CN213873999U - Carrier rocket - Google Patents
Carrier rocket Download PDFInfo
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- CN213873999U CN213873999U CN202120851609.5U CN202120851609U CN213873999U CN 213873999 U CN213873999 U CN 213873999U CN 202120851609 U CN202120851609 U CN 202120851609U CN 213873999 U CN213873999 U CN 213873999U
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Abstract
The utility model discloses a carrier rocket, which comprises a plurality of carrier cabin sections which are connected in sequence, wherein two adjacent carrier cabin sections are connected through an interstage parting surface, an engine spray pipe of the carrier cabin section is arranged inside the interstage parting surface, and the interstage parting surface comprises an upper stage residual shell section, a separating device and a lower stage separating shell section which are connected in sequence; wherein, the upper stage residual shell section and/or the lower stage separation shell section are integrally formed with the carrying cabin section. The utility model discloses well multistage carrier rocket forms the stage separation face of multistage delivery through separator, has consequently reduced the unusual separation risk of stage separation face to and improved the protection to the engine spray tube, the surplus shell section of higher authority is favorable to engine spray tube department air current guide in addition, avoids the engine spray tube too protrusion delivery capsule section, improves cabin section wholeness ability.
Description
Technical Field
The utility model relates to an aerospace propulsion technical field, concretely relates to carrier rocket.
Background
With the development of engine technology, rocket separation rings are larger and larger, and when the rocket is subjected to stage separation, a shell section is generally cut into an upper part and a lower part by an initiating explosive cutting rope, so that unlocking separation of two bodies is realized, an upper stage and a lower stage of the rocket are connected by the shell section, and the initiating explosive cutting rope is arranged on the shell section. When the firer cutting rope receives the separation signal, the firer cutting rope detonates to cut the shell section into an upper part and a lower part, one part continuously flies along with the upper stage, and the other part is thrown off along with the lower stage, so that two-stage separation is realized, and meanwhile, in order to reduce the takeoff weight of the upper stage, the separation surface is often close to the upper stage as much as possible.
And after the two-stage separation is caused by the separation mode, the distance for pulling out the spray pipe is longer, the risk of collision between the spray pipe of the engine at the upper stage and the shell section in the pulling-out process is increased, and the swing angle of the spray pipe in the separation process is also limited.
Disclosure of Invention
An object of the utility model is to provide a carrier rocket and carrier rocket to after solving among the prior art rocket split ring two-stage separation, the distance that the spray tube was extracted is longer, has increased and has extracted the in-process, and the risk of higher authority engine spray tube and shell section collision has also restricted the technical problem of the swing angle of spray tube in the separation process.
In order to solve the above technical problem, the utility model particularly provides the following technical scheme:
a launch vehicle comprising a plurality of launch capsule sections, adjacent two of said launch capsule sections being joined by an interstage separation surface, the engine nozzles of said launch capsule sections being disposed within said interstage separation surface, said interstage separation surface comprising an upper stage residual shell section, separation means, and a lower stage separation shell section joined in series;
wherein the upper stage residual shell section and/or the lower stage separation shell section are integrally formed with the carrier bay section.
As a preferred scheme of the utility model, separator include that both ends are connected respectively in the upper surplus shell section with the main shell section of lower level separation shell section all be provided with the hoop cutting cable in the circumference of the upper and lower tip of main shell section, the equidistant multichannel vertical cutting cable that is provided with on the surface of main shell section, the hoop cutting cable with the junction of vertical cutting cable sets up detonating joint or biography explosive joint.
As a preferred scheme of the utility model, the hoop cutting cable the longitudinal cutting cable corresponds be provided with the weakening groove on the surface of main shell section, the hoop cutting cable with the longitudinal cutting cable is all installed through the safety cover device on the main shell section, just the safety cover device makes the hoop cutting cable or the longitudinal cutting cable with the weakening groove keeps unanimous.
As an optimized scheme of the utility model, it connects with perpendicular to be provided with fastener installation arch on the internal surface of main shell section the safety cover location step on main shell section surface, safety cover location step with between the fastener installation arch main shell section forms the installation hoop cutting cable or the mounting groove of vertical cutting cable, the top of safety cover device with safety cover location step contact, just the safety cover device pass through the bolt with fastener installation arch is connected.
As a preferred scheme of the utility model, the safety cover device include with mounting groove complex safety cover main part, install the energy-absorbing gasket in the safety cover main part, the top of safety cover main part with safety cover location step contact.
As a preferred scheme of the utility model, the initiation connects and sets up the upper end of main shell section the hoop cutting cable with the junction of vertical cutting cable, and be in the hoop cutting cable with the redundant setting of junction of vertical cutting cable initiation connects and passes and explodes the joint.
Compared with the prior art, the utility model following beneficial effect has:
the utility model discloses well multistage carrier rocket forms the stage separation face of multistage delivery through separator, consequently, the unusual separation risk of stage separation face has been reduced, and the protection to the engine nozzle has been improved, it is favorable to engine nozzle department air current guide in addition to go up the surplus shell section of level, avoid the engine nozzle too protrusion delivery capsule section, improve capsule section wholeness ability, the weight of taking off when carrying out the rocket body separation through the accurate control rocket, and it increases the extraction length of spray tube not excessively to cross, thereby make the spray tube freely swing as early as possible, reduce the risk of engine nozzle and casing collision.
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. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
Fig. 1 is a schematic structural view of a shell segment provided with circumferential and longitudinal cutting cords according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a protective cover device according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a launch vehicle according to an embodiment of the present invention.
The reference numerals in the drawings denote the following, respectively:
1-a main shell section; 2, cutting a cable in a circumferential direction; 3-longitudinal cutting rope; 4-a detonating joint; 5-booster joint; 6-weakening grooves; 7-a protective cover device; 8-fastener mounting bosses; 9-a protective cover positioning step; 10-mounting grooves; 11-a bolt; 12-a carrying bay section; 13-interstage separation surface; 14-upper stage residual shell section; 15-lower stage separation shell section; 16-an engine nozzle;
71-a boot body; 72-energy absorbing shim.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
As shown in fig. 1 and 2, the utility model provides a carrier rocket, including main shell section 1, all be provided with hoop cutting cable 2 in the circumference of the upper and lower tip of main shell section 1, main shell section 1's equidistant multichannel vertical cutting cable 3 that is provided with on the surface, the junction of hoop cutting cable 2 and vertical cutting cable 3 sets up detonating joint 4 or booster joint 5.
In the process of rocket separation initiation, the grid cutting design of the shell section 1 is changed into grid cutting through the annular cutting cables 2 and the longitudinal cutting cables 3 in a pure linear cutting mode by adding T-shaped cross points (initiation joints 4 or booster joints 5) at the end part of the main shell section 1, and the main shell section 1 is uniformly divided after initiation is finished, so that more takeoff weights can be removed, the pulling-out length of the spray pipe is not increased, the spray pipe can freely swing as soon as possible, and the risk of collision between the spray pipe and the shell section is reduced.
The outer surface of the main shell section 1 corresponding to the annular cutting rope 2 and the longitudinal cutting rope 3 is provided with a weakening groove 6, the annular cutting rope 2 and the longitudinal cutting rope 3 are both installed on the main shell section 1 through a protection cover device 7, the protection cover device 7 enables the annular cutting rope 2 or the longitudinal cutting rope 3 to be consistent with the weakening groove 6, and the weakening groove 6 is specifically a groove with an arc-shaped longitudinal section, wherein the arc-shaped longitudinal section is arranged on the surface of the main shell section 1 opposite to the annular cutting rope 2 or the longitudinal cutting rope 3.
The inner surface of the main shell section 1 is provided with a fastener mounting protrusion 8 and a protective cover positioning step 9 vertically connected to the surface of the main shell section 1, the main shell section 1 between the protective cover positioning step 9 and the fastener mounting protrusion 8 forms a mounting groove 10 for mounting the circumferential cutting rope 2 or the longitudinal cutting rope 3 (the weakening groove 6 is located in the middle of the mounting groove 10), the top of the protective cover device 7 is in contact with the protective cover positioning step 9, and the protective cover device 7 is connected with the fastener mounting protrusion 8 through a bolt 11.
Compare with current rocket shell segment safety cover, the utility model provides a current elbow part of cutting cable safety cover upper end has been removed to safety cover location step 9, and the cutting piece probably can follow here departure, but safety cover location step replaces the safety cover to play clastic direction and guard action.
The fastener mounting boss 8 reduces the thickness of the protective cover device 7 and increases the thickness of the shell section 1, which functions in two ways:
1) the complexity of the longitudinal section of the protective cover device 7 is reduced, so that the protective cover device 7 is attached to the shell section 1 in a planar state, and the production and processing of the protective cover device 7 are simpler;
2) the thickness difference between the wall surface of the main shell section 1 and the cutting position is increased, and if the cutting position is torn, the thickening effect of the main shell section 1, which is played by the fastener mounting protrusion 8, can effectively prevent the crack from extending.
The protective cover device 7 comprises a protective cover main body 71 matched with the mounting groove 10, an energy absorption gasket 72 is mounted on the protective cover main body 71, and the top of the protective cover main body 71 is in contact with the protective cover positioning step 9;
the energy absorption gasket 72 is a special-shaped thin gasket, the thickness of the special-shaped thin gasket is about 1-2 mm, and the special-shaped thin gasket acts like a spring piece.
The lower end of the energy absorbing pad 72 is fixed to the bolt attachment hole of the main shell segment 1 for attaching the bolt 11 via the protective cover body 71, and the upper end of the energy absorbing pad 72 is closely attached to the protective cover body 71 up to the position of the cutting cord.
When the cutting rope works, the protective cover main body 71 is impacted to move backwards, and the energy-absorbing gasket 72 is impacted;
the energy-absorbing pad 72 moves backwards and then turns back under the elastic action of the energy-absorbing pad to hit the protective cover main body 71, so that the detonation energy of the initiating explosive device is dissipated, the deformation of the protective cover main body 71 is reduced, and the detonation energy is absorbed by increasing the energy-absorbing pad 72, so that the detonation impact of the initiating explosive device is reduced.
The initiation connector 4 is arranged at the joint of the circumferential cutting cable 2 and the longitudinal cutting cable 3 at the upper end part of the main shell section 1, and the initiation connector 4 and the booster connector 5 are redundantly arranged at the joint of the circumferential cutting cable 2 and the longitudinal cutting cable 3.
Specifically, taking 4 longitudinal cutting cables 3 as an example, the number of the initiation connectors 4 and the booster structures 5 located at the upper end portion of the main shell section 1 is two, and the two initiation connectors 4 and the two booster connectors 5 are symmetrically arranged with the circle center of the upper end portion of the main shell section 1 as a symmetry center.
Further, the utility model provides a launch vehicle, including a plurality of launch vehicle sections 12, two adjacent said launch vehicle sections 12 are connected through interstage separation face 13, the engine spray pipe 16 of said launch vehicle section 12 sets up inside said interstage separation face 13, said interstage separation face 13 includes the surplus shell section 14 of last stage, separation device and the lower stage separation shell section 15 that connect in order;
the upper stage residual shell section 14 and/or the lower stage separation shell section 15 are/is integrally formed with the carrier tank section 12, and the connection state of the upper stage residual shell section 14, the lower stage separation shell section 15 and the carrier tank section of the carrier rocket is controlled according to the inter-stage separation requirement of the carrier rocket in a specific flight environment.
Further illustratively, the axial length of the upper stage residual shell section 14 is smaller than the axial length of the lower stage separation shell section 15, and the upper stage residual shell section 14 is integrally formed with the main shell section 1 at the protective cover positioning step 9.
The utility model discloses well multistage carrier rocket forms the stage separation face of multistage delivery through separator, has consequently reduced the unusual separation risk of stage separation face to and improved the protection to the engine spray tube, the surplus shell section 14 of higher authority still is favorable to locating the air current guide to engine spray tube 14 in addition, avoids engine spray tube 14 too protrusion delivery capsule section 12, improves capsule section wholeness ability.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.
Claims (6)
1. A launch vehicle comprising a plurality of sequentially connected launch vehicle sections (12), adjacent two of said launch vehicle sections (12) being connected by an interstage separation surface (13), the engine nozzles (16) of said launch vehicle sections (12) being disposed inside said interstage separation surface (13), said interstage separation surface (13) comprising sequentially connected upper stage residual shell sections (14), separation means, and lower stage separation shell sections (15);
wherein the upper stage residual shell section (14) and/or the lower stage separation shell section (15) are integrally formed with the carrier bay section (12).
2. A launch vehicle according to claim 1, characterised in that the separation device comprises a main casing section (1) having two ends connected to the remaining casing section (14) of the upper stage and the separation casing section (15) of the lower stage, respectively, circumferential cutting wires (2) are provided in the circumferential direction of the upper and lower ends of the main casing section (1), a plurality of longitudinal cutting wires (3) are provided on the surface of the main casing section (1), and a detonation joint (4) or a booster joint (5) is provided at the joint of the circumferential cutting wires (2) and the longitudinal cutting wires (3).
3. A launch vehicle according to claim 2, characterised in that the circumferential cutting cables (2) and the longitudinal cutting cables (3) are provided with weakening grooves (6) on the outer surface of the main casing section (1) in correspondence of which the circumferential cutting cables (2) and the longitudinal cutting cables (3) are mounted on the main casing section (1) by means of protective cover means (7), and in that the protective cover means (7) keep the circumferential cutting cables (2) or the longitudinal cutting cables (3) in correspondence of the weakening grooves (6).
4. A launch vehicle according to claim 3, characterised in that the main hull section (1) is provided on its inner surface with fastener mounting bosses (8) and with boot positioning steps (9) attached perpendicularly to the surface of the main hull section (1), the main hull section (1) between the boot positioning steps (9) and the fastener mounting bosses (8) forming mounting slots (10) for the circumferential cutting wires (2) or the longitudinal cutting wires (3), the top of the boot device (7) being in contact with the boot positioning steps (9), and the boot device (7) being connected to the fastener mounting bosses (8) by means of bolts (11).
5. A launch vehicle according to claim 4, characterised in that the protective cover device (7) comprises a protective cover body (71) cooperating with the mounting slot (10), the protective cover body (71) having an energy absorbing pad (72) mounted thereon, the top of the protective cover body (71) being in contact with the protective cover positioning step (9).
6. A launch vehicle according to claim 2, characterised in that the initiation connection (4) is arranged at the junction of the circumferential cutting cord (2) and the longitudinal cutting cord (3) at the upper end of the main casing section (1), and that the initiation connection (4) and the booster connection (5) are redundantly arranged at the junction of the circumferential cutting cord (2) and the longitudinal cutting cord (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120851609.5U CN213873999U (en) | 2021-04-25 | 2021-04-25 | Carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120851609.5U CN213873999U (en) | 2021-04-25 | 2021-04-25 | Carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213873999U true CN213873999U (en) | 2021-08-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120851609.5U Active CN213873999U (en) | 2021-04-25 | 2021-04-25 | Carrier rocket |
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| CN (1) | CN213873999U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112109926A (en) * | 2020-08-31 | 2020-12-22 | 南京理工大学 | Explosive cutting and separating device for rapid cabin opening of aircraft |
| CN113865444A (en) * | 2021-10-29 | 2021-12-31 | 重庆零壹空间科技集团有限公司 | Solid rocket cold separation device and use method thereof |
| CN113865445A (en) * | 2021-08-31 | 2021-12-31 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN114322679A (en) * | 2021-12-31 | 2022-04-12 | 重庆零壹空间航天科技有限公司 | Solid rocket cold separation stage section suitable for automatic manufacturing |
| CN114623734A (en) * | 2022-03-04 | 2022-06-14 | 湖北航天技术研究院总体设计所 | Rocket interstage separation protection device and protection method |
| CN114906351A (en) * | 2022-05-17 | 2022-08-16 | 哈尔滨工业大学 | Composite material structure fire separation device capable of achieving tidy cutting |
| CN115535311A (en) * | 2022-10-27 | 2022-12-30 | 湖北航天技术研究院总体设计所 | Interstage separation device for multiple separation and separation method thereof |
-
2021
- 2021-04-25 CN CN202120851609.5U patent/CN213873999U/en active Active
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112109926A (en) * | 2020-08-31 | 2020-12-22 | 南京理工大学 | Explosive cutting and separating device for rapid cabin opening of aircraft |
| CN113865445A (en) * | 2021-08-31 | 2021-12-31 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN113865445B (en) * | 2021-08-31 | 2022-12-27 | 北京宇航系统工程研究所 | Network separation device without booster node |
| CN113865444A (en) * | 2021-10-29 | 2021-12-31 | 重庆零壹空间科技集团有限公司 | Solid rocket cold separation device and use method thereof |
| CN114322679A (en) * | 2021-12-31 | 2022-04-12 | 重庆零壹空间航天科技有限公司 | Solid rocket cold separation stage section suitable for automatic manufacturing |
| CN114623734A (en) * | 2022-03-04 | 2022-06-14 | 湖北航天技术研究院总体设计所 | Rocket interstage separation protection device and protection method |
| CN114906351A (en) * | 2022-05-17 | 2022-08-16 | 哈尔滨工业大学 | Composite material structure fire separation device capable of achieving tidy cutting |
| CN115535311A (en) * | 2022-10-27 | 2022-12-30 | 湖北航天技术研究院总体设计所 | Interstage separation device for multiple separation and separation method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220727 Address after: 511400 room 1702, No. 1, Cuiying street, Nansha District, Guangzhou, Guangdong Province (office only) Patentee after: Guangzhou Zhongke Aerospace Exploration Technology Co.,Ltd. Address before: 100190, No. 15 West Fourth Ring Road, Beijing, Haidian District Patentee before: INSTITUTE OF MECHANICS, CHINESE ACADEMY OF SCIENCES |
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| TR01 | Transfer of patent right |