CN116929161A - Rocket inserting and removing swing rod system - Google Patents
Rocket inserting and removing swing rod system Download PDFInfo
- Publication number
- CN116929161A CN116929161A CN202310789504.5A CN202310789504A CN116929161A CN 116929161 A CN116929161 A CN 116929161A CN 202310789504 A CN202310789504 A CN 202310789504A CN 116929161 A CN116929161 A CN 116929161A
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- Prior art keywords
- rocket
- rod
- swing
- core primary
- swing rod
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- Granted
Links
- 230000008878 coupling Effects 0.000 claims 1
- 238000010168 coupling process Methods 0.000 claims 1
- 238000005859 coupling reaction Methods 0.000 claims 1
- 238000003780 insertion Methods 0.000 abstract description 6
- 230000037431 insertion Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 3
- 230000006978 adaptation Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 239000011435 rock Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Electric Cable Installation (AREA)
Abstract
The invention provides a rocket inserting and removing swing rod system, which comprises a core primary tray fixed on a deck for launching a rocket, wherein the core primary tray is fixed with a core primary rocket; a pilot hole disposed on the core primary rocket; a swing link rotatably connected with the core primary tray; the first end of the swing rod is provided with a guide rod, and the guide rod is inserted into the guide hole to enable the first end of the swing rod to be connected with the core primary rocket; the rod body of the swing rod is connected with the primary core tray through a limiting rod; the rod body of the swing rod is connected with the rocket launching pad through a traction chain; when the rocket is ignited to lift to a preset space-time attitude, the guide rod is separated from the guide hole, the traction chain pulls the swing rod to separate from the core primary rocket along a preset track, and the preset space-time attitude is determined according to the offshore drifting amount of the deck. According to the scheme, the path of the detachment and the insertion can be accurately controlled, the detachment and the insertion, the cable and the rocket are prevented from touching, and the rocket is ensured to be normally launched.
Description
Technical Field
The invention relates to the technical field of rocket launching, in particular to a rocket inserting-removing swing rod system.
Background
Before the rocket is launched, the rocket needs to be connected with a ground detecting and launching system, the ground system provides power for carrying out detection and binding of all the systems, a plug for connecting the rocket with the ground system is called as a plug-out, the plug-out before the rocket is ignited automatically breaks the wired connection with the ground system, and if the plug-out is abnormal, the normal launching of the rocket can be influenced.
In the prior art, the release and insertion are generally carried out in a pneumatic release or mechanical mode, the release mode is required to be provided with a special release device on the rocket, the release direction of the release device cannot be controlled after release and insertion release, the release device is easy to contact with the rocket, and the normal launching of the rocket is disturbed.
Disclosure of Invention
The invention provides a rocket inserting and removing swing rod system, which aims to solve the problem that the removing direction of rocket inserting and removing cannot be controlled.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a rocket trip pendulum system comprising:
a core primary tray fixed on a deck for launching the rocket, wherein the core primary tray is fixed with the core primary rocket;
a pilot hole disposed on the core primary rocket;
a swing link rotatably connected with the core primary tray;
the first end of the swing rod is provided with a guide rod, and the guide rod is inserted into the guide hole to enable the first end of the swing rod to be connected with the core primary rocket;
the rod body of the swing rod is connected with the primary core tray through a limiting rod;
the rod body of the swing rod is connected with the rocket launching pad through a traction chain;
when the rocket is ignited to lift to a preset space-time attitude, the guide rod is separated from the guide hole, the traction chain pulls the swing rod to separate from the core primary rocket along a preset track, and the preset space-time attitude is determined according to the offshore drifting amount of the deck.
Optionally, the first-stage core tray is provided with a fixing hole, a second end of the swing rod is provided with a rotating shaft, and the rotating shaft is inserted into the fixing hole, so that the swing rod is rotationally connected with the first-stage core tray.
Optionally, a first connecting component and a second connecting component are arranged on the rod body of the swing rod; the first end of the limiting rod is fixedly connected with the first connecting component, and the second end of the limiting rod is fixedly connected with the core primary tray.
Optionally, the traction chain includes: a spring and an adjustment chain;
the first end of the spring is fixedly connected with the first end of the adjusting chain, the second end of the spring is fixedly connected with the second connecting component, and the second end of the adjusting chain is fixedly connected with the rocket launching pad.
Optionally, the adjusting chain is wound on a connecting piece on the rocket launching platform, and the length of the adjusting chain is adjusted according to the length of the spring.
Optionally, a fixing frame is fixedly connected to the swing rod, and a groove is formed in the side face of the fixing frame.
Optionally, a cable is disposed in the groove, and the inner diameter of the groove is adapted to the diameter of the cable, so that the cable is clamped in the groove.
Optionally, the cable passes through the first-stage core tray and is fixed on the fixing frame, and the outgoing line direction of the cable is along the tangential direction of the first-stage core tray and deflects a preset angle.
Optionally, a plug is arranged at the end of the cable, and the plug is spliced with a socket on the core primary rocket.
Optionally, the detachment direction of the swing rod is the same as the outgoing line direction of the cable.
The scheme of the invention at least comprises the following beneficial effects:
the scheme of the invention comprises the following steps: a core primary tray fixed on a deck for launching the rocket, wherein the core primary tray is fixed with the core primary rocket; a pilot hole disposed on the core primary rocket; a swing link rotatably connected with the core primary tray; the first end of the swing rod is provided with a guide rod, and the guide rod is inserted into the guide hole to enable the first end of the swing rod to be connected with the core primary rocket; the rod body of the swing rod is connected with the primary core tray through a limiting rod; the rod body of the swing rod is connected with the rocket launching pad through a traction chain; when the rocket is ignited to lift to a preset space-time attitude, the guide rod is separated from the guide hole, the traction chain pulls the swing rod to separate from the core primary rocket along a preset track, and the preset space-time attitude is determined according to the offshore drifting amount of the deck. According to the scheme, when the disengaging and inserting are separated, the motion path is controlled by the swing rod and the traction chain, so that the disengaging and inserting path can be accurately controlled, the disengaging and inserting and the cable are prevented from touching a rocket launching supporting component, the normal launching of a rocket is influenced, and meanwhile, the disengaging and inserting swing rod can smoothly drop to a designated position, and the recovery of devices such as the cable, the disengaging and inserting device is facilitated.
Drawings
FIG. 1 is a front view of a rocket take-off and insertion pendulum system provided by an embodiment of the present invention;
FIG. 2 is a side view of a rocket trip pendulum system provided by an embodiment of the present invention;
fig. 3 is a schematic structural view of a swing link according to an embodiment of the present invention.
Reference numerals illustrate:
1. a guide hole; 2. swing rod; 21. a guide rod; 22. a rotating shaft; 23. a fixing frame; 231. a groove; 24. a first connecting member; 25. a second connecting member; 3. a limit rod; 4. a drag chain; 41. a spring; 42. an adjustment chain; 5. a cable; 51. a plug; 6. a core primary rocket; 7. a core primary tray; 8. rocket launching pad.
Detailed Description
Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
As shown in fig. 1 to 3, an embodiment of the present invention proposes a rocket inserting and removing swing rod system, including:
a core stage tray 7 fixed on a deck for launching the rocket, wherein the core stage tray 7 is fixed with a core stage rocket 6;
a pilot hole 1 provided on the core primary rocket 6;
a swing rod 2 rotatably connected with the core primary tray 7;
the first end of the swing rod 2 is provided with a guide rod 21, and the guide rod 21 is inserted into the guide hole 1 to enable the first end of the swing rod 2 to be connected with the core primary rocket 6;
the rod body of the swing rod 2 is connected with the core primary tray 7 through a limiting rod 3;
the rod body of the swing rod 2 is connected with a rocket launching pad 8 through a traction chain 4;
when the rocket is ignited to lift to a preset space-time attitude, the guide rod 21 is separated from the guide hole 1, the traction chain 4 pulls the swing rod 2 to separate from the core primary rocket 6 along a preset track, and the preset space-time attitude is determined according to the offshore drifting amount of the deck.
In this embodiment, in the preparation stage of launching the rocket at sea, after the rocket is fixed on the deck, the swing rod 2 is adjusted to be in a vertical state, the traction chain 4 is adjusted to enable the spring 41 to be in a stretched state, and the support is provided for the swing rod 2 through the limit rod 3; inserting the guide rod 21 at the top of the swing rod 2 into the guide hole 1 at the tail section of the core primary rocket 6, connecting the swing rod 2 with the core primary rocket 6, connecting the cable 5 with the core primary rocket 6, and supplying power to the core primary rocket 6;
in the rocket ignition and lift-off process, along with the increase of the rocket flying height, the guide rod 21 of the swing rod 2 is automatically separated from the guide hole 1, the traction chain 4 pulls the swing rod 2, so that the plug 51 of the cable 5 is automatically separated from the core primary rocket 6, and the traction chain 4 pulls the swing rod 2 to fall backwards along the gap direction of the adjacent booster, and the plug-out swing rod is recovered. The contact with the rocket during the separation of the plug and the socket is avoided, and the normal emission of the rocket is ensured.
In this embodiment, the space-time attitude of the rocket flight includes: take-off time, take-off altitude, etc. In the process of rocket ignition and lift-off, as the rocket flying height is increased, due to the reaction force of the thrust of the rocket engine, the drift amount appears between the tail section center of the rocket body and the center of the launching platform on the ship, and in the actual test, when the rocket flies to 0.75 seconds, the rocket flying height is 0.1 meter, and the rocket drift amount is 87.83 millimeters; when the rocket flies to 0.89 seconds, the flying height of the rocket is 0.2 meter, and the drift amount of the rocket is 118.3 millimeters; when the rocket flies to 0.99 seconds, the flying height of the rocket is 0.3 meter, and the drift amount of the rocket is 142.6 millimeters;
therefore, the drift amount of the rocket is proportional to the flying height of the rocket, the depth of the guide rod 22 inserted into the guide hole 1 is 70 mm, the time for separating the inserting and the separating of the rocket is 0.75 seconds, and the time for the inserting and the separating of the swing rod is 0.75 seconds.
In an alternative embodiment of the present invention, the core primary tray 7 is provided with a fixing hole 71, the second end of the swing rod 2 is provided with a rotating shaft 22, and the rotating shaft 22 is inserted into the fixing hole 71, so that the swing rod 2 is rotatably connected with the core primary tray 7.
In this embodiment, the bottom of the swing rod 2 is symmetrically provided with a rotating shaft 22, and the rotating shaft 22 is adapted to a fixing hole 71 on the primary core tray 7, and can be inserted into the fixing hole 71, so that the swing rod 2 can rotate by a certain angle, and the effect of controlling the disengaging track of the disengaging swing rod is achieved.
In an alternative embodiment of the present invention, the rod body of the swing rod 2 is provided with a first connecting component 24 and a second connecting component 25; the first end of the limiting rod 3 is fixedly connected with the first connecting component 24, and the second end of the limiting rod 3 is fixedly connected with the core primary tray 7.
In this embodiment, the stop lever 3 may be a hydraulic lever, when the swing lever 2 is erected and connected with the core primary rocket 6, due to the tension of the spring 41, the swing lever 2 may deform, and by supporting the swing lever 2 by the stop lever 3, excessive deformation of the swing lever 2 may be avoided, so that the swing lever 2 is damaged and broken, and the tension of the spring 41 is reduced, which causes that the rocket is ignited and lifted off, and the release and the insertion cannot be separated from the rocket normally.
In an alternative embodiment of the invention, the traction chain 4 comprises: a spring 41 and an adjustment chain 42;
the first end of the spring 41 is fixedly connected with the first end of the adjusting chain 42, the second end of the spring 41 is fixedly connected with the second connecting component 25, and the second end of the adjusting chain 42 is fixedly connected with the rocket launching platform 8.
In an alternative embodiment of the present invention, the adjustment chain 42 is wound around an anchor on the rocket launching pad 8, and the length of the adjustment chain 42 is adjusted according to the length of the spring 41.
In the above embodiment, the traction chain 4 is composed of a spring 41 and an adjustment chain 42; the spring 41 and the adjusting chain 42 are connected through circular hook rings at the end parts and are connected with the swing rod 2 or the rocket launching platform 8 through circular hooks;
the minimum working load of the spring 41 is 60 newtons, the maximum working load is 120 newtons, the working stroke is 600 millimeters, and the spring 41 can generate a tensile force which can meet the requirement of pulling the swing rod 2 to rotate and can bear the acting force generated by the drift amount of a rocket;
after the adjusting chain 42 is fixed with the ground anchor on the rocket launching pad 8, a margin is further provided, so that the length of the adjusting chain 42 can be conveniently adjusted according to the stretching state of the spring 42, the spring 42 is in a normal working load, the spring 42 is prevented from exceeding the maximum working load, and the spring 42 is prevented from being excessively stretched.
The first connecting member 24 and the second connecting member 25 may be circular hole-shaped connectors.
In an alternative embodiment, the adjustment chain 42 is composed of a plurality of quick-connect rings, and the length of the adjustment chain 42 may be adjusted by increasing or decreasing the number of rings.
In an alternative embodiment of the present invention, the swing rod 2 is fixedly connected with a fixing frame 23, and a groove 231 is formed on a side surface of the fixing frame 23.
In an alternative embodiment of the present invention, the cable 5 is disposed in the groove 231, and the inner diameter of the groove 231 is adapted to the diameter of the cable 5, so that the cable 5 is clamped in the groove 231.
In the above embodiment, the fixing frame 23 has an arc structure, and is fixed on the rod body of the swing rod 2 by welding or bonding, and is close to the upper position of the swing rod 2;
the side surface of the fixing frame 23 is provided with a groove 231, the inner diameter of the groove 231 is equal to the diameter of the cable 5, and the cable 5 can be clamped in the groove 231;
and the radian setting of this arc structure is great, makes the crookedness of cable 5 is less than 40 degrees, avoids because of cable 5's bending angle is too big, leads to cable 5 receives extra additional force with the junction of rocket, influences the connection reliability. Therefore, by using the angle setting in this embodiment, the firmness and reliability of the connection between the cable 5 and the rocket can be ensured.
In an alternative embodiment of the present invention, the cable 5 is fixed on the fixing frame 23 through the primary core tray 7, and the outgoing line direction of the cable 5 is along the tangential direction of the primary core tray 7 and is deflected by a predetermined angle.
In this embodiment, the rocket is detachably connected to the tail section of the core primary rocket 6, and the connection point is located at a position 22.5 degrees deviated from the first quadrant of the rocket launching pad 8; the cable 5 passes through a wire outlet hole preset in the primary core tray 7, and the wire outlet direction of the cable 5 is outwards deflected by 40 degrees along the tangential direction of the primary core tray 7.
The wire outlet direction is positioned at the interval position of the two thrusters, the assembly of the core primary rocket and the thrusters is not influenced, and the wire outlet direction has enough space, provides a working area for workers, and is convenient to connect and fix the inserting-removing, swinging rod and the core primary rocket.
In an alternative embodiment of the invention, the end of the cable 5 is provided with a plug 51, the plug 51 being plugged into a socket on the core primary rocket 6.
In this embodiment, after the plug 51 is plugged into the rocket socket, the ground system provides electric energy for the rocket and is connected with the ground test launch control system;
the plug 51 and the socket are provided with a plurality of structures for reinforcing connection, such as locking pins, locking holes, positioning rods, separating grooves and the like;
the design of this embodiment can guarantee that plug 51 and the rocket that take off to insert are well connected, avoids leading to the fact because of the rocket or pendulum rod 2 rocks plug 51 damages or unexpected unblock drops, guarantees that cable 5 can provide the electric energy for the rocket smoothly, reduces the risk that the rocket fails the normal power supply.
In an alternative embodiment of the present invention, the detachment direction of the swing rod 2 is the same as the outgoing direction of the cable 5.
In this embodiment, the detachment direction of the swing rod 2 is the same as the outgoing line direction of the cable 5, and is a direction of deflecting 40 degrees outwards along the tangential direction of the primary core tray 7, and the direction is located at the interval position of two thrusters, when the swing rod 2 is detached from the primary core rocket 6, the swing rod falls backwards under the action of the spring 41, and the backward falling direction and the backward falling position are located at the interval region of the two thrusters, so as to avoid touching the primary core rocket 6 and the thrusters, and ensure the safety of rocket flight.
According to the embodiment of the invention, under the action of 150N tension provided by the spring 41, the deformation amount of the swing rod 2 is 0.06 millimeter, so that the stress intensity of the swing rod 2 meets the working requirement, and the swing rod 2 cannot be excessively deformed, so that the rocket cannot be normally separated when taking off. Affecting rocket launch.
In the rocket inserting and removing swing rod system according to the above embodiment of the present invention, in a preparation stage of launching a rocket on the sea, after the rocket is fixed on a deck, the swing rod 2 is adjusted to be in a vertical state, and a traction chain is adjusted to make the spring 41 be in a stretched state, and at this time, the stop lever 3 provides support for the swing rod 2;
inserting the guide rod 21 at the top of the swing rod 2 into the guide hole 1 at the tail section of the core primary rocket 6, connecting the swing rod 2 with the core primary rocket 6, and connecting the plug 51 of the cable 5 with the socket at the tail section of the core primary rocket 6 to supply electric energy for the rocket;
in the rocket ignition and lift-off process, along with the increase of the rocket flying height, the guide rod 21 of the swing rod 2 is automatically separated from the guide hole 1, the spring 41 pulls the swing rod 2, so that the plug 51 of the cable 5 is automatically separated from the core primary rocket 6, and then the spring 41 pulls the swing rod 2 to fall backwards along the gap direction of the adjacent booster, and the plug-out swing rod is recovered.
The rocket inserting and removing swing rod system can accurately control the falling path of the inserting and removing swing rod, prevent the inserting and removing and the interference of the cable and the emission supporting component, enable the inserting and removing swing rod to smoothly fall to the appointed position, and facilitate recovery of the cable, the inserting and removing devices and the like.
While the foregoing is directed to the preferred embodiments of the present invention, it will be appreciated by those skilled in the art that various modifications and adaptations can be made without departing from the principles of the present invention, and such modifications and adaptations are intended to be comprehended within the scope of the present invention.
Claims (10)
1. A rocket release swing stem system, comprising:
a core primary tray (7) fixed on a deck for launching the rocket, wherein the core primary tray (7) is fixed with a core primary rocket (6);
a guide hole (1) arranged on the core primary rocket (6);
a swing rod (2) rotatably connected with the core primary tray (7);
a guide rod (21) is arranged at the first end of the swing rod (2), and the guide rod (21) is inserted into the guide hole (1) so that the first end of the swing rod (2) is connected with the core primary rocket (6);
the rod body of the swing rod (2) is connected with the core primary tray (7) through a limiting rod (3);
the rod body of the swing rod (2) is connected with a rocket launching pad (8) through a traction chain (4);
when the rocket is ignited to lift to a preset space-time attitude, the guide rod (21) is separated from the guide hole (1), the traction chain (4) pulls the swing rod (2) to separate from the core primary rocket (6) along a preset track, and the preset space-time attitude is determined according to the offshore drifting amount of the deck.
2. Rocket release swing stem system according to claim 1, wherein the core primary tray (7) is provided with a fixing hole (71), the second end of the swing stem (2) is provided with a rotating shaft (22), and the rotating shaft (22) is inserted into the fixing hole (71) so that the swing stem (2) is rotationally connected with the core primary tray (7).
3. Rocket-taking-off and-on swing-rod system according to claim 1, wherein the rod body of the swing-rod (2) is provided with a first connecting part (24) and a second connecting part (25); the first end of the limiting rod (3) is fixedly connected with the first connecting component (24), and the second end of the limiting rod (3) is fixedly connected with the core primary tray (7).
4. A rocket motor-generator system according to claim 3, wherein the traction chain (4) comprises: a spring (41) and an adjustment chain (42);
the first end of the spring (41) is fixedly connected with the first end of the adjusting chain (42), the second end of the spring (41) is fixedly connected with the second connecting component (25), and the second end of the adjusting chain (42) is fixedly connected with the rocket launching platform (8).
5. Rocket launch stick system according to claim 4 wherein said adjustment chain (42) is wound on a connection on said rocket launching pad (8), the length of said adjustment chain (42) being adjusted according to the length of said spring (41).
6. Rocket release swing stem system according to claim 1, wherein a fixing frame (23) is fixedly connected to the swing stem (2), and a groove (231) is arranged on the side surface of the fixing frame (23).
7. Rocket release swing stem system according to claim 6, wherein a cable (5) is arranged in the groove (231), the inner diameter of the groove (231) is adapted to the diameter of the cable (5), and the cable (5) is clamped in the groove (231).
8. Rocket release swing stem system according to claim 7, wherein said cable (5) is fixed on said fixed frame (23) through said core primary tray (7), the outgoing line direction of said cable (5) being along the tangential direction of said core primary tray (7) and being deflected by a preset angle.
9. Rocket take-off swing stem system according to claim 7, wherein the end of the cable (5) is provided with a plug (51), the plug (51) being plugged into a socket on the core primary rocket (6).
10. Rocket-like coupling pendulum system according to claim 8, wherein the pendulum (2) is separated in the same direction as the cable (5) is led out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310789504.5A CN116929161B (en) | 2023-06-30 | 2023-06-30 | Rocket inserting and removing swing rod system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310789504.5A CN116929161B (en) | 2023-06-30 | 2023-06-30 | Rocket inserting and removing swing rod system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116929161A true CN116929161A (en) | 2023-10-24 |
| CN116929161B CN116929161B (en) | 2024-03-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310789504.5A Active CN116929161B (en) | 2023-06-30 | 2023-06-30 | Rocket inserting and removing swing rod system |
Country Status (1)
| Country | Link |
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| CN (1) | CN116929161B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3578783A (en) * | 1968-11-05 | 1971-05-18 | France Etat | Extractor for an umbilical connector of a rocket |
| CN110030874A (en) * | 2019-03-29 | 2019-07-19 | 北京航天发射技术研究所 | A kind of rocket swing rod that zero second swings back automatically that takes off removes receipts system |
| CN110635309A (en) * | 2019-08-20 | 2019-12-31 | 西安航天动力技术研究所 | Guide rail type retractable separating mechanism |
| CN112758352A (en) * | 2020-12-29 | 2021-05-07 | 北京中科宇航技术有限公司 | Auxiliary pulling device for rocket launching cradle |
| CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
| CN217844931U (en) * | 2022-09-06 | 2022-11-18 | 烟台宇航工程技术有限公司 | A take off and pull out device for second grade rocket |
| CN116247468A (en) * | 2023-02-16 | 2023-06-09 | 北京天兵科技有限公司 | Rocket plug traction device and installation method thereof |
-
2023
- 2023-06-30 CN CN202310789504.5A patent/CN116929161B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3578783A (en) * | 1968-11-05 | 1971-05-18 | France Etat | Extractor for an umbilical connector of a rocket |
| CN110030874A (en) * | 2019-03-29 | 2019-07-19 | 北京航天发射技术研究所 | A kind of rocket swing rod that zero second swings back automatically that takes off removes receipts system |
| CN110635309A (en) * | 2019-08-20 | 2019-12-31 | 西安航天动力技术研究所 | Guide rail type retractable separating mechanism |
| CN112758352A (en) * | 2020-12-29 | 2021-05-07 | 北京中科宇航技术有限公司 | Auxiliary pulling device for rocket launching cradle |
| CN113739634A (en) * | 2021-08-11 | 2021-12-03 | 浙江蓝箭航天空间科技有限公司 | Drag slow release device and launching pad of carrier rocket |
| CN217844931U (en) * | 2022-09-06 | 2022-11-18 | 烟台宇航工程技术有限公司 | A take off and pull out device for second grade rocket |
| CN116247468A (en) * | 2023-02-16 | 2023-06-09 | 北京天兵科技有限公司 | Rocket plug traction device and installation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 杨森;赵宪斌;曾志;张乐;高昱;: "火箭发射装置上一种插拔机构改进设计", 山东工业技术, no. 18, pages 246 * |
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| Publication number | Publication date |
|---|---|
| CN116929161B (en) | 2024-03-19 |
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