Four-bar linkage lodging plugging mechanism and method

Abstract

The four-connecting-rod lodging inserting and pulling mechanism comprises a lower base, an upper connecting base and a lodging mechanism, the lodging mechanism is arranged on the lower base, the upper connecting base is arranged on the lodging mechanism, and the lodging mechanism locates forwards and backwards to drive the upper connecting base to move up and down; and the dead point position of the lodging mechanism is utilized to control and complete the action of lodging plugging and pulling, so that the locking device is suitable for being used for specific products with electromagnetic shielding requirements.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft launch control devices, and in particular relates to a four-link lodging plug-in mechanism and method. Background Art

[0002] At present, aircraft launches are mostly carried out using launch boxes or launch tubes, and whether the launch mode is hot launch or cold launch, electronic control is used. The commonly used electronic control launch relies on the signal transmission between the aircraft's own electronic control system and the external remote control system to achieve launch control.

[0003] With the quality requirements of equipment, this remote control launch technology is not applicable to certain specific products with electromagnetic shielding requirements. Such products can only realize the launch control of the aircraft through conventional cable electronic control. By connecting the external cable to the aircraft and keeping it powered on, after completing the launch command and igniting normally, the power between the aircraft and the external cable is disconnected.

[0004] For example, the patent document with publication number CN111106880B discloses a wireless test emission control system and method for an aircraft, the system includes: a ground device and an aircraft device, the ground device is provided with a first communication component and a power emission component; the aircraft device is provided with a second communication component and a power receiving component, the second communication component is used to wirelessly receive the test emission control instruction of the first communication component of the ground device, and transmit it to other devices of the aircraft device; other devices of the aircraft device complete autonomous test emission control according to the test emission control instruction and form a test emission control result, the second communication component wirelessly sends the test emission result to the first communication component; the power receiving component is used to wirelessly receive the electric energy of the power emission component. Emission control is achieved through signal transmission between the electric control system and the external remote control system.

[0005] However, the above-mentioned existing technology cannot be applied to certain specific products with electromagnetic shielding requirements. Therefore, it is necessary to invent a launch technology that can be applied to the above-mentioned specific products with electromagnetic shielding requirements, which can connect the external cable to the aircraft and keep it powered on. After completing the launch command and igniting normally, the power is cut off between the aircraft and the external cable. Summary of the invention

[0006] In view of the problems existing in the prior art, the present invention provides a four-link lodging plug-in and pull-out mechanism and method.

[0007] The present invention is implemented in this way. A four-link inverted plug-in mechanism includes a lower base, an upper connecting seat and a inverted mechanism. The inverted mechanism is arranged on the lower base, and the upper connecting seat is arranged on the inverted mechanism. The inverted mechanism inverts forward and backward to drive the upper connecting seat to move up and down.

[0008] Furthermore, the falling mechanism includes two groups of identical front link assemblies, rear link assemblies and spring link assemblies, the front link assemblies and rear link assemblies are movably connected to the upper connecting seat and the lower base respectively, and one end of the spring link assembly is movably connected to the front link assembly, and the other end is movably connected to the lower base.

[0009] Furthermore, the front connecting rod assembly includes a front movable rod, a first spring and a front fixed rod, the first spring is placed inside the front fixed rod, one end of the front movable rod enters the front fixed rod from the upper end of the front fixed rod and is connected to the first spring, the other end of the front movable rod is connected to the upper connecting seat through an upper hitch pin, and the lower end of the front fixed rod is connected to the lower base through a lower hitch pin.

[0010] Furthermore, the rear connecting rod assembly includes a rear movable rod, a second spring and a rear fixed rod, the second spring is placed inside the rear fixed rod, one end of the rear movable rod enters the rear fixed rod from the upper end of the rear fixed rod and is connected to the second spring, the other end of the rear movable rod is connected to the upper connecting seat through an upper hitch pin, and the lower end of the rear fixed rod is connected to the lower base through a lower hitch pin.

[0011] Furthermore, the spring-link assembly includes a limit rod, a third spring and a moving rod, the limit rod is connected to the front fixed rod through a small hitch pin, the moving rod is connected to the lower base through a small hitch pin, the moving rod is embedded in the limit rod, and the third spring is sleeved on the outside of the limit rod.

[0012] Furthermore, the front fixing rod is an L-shaped connecting piece, which is a stepped connecting rod in the vertical direction and a short cross bar in the horizontal direction. The two end points of the short cross bar are connected to the lower live hitch pin and the small live hitch pin in sequence from left to right.

[0013] Furthermore, the initial connection angle between the short cross bar and the limiting rod is 160° to 175°.

[0014] Furthermore, the angle of 180° between the short cross bar and the limiting rod is the movement dead point position of the spring connecting rod assembly.

[0015] Another object of the present invention is to provide a lodging and plugging method for a four-link lodging and plugging mechanism, wherein the four-link lodging and plugging method is as follows:

[0016] The lower base is fixed to the launch box wall or launch tube wall of the aircraft, the cable plug is fixed to the upper connecting seat by screws, the front connecting rod assembly and the rear connecting rod assembly are kept vertically 90° with the lower base, the upper connecting seat and the cable plug are pushed upward, and the cable plug is docked with the cable socket of the aircraft itself and kept locked;

[0017] When the aircraft is ignited and launched, the aircraft moves forward, driving the cable plug and the upper connecting seat to move forward, and the upper connecting seat drives the lodging mechanism to start the lodging movement;

[0018] Under the action of the forward force, the front link assembly and the rear link assembly of the lodging mechanism rotate forward counterclockwise around the lower hitch pin and lodging, driving the spring link assembly to extend in a straight line. When the movement position of the spring link assembly passes the dead point, the front link assembly and the rear link assembly accelerate the lodging action, driving the upper connecting seat and the cable plug to move downward quickly, and the cable plug is separated from the socket on the aircraft.

[0019] After the lying is completed, the cable plug always remains in the lying state under the elastic force of the third spring, avoiding the launch channel of the aircraft, and completing the lying plugging and unplugging movement.

[0020] Furthermore, the falling speed of the falling mechanism can be adjusted by the elastic force of the third spring, and the falling time is ≤180ms.

[0021] In summary, the beneficial effects of the present invention are:

[0022] (1) The present invention adopts a purely mechanical structure to complete the docking and automatic separation of the cable plug and the socket, and is suitable for use in specific products with electromagnetic shielding requirements. The overall structure has high reliability, good integrity, and light weight. The entire mechanism is mainly fastened by hole-shaft matching and threaded fastening, which is easy to install and adjust.

[0023] (2) The present invention can adjust the lodging time by adjusting the dead point position of the spring connecting rod assembly, and can adjust the lodging speed by adjusting the elastic force of the third spring. The overall structure has high flexibility and a wide range of applications.

[0024] (3) The external dimensions of the structural parts used in the present invention can be adjusted according to the requirements of the product, with a wide range of applications and low production costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for describing the embodiments are briefly introduced below.

[0026] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 yes Figure 1 AA section view;

[0028] Figure 3 yes Figure 1 BB section view;

[0029] Figure 4 It is a structural schematic diagram of the dead point position state of the present invention;

[0030] Figure 5 It is a schematic diagram of the structure of the present invention in a lodging position;

[0031] Figure 6 It is a structural schematic diagram of the upper connecting seat and the cable plug in the present invention in connection state;

[0032] Description of the accompanying drawings: 1-lower base, 2-front connecting rod assembly, 3-rear connecting rod assembly, 4-spring connecting rod assembly, 5-upper connecting seat, 6-upper sliphock pin, 7-lower sliphock pin, 8-small sliphock pin, 9-front movable rod, 10-first spring, 11-front fixed rod, 12-rear movable rod, 13-second spring, 14-rear fixed rod, 15-limit rod, 16-third spring, 17-sports rod, 18-cable plug, 19-screw. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0034] Combination Figures 1 to 6 The figure shows a specific embodiment of a four-link lodging plugging and unplugging mechanism and method provided by the present invention, and the specific contents are as follows:

[0035] The embodiment of the present invention provides a four-link inverted plug-in mechanism, including a lower base 1, an upper connecting seat 5 and an inverted mechanism, wherein the inverted mechanism is arranged on the lower base 1, and the upper connecting seat 5 is arranged on the inverted mechanism. The inverted mechanism inverts forward and backward to drive the upper connecting seat 5 to move up and down. Since the cable plug 18 is installed on the upper connecting seat 5, when the upper connecting seat 5 moves up and down, the cable plug 18 also moves up and down together, thereby realizing the connection and separation of the cable plug and the cable socket of the aircraft itself. The lower base 2 and the upper connecting seat 5 are universal structures, and the external dimensions can be adjusted according to actual product requirements.

[0036] In this embodiment, the lodging mechanism includes two identical front link assemblies 2, rear link assemblies 3 and spring link assemblies 4, the front link assemblies 2 and rear link assemblies 3 are respectively movably connected to the upper connecting seat 5 and the lower base 1, one end of the spring link assemblies 4 is movably connected to the front link assemblies 2, and the other end is movably connected to the lower base 1. The use of two identical front link assemblies 2, rear link assemblies 3 and spring link assemblies 4 ensures the stability and stability of the lodging mechanism when it is lodging, so that the upper connecting seat 5 can maintain a horizontal state when moving up and down, and enhances the accuracy of the connection and separation of the cable plug 18 and the aircraft's own cable socket. The front link assemblies 2 and rear link assemblies 3 are connecting assemblies, which can be adjusted according to actual product requirements.

[0037] In this embodiment, the front connecting rod assembly 2 includes a front movable rod 9, a first spring 10 and a front fixed rod 11. The first spring 10 is placed inside the front fixed rod 11. One end of the front movable rod 9 enters the front fixed rod 11 from the upper end of the front fixed rod 11 and is connected to the first spring 10. The other end of the front movable rod 9 is connected to the upper connecting seat 5 through an upper hitch pin 6. The lower end of the front fixed rod 11 is connected to the lower base 1 through a lower hitch pin 7. Through the above-mentioned structural design, under the elastic force of the first spring 10, the front movable rod 9 can be pushed to perform up and down telescopic movements, thereby completing the smooth up and down movement of the upper connecting seat 5, and through the upper hitch pin 6 and the lower hitch pin 7, the connection between the front connecting rod assembly 2 and the upper connecting seat 5 and the lower base 1 is more flexible and not stuck.

[0038] In this embodiment, the rear connecting rod assembly 3 includes a rear movable rod 12, a second spring 13 and a rear fixed rod 14, the second spring 13 is placed inside the rear fixed rod 14, one end of the rear movable rod 12 enters the rear fixed rod 14 from the upper end of the rear fixed rod 14 and is connected with the second spring 13, the other end of the rear movable rod 12 is connected to the upper connecting seat 5 through an upper hitch pin 6, and the lower end of the rear fixed rod 14 is connected to the lower base 1 through a lower hitch pin 7. Through the design of the above structure, under the elastic force of the second spring 13, the rear movable rod 12 can be pushed to perform up and down telescopic movement, thereby cooperating with the front connecting rod assembly to complete the smooth up and down movement of the upper connecting seat 5, and through the upper hitch pin 6 and the lower hitch pin 7, the connection between the front connecting rod assembly 3 and the upper connecting seat 5 and the lower base 1 is more flexible and not stuck, the second spring 13 and the first spring 10 are selected with springs of the same elastic force to ensure the consistency of the front and rear movement, and the elastic force can be adjusted according to actual product requirements.

[0039] In this embodiment, the spring-link assembly 4 includes a limit rod 15, a third spring 16 and a moving rod 17. The limit rod 15 is connected to the front fixed rod 11 through a small hitch pin 8, and the moving rod 17 is connected to the lower base 1 through a small hitch pin 8. The moving rod 17 is embedded in the limit rod 15, and the third spring 16 is sleeved on the outside of the limit rod 15. The spring-link assembly 4 and the front link assembly 2 are connected by a hitch, and the falling speed can be controlled by adjusting the elastic force of the third spring.

[0040] In this embodiment, the front fixed rod 11 is an L-shaped connecting part, which is a stepped connecting rod in the vertical direction and a short cross bar in the horizontal direction. The two end points of the short cross bar are connected to the lower hitch pin 7 and the small hitch pin 8 from left to right in sequence. The lower hitch pin 7 is used to connect the front fixed rod 11 and the lower base 1, and the small hitch pin 8 is used to connect with the limit rod 15 of the spring connecting rod assembly 4. The limit rod 15 is connected to the short cross bar of the front fixed rod 11 to form a certain angle. By controlling the change of the angle, the speed of lodging can be controlled.

[0041] In this embodiment, the initial connection angle between the short cross bar and the limiting rod 15 is 160° to 175°. In the normal standby initial state, the angle is maintained at 170°, so that the third spring 16 can be compressed.

[0042] In this embodiment, the angle between the short cross bar and the limit rod 15 is 180°, which is the dead point position of the spring link assembly 4. When the angle is greater than 180°, the front link assembly 2 and the rear link assembly 3 will accelerate the lodging action. The structural schematic diagram of the four-link lodging plug-in mechanism of the present application at the dead point position is as shown in FIG. Figure 4 As shown, at this time, the connection angle between the short cross bar of the front fixing rod 11 and the limiting rod 15 is 180°.

[0043] The four-link lodging plugging and unplugging method provided by the embodiment of the present invention is specifically as follows:

[0044] The lower base 1 is fixed on the launch box wall or launch tube wall of the aircraft, such as Figure 6 As shown, the cable plug 18 is fixed to the upper connecting seat 5 by screws 19. Under the elastic force of the springs in the front connecting rod assembly 2 and the rear connecting rod assembly 3, the upper connecting seat 5 and the cable plug 18 are pushed upward. At this time, the front connecting rod assembly 2 and the rear connecting rod assembly 3 are kept vertically at 90° with the lower base 1, and the cable plug 18 is docked with the aircraft's own cable socket and kept in a locked state, completing the aircraft cable connection.

[0045] When the aircraft is ignited and launched, the aircraft moves forward, driving the cable plug 18 and the upper connecting seat 5 to move forward, and the upper connecting seat 5 drives the lodging mechanism to start the lodging movement. During this process, the upper connecting seat 5 remains in a horizontal state, and the front connecting rod assembly 2 and the rear connecting rod assembly 3 of the lodging mechanism rotate forward counterclockwise around the lower slipknot pin 6 and lodging, driving the moving rod 17 in the spring connecting rod assembly 4 to perform telescopic linear motion relative to the limit rod 15. When the moving position of the spring connecting rod assembly 4 passes the dead point, the front connecting rod assembly 2 and the rear connecting rod assembly 3 accelerate the lodging action, driving the upper connecting seat 5 and the cable plug 18 to move downward quickly, and the cable plug 18 is separated from the socket on the aircraft;

[0046] After the inversion is completed, the cable plug 18 always remains in the inverted state under the elastic force of the third spring 16, avoiding the launch channel of the aircraft, completing the inverted plug-in movement, and realizing the normal electronic control launch of the aircraft. Figure 5 shown.

[0047] In this embodiment, the lodging speed of the lodging mechanism can be adjusted by the elastic force of the third spring 16, and the lodging time is ≤180ms. The lodging time requirement can be adjusted by adjusting the dead point position of the spring connecting rod assembly 4, such as Figure 5 The figure shows a schematic structural diagram of the four-linkage locking plug-in mechanism of the present application in a locked position. At this time, the angle between the short cross bar of the front fixing bar 11 and the limiting bar 15 is 270°.

[0048] It has been verified that the four-link inverted plug-in and pull-out mechanism in this embodiment satisfies the functions of plugging and fixing the external cable plug in the launch box or launch tube with the aircraft's own cable socket and automatically disengaging the plug during launch. The structure is simple and stable, with high operability, and realizes electronically controlled launch of the aircraft.

[0049] The above description is only a preferred embodiment of the present invention, and does not limit the patent scope of the present invention. All equivalent structural changes made by using the contents of the present invention specification and drawings under the concept of the present invention, or directly / indirectly applied in other related technical fields are included in the patent protection scope of the present invention.

Claims

1. A four-link lodging plug-in mechanism, characterized in that: It comprises a lower base (1), an upper connecting seat (5) and a falling mechanism, wherein the falling mechanism is arranged on the lower base (1), and the upper connecting seat (5) is arranged on the falling mechanism, and the falling mechanism falls forward and backward to drive the upper connecting seat (5) to move up and down.

2. The four-bar lodging plug-in mechanism according to claim 1, characterized in that: The falling mechanism comprises two groups of identical front connecting rod assemblies (2), rear connecting rod assemblies (3) and spring connecting rod assemblies (4); the front connecting rod assemblies (2) and rear connecting rod assemblies (3) are movably connected to the upper connecting seat (5) and the lower base (1) respectively; one end of the spring connecting rod assembly (4) is movably connected to the front connecting rod assembly (2), and the other end is movably connected to the lower base (1).

3. The four-bar lodging plug-in mechanism according to claim 2, characterized in that: The front connecting rod assembly (2) comprises a front movable rod (9), a first spring (10) and a front fixed rod (11); the first spring (10) is placed inside the front fixed rod (11); one end of the front movable rod (9) enters the interior of the front fixed rod (11) from the upper end of the front fixed rod (11) and is connected to the first spring (10); the other end of the front movable rod (9) is connected to the upper connecting seat (5) via an upper hitch pin (6); and the lower end of the front fixed rod (11) is connected to the lower base (1) via a lower hitch pin (7).

4. The four-bar lodging plug-in mechanism according to claim 2, characterized in that: The rear connecting rod assembly (3) comprises a rear movable rod (12), a second spring (13) and a rear fixed rod (14); the second spring (13) is placed inside the rear fixed rod (14); one end of the rear movable rod (12) enters the rear fixed rod (14) from the upper end thereof and is connected to the second spring (13); the other end of the rear movable rod (12) is connected to the upper connecting seat (5) via an upper hitch pin (6); and the lower end of the rear fixed rod (14) is connected to the lower base (1) via a lower hitch pin (7).

5. The four-bar lodging plug-in mechanism according to claim 2, characterized in that: The spring connecting rod assembly (4) comprises a limiting rod (15), a third spring (16) and a moving rod (17); the limiting rod (15) is connected to the front fixed rod (11) via a small hinge pin (8); the moving rod (17) is connected to the lower base (1) via a small hinge pin (8); the moving rod (17) is embedded in the limiting rod (15); and the third spring (16) is sleeved on the outside of the limiting rod (15).

6. The four-bar lodging plug-in mechanism according to claim 3, characterized in that: The front fixing rod (11) is an L-shaped connecting piece, which is a stepped connecting rod in the vertical direction and a short cross bar in the horizontal direction. The two ends of the short cross bar are connected to the lower hitch pin (7) and the small hitch pin (8) in sequence from left to right.

7. The four-bar lodging plug-in mechanism according to claim 6, characterized in that: The initial connection angle between the short cross bar and the limiting rod (15) is 160° to 175°.

8. The four-bar lodging plug-in mechanism according to claim 6, characterized in that: The angle between the short cross bar and the limiting rod (15) is 180°, which is the movement dead point position of the spring connecting rod assembly (4).

9. A method for lodging and plugging of the four-link lodging and plugging mechanism according to any one of claims 1 to 8, characterized in that: The four-link lodging plugging and unplugging method is specifically as follows: The lower base (1) is fixed to the launch box wall or launch tube wall of the aircraft, the cable plug (18) is fixed to the upper connecting seat (5) by means of screws (19), the front connecting rod assembly (2) and the rear connecting rod assembly (3) are kept vertically 90° with the lower base (1), the upper connecting seat (5) and the cable plug (18) are lifted upwards, and the cable plug (18) is docked with the cable socket of the aircraft itself and kept locked; When the aircraft is ignited and launched, the aircraft moves forward, driving the cable plug (18) and the upper connecting seat (5) to move forward, and the upper connecting seat (5) drives the falling mechanism to start falling movement; Under the action of the forward force, the front link assembly (2) and the rear link assembly (3) of the lodging mechanism rotate forward counterclockwise around the lower hitch pin (6) and lodging, driving the spring link assembly (4) to perform a straight-line motion. When the movement position of the spring link assembly (4) passes the dead point position, the front link assembly (2) and the rear link assembly (3) accelerate the lodging action, driving the upper connecting seat (5) and the cable plug (18) to move downward rapidly, and the cable plug (18) is separated from the socket on the aircraft. After the inversion is completed, the cable plug (18) always remains in the inverted state under the elastic force of the third spring (16), avoiding the launch channel of the aircraft, and completing the inverted plugging and unplugging movement.

10. The four-bar lodging plugging and unplugging method according to claim 9, characterized in that: The falling speed of the falling mechanism is adjusted by the elastic force of the third spring (16), and the falling time is ≤180ms.

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