CN216443802U

CN216443802U - Electromechanical signal cross starting mechanism for airplane lifesaving system

Info

Publication number: CN216443802U
Application number: CN202122952406.8U
Authority: CN
Inventors: 崔文博; 刘亮亮; 姜国纯; 莫明珠; 邹凌宇
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2021-11-29
Filing date: 2021-11-29
Publication date: 2022-05-06
Anticipated expiration: 2031-11-29

Abstract

The application provides an electromechanical signal cross-actuating mechanism for an aircraft life saving system, comprising: bearing structure, install rocking arm subassembly and actuator on bearing structure, wherein: the rocker arm assembly includes: the switching rocker arm is provided with a short edge and a long edge, and a preset included angle is formed between the short edge and the long edge; the balance rod is movably arranged in the long edge of the switching rocker arm, and two ends of the balance rod are used for connecting load equipment; the roller is arranged in the middle of the balancing rod, forms a contact point butted with the actuator and can rotate when the actuator pushes; the actuator includes: an actuator housing; the piston rod is arranged in the actuator shell and used for providing motion guidance and providing an air pressure driving area, and the piston rod is limited in the actuator shell through an end cover; the adjustable ejector rod is arranged at the front end of the piston rod, the outer surface of the adjustable ejector rod is matched with the inner thread arranged on the piston rod through the outer thread, and the distance between the adjusting actuator and the roller is adjusted through screwing in or screwing out.

Description

Electromechanical signal cross starting mechanism for airplane lifesaving system

Technical Field

The application belongs to the technical field of airplane lifesaving systems, and particularly relates to an electromechanical signal cross starting mechanism for an airplane lifesaving system.

Background

When important functions such as ejection channel cleaning and the like are realized in the conventional airplane lifesaving system, a control signal of the conventional airplane lifesaving system generally adopts a redundant form of double-channel parallel transmission. Although the reliability of the system task can be guaranteed in this form from the design requirement, the following problems exist:

a) the dual channels are only in a pure parallel relationship, and the equipment and the lines in each signal channel are still in a series relationship, wherein the fault of any one equipment and line can cause the integral failure of the channel, so that the redundancy of the system channel is lost;

b) the airplane lifesaving system is limited by weight and installation space, the redundancy of a channel cannot be increased without limit, and in order to ensure the overall reliability of the system, the reliability of equipment and circuits in the channel can be improved on the basis of a control signal dual-channel, which causes adverse effects on the aspects of cost, service life, development period and the like of related matched products;

c) the signal path of the ejection channel cleaning system of the airplane lifesaving system mainly transmits signals with the same property in parallel, and the signal property comprises modes of compressed gas, mechanical transmission, detonating cord explosion propagation and the like, so that on one hand, the hidden danger of common-mode faults exists, on the other hand, the testability of the signal path is not easy to realize, and the influence is formed on the safety of the lifesaving system.

Disclosure of Invention

It is an object of the present application to provide an electromechanical signal cross activation mechanism for an aircraft rescue system that addresses or mitigates at least one of the problems of the background art.

The technical scheme of the application is as follows: an electromechanical signal cross-activation mechanism for an aircraft life saving system, the cross-activation mechanism comprising: wholly become L form bearing structure, install rocking arm subassembly and the actuator on bearing structure, wherein:

the rocker arm assembly includes:

the switching rocker arm is provided with a short edge and a long edge, and a preset included angle is formed between the short edge and the long edge;

the balance rod is movably arranged in the long edge of the switching rocker arm, and two ends of the balance rod are used for connecting load equipment; and

the roller is arranged in the middle of the balancing rod, forms a contact point butted with the actuator and can rotate when the actuator pushes;

the actuator includes:

an actuator housing;

the piston rod is arranged in the actuator shell and used for providing motion guidance and providing an air pressure driving area, and the piston rod is limited in the actuator shell through an end cover;

the adjustable ejector rod is arranged at the front end of the piston rod, the outer surface of the adjustable ejector rod is matched with the inner thread arranged on the piston rod through the outer thread, and the distance between the actuator and the roller is adjusted through screwing in or screwing out the adjustable ejector rod.

Further, the support structure comprises a horizontal part and a vertical part, and the horizontal part and the vertical part form an L-shaped structure.

Further, the lateral portion has a gap for mounting the rocker arm assembly and the vertical portion has an opening for mounting the actuator.

Furthermore, the switching rocker arm of the rocker arm assembly is rotatably mounted on the supporting structure through a second flat head shaft, and a first clamping washer is arranged on one side or two sides of the switching rocker arm.

Furthermore, a contact plane is arranged on the short side of the switching rocker arm and used for providing a transmission interface of the driving device.

Further, the preset included angle between the short side and the long side of the switching rocker arm is larger than 90 degrees.

Furthermore, the middle part of the balancing rod is provided with a through groove, and the roller is rotatably arranged in the groove through a first flat head shaft.

Furthermore, one side or two sides of the roller are provided with second clamping washers.

Furthermore, a sealing ring is arranged on the outer side of the piston rod and used for sealing the piston rod.

Further, the volume of the inner cavity of the actuator shell and the sectional area of the piston rod are determined according to the driving air pressure condition.

The starting mechanism that this application provided can adapt to the start-up under the drive arrangement effect of different forms to form stable double-circuit and draw the starting machinery signal, realize the cross starting effect between the two starting signal passageways, the reliability is high.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic diagram of an electromechanical signal crossover pneumatic mechanism of the present application.

Fig. 2 is a schematic view of a support structure in an embodiment of the present application.

FIG. 3 is an exploded view of an electromechanical signal crossover pneumatic mechanism in an embodiment of the present application.

Fig. 4 is a schematic view of a switching rocker arm in an embodiment of the present application.

Fig. 5 is a schematic view of a stabilizer bar in an embodiment of the present application.

FIG. 6 is a cross-sectional view of an actuator according to an embodiment of the present application.

FIG. 7 is a schematic diagram of the electromechanical signal crossover pneumatic mechanism of the present application activated in an electrical mode.

FIG. 8 is a schematic diagram of the electromechanical signal crossing pneumatic mechanism of the present application activated in both pneumatic and electric modes.

FIG. 9 is a schematic diagram of the electromechanical signal crossover pneumatic mechanism of the present application activated in pneumatic mode.

Reference numerals:

1-support structure

2-Rocker arm Assembly

21-first clamping washer

22-roller

23-balance bar

24-second clamping washer

25-switching rocker arm

26-first cotter pin

27-first plain shaft

28-second cotter pin

29-second Flat head shaft

3-actuator

31-Adjustable ejector rod

32-lock nut

33-end cap

34-piston rod

35-sealing ring

36-actuator housing

4-fixing bolt

5-fixing nut

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to solve the problems, an electromechanical signal cross starting mechanism of the fighter plane lifesaving system is provided. The mechanism is based on the existing widely used electric ignition detonator or gas generating device, and can also be compatible with other forms of driving energy or equipment such as compressed gas and the like, can output two paths of mechanical signals as long as any one path of signals acts or is effective under the condition of double starting signal input so as to start a lower signal path or equipment to start working, and is provided with an independent starting interface outside the double starting signal input so as to start the lower signal path or equipment to start working under the condition that the double starting signal input is invalid.

As shown in fig. 1, the electromechanical signal cross starting mechanism for the airplane lifesaving system provided by the application comprises a supporting structure 1, a rocker arm assembly 2, an actuator 3, a fixing bolt 4 and a fixing nut 5. The starting mechanism is mounted and integrated on the structural basis that the supporting structure 1 is used as a part, the rocker arm assembly 2 is used as an action conversion part, and the pulling acting force directly given to the rocker arm and the thrust applied by the actuator 3 can be converted into two mechanical pulling acting forces to drive subordinate equipment to work. The related electric ignition detonator or gas generating device adopts mature products on the market, the application only relates to a specific application form, and the specific principle and the product structure do not belong to the scope of the application, so the related electric ignition detonator or gas generating device is not analyzed and described.

As shown in fig. 2, the support structure 1 is an integrated mounting bracket for the various components of the actuator mechanism and constitutes an integral mounting support structure for the actuator mechanism on a mounting platform, which is generally L-shaped, with a transverse portion 11, placed transversely on the left, having clearance for mounting the rocker arm assembly 2, and a vertical portion 12, placed vertically on the right, having an opening 13, the opening 13 being for mounting the actuator 3.

As shown in fig. 3, the rocker arm assembly 2 is mainly composed of a clamp washer 21, a roller 22, a balance bar 23, a clamp washer 24, a relay rocker arm 25, a cotter pin 26, a stub shaft 27, a cotter pin 28, a stub shaft 29, and the like. The rocker arm assembly 2 is integrally connected to a pivot bearing on the support structure 1 by a first clamping washer 21, a cotter pin 28 and a second stub shaft 29, the whole being able to rotate.

As shown in fig. 4, the switching rocker arm 25 is a basic structure of the rocker arm assembly 2, and can rotate integrally and drive the balance bar 23 to act to provide a starting load and a pulling stroke for starting the operation of the subordinate device after being mounted on the supporting structure 1. The switching rocker arm 25 is formed of a short side 251 and a long side 252 with an angle of not less than 90 degrees between the short side 251 and the long side 252, the intersection of the short side 251 and the long side 252 is a through hole for mounting the second stub shaft 29, and the switching rocker arm 25 is mounted on the lateral portion 11 of the support structure 1 via the second stub shaft 29. Wherein a first clamping washer 21 is provided on one or both sides of the switching rocker arm 25 and locked by a cotter pin 28. Contact flats 253 are formed on the short side 251 to provide a drive interface for actuating devices such as air cylinders and rams. The long side 252 has a notch 254 for mounting the roll balance bar 23 and a through hole 255 for mounting the rotation shaft.

As shown in fig. 4, the balance bar 23 has a groove 231 formed through the middle thereof, and the balance bar 23 is fitted into the notch 254 of the switching rocker arm 25 by the second clamp washer 24, the cotter pin 26, and the second stub shaft 27 being connected in series. The balance bar 23 has connection holes 233 at both ends thereof for connecting lower stage load devices, and the balance bar 23 can synchronously move along with the rotation of the transfer rocker arm 25 and can keep balance during the movement along with the transfer rocker arm 25 when the starting loads of the two lower stage load devices are the same.

The roller 22 is mounted in the stabilizer bar groove 231 by passing through the transfer rocker arm 25 and the first head shaft 27 of the stabilizer bar 23 to form a butt contact point between the rocker arm assembly 2 and the actuator 3, and can be rotated to avoid jamming when the actuator 3 pushes.

As shown in fig. 6, the actuator 3 is mainly composed of an adjustable jack 31, a lock nut 32, an end cap 33, a piston rod 34, a packing 35, an actuator housing 36, and the like, and is fixed to the support structure 1 by a fixing bolt 4 and a fixing nut 5.

The actuator housing 36 is an integrated structure of various parts, and its right open end is a connection interface of an electric detonator or a gas generating device in addition to the function of providing mounting and movement guidance of the piston rod 34.

The piston rod 34 is installed in the actuator housing 36 to provide a motion guide and a pneumatic driving area, the left exposed end of the piston rod is used for installing the adjustable push rod 31, the end of the piston rod located inside the piston rod is of a piston structure, and the installation of the sealing ring 35 is realized through a sealing ring installation groove.

End cap 33 is threadably engaged with actuator housing 36 to function to limit the range of travel of piston rod 34.

The adjustable ejector rod 31 is used for adjusting the distance between the actuator 3 and the roller 7, the surface external thread of the adjustable ejector rod 31 is matched with the internal thread on the piston rod 34, and the purpose of reducing and increasing the distance between the actuator 3 and the roller 7 is achieved by screwing in or screwing out the adjustable ejector rod 31. The adjustable mandril 31 is locked on the piston rod 34 through the locking nut 32 after the distance adjustment is completed.

In the embodiment of fig. 6, the actuator housing 36 is of a construction to accommodate the mounting of a threaded citrated electric detonator. The volume of the inner cavity between the internal threaded area (electric detonator installation position) on the right side of the actuator housing 36 to the piston rod 34 and the piston sectional area of the piston rod 34 need to be matched with the driving air pressure condition. In the form of detonator explosion gas drive as shown in fig. 6, the volume of the inner cavity of the actuator housing 36 should be controlled within a relatively small range to maximize the impact effect produced by the detonator explosion gas; if compressed gas is required as the driving power, the active cross-sectional area of piston rod 34 is correspondingly increased.

Fig. 7 shows an application example of starting and transmitting mechanical signals under the gas driving of two-way electric ignition detonators, wherein E1 and E2 are two electric control switches capable of being linked and are respectively used for starting the electric ignition detonators on two actuators. In the embodiment, the form that two electric control switches and two electric ignition detonators share one power supply is adopted, and the power supplies can be respectively prepared under the condition of higher reliability requirement. In the embodiment shown in fig. 7, under the action of an external control instruction, when any one of the two electrical control switches is closed, the other electrical control switch is synchronously driven to be closed, power is supplied to the corresponding electrical ignition detonator, and after the power is supplied, the electrical ignition detonator starts to output gas to drive the piston rod of the actuator to extend. Wherein, any one of the piston rods can be extended to rotate the rocker arm assembly 2 to form two mechanical pulling start signal outputs F3 and F4 for starting the next stage mechanism or access device. When the two paths of electric ignition detonators fail and cannot realize automatic signal transmission, the rocker arm component 2 is directly rotated through the pulling force of the handle at the F2 position, and the same output effect can be achieved. In the equipment maintenance state, the access state can be checked by a mode of measuring the on-off of the circuit after the cable connection of the electric ignition detonator is cut off, or compressed gas can be used for replacing the fuel gas of the electric ignition detonator to check the action performance of the starting mechanism, and the equipment and line states are recovered after the access state check and the action performance check.

Fig. 8 shows an application embodiment of the electric detonator driven by two working mediums, namely fuel gas and compressed gas, wherein one input starting signal is replaced by the compressed gas. When the mechanical drawing device is started, the electric control switch can be closed and the pneumatic valve can be switched simultaneously through linkage operation at F1, gas and compressed gas are respectively output to the actuators corresponding to the respective channels to enable the piston rods of the actuators to extend out, and two paths of mechanical drawing starting signals for starting the next-stage mechanism or channel equipment can also be output.

Fig. 9 shows an application example of two-way compressed gas working medium driving, the basic principle and the working form of the application example are the same as those of the first embodiment and the second embodiment in fig. 7 and 8, and a two-way mechanical drawing starting signal for starting the next-stage mechanism or the access device can also be output.

The utility model provides a starting mechanism can adapt to the start-up under the drive arrangement effect of different forms, and form stable double-circuit and draw starting machine tool signal, realize the cross start effect between the two starting signal passageways, the reliability is high, the system that can also make this mechanism of outfit possesses the modularization equipment basis, corresponding input and output interface equipment are selected as required, build the system architecture fast, this pneumatic mechanism has functional redundancy in addition, under the condition that the input starting signal of normal linkage manipulation totally became invalid, can directly be started by manual operation through independent starting interface, and it is simple, and reliable to constitute equipment.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An electromechanical signal cross activation mechanism for an aircraft life saving system, the cross activation mechanism comprising: a support structure (1) generally L-shaped, a rocker arm assembly (2) and an actuator (3) mounted on the support structure (1), wherein:

the rocker arm assembly (2) comprises:

a switching rocker arm (25) having a short side (251) and a long side (252), the short side (251) and the long side (252) having a predetermined included angle therebetween;

the balance rod (23) is movably arranged in the long side (252) of the switching rocker arm, and two ends of the balance rod (23) are used for connecting load equipment; and

the roller (22) is arranged in the middle of the balance rod (23), and the roller (22) forms a contact point butted with the actuator (3) and can rotate when the actuator (3) pushes;

the actuator (3) includes:

an actuator housing (36);

a piston rod (34) mounted within the actuator housing (36), the piston rod (34) providing a motion guide and providing a pneumatic drive area, the piston rod (34) being retained within the actuator housing (36) by an end cap (33);

the adjustable ejector rod (31) is arranged at the front end of the piston rod (34), the outer surface of the adjustable ejector rod (31) is matched with the inner thread arranged on the piston rod (34) through the outer thread, and the distance between the actuator (3) and the roller (22) is adjusted through screwing in or screwing out the adjustable ejector rod (31).

2. Electromechanical signal cross activation mechanism for an aircraft rescue system according to claim 1, characterized in that the support structure (1) comprises a transverse part (11) and a vertical part (12), the transverse part (11) and the vertical part (12) constituting an L-shaped structure.

3. Electromechanical signal cross activation mechanism for an aircraft lifesaving system according to claim 2 characterized in that the transverse part (11) has clearance for mounting the rocker arm assembly (2) and in that the vertical part (12) has an opening (13) for mounting the actuator (3).

4. Electromechanical signal cross activation mechanism for an aircraft rescue system according to claim 1, characterized in that the adapter rocker arm (25) of the rocker arm assembly (2) is rotatably mounted on the support structure (1) by means of a second flat shaft (29), and that a first clamping washer (21) is provided on one or both sides of the adapter rocker arm (25).

5. Electromechanical signal cross activation mechanism for an aircraft rescue system according to claim 4, characterized in that the short side (251) of the transfer rocker arm (25) has a contact plane (253) for providing a transmission interface for a drive device.

6. Electromechanical signal cross activation mechanism for an aircraft rescue system according to claim 4 or 5, characterized in that the predetermined angle between the short side (251) and the long side (252) of the transfer rocker (25) is larger than 90 degrees.

7. Electromechanical signal cross-actuation mechanism for an aircraft rescue system according to claim 1, characterized in that the balance bar (23) has a through-going recess (231) in its middle, the roller (22) being rotatably arranged in the recess (231) by means of a first flat axle (27).

8. Electromechanical signal cross activation mechanism for an aircraft rescue system according to claim 7, characterized in that the roller (22) is provided with a second clamping washer (24) on one or both sides.

9. Electromechanical signal cross actuation mechanism for an aircraft lifesaving system according to claim 1, characterized in that a sealing ring (35) is provided on the outside of the piston rod (34) for sealing the piston rod.

10. The electromechanical signal cross actuation mechanism for an aircraft rescue system according to claim 1, characterized in that the internal cavity volume of the actuator housing (36) and the piston cross-sectional area of the piston rod (34) are determined in accordance with driving air pressure conditions.