Rocket and loading rack disengagement assisting device

Abstract

The application discloses a rocket and loading rack dismounting and mounting auxiliary device, belonging to the field of rocket launching, comprising: a loading rack, a support frame, an extension device, a pulling device and a limiting device; the support frame is in L-shaped structure, comprising a first support rod and a second support rod; the extension device comprises a movable end capable of changing position; the extension device is fixedly connected with the support frame; the extension device is arranged in parallel with the second support rod; the pulling device is configured to connect a flexible pulling cable between the dismounting and mounting and the movable end of the extension device; the limiting device comprises a limiting mounting seat fixedly connected with the end of the second support rod; the limiting mounting seat comprises a limiting ring for the pulling device to pass through. The application can realize effective dismounting and mounting of the rocket body and the loading rack, and can control the falling path of the dismounting and mounting when the dismounting and mounting is separated from the rocket body, so as to prevent the pulling cable from interfering with the launching support component.

Description

Technical Field

[0001] The present invention relates to the field of rocket launching, and in particular to an auxiliary device for disconnecting and inserting a rocket and a loading frame. Background Art

[0002] Before a rocket is launched, a booster launch support system is required for preliminary transportation and support. The booster launch support system includes a erection frame and a power supply device. The erection frame is mainly used to support the bottom of the rocket before launch to prevent the rocket from tipping over and enable the rocket to maintain its launch posture. The power supply device is used to provide electrical energy to the rocket during launch. Before the rocket is launched into the sky, the power supply device provides electrical energy to the rocket body through a cable. When the rocket is ready to take off into the sky, the cable needs to be disconnected from the rocket body. Specifically, a plug is provided on the rocket body. When providing electrical energy to the rocket body, one end is connected to the cable and the other end is connected to the plug.

[0003] Currently, the cable is disconnected from the rocket body by installing a hydraulic winch on the erection frame, followed by a disconnect cable. One end of the cable is connected to the disconnect plug, and the other end is connected to the hydraulic winch. When the disconnect plug needs to be disconnected from the rocket body, the disconnect plug is automatically disconnected electrically, and power is cut off. Then, the hydraulic winch begins to rotate, driving the disconnect cable to retract, and the cable pulls the disconnect plug away from the plug.

[0004] Invention patent CN 112758352 A has a similar function in an auxiliary removal device for a rocket launcher, including two supports and two pulling ropes. The erection frame is tilted in sequence and then the stripper and plug are separated. Before the rocket is launched, the erection frame is tilted relative to the rocket body, and the stripper is separated from the plug. The pulling rope is used to control the drop path of the stripper. There is no restriction on the movement path of the cable, and the risk of interference between the cable and launch support components such as the load-balancing bracket and clamps cannot be completely avoided. There is a lack of the ability to adapt to deflection during rocket transportation and insurance measures for unexpected situations.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0006] In order to solve the above technical problems, the present application provides a rocket and loading rack disconnection auxiliary device, which can realize the effective disconnection and disconnection of the rocket body and the loading rack before the rocket is launched, and can control the disconnection and falling path when the disconnection and disconnection are separated from the rocket body, to prevent interference between the cable and the launch support components.

[0007] A rocket and loading frame disconnection auxiliary device, comprising:

[0008] loading rack;

[0009] The support frame is L-shaped and comprises a first support rod and a second support rod; the first support rod is fixedly connected with the loading frame; one end of the second support rod is fixedly connected with the first support rod; the other end of the second support rod extends into a preset position close to the rocket body with the plug;

[0010] The telescopic device is fixedly connected with the support frame; the telescopic direction of the telescopic device is the same as the movement direction of the plug disengaging the socket;

[0011] The pulling device is configured to connect the plug disengaging device and the flexible pulling cable at the moving end of the telescopic device;

[0012] The limiting device comprises a limiting ring for limiting the pulling device.

[0013] Preferably, the telescopic device comprises a first telescopic device and a second telescopic device arranged in parallel with each other.

[0014] Preferably, the pulling device comprises a first pulling cable, a second pulling cable and a third pulling cable; the first pulling cable, the second pulling cable and the third pulling cable are fixedly connected at the ends to form a Y-shaped structure; the end of the first pulling cable is fixedly connected with the moving end of the first telescopic device; the end of the second pulling cable is fixedly connected with the moving end of the second telescopic device; the end of the third pulling cable is fixedly connected with the plug disengaging device.

[0015] Preferably, the limiting device further comprises a limiting fixed seat and a limiting adjustment seat; the limiting ring is connected with the limiting fixed seat through the limiting adjustment seat; the limiting adjustment seat is connected with the limiting fixed seat in a sliding manner; the limiting ring is connected with the limiting adjustment seat in a rotating manner.

[0016] Preferably, the device further comprises a proximity switch for detecting whether the plug disengaging device has completed disengagement.

[0017] Preferably, the device further comprises an adjusting device for adjusting the relative angle between the first support rod and the second support rod.

[0018] Preferably, the device further comprises an electromagnet driving device; the electromagnet driving device comprises a counterweight and an electromagnet; the counterweight is fixedly connected with the third pulling cable through a fourth pulling cable; the counterweight is attracted to the lower side of the electromagnet by electromagnetic force.

[0019] Compared with the prior art, the device has at least the following beneficial effects:

[0020] 1、The application can control the falling path when the plug is separated from the rocket body, prevent the cable from interfering with the launch support part, prevent the plug from touching the rocket body during the falling process and causing damage to the rocket body, make the cable fall smoothly to the designated position, and facilitate the cable recovery.

[0021] 2、The twist point position of the plug device can be adjusted, so that the twist point is directly opposite the longitudinal center axis of the rocket body when the plug is inserted into the rocket body, thereby ensuring effective connection of the plug and the socket, and effectively avoiding the situation that the plug is stuck due to the rolling of the rocket body.

[0022] 3、The application includes multiple sets of telescopic devices, which are mutually reserved to ensure that the plug can be separated from the socket.

[0023] 4、The pulling device includes a first pulling cable, a second pulling cable, and a third pulling cable, forming a Y-shaped structure, which effectively avoids the winding problem of the cable.

[0024] 5、The application relies on the support of the support frame to shorten the distance between the hinge point of the pulling device and the socket, effectively reducing the time when the plug is pulled out, improving the pulling-out efficiency, and also reducing the risk of cable winding. BRIEF DESCRIPTION OF DRAWINGS

[0025] Some specific embodiments of the application will be described in detail below with reference to the accompanying drawings, which are exemplary and not limiting. The same reference signs in the drawings indicate the same or similar components or parts. Those skilled in the art should understand that these drawings are not necessarily drawn to scale. In the drawings:

[0026] Fig. 1 is a schematic diagram of the overall mechanism of a rocket and loading rack plug-in auxiliary device embodiment 1 of the application;

[0027] Fig. 2 is a schematic diagram of the structure of a rocket and loading rack plug-in auxiliary device embodiment 1 of the application omitting the loading rack;

[0028] Fig. 3 is a schematic diagram of the structure of a rocket and loading rack plug-in auxiliary device embodiment 2 of the application omitting the loading rack.

[0029] Among the above-mentioned drawings, the following reference signs are included:

[0030] 1, loading rack, 2, telescopic device, 3, support frame, 4, pulling device, 5, plug, 6, fixed seat, 7, limiting device, 8, counterweight, 9, electromagnet.

[0031] 21. First telescopic device, 22. Second telescopic device, 31. First support rod, 32. Second support rod, 41. First pulling cable, 42. Second pulling cable, 43. Third pulling cable, 44. Fourth pulling cable; 71. Position limiting fixing seat, 72. Position limiting adjustment seat; 73. Position limiting ring. DETAILED DESCRIPTION

[0032] To make the purpose, technical solutions, and advantages of this application more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the specific embodiments of this application and the corresponding drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0033] The existing technology generally uses a hydraulic winch installed on the erection frame, followed by a separation wire rope. One end of the separation wire rope is connected to the plug-in connector and the other end is connected to the hydraulic winch. When the plug-in connector needs to be separated from the plug on the rocket body, the plug-in connector and the socket are automatically disconnected electrically, and the hydraulic winch begins to rotate, driving the separation wire rope to retract, and the separation wire rope drives the plug-in connector to detach from the plug.

[0034] When a rocket is transported horizontally, it needs to be placed on a loading rack. Due to the heavy weight of the rocket, both the rocket body and the loading rack may deform during transportation. If the wire rope is too short, the deformation of the rocket body and the loading rack may cause the plug to separate from the socket or cause the plug to be loosely inserted into the socket. If the wire rope is too long, the separation time will be prolonged when the plug is separated from the socket, and the plug may touch the rocket body during the separation process, causing damage, or cause the plug to become entangled with the support frame during the separation process. In addition, the longer the wire rope is, the greater its own weight, which makes it more likely that the plug will fall off the socket or be loosely inserted during horizontal transportation.

[0035] In addition, when the rocket body is placed on the loading rack and during the erection process, the rocket body may roll, causing the plug-out path to be offset from the socket at a certain angle. When the angle exceeds ±3°, the plug-out and the socket will be stuck, resulting in the plug-out being unable to be removed from the socket, affecting the rocket launch.

[0036] Example 1

[0037] like Figs. 1-3 As shown, a rocket and loading frame insertion and removal auxiliary device includes a loading frame 1, a telescopic device 2, a support frame 3, a pulling device 4 and a limiting device 7.

[0038] The support frame 2 is L-shaped structure, including a first support rod 31 and a second support rod 32, the first support rod 31 is fixedly connected with the loading frame 1. The second support rod 32 is fixedly connected with the first support rod 31 at one end, and the other end extends into the preset position close to the rocket body with the plug. The preset position is close to the rocket body, and will not hinder the launch of the rocket. The telescopic device 2 is fixedly connected with the support frame 3 through the fixing seat 6, and the telescopic direction of the telescopic device 2 is the same as the movement direction of the disconnection and plug 5 from the socket. The telescopic device 2 includes a first telescopic device 31 and a second telescopic device 32 which are the same in structure and size, and the first telescopic device 31 and the second telescopic device 32 are arranged in parallel with each other. The first telescopic device 31 and the second telescopic device 32 are preferably electric push rods of the same model. The pulling device 4 is configured as a flexible pulling cable connected between the disconnection and plug 5 and the moving end of the telescopic device 2. The pulling device 4 includes a first pulling cable 41, a second pulling cable 42 and a third pulling cable 43. The first pulling cable 41, the second pulling cable 42 and the third pulling cable 43 are fixedly connected at the end to form a Y-shaped structure. The end of the first pulling cable 41 is fixedly connected with the moving end of the first telescopic device 31, the end of the second pulling cable 42 is fixedly connected with the moving end of the second telescopic device 32, and the end of the third pulling cable 43 is fixedly connected with the disconnection and plug 5.

[0039] The limiting device 7 includes a limiting fixing seat 71, a limiting adjusting seat 72 and a limiting ring 73. The limiting fixing seat 71 is fixedly connected with the end of the second support rod 32. The limiting ring 73 is connected with the limiting fixing seat 71 through the limiting adjusting seat 72. The limiting fixing seat 71 includes not less than two vertically arranged fixed long grooves and one horizontally arranged fixed long groove. The two vertically arranged fixed long grooves are arranged in parallel with each other. The limiting adjusting seat 72 is fixedly connected with the limiting fixing seat 71 through the vertically arranged fixed long grooves by means of bolts. The limiting ring 73 is fixedly connected with the limiting adjusting seat 72 through a bolt penetrating the horizontally arranged fixed long groove. Since there is only one bolt, the limiting ring 73 can rotate around the center of the bolt, so that the limiting ring 73 can be adjusted as a twisting point position, so that when the disconnection and plug 5 is plugged into the socket, the twisting point is directly opposite to the longitudinal center axis of the rocket body, thereby ensuring the effective connection between the disconnection and plug 5 and the socket, and effectively avoiding the situation that the disconnection and plug 5 is stuck with the plug due to the rolling of the rocket body.

[0040] In some embodiments of the present application, a rocket and loading frame disconnection and plug auxiliary device further includes a proximity switch for detecting whether the disconnection and plug 5 has been disconnected from the socket, and the proximity switch is fixedly arranged on the limiting fixing seat 71 or the limiting adjusting seat 72.

[0041] In some embodiments of the present application, a rocket and loading frame disconnection and plug auxiliary device further includes an adjusting device for adjusting the relative angle between the first support rod 31 and the second support rod 32. The adjusting device includes a first part and a second part which are hingedly connected with each other, and the relative position between the first part and the second part can be fixed by means of bolts other than the hinge point.

[0042] Example 2

[0043] The structure of Example 2 is the same as that of Example 1, except that:

[0044] As shown in Fig. 3 The electromagnet driving device includes a counterweight 8 and an electromagnet 9. The electromagnet 9 is fixed to the lower surface of the fixed seat 6, and the counterweight 8 is fixedly connected to the third pulling cable 43 through the fourth pulling cable 44. The counterweight 8 is adsorbed below the electromagnet 9 by electromagnetic force.

[0045] For the purposes of this description, spatially relative terms such as "above", "below", "up", "down", "between", "within", "left", "right", "front", "back", and the like can be used herein for ease of description to describe one element's or feature's relationship to another element(s) or feature(s) as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientations depicted in the figures. For example, if a device is inverted in the figure, a spatially relative term such as "above" or "up" can be interpreted as meaning "below" or "down" in view of the device's inverted orientation with respect to other devices or structures as shown in the figure. The device can also be oriented in the opposite direction (that is, rotated 180 degrees) with respect to the orientation shown in the figure, and the spatially relative terms used herein interpreted accordingly. The terms "first", "second", "third", etc. can be used herein to describe various elements, regions, layers and / or sections but are not intended to be a permanent or absolute nomenclature.

[0046] It is to be noted that the terms used herein are merely for the purpose of describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising", when used in this specification, specify the presence of stated features, steps, operations, elements, components, and / or groups thereof, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and / or groups thereof.

[0047] It should be noted that the terms "first", "second", and so on as used in the specification and the claims, and above-described drawings, are used to distinguish similar objects, and are not necessarily used to describe a particular sequential or chronological order. It should be understood that the data thus used can be interchanged, where appropriate, to refer to an embodiment of the present application described herein in any appropriate order other than those illustrated or otherwise described herein.

[0048] The above merely provides the preferred embodiments of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the principles and technical scope of the present application shall fall into the scope of the present application.

Claims

1. A rocket and loading stand insertion and extraction auxiliary device, which is applied to the rocket transfer, erecting and launching process, characterized in that, The utility model relates to a rocket plug-in and pull-out device, which comprises a loading frame, a supporting frame, a telescopic device, a pulling device, a limiting device and an electromagnet driving device. The supporting frame is L-shaped and comprises a first supporting rod and a second supporting rod. The first supporting rod is fixedly connected with the loading frame. One end of the second supporting rod is fixedly connected with the first supporting rod. The other end of the second supporting rod extends into a preset position close to the rocket body with a plug. The telescopic device is fixedly connected with the supporting frame. The telescopic direction of the telescopic device is the same as the movement direction of the plug-in and pull-out device. The pulling device is configured to connect the plug-in and pull-out device with the moving end of the telescopic device. The limiting device comprises a limiting ring for limiting the pulling device. The telescopic device comprises a first telescopic device and a second telescopic device arranged in parallel with each other. The pulling device comprises a first pulling cable, a second pulling cable and a third pulling cable. The first pulling cable, the second pulling cable and the third pulling cable are fixedly connected at the ends to form a Y-shaped structure.

2. The device as claimed in claim 1, wherein, The end of the first pulling cable is fixedly connected with the moving end of the first telescopic device.

3. The device of claim 1, wherein: The end of the second pulling cable is fixedly connected with the moving end of the second telescopic device. The end of the third pulling cable is fixedly connected with the plug-in and pull-out device. The electromagnet driving device comprises a counterweight iron block and an electromagnet. The counterweight iron block is fixedly connected with the third pulling cable through a fourth pulling cable. The counterweight iron block is adsorbed below the electromagnet by electromagnetic force. The limiting device comprises a limiting fixed seat, a limiting adjustment seat and a limiting ring. The limiting fixed seat is fixedly connected with the end of the second supporting rod. The limiting ring is connected with the limiting fixed seat through the limiting adjustment seat. The limiting fixed seat comprises at least two vertically arranged fixed long grooves and one horizontally arranged fixed long groove. The two vertically arranged fixed long grooves are arranged in parallel with each other. The limiting adjustment seat is fixedly connected with the limiting fixed seat through the vertically arranged fixed long grooves by means of bolts. The limiting ring is fixedly connected with the limiting adjustment seat through the horizontally arranged fixed long groove by means of a bolt. The device further comprises a proximity switch for detecting whether the plug-in and pull-out device is completely pulled out. The device further comprises an adjusting device for adjusting the relative angle between the first supporting rod and the second supporting rod.

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