Mechanical redundant rocket fairing air conditioner connector automatic disengaging device

Abstract

The invention relates to the technical field of aerospace, in particular to a mechanical redundant rocket fairing air conditioner connector automatic disengaging device which comprises an electric push rod, a connecting rod mechanism, a steel wire rope, a connecting rod supporting mechanism, an electric locking and separating mechanism and a connector body. The front end of the electric push rod is fixed to the launching rack, the rear end of the electric push rod is hinged to the front end of the connecting rod mechanism, the rear end of the connecting rod mechanism is connected to the rear end of the steel wire rope, the front end of the steel wire rope is connected to the rear end of the connector body, the front end of the connecting rod supporting mechanism is fixed to the launching rack, and the rear end of the connecting rod supporting mechanism is hinged to the middle of the connecting rod mechanism. And the electric locking and separating mechanism is arranged on the connector main body, the front end of the electric locking and separating mechanism extends into the insertion hole of the mounting flange on the rocket, the electric locking and separating mechanism receives the separating electric signal, and the front end of the electric locking and separating mechanism retracts backwards according to the separating electric signal and is separated from the insertion hole. The air inlet pipe and the connector of the air conditioner can be separated from the fairing easily, and the launching process is not prone to being delayed.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to an automatic detachment device for a mechanically redundant rocket fairing air conditioning connector. Background Technology

[0002] Before launch, the air conditioning intake duct connected to the fairing and the connector connecting the air conditioning intake duct to the fairing need to be separated from the fairing. Currently, during most rocket launches, the separation of the air conditioning intake duct and connector from the fairing requires manual operation at high altitudes, which makes the separation of the air conditioning intake duct and connector from the fairing cumbersome and prone to delaying the launch process.

[0003] Therefore, how to simplify the separation of the air conditioning intake duct and connector from the fairing without delaying the launch process is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] This application provides a mechanically redundant automatic disconnection device for the air conditioning connector of a rocket fairing, which simplifies the separation of the air conditioning inlet duct and connector from the fairing and reduces the likelihood of delaying the launch process.

[0005] To solve the above-mentioned technical problems, this application provides the following technical solution:

[0006] An automatic detachment device for a mechanically redundant rocket fairing air conditioning connector includes: an electric actuator, a linkage mechanism, a steel wire rope, a linkage support mechanism, an electrical locking and separation mechanism, and a connector body. The front end of the electric actuator is fixed to the launch pad, and the rear end of the electric actuator is hinged to the front end of the linkage mechanism. The rear end of the linkage mechanism is connected to the rear end of the steel wire rope, and the front end of the steel wire rope is connected to the rear end of the connector body. The front end of the linkage support mechanism is fixed to the launch pad, and the rear end of the linkage support mechanism is hinged to the middle part of the linkage mechanism. The electrical locking and separation mechanism is mounted on the connector body, and its front end extends into the insertion hole of the rocket mounting flange. When the connector body is separated from the rocket mounting flange, the electrical locking and separation mechanism receives a separation electrical signal and, based on the separation signal, retracts its front end, disengaging from the insertion hole of the rocket mounting flange, thus separating the connector body from the rocket mounting flange.

[0007] In the mechanically redundant rocket fairing air conditioning connector automatic detachment device described above, preferably, the portion of the linkage mechanism near the rear end bends forward, and the rear end of the wire rope is connected to the bent portion of the linkage mechanism.

[0008] In the mechanically redundant rocket fairing air conditioning connector automatic detachment device described above, preferably, the middle part of the steel wire rope is movably connected to the inner end of the pulling support rod, the outer end of the pulling support rod is connected to the launch pad or linkage support mechanism, and the pulling support rod pulls the steel wire rope outward.

[0009] In the mechanically redundant rocket fairing air conditioning connector automatic detachment device described above, preferably, the middle part of the support rod is bent, the inner section of the support rod is pulled inward, and the outer section of the support rod is pulled backward.

[0010] In the mechanically redundant rocket fairing air conditioning connector automatic disengagement device described above, preferably, the front section of the linkage support mechanism extends downward and the rear section of the linkage support mechanism extends rearward; the front section of the linkage support mechanism near the upper part has a channel passing through both sides, the fixing rod of the electric actuator passes through the channel of the linkage support mechanism, and the fixing rod of the electric actuator is supported on the lower surface of the channel.

[0011] In the mechanically redundant rocket fairing air conditioning connector automatic disengagement device described above, preferably, the front section of the linkage support mechanism has a support wing that gradually extends upward from front to back, and the movable rod of the electric actuator is supported on the upper surface of the support wing.

[0012] In the mechanically redundant rocket fairing air conditioning connector automatic detachment device described above, preferably, the left and right sides of the rear end of the connector body are connected to the front end of a steel wire rope, the rear end of each steel wire rope is connected to the rear end of a linkage mechanism, and the front end of each linkage mechanism is connected to the rear end of an electric actuator; the rear section of the linkage support mechanism is divided into left and right linkage support rods, each linkage support rod is hinged to a linkage mechanism, and the front section of the linkage support mechanism has two support wings, with the movable rod of each electric actuator supported on the upper surface of one support wing.

[0013] In the mechanically redundant rocket fairing air conditioning connector automatic detachment device described above, preferably, the two steel wire ropes are converged by a convergence clamp near the rear end.

[0014] As described above, in the mechanically redundant rocket fairing air conditioning connector automatic disengagement device, preferably, the connector body is connected to the end of the rocket mounting flange located outside the fairing; a cover-closing mechanism is provided on the outside of the fairing, the cover-closing mechanism including: a cover body, a torsion spring, a hinge shaft, an upper locking body, a lower locking body, a return pin, and a return spring; the inner surface of the cover body is placed on the upper surface of the connector body, and the upper edge of the cover body is hinged to the outer side of the fairing via the hinge shaft, the torsion spring being fitted onto the hinge... On the shaft, the torsion arm of the torsion spring drives the cover to rotate inward; the upper locking body is fixed to the outer surface of the cover near the lower edge, and the upper locking body has an upper locking hole that runs through the top and bottom; the lower locking body is fixed to the outer side of the fairing, and the lower locking body has a lower locking hole that is recessed from top to bottom; the rebound spring is fitted on the rebound post, and the rebound post passes through the upper locking hole. When the cover rotates to the port of the sealing flange, the rebound spring drives the rebound post to move downward, and its lower end is inserted into the lower locking hole of the lower locking body.

[0015] In the mechanically redundant rocket fairing air conditioning connector automatic disengagement device described above, preferably, the upper surface of the lower locking body is divided into an inclined surface away from the outer side of the fairing, and the inclined surface gradually slopes upward from away from the outer side of the fairing to near the outer side of the fairing; the lower end face of the rebound pin is an inclined end face, and the inclined end face gradually slopes upward from away from the outer side of the fairing to near the outer side of the fairing; during the process of the cover rotating to the port of the sealing flange, the rebound pin moves downward, and the inclined end face of the rebound pin contacts the inclined surface of the lower locking body. Under the action of the inclined surface of the lower locking body, the rebound pin gradually moves upward. After the upper locking hole of the upper locking body is aligned with the lower locking hole of the lower locking body, the rebound spring drives the rebound pin to fall completely and insert into the lower locking hole of the lower locking body.

[0016] Compared to the aforementioned background technology, this application employs a drive mechanism consisting of an electric actuator, a linkage mechanism, and a steel wire rope. The transmission direction between the linkage mechanism and the steel wire rope is bent, thereby reducing the installation space of the drive mechanism. This allows the drive mechanism to adapt to situations where there is insufficient space at the top of the launch pad, enabling it to perform the function of pulling away and recovering the air conditioning intake duct connected to the fairing within a limited space. If any of the electrical locking and separation mechanisms fails to unlock, the tension force generated when the electric actuator retracts is transmitted through the linkage mechanism and, under the action of the steel wire rope's pulling force, can mechanically separate the connector body from the rocket mounting flange. This simplified mechanism and electrical locking and separation mechanism provide redundant design for separating the connector body from the rocket mounting flange, ensuring successful separation. This application replaces the cumbersome manual operation steps required before launch for many existing rocket models and is less likely to delay the launch process. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings.

[0018] Figure 1 This is a schematic diagram of a mechanically redundant rocket fairing air conditioning connector automatic disconnection device.

[0019] Figure 2 This is an opening diagram of the automatic disengagement device and cover closing mechanism for the mechanically redundant rocket fairing air conditioning connector.

[0020] Figure 3 This is a closed diagram of the automatic disengagement device for the rocket fairing air conditioning connector with mechanical redundancy.

[0021] Figure 4 This is a diagram showing the fit of the lock body in the cover closing mechanism;

[0022] Figure 5 This is a schematic diagram of the locking body and the return pin of the cover closing mechanism. Detailed Implementation

[0023] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0024] like Figure 1 As shown, this application provides a mechanically redundant automatic detachment device for a rocket fairing air conditioning connector, comprising: an electric push rod 10, a linkage mechanism 20, a wire rope 30, a linkage support mechanism 40, an electrical locking and separation mechanism 50, and a connector body 60.

[0025] The front end of the electric actuator 10 is fixed to the launcher 200, which supports the actuator 10. The rear end of the electric actuator 10 is hinged to the front end of the linkage mechanism 20. The rear end of the linkage mechanism 20 is connected to the rear end of the wire rope 30, and the front end of the wire rope 30 is connected to the rear end of the connector body 60. Thus, the electric actuator 10 pulls the linkage mechanism 20 to rotate around its hinge point, thereby causing the wire rope 30 to pull the connector body 60 backward. Here, "front" refers to... Figure 1 The direction indicated by the middle arrow, "back" here, is the opposite of "forward".

[0026] Optionally, the portion of the linkage mechanism 20 near its rear end bends forward, and the rear end of the wire rope 30 is connected to the bent portion of the linkage mechanism 20. This facilitates the connection between the rear end of the linkage mechanism 20 and the rear end of the wire rope 30, and also avoids interference between the wire rope 30 and the linkage mechanism 20. Alternatively, a connecting ring 70 is connected to the rear end of the linkage mechanism 20, and the rear end of the wire rope 30 is connected to the connecting ring 70 located at the rear end of the linkage mechanism 20. A connecting ring 70 is also connected to the rear end of the connector body 60, and the front end of the wire rope 30 is connected to the connecting ring 70 located at the rear end of the connector body 60. The connecting ring 70 facilitates the connection between the wire rope 30 and the linkage mechanism 20, as well as the connection between the wire rope 30 and the connector body 60.

[0027] Optionally, the middle portion of the wire rope 30 is movably connected to the inner end of the pull support rod 80, and the outer end of the pull support rod 80 is connected to the launcher 200 or the linkage support mechanism 40. Pulling the support rod 80 pulls the wire rope 30 outward, thereby preventing the wire rope 30 from contacting the air conditioning inlet duct 300 connected to the rear end of the connector body 60, thus avoiding interference with the separation of the connector body 60 from the rocket mounting flange 400 on the fairing. Alternatively, the inner end of the pull support rod 80 is connected to a connecting ring 70, and the middle portion of the wire rope 30 passes through the connecting ring 70 located at the inner end of the pull support rod 80, thereby achieving a movable connection between the middle portion of the wire rope 30 and the inner end of the pull support rod 80. Alternatively, the middle part of the support rod 80 can be bent, and the inner section of the support rod 80 can be extended inward and the outer section of the support rod 80 can be extended backward. This reduces the space occupied by the support rod 80 in the left and right directions, thereby reducing the necessary installation space of the device as a whole. The "left and right" direction mentioned here is the direction perpendicular to the "front and back" direction.

[0028] The front end of the linkage support mechanism 40 is fixed to the launcher 200, and the rear end of the linkage support mechanism 40 is hinged to the middle part of the linkage mechanism 20, so that the hinge point of the linkage mechanism 20 is located in the middle part, and the linkage support mechanism 40 provides support for the linkage mechanism 20.

[0029] Optionally, the front section of the linkage support mechanism 40 extends downward and the rear section extends rearward, making the linkage support mechanism 40 approximately "inverted L" shaped, which facilitates support for the electric actuator 10 and hinge connection with the linkage mechanism 20. Alternatively, the front section of the linkage support mechanism 40 near the top has a channel 41 extending through both sides, through which the fixed rod 11 of the electric actuator 10 passes, and is supported on the lower surface of the channel 41, thus supporting the fixed rod 11 of the electric actuator 10 via the linkage support mechanism 40. Still alternatively, the front section of the linkage support mechanism 40 has a support wing 42 that gradually extends upward from front to rear, with the movable rod 12 of the electric actuator 10 supported on the upper surface of the support wing 42, thus supporting the movable rod 12 of the electric actuator 10 via the linkage support mechanism 40. Alternatively, the upper surface of the support wing 42 may have a downwardly recessed groove, in which the movable rod 12 of the electric actuator 10 is located, thereby limiting the movable rod 12 of the electric actuator 10 and preventing it from falling off the support wing 42.

[0030] In addition, to ensure the smooth separation of the connector body 60 from the mounting flange 400, the left and right sides of the rear end of the connector body 60 are connected to the front end of a steel wire rope 30. To facilitate the connection of the two steel wire ropes 30, the rear end of each steel wire rope 30 is connected to the rear end of a linkage mechanism 20, and the front end of each linkage mechanism 20 is connected to the rear end of an electric actuator 10. Furthermore, to support the two electric actuators 10 and the two linkage mechanisms 20, the rear section of the linkage support mechanism 40 is divided into left and right linkage support rods, each of which is hinged to a linkage mechanism 20; the front section of the linkage support mechanism 40 has two support wings 42, and the movable rod 12 of each electric actuator 10 is supported on the upper surface of one support wing 42.

[0031] In addition, to reduce space occupation, the distance between the two linkage mechanisms 20 and the distance between the two electric actuators 10 need to be set smaller. Therefore, in this application, the two wire ropes 30 are combined near the rear end by a combining clamp 90. That is, they can be combined together first and then separated by a certain distance by the combining clamp 90, so that the distance between the two wire ropes 30 near the rear end is smaller. Optionally, the combining clamp 90 includes a base plate 91 and a cover plate 92; the base plate 91 has a converging post and two separating posts. The two wire ropes 30 are wound around the converging post, thereby converging the two wire ropes 30. The two wire ropes 30 are located on the outside of the two separating posts, thereby separating the two wire ropes 30 by a certain distance; the cover plate 92 is fastened to the side of the base plate 91 with the converging post and the separating post, so that the converging post, the separating post and the wire ropes 30 are surrounded inside.

[0032] An electrical locking and separating mechanism 50 is disposed on the connector body 60, and its front end extends into the insertion hole of the mounting flange 400. When the connector body 60 is to be separated from the mounting flange 400, the electrical locking and separating mechanism 50 receives a separation electrical signal, and its front end retracts backward according to the separation electrical signal, disengaging from the insertion hole of the mounting flange 400, thereby achieving the separation of the connector body 60 from the mounting flange 400. Optionally, multiple electrical locking and separating mechanisms 50 are provided on the connector body 60, and the multiple electrical locking and separating mechanisms 50 are evenly distributed on the connector body 60, thereby making the separation of the connector body 60 from the mounting flange 400 more stable. Alternatively, four electrical locking and separating mechanisms 50 are evenly provided on the connector body 60, which not only makes the separation of the connector body 60 from the mounting flange 400 more stable, but also simplifies the connection between the connector body 60 and the mounting flange 400.

[0033] Based on the above, to ensure successful separation of the connector body 60 from the rocket mounting flange 400, the front end of the connector body 60 is connected to the front end of the pull spring 100, and the rear end of the pull spring 100 is connected to the launcher 200. The pull spring 100 is stretched, thus accelerating the separation of the connector body 60 from the rocket mounting flange 400 during separation, allowing for rapid separation. Optionally, a connecting ring 70 is also connected to the front end of the connector body 60, with the front end of the pull spring 100 connected to the connecting ring 70 located at the front end of the connector body 60, making the installation of the pull spring 100 simple and convenient. Alternatively, connecting rings 70 are provided on both the left and right sides of the front end of the connector body 60, with each connecting ring 70 connected to the front end of a pull spring 100, enabling rapid and stable separation of the connector body 60 from the rocket mounting flange 400.

[0034] When it is necessary for the connector body 60 to separate from the rocket mounting flange 400, the control center sends a separation signal to the electrical locking separation mechanism 50. The electrical locking separation mechanism 50 separates from the rocket mounting flange 400, and simultaneously, the electric push rod 10 retracts, causing the linkage mechanism 20 to rotate. This pulls the connector body 60 and all components on the connector body 60, including the electrical locking separation mechanism 50, backward via the steel wire rope 30, achieving the separation of the connector body 60 from the rocket mounting flange 400. This prevents the connector body 60 from crashing back into the fairing, thus replacing the cumbersome manual operation steps required before launch for many existing launch vehicle models and shortening the launch process. Simultaneously, the elastic force of the pull spring 10 accelerates the separation of the connector body 60 from the mounting flange 400.

[0035] This application employs a drive mechanism consisting of an electric actuator 10, a linkage mechanism 20, and a wire rope 30, and bends the transmission direction between the linkage mechanism 20 and the wire rope 30, thereby folding the installation space of the drive mechanism. This allows the drive mechanism to adapt to situations where there is insufficient space at the top of the launcher 200, thus enabling it to perform the function of pulling out and retrieving the air conditioning inlet duct 300 of the fairing within a limited space.

[0036] If any of the electrical locking and separation mechanisms 50 fails to unlock, the tension force generated when the electric push rod 10 retracts is transmitted through the linkage mechanism 20 and, under the pulling force of the wire rope 30, can mechanically separate the connector body 60 from the rocket mounting flange 400. Thus, through a simple mechanism (electric push rod 10, linkage mechanism 20, and wire rope 30) and the electrical locking and separation mechanism 50, the separation of the connector body 60 from the rocket mounting flange 400 is redundantly designed, thereby ensuring that the connector body 60 from the rocket mounting flange 400 can be successfully separated. This application replaces the cumbersome manual operation steps before the launch of many existing rocket models and is less likely to delay the launch process.

[0037] like Figure 2 and Figure 3 As shown, in order to ventilate the inside of the fairing 500, an installation port that runs through the inside and outside is provided on the fairing 500. The on-arrow mounting flange 400 is inserted into the installation port of the fairing 500. The connector body 60 is connected to the end of the on-arrow mounting flange 400 located on the outside of the fairing 500. In order to close the port of the on-arrow mounting flange 400 on the fairing 500 after the connector body 60 is separated from the on-arrow mounting flange 400 and falls off, the cover mechanism 110 is provided on the outer side of the fairing 500 in this application.

[0038] The closing mechanism 110 includes: a closing cover body 111, a torsion spring 112, a hinge shaft 113, an upper locking body 114, a lower locking body 115, a return pin 116, and a return spring (not shown in the figure). The inner surface of the closing cover body 111 is placed on the upper surface of the connector body 60, where the inner surface of the closing cover body 111 is the side of the closing cover body 111 facing the connector body 60, and the upper edge of the closing cover body 111 is hinged to the outer side of the fairing 500 via the hinge shaft 113. The torsion spring 112 is fitted onto the hinge shaft 113, and the torsion arm of the torsion spring 112 drives the closing cover body 111 to rotate inward, that is, drives the closing cover body 111 to rotate toward the connector body 60, so that the connector body 60 and the... After the mounting flange 400 on the arrow separates and falls off, the cover body 111 closes the port of the mounting flange 400 under the drive of the torsion spring 112; the upper locking body 114 is fixed to the outer surface of the cover body 111 near the lower edge, and the upper locking body 114 has an upper locking hole that runs through the top and bottom; the lower locking body 115 is fixed to the outer side of the fairing 500, and the lower locking body 115 has a lower locking hole that is recessed from top to bottom; the return spring is fitted on the return pin 116, and the return pin 116 passes through the upper locking hole. When the cover body 111 rotates to close the port of the mounting flange 400, the return spring drives the return pin 116 to move downward, so that the lower end of the return pin 116 is inserted into the lower locking hole of the lower locking body 115, thereby achieving locking.

[0039] Optionally, the lower locking hole is a through hole running vertically. Alternatively, as... Figure 4 and Figure 5 As shown, the upper surface of the lower locking body 115, away from the outer side of the fairing 500, is divided into an inclined surface, and this inclined surface gradually slopes upward from the side away from the outer side of the fairing 500 to the side closer to the outer side of the fairing 500; the lower end face of the spring-loaded pin 116 is an inclined end face, and this inclined end face gradually slopes upward from the side away from the outer side of the fairing 500 to the side closer to the outer side of the fairing 500. Thus, during the process of the cover body 111 rotating to close the port of the mounting flange 400, the spring-loaded pin 116 moves downward, and the inclined end face of the spring-loaded pin 116 contacts the inclined surface of the lower locking body 115. Under the action of the inclined surface of the lower locking body 115, the spring-loaded pin 116 will gradually move upward. After the upper locking hole of the upper locking body 114 is aligned with the lower locking hole of the lower locking body 115, the spring-loaded spring drives the spring-loaded pin 116 to fall completely into the lower locking hole of the lower locking body 115, which can play the functions of sealing and preventing opening.

[0040] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0041] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A mechanically redundant automatic disconnection device for the air conditioning connector of a rocket fairing, characterized in that, include: Electric actuator, linkage mechanism, wire rope, linkage support mechanism, electric locking and separation mechanism, and connector body; The front end of the electric actuator is fixed to the launcher, the rear end of the electric actuator is hinged to the front end of the linkage mechanism, the rear end of the linkage mechanism is connected to the rear end of the wire rope, the front end of the wire rope is connected to the rear end of the connector body, the front end of the linkage support mechanism is fixed to the launcher, and the rear end of the linkage support mechanism is hinged to the middle part of the linkage mechanism. The electrical locking and separation mechanism is installed on the connector body, and its front end extends into the insertion hole of the mounting flange on the arrow. When the connector body is separated from the mounting flange on the arrow, the electrical locking and separation mechanism receives the separation electrical signal. According to the separation electrical signal, its front end retracts backward and disengages from the insertion hole of the mounting flange on the arrow, thereby realizing the separation of the connector body from the mounting flange on the arrow.

2. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 1, characterized in that, The part of the linkage mechanism near the rear end bends forward, and the rear end of the wire rope is connected to the bent part of the linkage mechanism.

3. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 1 or 2, characterized in that, The middle part of the wire rope is movably connected to the inner end of the pull support rod, and the outer end of the pull support rod is connected to the launch frame or linkage support mechanism. Pulling the support rod will pull the wire rope outward.

4. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 3, characterized in that, Pull the middle part of the support rod to bend it, and pull the inner section of the support rod to extend inward, and pull the outer section of the support rod to extend backward.

5. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 1 or 2, characterized in that, The front section of the linkage support mechanism extends downward, and the rear section of the linkage support mechanism extends backward. The front section of the linkage support mechanism near the top has a channel that runs through both sides. The fixing rod of the electric actuator passes through the channel of the linkage support mechanism and is supported on the lower surface of the channel.

6. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 5, characterized in that, The front section of the linkage support mechanism has a support wing that gradually extends upward from front to back, and the movable rod of the electric actuator is supported on the upper surface of the support wing.

7. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 1 or 2, characterized in that, The left and right sides of the rear end of the connector body are connected to the front end of a steel wire rope. The rear end of each steel wire rope is connected to the rear end of a linkage mechanism. The front end of each linkage mechanism is connected to the rear end of an electric actuator. The rear section of the linkage support mechanism is divided into two linkage support rods, left and right. Each linkage support rod is hinged to a linkage mechanism. The front section of the linkage support mechanism has two support wings, and the movable rod of each electric actuator is supported on the upper surface of one support wing.

8. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 7, characterized in that, The two wire ropes are combined using a combining clamp near the rear end.

9. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 1 or 2, characterized in that, The connector body is connected to the end of the rocket mounting flange located outside the fairing; A cover-closing mechanism is provided on the outside of the fairing. The cover-closing mechanism includes: a cover body, a torsion spring, a hinge shaft, an upper lock body, a lower lock body, a return pin, and a return spring. The inner surface of the cover is placed on the upper surface of the connector body, and the upper edge of the cover is hinged to the outer side of the fairing via a hinge shaft. A torsion spring is mounted on the hinge shaft, and the torsion arm of the torsion spring drives the cover to rotate inward. The upper locking body is fixed to the outer surface of the cover near the lower edge, and the upper locking body has a through-hole. The lower locking body is fixed to the outer side of the fairing, and the lower locking body has a recessed hole from top to bottom. The spring is fitted onto the spring post, which is inserted into the upper locking hole. When the cover body is rotated to the port of the sealing flange, the spring drives the spring post to move downward, and its lower end is inserted into the lower locking hole of the lower lock body.

10. The automatic disconnection device for the mechanically redundant rocket fairing air conditioning connector according to claim 9, characterized in that, The upper surface of the lower lock body is divided into an inclined surface away from the outer side of the fairing, and the inclined surface gradually slopes upward from away from the outer side of the fairing to near the outer side of the fairing; The lower end face of the rebound column is an inclined end face, and the inclined end face gradually slopes upward from away from the outer side of the fairing to near the outer side of the fairing. During the process of rotating the cover body to close the port of the mounting flange, the spring-loaded pin moves downward and the inclined end face of the spring-loaded pin contacts the inclined surface of the lower lock body. Under the action of the inclined surface of the lower lock body, the spring-loaded pin gradually moves upward. After the upper locking hole of the upper lock body is aligned with the lower locking hole of the lower lock body, the spring-loaded pin is driven to fall completely and insert into the lower locking hole of the lower lock body.

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