CN115507699B - Automatic reversing type drag release device - Google Patents
Automatic reversing type drag release device Download PDFInfo
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- CN115507699B CN115507699B CN202210973682.9A CN202210973682A CN115507699B CN 115507699 B CN115507699 B CN 115507699B CN 202210973682 A CN202210973682 A CN 202210973682A CN 115507699 B CN115507699 B CN 115507699B
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- drag
- drag release
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- 230000005540 biological transmission Effects 0.000 claims description 18
- 230000003014 reinforcing effect Effects 0.000 claims description 16
- 230000007246 mechanism Effects 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 5
- 230000006835 compression Effects 0.000 claims description 4
- 238000007906 compression Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000011897 real-time detection Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000000452 restraining effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
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Abstract
The application provides an automatic reverse type drag release device which comprises a box body, a reverse support, a mounting plate, a drag release body, a locking assembly and a reverse cylinder, wherein the box body is provided with a reverse opening; the box body is arranged on the mounting plate through the reverse support, and the holding-down release body and the locking component are both arranged in the box body; the locking component is used for locking, boosting and releasing the drag release body; the drag release body can rotate in a pitching mode relative to the supporting component at the top of the box body, and the drag release body and the supporting component at the top of the box body jointly realize drag and release of the carrier rocket; the return cylinder is arranged on the mounting plate, the output end of the return cylinder is hinged with the box body, and the return cylinder is used for pushing the box body to rotate around the return support. The application adopts a non-fire separation mode to reliably hold and release the carrier rocket, can effectively reduce separation impact, protects the automatic reverse hold-down release device from being damaged, and can realize repeated use.
Description
Technical Field
The application belongs to the field of a carrier rocket drag release device, and particularly relates to an automatic reversing drag release device.
Background
The rocket drag release launching technology is mainly used for supporting, dragging and releasing in the rocket ignition and take-off stage. The drag release device is divided into an explosion nut type and a connecting rod mechanism type, and the connecting rod mechanism type also adopts explosion nut type hinge point separation links, however, the drag release device has huge instantaneous separation impact and has larger influence on the load state of the rocket release moment. In addition, most of active carrier rockets adopt a bottom tail end face supporting mode, a supporting device is fixedly arranged on the upper surface of a launching platform, and proper installation space is reserved to avoid interference of rocket take-off drift; however, for medium/heavy carrier rockets with lumbar support, the takeoff drift space requirement is significantly elevated. Therefore, there is a need to develop an automatic back-down drag release device for a launch vehicle to meet the safe takeoff and reuse requirements of medium/heavy launch vehicles.
Disclosure of Invention
To overcome at least some of the problems associated with the prior art, the present application provides an automatic back-up drag release device.
According to an embodiment of the application, the application provides an automatic reversing type drag release device, which comprises a box body, a reversing support, a mounting plate, a drag release body, a locking assembly and a reversing cylinder; the box body is arranged on the mounting plate through the reversing support, and the drag release body and the locking component are both arranged in the box body; the locking component is used for locking, boosting and releasing the containment release body; the drag release body can rotate in a pitching mode relative to the supporting component at the top of the box body, and the drag release body and the supporting component at the top of the box body jointly realize drag and release of the carrier rocket; the reverse cylinder is arranged on the mounting plate, the output end of the reverse cylinder is hinged with the box body, and the reverse cylinder is used for pushing the box body to rotate around the reverse support.
In the automatic reversing type drag release device, the limiting plate is arranged on the mounting plate and used for limiting the rotation amplitude of the box body around the reversing support.
In the automatic reverse type drag release device, the drag release body comprises a force transmission plate, a drag hydraulic cylinder, a connecting arm and a pressing plate; a vertical plate is arranged in the box body, a base is arranged on the top surface of the vertical plate, the force transmission plate is arranged on the vertical plate, and one end of the bottom of the force transmission plate is hinged with the base; the bottom surface of the box body is provided with an installation seat, one end of the holding hydraulic cylinder is connected with the installation seat, and the other end of the holding hydraulic cylinder is connected with the other end of the bottom of the force transmission plate; the top of the force transfer plate is connected with one end of the pressing plate through the connecting arm; the support assembly is arranged in the box body, a reinforcing block is arranged on the inner side wall of the support assembly, the other end of the press plate is hinged with the reinforcing block, the head of the other end of the press plate is located above the support assembly, and the head of the other end of the press plate is matched with the support assembly to press a support on the side wall of the carrier rocket.
Still further, the supporting component comprises a bearing platform and a supporting seat, wherein the bearing platform is fixedly connected to the side wall or the top end of the box body, and the supporting seat is arranged on the bearing platform.
Further, the reinforcing block is fixedly connected with the inner side wall of the bearing table; the head of the other end of the pressing plate is positioned above the supporting seat, and is matched with the supporting seat for use and used for pressing the supporting seat on the side wall of the carrier rocket.
Further, an anti-collision rubber wheel is further arranged on the vertical plate in the box body, the anti-collision rubber wheel is located on one side of the force transmission plate rotating clockwise, and the anti-collision rubber wheel is fixedly connected with the vertical plate.
Further, the drag release body further comprises a pressure sensor disposed on the connecting arm for real-time detection of the drag load.
Further, the locking component comprises a rotating nut, a reinforcing handle, a connecting screw, a tension meter, an electric separator and a connecting support lug; the rotating nut is arranged on the side plate of the box body in a penetrating mode, the force increasing handle is located outside the box body and fixedly connected with the rotating nut, one end of the connecting screw rod is screwed into the rotating nut, the other end of the connecting screw rod is connected with the electric separator through the tension meter, and the electric separator is hinged to the joint of the top of the force transferring plate and the connecting arm through the connecting support lug.
Furthermore, a locking mechanism is arranged in the electric separator, when the electric separator receives a separation electric signal, the locking mechanism is unlocked, and the electric separator is separated into two parts, so that free release of a hinge point of the connecting support lug and the force transmission plate is realized.
In the automatic reversing type drag release device, the reversing cylinder comprises a cylinder barrel, a cushion pad arranged in the cylinder barrel, a return spring and a piston rod; the cushion pad is arranged near one end of the cylinder barrel, and the return spring is sleeved on the piston rod; the extending end of the piston rod is hinged with the outer side wall of the box body; under the action of an external air source, the return spring is compressed, and the piston rod stretches out to drive the box body to rotate clockwise around the reversing support; under the action of the compression load of the return spring, the piston rod is recovered to drive the box body to rotate anticlockwise around the return support.
According to the above specific embodiments of the present application, at least the following advantages are achieved: the automatic reverse type containment releasing device provided by the application comprises a box body, a reverse support, a mounting plate, a containment releasing body, a locking assembly and a reverse cylinder; the box body is arranged on the mounting plate through the reverse support, and the holding-down release body and the locking component are both arranged in the box body; the locking component is used for locking, boosting and releasing the drag release body; the drag release body can rotate in a pitching mode relative to the supporting component at the top of the box body, and the drag release body and the supporting component at the top of the box body jointly realize drag and release of the carrier rocket; the return air cylinder is arranged on the mounting plate, the output end of the return air cylinder is hinged with the box body, and the return air cylinder is used for pushing the box body to rotate around the return support; the application adopts a non-fire separation mode to reliably hold and release the carrier rocket, can effectively reduce separation impact, protects the automatic reverse hold-down release device from being damaged, and can realize repeated use.
According to the automatic reversing type containment release device, the reversing cylinder is arranged and used for pushing the box body to rotate around the reversing support, so that the automatic reversing type containment release device can automatically reverse the middle/heavy type rocket with waist support when the middle/heavy type rocket takes off and drifts, and can automatically avoid the carrier rocket.
It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the application, as claimed.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description, serve to explain the principles of the application.
FIG. 1 is a schematic view of an automatic back-down type drag release device according to an embodiment of the present application.
FIG. 2 is a schematic view showing a state of an automatic back-down type drag release device supporting a drag carrier rocket according to an embodiment of the present application.
Fig. 3 is a schematic view of a state of a launch vehicle at a take-off moment after a launch vehicle is released by an automatic back-down type drag release device according to an embodiment of the present application.
Fig. 4 is a schematic view of a take-off state of a carrier rocket when an automatic reversing type drag release device reverses to avoid the rocket according to an embodiment of the present application.
Reference numerals illustrate:
1. A case;
11. A support assembly; 111. a force bearing table; 112. the supporting seat; 12. a riser; 13. a base; 14. a mounting base; 15. a reinforcing block; 16. an anti-collision rubber wheel;
2. The support is reversed;
3. A mounting plate;
4. A drag release body;
41. a force transfer plate; 42. a hydraulic cylinder is held; 43. a connecting arm; 44. a pressing plate; 45. a pressure sensor;
5. a locking assembly;
51. rotating the nut; 52. a booster handle; 53. a connecting screw; 54. a tension meter; 55. an electric separator; 56. connecting the lugs;
6. reversing the cylinder;
61. a cylinder; 62. a cushion pad; 63. a return spring; 64. a piston rod;
7. A cylinder block; 8. a limiting plate;
10. and (5) a support.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the spirit of the present disclosure will be clearly described in the following drawings and detailed description, and any person skilled in the art, after having appreciated the embodiments of the present disclosure, may make alterations and modifications by the techniques taught by the present disclosure without departing from the spirit and scope of the present disclosure.
The exemplary embodiments of the present application and the descriptions thereof are intended to illustrate the present application, but not to limit the present application. In addition, the same or similar reference numerals are used for the same or similar parts in the drawings and the embodiments.
The terms "first," "second," …, etc. as used herein do not denote a particular order or sequence, nor are they intended to limit the application, but rather are merely used to distinguish one element or operation from another in the same technical term.
As used herein, the terms "comprising," "including," "having," "containing," and the like are intended to be inclusive and mean an inclusion, but not limited to.
As used herein, "and/or" includes any or all combinations of such things.
Reference herein to "a plurality" includes "two" and "more than two"; the term "plurality of sets" as used herein includes "two sets" and "more than two sets".
Certain words used to describe the application will be discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the application.
The automatic reverse type drag release device provided by the embodiment of the application is used in a medium/heavy carrier rocket to reliably drag and release the carrier rocket in the carrier rocket take-off stage; in the release link, the application adopts a non-fire separation mode, can effectively reduce separation impact and realize repeated use for a plurality of times.
As shown in fig. 1, the automatic reverse type drag release device provided by the embodiment of the application comprises a box body 1, a reverse support 2, a mounting plate 3, a drag release body 4, a locking assembly 5 and a reverse cylinder 6.
Wherein, box 1 sets up on mounting panel 3 through returning support 2, and the release body that holds in the palm 4 and locking subassembly 5 all set up in box 1. The locking assembly 5 is used for locking, boosting and releasing the containment release body 4. The drag release body 4 can rotate in a pitching mode relative to the supporting component 11 at the top of the box body 1, and the drag release body 4 and the supporting component 11 at the top of the box body 1 jointly achieve drag and release of the carrier rocket by adopting a connecting rod-lever two-stage boosting principle. The backing cylinder 6 is arranged on the mounting plate 3 through the cylinder seat 7, the output end of the backing cylinder 6 is hinged with the box body 1, and the backing cylinder 6 is used for pushing the box body 1 to rotate around the backing support 2 so that the holding-down release body 4 and the supporting component 11 at the top of the box body 1 can support or avoid the carrier rocket.
The box body 1 is formed by welding steel plates, and is used for installing the drag release body 4 and the locking assembly 5, and also used for bearing a carrier rocket and bearing the weight of the carrier rocket.
In a specific embodiment, a limiting plate 8 is arranged on the mounting plate 3 on one side of the box body 1 which rotates clockwise around the backing support 2, and the limiting plate 8 is used for limiting the rotation amplitude of the box body 1 around the backing support 2.
In a specific embodiment, the hold-down release body 4 includes a force transfer plate 41, a hold-down cylinder 42, a connecting arm 43, and a pressure plate 44. Wherein, be provided with riser 12 in the box 1, be provided with base 13 on the top surface of riser 12, the biography power board 41 sets up on riser 12, and the one end of its bottom is articulated with base 13.
The bottom surface inside the box 1 is provided with a mounting seat 14, one end of a holding hydraulic cylinder 42 is connected with the mounting seat 14, and the other end is connected with the other end of the bottom of the force transmission plate 41. The top of the force transfer plate 41 is connected to one end of a pressure plate 44 by a connecting arm 43. The supporting component 11 is arranged in the box body 1 below the other end of the pressing plate 44, the reinforcing block 15 is arranged on the inner side wall of the supporting component 11, the other end of the pressing plate 44 is hinged with the reinforcing block 15, the head of the other end of the pressing plate 44 is located above the supporting component 11 and is matched with the supporting component 11 to press the support 10 on the side wall of the carrier rocket, so that the carrier rocket is restrained.
Specifically, the supporting assembly 11 includes a bearing platform 111 and a supporting seat 112, the bearing platform 111 is fixedly connected to a side wall or a top end of the box 1, and the supporting seat 112 is disposed on the bearing platform 111. The reinforcing block 15 is fixedly connected to the inner side wall of the bearing block 111. The head of the other end of the pressure plate 44 is located above the support block 112 and cooperates with the support block 112 for pressing against the support blocks 10 on the side walls of the launch vehicle.
In another specific embodiment, a rubber wheel 16 is further arranged on the vertical plate 12 in the box body 1, the rubber wheel 16 is located on one side of the force transmission plate 41 rotating clockwise, and the rubber wheel 16 is fixedly connected with the vertical plate 12 through bolts. The anti-collision rubber wheel 16 can prevent the force transmission plate 41 from being quickly separated from the locking assembly 5 and then colliding with the box body 1, so that the box body 1 is protected.
In another specific embodiment, the containment release body 4 further comprises a pressure sensor 45, the pressure sensor 45 being arranged on the connecting arm 43 for real-time detection of the containment load.
In one particular embodiment, the locking assembly 5 includes a swivel nut 51, a booster handle 52, a connecting screw 53, a tension gauge 54, a motorized separator 55, and a connecting lug 56.
The rotating nut 51 is arranged on a side plate of the box body 1 in a penetrating way, the reinforcing handle 52 is positioned outside the box body 1 and fixedly connected with the rotating nut 51, one end of the connecting screw 53 is screwed into the rotating nut 51, the other end of the connecting screw 53 is connected with the electric separator 55 through the tension meter 54, and the electric separator 55 is hinged at the joint of the top of the force transmission plate 41 and the connecting arm 43 through the connecting lug 56.
The force and load of the locking assembly 5 can be increased and removed by hand-shaking the force lever 52, and the force load during operation can be read by the tension meter 54. The electric separator 55 is internally provided with a locking mechanism, when the electric separator 55 receives a separation electric signal, the locking mechanism is unlocked, and the electric separator 55 is separated into two parts, so that free release of a hinge point of the connecting lug 56 and the force transmission plate 41 is realized.
In a specific embodiment, the knock-back cylinder 6 includes a cylinder 61, and a cushion 62, a return spring 63, and a piston rod 64 disposed within the cylinder 61. Wherein, the buffer pad 62 is arranged near one end of the cylinder 61, and the return spring 63 is sleeved on the piston rod 64. The protruding end of the piston rod 64 is hinged to the outer side wall of the case 1.
Under the action of an external air source, the return spring 63 is compressed in the process that the piston rod 64 is pushed out, and the extending end of the piston rod 64 pushes the box body 1 to rotate clockwise around the reversing support 2; under the compression load of the return spring 63, the extended end of the piston rod 64 is retracted to rotate the case 1 counterclockwise around the reverse support 2.
When the automatic back-down type drag release device provided by the embodiment of the application is used in a medium/heavy carrier rocket, the device specifically comprises the following steps:
S1, rocket carrying and supporting process:
The reverse cylinder 6 is controlled so that a piston rod 64 in the reverse cylinder 6 extends out to compress a return spring 63, the piston rod 64 in the reverse cylinder 6 pushes the box body 1 to integrally rotate clockwise around the reverse support 2 until reaching the limit position of the reverse support 2, and a pneumatic electromagnetic valve connected with an external air source and the reverse cylinder 6 is closed, so that the upper plane of the box body 1 is in a horizontal state.
The connection bolt of the electric separator 55 and the connection lug 56 is released, and the locking assembly 5 is in the disconnected state.
The piston rod in the hydraulic driving and restraining hydraulic cylinder 42 stretches out, and the piston rod in the hydraulic cylinder 42 pushes the force transfer plate 41 to rotate clockwise around the hinge point at which one end of the bottom of the force transfer plate 41 is hinged with the base 13, and drives the pressing plate 44 to rotate anticlockwise around the hinge point at which the other end of the pressing plate 44 is hinged with the reinforcing block 15, so that the descending space of the support 10 on the side wall of the carrier rocket is avoided.
The carrier rocket is hoisted and lowered until the support 10 contacts with the supporting seat 112, and the carrier rocket is supported and supported by the box body 1. After the state of the carrier rocket is stable, the return air cylinder 6 is controlled to release the air in the rodless cavity, the return spring 63 is still in a compressed state, and the load balance of the whole position and load of the return air cylinder 6 and the rocket weight is realized.
S2, a rocket restraining process:
The piston rod in the hydraulic control hydraulic cylinder 42 is driven to be recovered, the piston rod pulls the force transmission plate 41 to rotate anticlockwise around the hinge point at which one end of the bottom of the force transmission plate 41 is hinged with the base 13, the pressing plate 44 is driven to rotate clockwise around the hinge point at which the other end of the pressing plate 44 is hinged with the reinforcing block 15, and the initial reinforcement control is completed until the control hydraulic cylinder 42 reaches the preset pressure or the pressure sensor 45 reaches the preset load.
The electric separator 55 and the connecting lugs 56 are connected through connecting bolts, the force-increasing crank is adapted to shake in the connecting process, and after the electric separator 55 and the connecting lugs 56 are reliably connected, the force-increasing crank is swayed clockwise to increase force until the tension meter 54 reaches a preset load or the pressure sensor 45 reaches a preset load, so that final force-increasing restraint is completed. As shown in FIG. 2, the automatic back-down type drag release device provided by the embodiment of the application can reliably and stably support the drag.
S3, releasing a rocket:
after receiving the release signal, the electric separator 55 is instantaneously separated, and under the action of the energizing load of the locking assembly 5, the force transfer plate 41 drives the connecting lugs 56 to rapidly rotate clockwise around the hinge point where one end of the bottom of the force transfer plate 41 is hinged with the base 13.
The rodless cavity of the hold-down hydraulic cylinder 42 is quickly filled with oil, the rod cavity is quickly returned with oil, the piston rod in the hold-down hydraulic cylinder 42 is quickly extended, the pressing plate 44 is quickly rotated anticlockwise around the hinge point at which the other end of the pressing plate 44 is hinged with the reinforcing block 15, and the force transfer plate 41 is impacted to the anti-collision rubber wheel 16 to realize buffering. The rodless chamber of the hold-down hydraulic cylinder 42 is kept pressure-maintaining to ensure no rebound after the impact of the force transfer plate 41, and finally the pressure plate 44 is kept in a final open state, as shown in fig. 3, to realize the release of the carrier rocket.
S4, avoiding a rocket:
as the drag load rapidly drops to disappear, the carrier rocket gradually leaves the bearing surface of the supporting seat in the box body 1 under the action of the pushing force, and the bearing force of the bearing surface is reduced and disappears.
As shown in fig. 4, under the compression load of the return spring 63, the piston rod 64 in the return cylinder 6 is recovered, and the piston rod 64 drives the box 1 to rotate around the return support 2 in a quick anticlockwise manner, so as to quickly avoid the rocket takeoff space.
The automatic back-down type drag release device provided by the embodiment of the application can reliably drag and release the carrier rocket in the take-off stage of the carrier rocket.
In the step of releasing the carrier rocket, the automatic reverse type containment releasing device provided by the embodiment of the application adopts a non-fire separation mode, so that separation impact can be effectively reduced, the automatic reverse type containment releasing device is protected from being damaged, and repeated utilization is realized.
The automatic back-down type drag release device provided by the embodiment of the application can automatically avoid the carrier rocket when the middle/heavy rocket with the waist support takes off and drifts.
The foregoing is merely illustrative of the embodiments of this application and any equivalent and equivalent changes and modifications can be made by those skilled in the art without departing from the spirit and principles of this application.
Claims (8)
1. The automatic reverse type drag release device is characterized by comprising a box body, a reverse support, a mounting plate, a drag release body, a locking assembly and a reverse cylinder;
The box body is arranged on the mounting plate through the reversing support, and the drag release body and the locking component are both arranged in the box body; the locking component is used for locking, boosting and releasing the containment release body; the drag release body can rotate in a pitching mode relative to the supporting component at the top of the box body, and the drag release body and the supporting component at the top of the box body jointly realize drag and release of the carrier rocket;
the return air cylinder is arranged on the mounting plate, the output end of the return air cylinder is hinged with the box body, and the return air cylinder is used for pushing the box body to rotate around the return support;
the drag release body comprises a force transfer plate, a drag hydraulic cylinder, a connecting arm and a pressing plate;
a vertical plate is arranged in the box body, a base is arranged on the top surface of the vertical plate, the force transmission plate is arranged on the vertical plate, and one end of the bottom of the force transmission plate is hinged with the base;
the bottom surface of the box body is provided with an installation seat, one end of the holding hydraulic cylinder is connected with the installation seat, and the other end of the holding hydraulic cylinder is connected with the other end of the bottom of the force transmission plate; the top of the force transfer plate is connected with one end of the pressing plate through the connecting arm; the support assembly is arranged in the box body, a reinforcing block is arranged on the inner side wall of the support assembly, the other end of the press plate is hinged with the reinforcing block, the head of the other end of the press plate is positioned above the support assembly, and the support assembly is matched with the support assembly to press a support on the side wall of the carrier rocket;
The locking component comprises a rotating nut, a reinforcing handle, a connecting screw, a tension meter, an electric separator and a connecting support lug;
The rotating nut is arranged on the side plate of the box body in a penetrating mode, the force increasing handle is located outside the box body and fixedly connected with the rotating nut, one end of the connecting screw rod is screwed into the rotating nut, the other end of the connecting screw rod is connected with the electric separator through the tension meter, and the electric separator is hinged to the joint of the top of the force transferring plate and the connecting arm through the connecting support lug.
2. The automatic back-down type drag release device according to claim 1, wherein a limiting plate is arranged on the mounting plate on one side of the box body rotating clockwise around the back-down support, and the limiting plate is used for limiting the rotation amplitude of the box body around the back-down support.
3. The automatic back-down drag release device of claim 1, wherein the support assembly comprises a load-bearing table fixedly connected to a side wall or a top end of the case and a support base disposed on the load-bearing table.
4. The automatic back-down drag release device of claim 3, wherein the reinforcing block is fixedly connected with the inner side wall of the force bearing table; the head of the other end of the pressing plate is positioned above the supporting seat, and is matched with the supporting seat for use and used for pressing the supporting seat on the side wall of the carrier rocket.
5. The automatic back-down type drag release device according to claim 1, wherein an anti-collision rubber wheel is further arranged on the vertical plate in the box body, the anti-collision rubber wheel is located on one side of the force transmission plate rotating clockwise, and the anti-collision rubber wheel is fixedly connected with the vertical plate.
6. The automatic back-up type drag release device of claim 1, wherein the drag release body further comprises a pressure sensor disposed on the connecting arm for real-time detection of the drag load.
7. The automatic back-down type drag release device according to claim 1, wherein a locking mechanism is arranged inside the electric separator, when the electric separator receives a separation electric signal, the locking mechanism is unlocked, and the electric separator is separated into two parts, so that free release of a hinge point of the connecting support lug and the force transmission plate is realized.
8. The automatic retracting-back type drag release device according to claim 1 or 2, wherein the retracting cylinder comprises a cylinder tube, and a cushion, a return spring and a piston rod provided in the cylinder tube;
The cushion pad is arranged near one end of the cylinder barrel, and the return spring is sleeved on the piston rod; the extending end of the piston rod is hinged with the outer side wall of the box body;
under the action of an external air source, the return spring is compressed, and the piston rod stretches out to drive the box body to rotate clockwise around the reversing support;
under the action of the compression load of the return spring, the piston rod is recovered to drive the box body to rotate anticlockwise around the return support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210973682.9A CN115507699B (en) | 2022-08-15 | 2022-08-15 | Automatic reversing type drag release device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210973682.9A CN115507699B (en) | 2022-08-15 | 2022-08-15 | Automatic reversing type drag release device |
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| Publication Number | Publication Date |
|---|---|
| CN115507699A CN115507699A (en) | 2022-12-23 |
| CN115507699B true CN115507699B (en) | 2024-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210973682.9A Active CN115507699B (en) | 2022-08-15 | 2022-08-15 | Automatic reversing type drag release device |
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| GB2096287A (en) * | 1981-04-04 | 1982-10-13 | British Aerospace | Launch vehicle constraining |
| CN101419037A (en) * | 2008-12-11 | 2009-04-29 | 北京航天发射技术研究所 | Air spring slow-releasing mechanism |
| CN111207625A (en) * | 2020-01-10 | 2020-05-29 | 北京航天发射技术研究所 | Traction release device integrating supporting, traction and slow release |
| 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 |
| CN113800012A (en) * | 2021-09-30 | 2021-12-17 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
| CN218764854U (en) * | 2022-08-15 | 2023-03-28 | 蓝箭航天空间科技股份有限公司 | Drag release device |
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| CN115507699A (en) | 2022-12-23 |
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