CN112815789B - Cowling level throwing separation device with spring pushing effect - Google Patents
Cowling level throwing separation device with spring pushing effect Download PDFInfo
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- CN112815789B CN112815789B CN202110082641.6A CN202110082641A CN112815789B CN 112815789 B CN112815789 B CN 112815789B CN 202110082641 A CN202110082641 A CN 202110082641A CN 112815789 B CN112815789 B CN 112815789B
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- energy storage
- fairing
- cover body
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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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
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- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention relates to a fairing horizontal projectile separating device with a spring pushing effect, which comprises a fairing body, wherein the fairing body comprises a first fairing body and a second fairing body, the first fairing body and the second fairing body are connected through explosion bolts, four groups of separating mechanisms are arranged in the fairing body, and the four groups of separating mechanisms are arranged in a central symmetry mode around the gravity center of the fairing body; each group of separation mechanism comprises a plurality of separation devices, each separation device comprises a first installation seat and a second installation seat, each first installation seat and each second installation seat are respectively fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between each first installation seat and each second installation seat, and when the explosion bolt is unlocked, the energy storage device is used for applying impulse to the first cover body and the second cover body. 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 projectile separation device with a spring pushing effect.
Background
The function of the rocket fairing is to protect the rocket when penetrating through the atmosphere, when the rocket fairing leaves the atmosphere, the fairing is required to be separated from the rocket, and the existing fairing separation mode comprises integral front projectile separation, two-petal rotary projectile separation and flat projectile separation, wherein the two-petal flat projectile separation mode is suitable for medium and large rockets.
The existing horizontal projectile separation mode is to provide separation energy by a small solid rocket or a pneumatic thrust device, wherein the heat flow of the small solid rocket can pollute satellites, the performance of the small solid rocket cannot be directly checked, and the reliability is low. The pneumatic pushing device stores inert gas in a gas cylinder in advance, and has the defects of difficult balance of 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 projectile separating device with the spring pushing effect, 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 problems, the fairing horizontal projectile separating device with the spring pushing effect comprises a fairing body, wherein the fairing body comprises a first fairing body and a second fairing body, the first fairing body and the second fairing body are connected through explosion bolts, four groups of separating mechanisms are arranged in the fairing body, and the four groups of separating mechanisms are arranged in a central symmetry mode around the gravity center of the fairing body; each group of separation mechanism comprises a plurality of separation devices, each separation device comprises a first installation seat and a second installation seat, each first installation seat and each second installation seat are respectively fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between each first installation seat and each second installation seat, and when the explosion bolt is unlocked, the energy storage device is used for applying impulse to the first cover body and the second cover body.
When the rocket is launched, the fairing body is positioned at the outer side of the rocket so as to protect the rocket when penetrating through the atmosphere, and after the rocket penetrates 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 so as to enable the first cover body and the second cover body to be horizontally thrown and separated. In the invention, the four-component separating mechanism is symmetrically arranged around the center of gravity of the fairing body, has the advantages of balanced impulse and small impact, and has simpler and controllable structure, effectively reduced cost and better economy by utilizing the mechanical energy storage device.
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 energy storage device is separated in a horizontal throwing mode, 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 protection is facilitated.
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, which is far away from the piston, is fixedly connected with the first mounting seat, and one end of the piston, which is far away from the guide seat, is abutted with the second mounting seat; an energy storage spring is arranged between the piston and the guide seat.
Preferably, a first boss is formed by outwards extending one end of the piston, which is close to the second mounting seat, a second boss is formed by outwards extending one end of the guide seat, which is close to the first mounting seat, the energy storage spring is sleeved on the periphery of the piston, and the energy storage spring is in compression abutting connection between the second bosses of the first boss. Before the explosion bolt is unlocked, the energy storage spring is always in a compressed state, after the explosion 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 mutually separated.
Preferably, a circle of positioning groove is arranged on 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 stop component is arranged on one side of the guide seat far away from the first mounting seat, and the periphery of the stop component protrudes out of the outer wall of the guide seat; and a limiting plate matched with the stop component is formed by inward extending at one end of the piston, which is close to the first mounting seat. The design of limiting plate and backstop subassembly can inject the effective stroke of adjusting energy storage device, and after the separation of first cover body and 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 comprises a stop screw in threaded connection with the guide holder.
Preferably, the stop assembly further comprises a plurality of stop gaskets clamped between the stop screw and the guide seat. The design of backstop gasket is convenient for adjust each energy storage device's effective stroke for each energy storage device's effective stroke is unanimous, ensures that impulse is balanced, makes the steady separation of first cover body and second cover body.
Preferably, a first positioning hole is formed in the radial direction of the piston in a penetrating manner, a second positioning hole is formed in the radial direction of the guide seat in a penetrating manner, and the same positioning rod is movably arranged in the first positioning hole and the second positioning hole in a penetrating manner. The design of locating lever can inject the relative position between piston and the guide holder before the installation, after separator installs on the radome fairing body, can take off the locating lever.
Preferably, the fairing body includes bipyramid section, cylindricality section and first toper section in proper order from front to back, bipyramid section includes second toper section and third toper section from front 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 embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. Like elements or portions are generally identified by like reference numerals throughout the several figures. In the drawings, elements or portions thereof are not necessarily drawn to scale.
Fig. 1 is a schematic structural diagram of a dome level-throwing separation device with spring thrust action according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a connection structure between a first cover and four sets of separating mechanisms according to an embodiment of the present invention;
FIG. 3 is a schematic view 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 housing; 12-a second cover; 2-separation means; 21-a first mount; 22-a second mount; 23-a guide seat; 24-piston; 241-limiting plate; 25-energy storage springs; 26-stop screw; 27-locating lever.
Detailed Description
Embodiments of the technical scheme of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for more clearly illustrating the technical aspects of the present invention, and thus are merely examples, and are not intended to limit the scope of the present invention.
As shown in fig. 1, fig. 2, fig. 3 and fig. 4, the present embodiment provides a fairing level-throwing separation device with spring pushing effect, including a fairing body 1, the fairing body 1 sequentially includes a double cone section, a cylindrical section and a first cone section from front to back, the double cone section includes a second cone section and a third cone section from front to back, large diameter ends of the first cone section and the third cone section are connected with the cylindrical section, and taper of the second cone section is greater than taper of the third cone section.
Specifically, the fairing body 1 includes a first fairing body 11 and a second fairing body 12, where the first fairing body 11 and the second fairing body 12 are connected by explosion bolts (not shown in the figure), and four sets of separation mechanisms are provided in the fairing body 1 and are arranged in a central symmetry manner around the center of gravity of the fairing body 1. When the explosion bolt is unlocked, each group of separation mechanisms simultaneously provides 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, and because the four groups of separation mechanisms are arranged in a central symmetry mode around the gravity center of the fairing body 1, the impulse is more balanced, and the separation of the fairing body 1 is more stable.
In this embodiment, each of the separating mechanisms includes a separating device 2, where 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. An energy storage device is arranged between the first mounting seat 21 and the second mounting seat 22, the energy storage device comprises a guide seat 23 and a piston 24 sleeved on the periphery of the guide seat 23, one end, away from the piston 24, of the guide seat 23 is fixedly connected with the first mounting seat 21, and one end, away from the guide seat 23, of the piston 24 is abutted with the second mounting seat 22. Specifically, a first boss is formed by extending one end of the piston 24 close to the second mounting seat 22 outwards, a second boss is formed by extending one end of the guide seat 23 close to the first mounting seat 21 outwards, an energy storage spring 25 is sleeved on the periphery of the piston 24, the energy storage spring 25 is in compression butt between the second bosses of the first boss, a circle of positioning groove is formed in one side, far away from the first mounting seat 21, of the second boss, and the energy storage spring 25 is arranged in the positioning groove in a penetrating mode.
The dome horizontal projectile separation device with the spring pushing effect in this embodiment is used for protecting a rocket when penetrating through the atmosphere, after penetrating through the atmosphere, an ignition control explosion bolt is unlocked, and when the explosion bolt is unlocked, the piston 24 and the guide seat 23 are mutually far away under the action of the energy storage spring 25, and impulse is respectively transmitted to the first cover 11 and the second cover 12, so that the first cover 11 and the second cover 12 are mutually separated. The mechanical separation structure is simple to operate, low in cost and good in economical efficiency.
Further, a stop assembly is arranged on one side of the guide seat 23 far 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 periphery of a screw head of the stop screw 26 protrudes out of the outer wall of the guide seat 23; a limiting plate 241 is formed to be fitted to the stopper assembly by extending inward at an end of the piston 24 near the first mounting seat 21. During separation, the piston 24 and the guide seat 23 are far away from each other, but under the cooperation of the limiting 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 garbage is prevented from being generated.
In this embodiment, the minimum distance between the limiting plate 241 and the stop assembly is the effective stroke of the energy storage device 2, and by adjusting the effective stroke, the impulse acting on the fairing body 1 can be adjusted, so that the stop assembly of this embodiment further includes a plurality of stop gaskets (not shown in the figure) sandwiched between the stop screw 26 and the guide seat 23, and when necessary, the stop gaskets can be added to adjust the effective stroke, so that the adjustment process is simple and convenient, and safe and reliable.
More specifically, a first positioning hole is formed through the piston 24 in the radial direction, a second positioning hole is formed through the guide seat 23 in the radial direction, and the same positioning rod 27 is movably inserted into the first positioning hole and the second positioning hole. Before installation, the positioning rod 27 can be used for limiting the relative position between the piston 24 and the guide seat 23, and after the separating device 2 is installed on the fairing body 1, the positioning rod 27 can be removed, so that the separating device can be separated after the later explosion bolt is unlocked.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the 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 scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced with equivalents; such modifications and substitutions do not depart from the spirit of the invention, and are intended to be included within the scope of the appended claims and description.
Claims (6)
1. The utility model provides a radome fairing level jettisoning separator of spring thrust effect, includes the radome fairing body, and this radome fairing body includes first cover body and second cover body, first cover body and second cover body pass through explosion bolted connection, its characterized in that:
four groups of separation mechanisms are arranged in the fairing body and are arranged in a central symmetry mode around the gravity center of the fairing body;
each group of separation mechanism comprises a plurality of separation devices, each separation device comprises a first installation seat and a second installation seat, the first installation seats and the second installation seats are respectively and fixedly connected with the first cover body and the second cover body, an energy storage device is arranged between the first installation seats and the second installation seats, and when the explosion bolts are unlocked, the energy storage device is used for applying impulse to the first cover body and the second cover body;
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 with the second mounting seat;
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, which is far away from the piston, is fixedly connected with the first mounting seat, and one end of the piston, which is far away from the guide seat, is abutted with the second mounting seat;
an energy storage spring is arranged between the piston and the guide seat;
one end of the piston, which is close to the second mounting seat, extends outwards to form a first boss, one end of the guide seat, which is 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 in compression abutting joint between the second bosses of the first boss;
a stop component is arranged on one side, far away from the first mounting seat, of the guide seat, and the periphery of the stop component protrudes out of the outer wall of the guide seat;
and a limiting plate matched with the stop component is formed by inward extending at one end of the piston, which is close to the first mounting seat.
2. A spring thrust dome level throw separator as set forth in claim 1 wherein:
one side of the second boss, which is far away from the first mounting seat, is provided with a circle of positioning groove, and the energy storage spring is arranged in the positioning groove in a penetrating way.
3. A spring thrust dome level throw separator as set forth in claim 1 wherein:
the stop assembly comprises a stop screw in threaded connection with the guide seat.
4. A spring thrust dome level throw separator as set forth in claim 3 wherein:
the stop assembly further comprises a plurality of stop gaskets clamped between the stop screw and the guide seat.
5. A spring thrust dome level throw separator as set forth in claim 1 wherein:
the radial direction of the piston is communicated with a first positioning hole, the radial direction of the guide seat is communicated with a second positioning hole, and the first positioning hole and the second positioning hole are internally and movably penetrated with the same positioning rod.
6. A spring thrust dome level throw separator as set forth in claim 1 wherein:
the fairing body includes bipyramid section, cylindricality section and first toper section in proper order from front to back, bipyramid section is from front to back including second toper section and third toper section, 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 CN112815789A (en) | 2021-05-18 |
| CN112815789B true 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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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| US6494406B1 (en) * | 1998-12-24 | 2002-12-17 | National Space Development Agency Of Japan | Rocket fairing and method of opening the same |
| JP2017121859A (en) * | 2016-01-07 | 2017-07-13 | 川崎重工業株式会社 | Fairing, rocket provided with the same, and separation method of fairing |
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| JP4298306B2 (en) * | 2003-01-27 | 2009-07-15 | 日油技研工業株式会社 | Member separation device |
| JP2014037166A (en) * | 2012-08-11 | 2014-02-27 | Moritaka Nagasaki | Coupling-separation mechanism of rocket fairing |
| CN103292641B (en) * | 2013-05-10 | 2014-11-19 | 北京宇航系统工程研究所 | Explosive separation device used for longitudinal separation of fairing |
| CN103407585A (en) * | 2013-07-25 | 2013-11-27 | 上海宇航系统工程研究所 | Spring separating device |
| CN106321573A (en) * | 2016-11-04 | 2017-01-11 | 哈尔滨理工大学 | Quickly butting structure for fairing |
| CN206801707U (en) * | 2017-04-20 | 2017-12-26 | 中国航发商用航空发动机有限责任公司 | Rectification shade assembly, nacelle and fanjet |
| CN109186376A (en) * | 2018-10-09 | 2019-01-11 | 北京星际荣耀空间科技有限公司 | A kind of limit-type Separation momentum offer device based on spring |
| CN208818087U (en) * | 2018-10-09 | 2019-05-03 | 北京星际荣耀空间科技有限公司 | A kind of limit-type Separation momentum offer device based on spring |
| US10377510B1 (en) * | 2018-11-14 | 2019-08-13 | Vector Launch Inc. | Enhanced fairing mechanisms for launch systems |
| CN109625338B (en) * | 2018-12-12 | 2022-07-15 | 湖北航天飞行器研究所 | Self-throwing-away fairing and rocket |
| CN109573115B (en) * | 2018-12-29 | 2020-09-15 | 湖北航天技术研究院总体设计所 | Radome fairing opening device |
| CN110282161A (en) * | 2019-05-27 | 2019-09-27 | 上海机电工程研究所 | Radome fairing separator and its separation method |
| CN210942314U (en) * | 2019-08-12 | 2020-07-07 | 重庆零壹空间科技集团有限公司 | Elastic separation mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1834482A1 (en) * | 1991-01-02 | 1996-04-27 | Научно-производственное объединение "Тайфун" | Method of separation of nose section and fairing and nose section of research rocket |
| US6494406B1 (en) * | 1998-12-24 | 2002-12-17 | National Space Development Agency Of Japan | Rocket fairing and method of opening the same |
| JP2017121859A (en) * | 2016-01-07 | 2017-07-13 | 川崎重工業株式会社 | Fairing, rocket provided with the same, and separation method of fairing |
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| CN112815789A (en) | 2021-05-18 |
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