CN216745740U - Fairing air conditioner interface and carrier rocket - Google Patents
Fairing air conditioner interface and carrier rocket Download PDFInfo
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- CN216745740U CN216745740U CN202122371978.7U CN202122371978U CN216745740U CN 216745740 U CN216745740 U CN 216745740U CN 202122371978 U CN202122371978 U CN 202122371978U CN 216745740 U CN216745740 U CN 216745740U
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- pipe orifice
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- fairing
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Abstract
The utility model provides a fairing air-conditioning interface and a carrier rocket, wherein the fairing air-conditioning interface comprises: a cover, a pipe orifice and a rotating shaft; the edge of the pipe orifice is fixedly connected with the fairing, and a through hole penetrating through the pipe orifice is formed in the center of the pipe orifice; the opening cover is arranged inside the fairing; the first end of the cover is connected with the first end of the pipe orifice through a rotating shaft, and the cover is used for rotating around the rotating shaft relative to the pipe orifice so as to open or close the through hole in the fairing. This air conditioner interface can effectively reduce the unable risk of closing of air conditioner interface flap.
Description
Technical Field
The utility model relates to the field of carrier rockets, in particular to a fairing air conditioner interface and a carrier rocket.
Background
The carrier rocket fairing air-conditioning interface is used for being connected with a ground air-conditioning pipeline in a launching preparation stage and plugging the air-conditioning interface by adopting a cover after being separated from the ground air-conditioning pipeline. At present, a carrier rocket fairing air conditioner interface is arranged outside a fairing, and a cover has the risk of being incapable of being closed after a ground air conditioner pipeline is separated from the fairing air conditioner interface. If the covering cap can not be effectively closed, the closed environment of the effective load in the fairing can be damaged in the flight process of the carrier rocket, and the covering cap can fall off under the action of vibration and air flow, so that the hidden danger of redundancy is formed. In addition, the external fairing air conditioning interface can form fairing protrusions, which affect the aerodynamic characteristics of the carrier rocket.
In order to reduce the risk that the air conditioner interface cover cannot be closed, it is important to design a fairing air conditioner interface.
Disclosure of Invention
The utility model aims to overcome the defects in the prior art and provides a fairing air conditioner interface and a carrier rocket.
The utility model provides a dome air conditioning interface, comprising: a cover, a pipe orifice and a rotating shaft; the edge of the pipe orifice is used for being fixedly connected with the fairing, and a through hole penetrating through the pipe orifice is formed in the center of the pipe orifice; the opening cover is arranged inside the fairing; the first end of the cover is connected with the first end of the pipe orifice through a rotating shaft, and the cover is used for rotating around the rotating shaft relative to the pipe orifice so as to open or close the through hole in the fairing.
According to one embodiment of the present invention, the second end of the flap is provided with a locking pin; the second end of the nozzle is provided with a locking hole for locking the locking pin when the nozzle cover closes the nozzle.
According to one embodiment of the utility model, at least two lock pin mounting brackets are arranged at the second end of the cover at intervals, two ends of the lock pin are respectively connected with the cover through the two lock pin mounting brackets, and the two ends of the lock pin are slidably connected with the two lock pin mounting brackets.
According to one embodiment of the utility model, further comprising a spring; a circle of bulges are arranged on the lock pin in the circumferential direction between the lock pin mounting frames; the spring is sleeved on the lock pin, one end of the spring props against the bulge, the other end of the spring props against the lock pin mounting rack close to the center of the opening cover, and the spring is used for enabling the lock pin to reset.
According to one embodiment of the utility model, the end of the lock pin remote from the edge of the flap is provided with a split collar for the shaft, which split collar is used to limit the lock pin from coming out of the two lock pin mounting brackets towards the edge of the flap.
According to one embodiment of the utility model, the lock pin is a stepped shaft with a thin shaft at one end and a thick shaft at the other end; the thin shaft of the lock pin is connected with the lock pin mounting bracket close to the center of the cover, and the thick shaft of the lock pin is connected with the lock pin mounting bracket far away from the center of the cover; the spring is sleeved on the thin shaft of the lock pin; the protrusion is formed on the transition end surface of the thin shaft and the thick shaft.
According to an embodiment of the present invention, the second end of the spout is further provided with a sliding groove for guiding the locking pin during the closing of the flap to facilitate the locking pin to enter the locking hole.
According to one embodiment of the utility model, the device further comprises a torsion spring, wherein the torsion spring is sleeved on the rotating shaft; one support arm of the torsion spring is limited through the pipe orifice, and the other support arm of the torsion spring is limited through the opening cover.
According to one embodiment of the utility model, a first end of the opening cover is provided with a limiting groove perpendicular to the axial direction of the rotating shaft, and one arm of the torsion spring is placed in the limiting groove to limit the one arm of the torsion spring; the first end of the pipe orifice is correspondingly provided with a support so as to limit the other support arm of the torsion spring.
Another aspect of the present invention provides a launch vehicle, including the above air-conditioning interface.
According to the air conditioner interface of the fairing, the opening cover is arranged in the fairing, and the opening cover is pushed away towards the interior of the fairing when the ground air conditioner pipeline is connected with the air conditioner interface of the fairing. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the through hole at the pipe orifice is closed by the cover cap. Because the flap is inside opening at the radome fairing, consequently, carrier rocket takes off the back, according to Bernoulli's principle, because the gaseous high-speed flow in the radome fairing outside can make the flap more laminate the mouth of pipe, makes the flap automatic production sealed trend, has reduced because the flap can't seal up the influence to the environment of radome fairing internal payload, has improved the reliability of launching task. Meanwhile, the aerodynamic shape of the carrier rocket is optimized, and the flight control capability of the carrier rocket is improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the utility model and together with the description, serve to explain the principles of the utility model.
FIG. 1 is a perspective view of a launch vehicle fairing according to one embodiment of the utility model;
FIG. 2 is a schematic diagram of a closed and open state of a cover of a cowling air conditioning interface in accordance with an embodiment of the present invention;
FIG. 3 is a schematic view of a closed state of a cover of the cowling air conditioning interface in accordance with one embodiment of the present invention;
FIG. 4 is a cross-sectional view taken along the line C-C of the right side view of FIG. 3;
FIG. 5 is an enlarged view of A in FIG. 4;
fig. 6 is an enlarged view of B in fig. 4.
Description of reference numerals:
the air conditioner comprises a cover 1, a lock pin 2, a spring 3, a split collar 4, a nozzle 5, a torsion spring 6, a rotating shaft 7, a locking hole 51, a sliding groove 52, a fairing 8, an air conditioner interface 9, a lock pin mounting frame 10, an ear plate 11, a limiting groove 12 and a support 13.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not to be construed as limiting the utility model, for the purposes of illustrating the principles of the utility model. Additionally, the components in the drawings are not necessarily to scale. For example, the dimensions of some of the elements or regions in the figures may be exaggerated relative to other elements or regions to help improve understanding of embodiments of the present invention.
The directional terms used in the following description are used in the illustrated directions, and do not limit the specific configurations of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise specified, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood as appropriate to those of ordinary skill in the art.
Furthermore, the terms "comprises," "comprising," "includes," "including," "has," "having" or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a structure or component comprising a list of elements does not include only those elements but may include other mechanical components not expressly listed or inherent to such structure or component. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of additional like elements in the article or device comprising the element.
Spatially relative terms such as "below," "… below," "low," "above," "…," "high," and the like are used for convenience in description to explain the positioning of one element relative to a second element, and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc., and are not particularly meant to imply a sequential or chronological meaning, and should not be taken as limiting. Like terms refer to like elements throughout the description.
In describing the present invention below, it is possible to use only "rockets", "launch vehicles" or "missiles" in a scenario description, which is for convenience of description only and the meaning is not limited to the specific words used. Generally, the launch vehicle of the present invention includes both launch vehicles for carrying satellites or spacecraft or other detectors, and weapons such as missiles, rocket projectiles of all types for carrying military loads, and the like that are capable of delivering payloads into the air. Those skilled in the art, in interpreting the above specific terms, should not be construed as limiting the vehicle to only one of a launch vehicle or a missile, depending on the specific terms used in describing the scenario, thereby narrowing the scope of the present invention.
It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
FIG. 1 is a perspective view of a launch vehicle fairing according to one embodiment of the utility model; FIG. 2 is a schematic diagram of a closed and open state of a cover of a cowling air conditioning interface in accordance with an embodiment of the present invention; FIG. 3 is a schematic view of a closed state of a cover of the cowling air conditioning interface in accordance with one embodiment of the present invention; FIG. 4 is a cross-sectional view taken along the line C-C of the right side view of FIG. 3; FIG. 5 is an enlarged view of A in FIG. 4; fig. 6 is an enlarged view of B in fig. 4.
As illustrated in fig. 1, 2 and 3, the present invention provides a dome air conditioning interface comprising: a cover 1, a nozzle 5 and a rotating shaft 7. The edge of the pipe orifice 5 is fixedly connected with the fairing 8, and the center of the pipe orifice 5 is provided with a through hole penetrating through the pipe orifice 5. Flap 1 sets up inside 8 cowlings, and the first end of flap 1 is connected through pivot 7 with the first end of mouth of pipe 5. The flap 1 is adapted to rotate about a rotation axis 7 relative to the spout 5 to open or close a through hole inside the cowling 8.
Specifically, at present, the air conditioner interface of the carrier rocket fairing is arranged outside the fairing, and the cover plate usually adopts a flap structure and opens or closes the air conditioner interface outside the fairing. When the ground air-conditioning pipeline is connected with the air-conditioning interface of the fairing, the opening cover needs to be opened manually. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover is closed under the action of the torsion spring, and the opening cover is limited to rebound through the tongue spring when closed. However, there is a risk that the flap cannot be closed after the ground air conditioning duct is separated from the cowling air conditioning interface. If the covering cap can not be effectively closed, the closed environment of the effective load in the fairing can be damaged in the flight process of the carrier rocket, and the covering cap can fall off under the action of vibration and air flow, so that the hidden danger of redundancy is formed. In addition, the external fairing air conditioning interface can form fairing protrusions, which affect the aerodynamic characteristics of the carrier rocket.
In this embodiment, the opening cover 1 of the air conditioner interface 8 is arranged inside the fairing 8, and when the ground air conditioner pipeline is connected with the air conditioner interface of the fairing, the opening cover 1 rotates around the rotating shaft 7 to be opened towards the inner direction of the fairing. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover 1 rotates around the rotating shaft 7 to close the through hole of the pipe orifice 5. Because flap 1 is to the inside rotation of radome fairing when opening, so, carrier rocket take off the back, according to bernoulli's principle, because the gaseous high-speed flow in the radome fairing outside can make flap 1 laminate mouth of pipe 5 more, makes flap 1 automatic production sealed trend. The air conditioner interface that this embodiment provided has reduced the unable risk of closing of flap 1, has also consequently reduced because flap 1 can't seal up the influence to the environment of the inside payload of radome fairing, has improved the reliability of launching the task. Meanwhile, the aerodynamic configuration of the carrier rocket is optimized, and the flight control capability of the carrier rocket is improved.
Further, the flap 1 has a plate-shaped structure, and the overall weight of the cowling can be further reduced.
As shown in fig. 4, according to one embodiment of the present invention, the second end of the flap 1 is provided with the locking pin 2, and the second end of the spout 5 is provided with a locking hole 51, the locking hole 51 being used to lock the locking pin 2 when the flap 1 closes the spout 5.
Specifically, as shown in fig. 4, when the ground air-conditioning pipeline is connected with the air-conditioning interface of the fairing, the lock pin 2 is pulled out of the locking hole 51, and the cover cap 1 is pushed towards the interior of the fairing to achieve an open circulation state. After the air-conditioning pipeline is connected with the air-conditioning interface of the fairing, the opening cover 1 is supported by the air-conditioning pipeline to keep an open circulation state. After the ground air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover 1 rotates towards the direction of the pipe orifice 5 around the rotating shaft 7, and the lock pin 2 is inserted into the locking hole 51 to lock the lock pin 2. Locking detent 2, which can reinforce the seal of flap 1 against spout 5.
As shown in fig. 4 and 5, according to an embodiment of the present invention, at least two pin mounting brackets 10 are disposed at intervals at the second end of the door 1, two ends of the pin 2 are respectively connected to the door 1 through the two pin mounting brackets 10, and two ends of the pin 2 are slidably connected to the two pin mounting brackets 10.
As shown in fig. 4 and 5, further, a spring 3 is included. The lock pin 2 is provided with a circle of bulges in the circumferential direction between the lock pin mounting frames 10, and the spring 3 is sleeved on the lock pin 2. Wherein one end of the spring 3 is propped against the bulge, the other end of the spring 3 is propped against the lock pin mounting rack 10 close to the center of the opening cover 1, and the spring 3 is used for resetting the lock pin 2.
Specifically, after the pipeline of the surface air conditioner is separated from the air conditioner interface of the fairing, the opening cover 1 rotates towards the direction of the pipe orifice 5 around the rotating shaft 7, when the opening cover 1 is contacted with the pipe orifice 5 and the opening cover completely closes the pipe orifice 5, the lock pin 2 is moved to the central direction of the opening cover 1 for a certain distance (for example, the lock pin 2 is manually pulled), at the moment, the spring 3 is extruded and deformed, when the lock pin 2 reaches the locking hole, namely, when the opening cover 1 is completely closed, the spring 3 rebounds, the lock pin 2 is reset, one end, far away from the center of the opening cover 1, of the lock pin 2 enters the locking hole, and the lock pin 2 is locked.
In this embodiment, the spring 3 may be a cylindrical compression spring.
As shown in fig. 5, further, the end of the lock pin 2 away from the edge of the flap 1 is provided with a split-ring 4, and the split-ring 4 is used for limiting the lock pin 2 from being separated from the two lock-pin mounting brackets 10 to the edge of the flap 1.
Specifically, when the flap 1 is opened, the lock pin 2 is pulled out of the lock hole 51, and the spring 3 is deformed by compression. After flap 1 opened, spring 3 kick-backs, and split ring 4 supports the lockpin mounting bracket, deviates from flap 1 edge under the effort that the spring rebounded when preventing lockpin 2 from reseing. The circlip 4 may be a circlip for a shaft.
Further, one end, far away from the edge of the opening cover 1, of the lock pin 2 is provided with a check ring clamping groove along the circumferential direction of the lock pin 2, and the check ring clamping groove is a circle of groove and used for installing a split check ring 4.
As shown in fig. 5, the lock pin 2 is a stepped shaft having a thin shaft at one end and a thick shaft at the other end. The thin shaft of the lock pin 2 is connected with a lock pin mounting bracket close to the center of the opening cover 1, and the thick shaft of the lock pin 2 is connected with a lock pin mounting bracket far away from the center of the opening cover 1. The spring 3 is sleeved on the thin shaft of the lock pin 2. The transition end surfaces of the thin shaft and the thick shaft of the lock pin 2 form a bulge.
Specifically, one end of the spring 3 abuts against a bulge formed by the transition end faces of the thin shaft and the thick shaft of the lock pin 2, and the other end abuts against the lock pin mounting rack 10 close to the center of the flap 1. When the lock pin 2 displaces towards the center of the opening cover 1, the spring 3 is extruded and deformed, and after the lock pin 2 is released, the lock pin 2 is reset under the action of the spring 3.
As shown in fig. 6, the second end of the spout 5 is further provided with a slide groove 52 for guiding the locking pin 2 during the closing of the flap 1 to facilitate the locking pin 2 to enter the locking hole 51 according to an embodiment of the present invention.
Further, one end of the lock pin 2, which is far away from the center of the cover 1, is spherical, so that the lock pin 2 can be smoothly displaced towards the center of the cover 1 and locked in the locking hole 51 under the guiding action of the sliding groove 52 after contacting the sliding groove 52.
Specifically, when the flap 1 contacts the spout 5 until the flap completely closes the spout 5, the lock pin 2 enters the lock hole 51 under the guiding action of the slide groove 52, so that the flap 1 closes the spout 5.
As shown in fig. 6, further, a torsion spring 6 is further included. The torsional spring 6 is sleeved on the rotating shaft 7, one support arm of the torsional spring 6 is limited through the pipe orifice 1, and the other support arm of the torsional spring 6 is limited through the opening cover 1.
Specifically, the two arms at the end of the torsion spring 6 may be straight arms or wound in a hook shape. The torsion spring 6 acts in a direction to restrict the opening of the flap 1. After the air-conditioning pipeline is separated from the air-conditioning interface of the fairing, the opening cover 1 rotates towards the direction of the pipe orifice 5 around the rotating shaft 7 under the action of gravity and the torsion spring 6, and when the opening cover 1 contacts the pipe orifice 5 and the opening cover 1 completely closes the pipe orifice 5, the lock pin 2 enters the locking hole 51 under the guiding action of the sliding groove 52, so that the opening cover 1 closes the pipe orifice 5. According to the radome fairing air conditioner interface that this embodiment provided, the flap circles round to the mouth of pipe direction under the combined action of gravity and torsional spring to get into the locking hole and lock under the spout guide effect, can realize that the flap self-closing mouth of pipe.
Further, the first end of flap 1 is provided with the spacing groove of perpendicular to 7 axial directions of pivot, places a cantilever of torsional spring 6 in spacing groove 12 to carry on spacingly to a cantilever of torsional spring 6. The first end of the pipe orifice 5 is correspondingly provided with a support seat 13 so as to limit the other support arm of the torsion spring 6.
Further, the two sides of the first end of the opening cover 1 and the two sides of the first end of the pipe orifice 5 are respectively provided with an ear plate 11 for connecting the opening cover 1 with the pipe orifice 5 through a rotating shaft 7. The limiting groove 12 formed at the first end of the covering cap 1 can be a groove perpendicular to the axial direction of the rotating shaft 7 or formed by two straight plates perpendicular to the axial direction of the rotating shaft 7 at intervals. The seat 13 provided at the first end of the nozzle 5 may be a straight plate parallel to the axial direction of the nozzle 5.
The present embodiment does not limit the number of the torsion springs 6, and may include 2 torsion springs symmetrically installed on both sides of the rotation shaft 7. Correspondingly, the number of the limiting grooves 11 and the abutments 13 is also not limited in this embodiment.
The utility model is described by taking the nozzle and the flap as circular shapes, but the utility model is not limited to the claimed scope. For example, the through hole and the cover of the nozzle are polygonal. Also, the present invention is not limited to the connection between the nozzle and the cowling, and the nozzle and the cowling may be integrally formed. For another example, the entire nozzle is similar to a flange structure, the outer ring of the nozzle is a circular ring, and the inner ring is a circular ring protruding in the axial direction of the circular ring. The outer ring of the pipe orifice is connected with the fairing, and the inner ring of the pipe orifice is connected with the cover in a matched mode to seal the pipe orifice.
In another aspect, the utility model provides a launch vehicle comprising the air conditioning interface. The carrier rocket provided by the utility model has corresponding technical effects due to the fact that the carrier rocket comprises the air conditioning structure.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A dome air conditioning interface, comprising: a cover, a pipe orifice and a rotating shaft;
the edge of the pipe orifice is fixedly connected with the fairing, and a through hole penetrating through the pipe orifice is formed in the center of the pipe orifice; the opening cover is arranged inside the fairing;
the first end of the cover is connected with the first end of the pipe orifice through a rotating shaft, and the cover is used for rotating around the rotating shaft relative to the pipe orifice so as to open or close the through hole in the fairing.
2. An air conditioning interface as set forth in claim 1 wherein said flap second end is provided with a detent; and the second end of the nozzle is provided with a locking hole for locking the locking pin when the nozzle cover closes the nozzle.
3. An air conditioning interface as recited in claim 2 wherein the second end of the door has at least two spaced apart pin mounts, the two ends of the pin are connected to the door by the two pin mounts, respectively, and the two ends of the pin are slidably connected to the two pin mounts.
4. The air conditioning interface of claim 3, further comprising a spring;
a circle of bulges are arranged on the lock pin in the circumferential direction between the lock pin mounting frames;
the spring is sleeved on the lock pin, one end of the spring props against the bulge, the other end of the spring props against the lock pin mounting rack close to the center of the opening cover, and the spring is used for enabling the lock pin to reset.
5. An air conditioning interface as set forth in claim 4 wherein said pin is provided with a shaft circlip at an end of said pin remote from said flap edge, said circlip being adapted to limit said pin from disengaging from said two pin mounts toward said flap edge.
6. The air conditioning interface of claim 5 wherein the latch is a stepped shaft with a thin shaft at one end and a thick shaft at the other end; the thin shaft of the lock pin is connected with the lock pin mounting bracket close to the center of the cover, and the thick shaft of the lock pin is connected with the lock pin mounting bracket far away from the center of the cover; the spring is sleeved on the thin shaft of the lock pin; the protrusion is formed on the transition end surface of the thin shaft and the thick shaft.
7. An air conditioning interface as claimed in any of claims 2 to 6 wherein said second end of said nozzle is further provided with a slide slot for guiding said locking pin during closing of said flap to facilitate entry of said locking pin into said locking hole.
8. The air conditioner interface of claim 7 further comprising a torsion spring disposed about said shaft; one support arm of the torsion spring is limited through the pipe orifice, and the other support arm of the torsion spring is limited through the opening cover.
9. The air conditioner interface of claim 8, wherein the first end of the flap is provided with a limiting groove perpendicular to the axial direction of the rotating shaft, and a leg of the torsion spring is placed in the limiting groove to limit the leg of the torsion spring;
the first end of the pipe orifice is correspondingly provided with a support so as to limit the other support arm of the torsion spring.
10. A launch vehicle comprising an air conditioning interface according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122371978.7U CN216745740U (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface and carrier rocket |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122371978.7U CN216745740U (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface and carrier rocket |
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| Publication Number | Publication Date |
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| CN216745740U true CN216745740U (en) | 2022-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202122371978.7U Active CN216745740U (en) | 2021-09-29 | 2021-09-29 | Fairing air conditioner interface and carrier rocket |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116294841A (en) * | 2023-02-13 | 2023-06-23 | 东方空间技术(山东)有限公司 | Automatic butt joint device for rocket air conditioner winch |
-
2021
- 2021-09-29 CN CN202122371978.7U patent/CN216745740U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116294841A (en) * | 2023-02-13 | 2023-06-23 | 东方空间技术(山东)有限公司 | Automatic butt joint device for rocket air conditioner winch |
| CN116294841B (en) * | 2023-02-13 | 2023-08-11 | 东方空间技术(山东)有限公司 | Automatic butt joint device for rocket air conditioner winch |
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