CN112815789A - Fairing horizontal throwing separation device with spring pushing and punching functions - Google Patents
Fairing horizontal throwing separation device with spring pushing and punching functions Download PDFInfo
- Publication number
- CN112815789A CN112815789A CN202110082641.6A CN202110082641A CN112815789A CN 112815789 A CN112815789 A CN 112815789A CN 202110082641 A CN202110082641 A CN 202110082641A CN 112815789 A CN112815789 A CN 112815789A
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- fairing
- mounting seat
- cover body
- energy storage
- piston
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- 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
Abstract
The invention relates to a fairing horizontal throwing separation device with a spring pushing and impacting effect, which comprises a fairing body, wherein the fairing body comprises a first cover body and a second cover body, the first cover body and the second cover body are connected through an explosive bolt, four groups of separation mechanisms are arranged in the fairing body, and the four groups of separation mechanisms are arranged around the center of gravity of the fairing body in a centrosymmetric manner; each group of separating mechanism comprises a plurality of separating devices, each separating device comprises a first mounting seat and a second mounting seat, the first mounting seat and the second mounting seat are respectively and fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between the first mounting seat and the second mounting seat, and the energy storage device is used for applying impulse to the first cover body and the second cover body when the explosive bolt is unlocked. The invention can provide effective separation impulse when the fairing is unlocked, and has the advantages of balanced impulse, small impact, simple structure, good economy and the like.
Description
Technical Field
The invention relates to the technical field of fairing separation devices, in particular to a fairing horizontal throwing separation device with a spring pushing and impacting function.
Background
The rocket fairing has the function of protecting the rocket during atmospheric layer crossing, the fairing needs to be separated from the rocket when leaving the atmospheric layer, and the existing fairing separation mode comprises integral forward-throwing separation, two-petal rotary-throwing separation and horizontal-throwing separation, wherein the two-petal horizontal-throwing separation mode is suitable for medium and large rockets.
The existing horizontal projectile separation mode is that a solid small rocket or a pneumatic thrust device provides separation energy, wherein the heat flow of the solid small rocket can pollute a satellite, the performance of the solid small rocket cannot be directly checked, and the reliability is low. The pneumatic pushing and flushing device is used for pressurizing and storing inert gas in a gas cylinder in advance, and has the defects of difficulty in balancing separation energy, complex equipment and high cost.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide the fairing horizontal throwing separation device with the spring pushing and impacting functions, which can provide effective separation impulse when the fairing is unlocked and has the advantages of balanced impulse, small impact, simple structure, good economy and the like.
In order to solve the technical problem, the fairing horizontal throw separation device with the spring pushing and impacting functions comprises a fairing body, wherein the fairing body comprises a first cover body and a second cover body, the first cover body and the second cover body are connected through an explosive bolt, four groups of separation mechanisms are arranged in the fairing body, and the four groups of separation mechanisms are arranged around the center of gravity of the fairing body in a centrosymmetric manner; each group of separating mechanism comprises a plurality of separating devices, each separating device comprises a first mounting seat and a second mounting seat, the first mounting seat and the second mounting seat are respectively and fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between the first mounting seat and the second mounting seat, and the energy storage device is used for applying impulse to the first cover body and the second cover body when the explosive bolt is unlocked.
When the rocket is launched, the fairing body is positioned on the outer side of the rocket to protect the rocket when passing through the atmosphere, after the rocket passes through the atmosphere, the ignition control explosion bolt is unlocked, and at the moment, the energy storage device applies impulse to the first cover body and the second cover body to enable the first cover body and the second cover body to be horizontally thrown and separated. In the invention, the four groups of separating mechanisms are symmetrically arranged around the center of gravity of the fairing body, so that the fairing has the advantages of balanced impulse and small impact, and in addition, the mechanical energy storage device is utilized, so that the structure is simpler and more controllable, the cost can be effectively reduced, and the economical efficiency is better.
Preferably, one end of the energy storage device is fixedly connected with the first mounting seat, and the other end of the energy storage device is abutted to the second mounting seat. When the flat throwing is separated, the energy storage device, the first mounting seat and the first cover body move together, and the second mounting seat and the second cover body move together, so that space garbage is not generated, and the environment is protected.
Preferably, the energy storage device comprises a guide seat and a piston sleeved on the periphery of the guide seat, one end of the guide seat, far away from the piston, is fixedly connected with the first mounting seat, and one end of the piston, far away from the guide seat, is abutted against the second mounting seat; and an energy storage spring is arranged between the piston and the guide seat.
Preferably, one end of the piston close to the second mounting seat extends outwards to form a first boss, one end of the guide seat close to the first mounting seat extends outwards to form a second boss, the energy storage spring is sleeved on the periphery of the piston, and the energy storage spring is compressed and abutted between the second bosses of the first bosses. Before the explosive bolt is unlocked, the energy storage spring is always in a compressed state, and after the explosive bolt is unlocked, the energy storage spring applies impulse to the second cover body through the piston and the second mounting seat and applies impulse to the first cover body through the guide seat and the first mounting seat, so that the first cover body and the second cover body are separated from each other.
Preferably, a circle of positioning groove is formed in one side, far away from the first mounting seat, of the second boss, and the energy storage spring is arranged in the positioning groove in a penetrating mode.
Preferably, a stopping component is arranged on one side, away from the first mounting seat, of the guide seat, and the periphery of the stopping component protrudes out of the outer wall of the guide seat; and a limiting plate matched with the stop component is formed by inwards extending one end of the piston close to the first mounting seat. The design of limiting plate and backstop subassembly can inject the effective stroke of adjusting energy storage equipment, and after first cover body and the separation of second cover body, can guarantee that piston, guide holder and energy storage spring still with first mount pad fixed connection, can not produce space rubbish.
Preferably, the stop assembly includes a stop screw threadedly coupled with the guide housing.
Preferably, the stop assembly further comprises a plurality of stop washers interposed between the stop screw and the guide seat. Due to the design of the stop gaskets, the effective strokes of the energy storage devices are convenient to adjust, the effective strokes of the energy storage devices are consistent, the impulse balance is ensured, and the first cover body and the second cover body are stably separated.
Preferably, a first positioning hole penetrates through the piston in the radial direction, a second positioning hole penetrates through the guide seat in the radial direction, and the same positioning rod penetrates through the first positioning hole and the second positioning hole in a movable mode. The design of locating lever can be before the installation limited piston and the guide holder between the relative position, after separator installs on the radome fairing body, can take off the locating lever.
Preferably, the fairing body includes two conic sections, cylindricality section and first toper section from the past to back in proper order, two conic sections include second toper section and third toper section from the past to back, first toper section with the major diameter end of third toper section all with cylindricality section is connected, just the tapering of second toper section is greater than the tapering of third toper section.
Drawings
In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
FIG. 1 is a schematic structural diagram of a fairing horizontal projectile separation device with spring thrust action according to an embodiment of the invention;
FIG. 2 is a schematic view of a connection structure of a first cover and a quadruple separating mechanism according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a separation device according to an embodiment of the present invention;
fig. 4 is a cross-sectional view of a separation device according to an embodiment of the present invention.
Reference numerals:
1-a fairing body; 11-a first cover; 12-a second cover; 2-a separation device; 21-a first mount; 22-a second mount; 23-a guide seat; 24-a piston; 241-limiting plate; 25-an energy storage spring; 26-a stop screw; 27-positioning rod.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
As shown in fig. 1, fig. 2, fig. 3, and fig. 4, the present embodiment provides a fairing horizontal throwing separation device with a spring pushing and impacting function, including a fairing body 1, where the fairing body 1 includes, in order from front to back, a double cone section, a cylindrical section, and a first cone section, the double cone section includes, from front to back, a second cone section and a third cone section, large diameter ends of the first cone section and the third cone section are both connected to the cylindrical section, and a taper of the second cone section is greater than a taper of the third cone section.
Specifically, the cowl body 1 includes a first cowl body 11 and a second cowl body 12, the first cowl body 11 and the second cowl body 12 are connected by explosive bolts (not shown in the drawings), and four sets of separating mechanisms are provided in the cowl body 1, and are arranged in a centrosymmetric manner around the center of gravity of the cowl body 1. When the explosion bolt is unlocked, each group of separating mechanisms simultaneously provides impulse for the first cover body 11 and the second cover body 12, so that the first cover body 11 and the second cover body 12 are separated from each other, and because the four groups of separating mechanisms are arranged in a central symmetry mode around the center of gravity of the fairing body 1, the impulse can be more balanced, and the separation of the fairing body 1 is more stable.
In this embodiment, each separating mechanism includes a separating device 2, the separating device 2 includes a first mounting seat 21 and a second mounting seat 22, and the first mounting seat 21 and the second mounting seat 22 are fixedly connected to the first cover 1 and the second cover 12, respectively. Be provided with energy storage equipment between first mount pad 21 and second mount pad 22, this energy storage equipment includes guide holder 23, and the piston 24 of cover establishing in this guide holder 23 periphery, and the one end and the first mount pad 21 fixed connection of piston 24 are kept away from to guide holder 23, and the one end and the second mount pad 22 butt that guide holder 23 was kept away from to piston 24. Specifically, the one end that piston 24 is close to second mount pad 22 outwards extends and is formed with first boss, and the one end that guide holder 23 is close to first mount pad 21 outwards extends and is formed with the second boss, overlaps in the periphery of piston 24 to be equipped with energy storage spring 25, and this energy storage spring 25 compression butt is between the second boss of first boss, and is provided with the round constant head tank in the one side that first mount pad 21 was kept away from to the second boss, and energy storage spring 25 wears to establish in this constant head tank.
The fairing horizontal projectile separation device with the spring thrust action is used for protecting a rocket during atmospheric layer crossing, after the rocket penetrates through the atmospheric layer, an ignition control explosion bolt is unlocked, and during unlocking, the piston 24 and the guide seat 23 are mutually separated under the action of the energy storage spring 25 and respectively transmit the impulse to the first cover body 11 and the second cover body 12, so that the first cover body 11 and the second cover body 12 are mutually separated. The mechanical separation structure has the advantages of simple operation, low cost and good economy.
Further, a stop assembly is arranged on one side of the guide seat 23 away from the first mounting seat 21, the stop assembly comprises a stop screw 26 in threaded connection with the guide seat 23, and the outer periphery of a screw head of the stop screw 26 protrudes out of the outer wall of the guide seat 23; a stopper plate 241 fitted with a stopper assembly is formed to extend inward at an end of the piston 24 adjacent to the first mounting seat 21. When the piston 24 and the guide seat 23 are separated, the piston 24 and the guide seat 23 are far away from each other, but under the cooperation of the limit plate 241 and the stop screw 26, the piston 24 and the guide seat 23 cannot be completely separated, and still move together with the first cover 11 as a whole, so that space debris is prevented from being generated.
In this embodiment, the minimum distance between limiting plate 241 and the backstop subassembly is the effective stroke of energy storage device 2, through adjusting this effective stroke, can adjust the impulse of effect on radome fairing body 1, for this reason, the backstop subassembly of this embodiment still further includes a plurality of backstop gaskets (not shown in the figure) of clamp setting between backstop screw 26 and guide holder 23, when needs, can add the backstop gasket and adjust effective stroke, accommodation process is simple and convenient, and safe and reliable.
More specifically, a first positioning hole is provided in the piston 24 in a radial direction, a second positioning hole is provided in the guide holder 23 in a radial direction, and the same positioning rod 27 is movably inserted into the first positioning hole and the second positioning hole. Before installation, the locating rod 27 can be used for limiting the relative position between the piston 24 and the guide seat 23, and after the separation device 2 is installed on the fairing body 1, the locating rod 27 can be taken down, so that separation can be conveniently carried out after later explosion bolt unlocking.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; these modifications and substitutions do not cause the essence of the corresponding technical solution to depart from the scope of the technical solution of the embodiments of the present invention, and are intended to be covered by the claims and the specification of the present invention.
Claims (10)
1. The utility model provides a spring pushes away flat separator of throwing of radome fairing of dashing effect, includes the radome fairing body, and this radome fairing body includes the first cover body and the second cover body, the first cover body and the second cover body pass through explosion bolted connection, its characterized in that:
four groups of separating mechanisms are arranged in the fairing body, and the four groups of separating mechanisms are arranged around the center of gravity of the fairing body in a centrosymmetric manner;
each group of separating mechanism comprises a plurality of separating devices, each separating device comprises a first mounting seat and a second mounting seat, the first mounting seat and the second mounting seat are respectively and fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between the first mounting seat and the second mounting seat, and the energy storage device is used for applying impulse to the first cover body and the second cover body when the explosive bolt is unlocked.
2. The spring thrust fairing flat throw separation assembly of claim 1, wherein:
one end of the energy storage device is fixedly connected with the first mounting seat, and the other end of the energy storage device is abutted to the second mounting seat.
3. The spring thrust fairing flat throw separation assembly of claim 2, wherein:
the energy storage device comprises a guide seat and a piston sleeved on the periphery of the guide seat, one end of the guide seat far away from the piston is fixedly connected with the first mounting seat, and one end of the piston far away from the guide seat is abutted to the second mounting seat;
and an energy storage spring is arranged between the piston and the guide seat.
4. A spring thrust fairing flat throw separation assembly as defined in claim 3 wherein:
the piston is close to the one end of second mount pad outwards extends and is formed with first boss, the guide holder is close to the one end of first mount pad outwards extends and is formed with the second boss, the energy storage spring cover is established the periphery of piston, and this energy storage spring compression butt is in between the second boss of first boss.
5. The spring thrust fairing flat throw separation assembly of claim 4, wherein:
and a circle of positioning groove is formed in one side, far away from the first mounting seat, of the second boss, and the energy storage spring is arranged in the positioning groove in a penetrating mode.
6. A spring thrust fairing flat throw separation assembly as defined in claim 3 wherein:
a stopping component is arranged on one side, away from the first mounting seat, of the guide seat, and the periphery of the stopping component protrudes out of the outer wall of the guide seat;
and a limiting plate matched with the stop component is formed by inwards extending one end of the piston close to the first mounting seat.
7. The spring thrust fairing flat throw separation assembly of claim 6, wherein:
the stop component comprises a stop screw in threaded connection with the guide seat.
8. The spring thrust fairing flat throw separation assembly of claim 7, wherein:
the stop assembly further comprises a plurality of stop gaskets clamped between the stop screw and the guide seat.
9. A spring thrust fairing flat throw separation assembly as defined in claim 3 wherein:
the radial direction of the piston is provided with a first positioning hole in a penetrating mode, the radial direction of the guide seat is provided with a second positioning hole in a penetrating mode, and the first positioning hole and the second positioning hole are internally movably provided with the same positioning rod in a penetrating mode.
10. The spring thrust fairing flat throw separation assembly of claim 6, wherein:
the fairing body includes two conic sections, cylindricality section and first toper section from the past to back in proper order, two conic sections include second toper section and third toper section from the past to the back, first toper section with the major diameter end of third toper section all with the cylindricality section is connected, just the tapering of second toper section is greater than the tapering of third toper section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082641.6A CN112815789B (en) | 2021-01-21 | 2021-01-21 | Cowling level throwing separation device with spring pushing effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110082641.6A CN112815789B (en) | 2021-01-21 | 2021-01-21 | Cowling level throwing separation device with spring pushing effect |
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| Publication Number | Publication Date |
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| CN112815789A true CN112815789A (en) | 2021-05-18 |
| CN112815789B CN112815789B (en) | 2023-05-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110082641.6A Active CN112815789B (en) | 2021-01-21 | 2021-01-21 | Cowling level throwing separation device with spring pushing effect |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114838630A (en) * | 2022-05-11 | 2022-08-02 | 北京中科宇航技术有限公司 | Rocket radome fairing auxiliary opening device |
| CN115127407A (en) * | 2022-08-10 | 2022-09-30 | 北京凌空天行科技有限责任公司 | Rocket hood separator based on spring |
| CN115200423A (en) * | 2022-06-21 | 2022-10-18 | 上海机电工程研究所 | Mechanical separation device and separation method based on explosive bolt |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114838630B (en) * | 2022-05-11 | 2023-09-19 | 北京中科宇航技术有限公司 | Auxiliary opening device for rocket fairing |
| CN115200423A (en) * | 2022-06-21 | 2022-10-18 | 上海机电工程研究所 | Mechanical separation device and separation method based on explosive bolt |
| CN115127407A (en) * | 2022-08-10 | 2022-09-30 | 北京凌空天行科技有限责任公司 | Rocket hood separator based on spring |
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| CN112815789B (en) | 2023-05-16 |
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