracts, the constraint of the lock cavity 7 is removed, the emergency medium is separated to lock the push sleeve 3 and the piston rod 10, and the high-pressure emergency medium pushes the piston rod 10 to extend rightwards, so that redundancy emergency is realized.

See fig. 3. The emergency disconnect assembly comprises: the thread insert 8 sealed in the ring groove at the cylinder end of the lock push sleeve 3 through the seal ring, the radial lock cap 5 radially extending out of the lock hole at the sleeve end of the thread insert 8 restrains the return spring 9 in the blind hole of the radial lock cap 5, and the return spring 9 provides locking force for the radial lock cap 5.

The sleeve end of the threaded sleeve 8 is provided with a sealing ring groove of the sealing radial lock cap 5, and the sealing ring groove seals the radial lock cap 5 through a sealing ring.

The end plane of the thread sleeve 8 can enter a stepped hole of a piston which is connected with a hollow opening at the tail of the piston rod 10.

The two emergency disengaging assemblies are mirror symmetric about the lead screw 11.

The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the utility model as claimed. The scope of the utility model is defined by the appended claims and equivalents thereof.

Claims

1. An energy conversion device for a multi-medium emergency retraction piston rod comprises: connect the screw drive mechanism of redundancy electromechanical actuator motor main shaft, the suit is converted rotary motion into linear reciprocating motion's lead screw (11) in screw nut (4), makes reciprocating motion's piston rod (10) in actuator cylinder body (2), its characterized in that: the emergency separation component (6) is axially connected in series between the locking and pushing sleeve (3) and the step hole of the hollow piston of the piston rod (10) through sealing rings at two ends, the sealing rings are packaged in a ring groove at the cylinder end of the locking and pushing sleeve (3), the electromechanical actuator is in a normal working state, the emergency separation component (6) is locked in a locking cavity (7) of the piston rod (10) through a radial locking cap (5), a lead screw pair of a lead screw (11) drives the piston rod (10) to make linear motion through a lead screw nut (4), and rotary motion is converted into linear reciprocating motion for normally retracting the piston rod (10); under the emergency release state that a transmission mechanism is blocked or the motor cannot normally supply power, a high-pressure emergency medium enters an inner ring cavity formed by an actuating cylinder body (2) and the outer circle of a piston rod (10) from an emergency medium nozzle (1) on a tail pipe of the actuating cylinder body (2), high-pressure emergency fluid pushes and seals in an emergency separation assembly (6), a radial lock cap (5) is compressed, outward elasticity of a return spring (9) is overcome, the high-pressure emergency medium is separated from the lock cavity (7) of the piston rod (10), the radial lock cap (5) retracts, constraint of the lock cavity (7) is removed, the emergency medium is separated from a lock push sleeve (3) and the piston rod (10), and the high-pressure emergency medium pushes the piston rod (10) to extend rightwards, so that redundancy emergency is realized.

2. The multi-media energy conversion device for emergency retraction of a piston rod according to claim 1, wherein: the emergency disconnect assembly comprises: the lock is characterized in that a threaded sleeve (8) sealed in a cylinder end annular groove of the lock pushing sleeve (3) through a sealing ring and a radial lock cap (5) radially extending out of a lock hole at the sleeve end of the threaded sleeve (8) are used for restraining a return spring (9) in a radial lock cap (5) n-shaped blind hole, and the return spring (9) provides an upper locking force for the radial lock cap (5).

3. The multi-media energy conversion device for emergency retraction of a piston rod according to claim 2, wherein: the sleeve end of the screw sleeve (8) is provided with a sealing radial locking cap (5) sealing ring groove, and the sealing ring groove seals the radial locking cap (5) through a sealing ring.

4. The multi-media energy conversion device for emergency retraction of a piston rod according to claim 3, wherein: the end plane of the screw sleeve (8) is connected with the stepped hole of the piston in a tail mode.

5. The multi-media energy conversion device for emergency retraction of a piston rod according to claim 1, wherein: the two emergency disengaging assemblies are mirror-symmetrical about the screw (11).