CN115790294A - Binding connecting rod mechanism of rocket booster - Google Patents
Binding connecting rod mechanism of rocket booster Download PDFInfo
- Publication number
- CN115790294A CN115790294A CN202310044909.6A CN202310044909A CN115790294A CN 115790294 A CN115790294 A CN 115790294A CN 202310044909 A CN202310044909 A CN 202310044909A CN 115790294 A CN115790294 A CN 115790294A
- Authority
- CN
- China
- Prior art keywords
- bolt
- rocket
- cylinder
- fixedly connected
- rocket booster
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Clamps And Clips (AREA)
Abstract
The invention provides a binding connecting rod mechanism of a rocket booster, and relates to the technical field of connecting structures. The problems that the length of a traditional binding connecting rod mechanism cannot be adjusted, connection is complex, and an explosive bolt is easy to rebound to cause separation failure and the like are solved. The binding link mechanism of the rocket booster comprises: the first pull lug is used for being connected with the rocket booster; the first separating barrel is fixedly connected with the first pull lug; a second separator bowl detachably connected to the first separator bowl; the adjusting cylinder is fixedly connected with the second separating cylinder; and the second pulling lug is fixedly connected with the adjusting cylinder and is used for being connected with the core-level rocket. The scheme of the invention realizes the adjustment of the integral length of the binding connecting rod mechanism, and has the advantages of reliable separation, small mass, simple structure and convenient installation.
Description
Technical Field
The invention relates to the technical field of connecting structures, in particular to a binding connecting rod mechanism of a rocket booster.
Background
The binding connecting rod mechanism is used for a main connection mode of the rocket booster and the core-stage rocket, has the main function of bearing the additional moment generated by the booster to the core stage, and realizes the function of separating the booster when the booster is separated. The binding mechanism of the rocket booster is mainly divided into the following parts according to the form: a connecting rod type binding mechanism, a wedge type binding mechanism, a ball head connecting rod mechanism and the like. The binding mechanism divided according to the separation mode mainly comprises: pneumatic unlocking, mechanical unlocking, electric unlocking and initiating explosive device unlocking.
The binding connecting rod mechanism needs to comprehensively consider the defects of simple structure, light weight, reliable separation, assembly adjustability, release local degree of freedom and the like, the traditional binding connecting rod does not have the length adjustable quantity, the connection is complex, the expansion of the rocket booster easily causes the relative displacement between the rocket booster and a core-level rocket, and the separation failure is caused by the easy rebound of an explosive bolt.
Disclosure of Invention
The invention provides a binding connecting rod mechanism of a rocket booster. The problems that the length of a traditional binding connecting rod mechanism cannot be adjusted, the connection is complex, and an explosive bolt is easy to rebound to cause failure and the like are solved.
In order to solve the technical problems, the technical scheme of the invention is as follows:
the embodiment of the invention provides a binding connecting rod mechanism of a rocket booster, which comprises:
the first pull lug is used for being connected with the rocket booster;
the first separating barrel is fixedly connected with the first pull lug;
a second separator bowl detachably connected to the first separator bowl;
the adjusting cylinder is fixedly connected with the second separating cylinder;
and the second pulling lug is fixedly connected with the adjusting cylinder and is used for being connected with the core-level rocket.
Optionally, the second separating cylinder is provided with a left-handed thread, and the second pull lug is provided with a right-handed thread;
the adjusting cylinder is connected with the second separating cylinder through a left-handed thread at one end, and the second pull lug is connected with the right-handed thread at one end.
Optionally, the first separation cylinder is detachably connected to the second separation cylinder through an explosion bolt and an explosion bolt nut.
Optionally, an explosive bolt washer is arranged in a clamping gap between the second separating cylinder and the explosive bolt.
Optionally, the first pull tab and the second pull tab are placed at 90 degrees.
Optionally, a first energy absorption block is arranged inside the first pull lug; and a second energy absorption block is arranged in the second pull lug.
Optionally, the first pull lug is fixedly connected with the rocket booster through a first pin bolt and a first self-locking nut; and the first end of the second pull lug is connected with the core-level rocket through a second pin bolt and a second self-locking nut.
Optionally, the binding link mechanism of the rocket booster further includes: an explosive bolt cable on the first and second separation barrels, the explosive bolt cable electrically connected with the explosive bolt;
and covering the heat-proof protective cover of the explosive bolt cable, wherein the heat-proof protective cover is fixedly connected with the first separating cylinder and the second separating cylinder.
Optionally, the heat-proof protective cover is fixedly connected with the first separating cylinder and the second separating cylinder through at least one protective cover bolt.
Optionally, when the protection cover bolt is inserted into the connecting hole of the heat-proof protection cover, the protection cover bolt and the heat-proof protection cover are further provided with a protection cover spring washer and a protection cover flat washer.
The scheme of the invention at least comprises the following beneficial effects:
the invention relates to a binding connecting rod mechanism of a rocket booster, which comprises: the first pull lug is used for being connected with the rocket booster; the first separating barrel is fixedly connected with the first pull lug; a second separator bowl detachably connected to the first separator bowl; the adjusting cylinder is fixedly connected with the second separating cylinder; and the second pulling lug is fixedly connected with the adjusting cylinder and is used for being connected with the core-level rocket. The binding linkage mechanism has the advantages of adjustable overall length, reliable separation, small mass, simple structure and convenient installation.
Drawings
FIG. 1 is a cross-sectional view in elevation of a binding linkage mechanism of the rocket booster of the present invention;
FIG. 2 is a perspective view of a binding linkage mechanism of the rocket booster of the present invention;
FIG. 3 is an elevation view of a binding linkage mechanism of the rocket booster of the present invention;
FIG. 4 is a top view of the binding linkage mechanism of the rocket booster of the present invention;
figure 5 is an exploded schematic view in cross section of the binding linkage mechanism of the rocket booster of the present invention.
Description of reference numerals:
1. a first pin bolt; 2. a first self-locking nut; 20. a separating surface; 21. a second pin bolt; 22. a second self-locking nut; 23. a second flat washer; 3. a first flat gasket; 4. a first pull tab; 5. a first separation drum; 6. a first energy absorbing block; 7. explosive bolt cables; 8. a heat-proof protective cover; 9. exploding the bolt and nut; 10. exploding the bolt; 11. a second separation drum; 12. an explosive bolt washer; 13. an adjusting cylinder; 14. a second energy absorbing block; 15. a second pull tab; 16. a shield bolt.
Description of the preferred embodiment
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1 to 5, an embodiment of the present invention provides a binding link mechanism of a rocket booster, including:
a first pull lug 4 for connecting with the rocket booster;
the first separating cylinder 5 is fixedly connected with the first pull lug 4;
a second separation cylinder 11 detachably connected to the first separation cylinder 5;
the adjusting cylinder 13 is fixedly connected with the second separating cylinder 11;
and the second pull lug 15 is fixedly connected with the adjusting cylinder 13, and the second pull lug 15 is used for being connected with the core-level rocket.
The first pull lug 4 is fixedly connected with the rocket booster through a first pin bolt 1 and a first self-locking nut 2.
In this embodiment, a first end of the first pull lug 4 is fixedly connected with the rocket booster, a second end of the first pull lug 4 is provided with an external thread, a first end of the first separation barrel 5 is provided with an internal thread, and a second end of the first pull lug 4 is fixedly connected with a first end of the first separation barrel 5 through the internal and external threads;
the first pull lug 4 is fixedly connected with the rocket booster through a first pin bolt 1 and a first self-locking nut 2, and a first flat washer 3 for preventing the first pin bolt 1 from loosening is further arranged when the first pin bolt 1 is connected with the first self-locking nut 2; the first pin bolt 1 and the first self-locking nut 2 are connected more tightly;
the first end of the second pull lug 15 is fixedly connected with the core-grade rocket through a second pin bolt 21 and a second self-locking nut 22, and a second flat washer 23 for preventing the second pin bolt 21 from loosening is further arranged when the second pin bolt 21 is connected with the second self-locking nut 22.
In an alternative embodiment of the present invention, the second separating cylinder 11 is provided with a left-hand thread, and the second pull tab 15 is provided with a right-hand thread;
the end of the adjusting cylinder 13 connected with the second separating cylinder 11 is a left-hand thread, and the end connected with the second pull lug 15 is a right-hand thread.
In this embodiment, a first end of the second separating cylinder 11 is provided with a left-handed external thread, a first end of the adjusting cylinder 13 is provided with a left-handed internal thread, the first end of the second separating cylinder 11 is fixedly connected with the first end of the adjusting cylinder 13 through an internal thread and an external thread, a second end of the second pull tab 15 is provided with a right-handed external thread, a second end of the adjusting cylinder 13 is provided with a right-handed internal thread, and the second end of the second pull tab 15 is fixedly connected with the second end of the adjusting cylinder 13 through an internal thread and an external thread; after the second pull lug 15 and the second separation barrel 11 are connected through the adjusting barrel 13, the distance between the second pull lug 15 and the second separation barrel 11 can be adjusted by rotating the adjusting barrel 13 under the condition that the second pull lug 15 and the second separation barrel 11 are kept horizontally immovable.
In this embodiment, the two ends of the adjusting cylinder 13 are designed with different threads, so that the length of the whole binding linkage mechanism can be adjusted by rotating the adjusting cylinder 13 under the condition that the horizontal direction of the second separating cylinder 11 and the second pull lug 15 is kept immovable after the binding linkage mechanism is completed, and the axial displacement difference between the booster and the core-level rocket is satisfied during flight.
In an alternative embodiment of the invention, the first separating cylinder 5 is detachably connected to the second separating cylinder 11 by means of a bursting bolt 10 and a bursting bolt nut 9.
And an explosive bolt washer 12 is arranged in the second separating cylinder 11 and in a clamping gap of the explosive bolt 10, and the explosive bolt washer 12 is sleeved on the explosive bolt 10.
In this embodiment, the explosive bolt nut 9 is disposed in the first separation cylinder 5, the explosive bolt 10 is disposed in the second separation cylinder 11, when assembling, the first separation cylinder 5 and the second separation cylinder 11 are fixedly connected by screwing the explosive bolt nut 9 and the explosive bolt 10, and when the first separation cylinder 5 and the second separation cylinder 11 need to be separated, the explosive bolt nut 9 and the explosive bolt 10 are separated.
In an optional embodiment of the invention, the first pull lug 4 and the second pull lug 15 are placed at 90 degrees, and the design can ensure that the binding link mechanism rotates in two different directions, so that the condition that the rocket booster and the core-level rocket generate relative displacement due to expansion of the rocket booster is effectively prevented.
In an alternative embodiment of the present invention, a first energy absorption block 6 is arranged inside the first pull lug 4; and a second energy absorption block 14 is arranged inside the second pull lug 15.
In this embodiment, a first cavity for accommodating a first energy absorbing block 6 is arranged at a second end of the first pull lug 4, the first energy absorbing block 6 is arranged in the first cavity, a second cavity for accommodating a second energy absorbing block 14 is arranged at a second end of the second pull lug 15, the second energy absorbing block 14 is arranged in the second cavity, and the first energy absorbing block 6 and the second energy absorbing block 14 are designed to eliminate redundant energy generated by separating the explosive bolt nut 9 from the explosive bolt 10 and prevent separation failure caused by rebounding of two separated end debris.
In an optional embodiment of the present invention, the binding linkage mechanism of the rocket booster may further include: explosion bolt cables 7 on the first and second separation barrels 5 and 11, the explosion bolt cables 7 being electrically connected to the explosion bolts 10;
and a heat-proof protective cover 8 covering the explosive bolt cable 7, wherein the heat-proof protective cover 8 is fixedly connected with the first separating cylinder 5 and the second separating cylinder 11.
The heat protection shield 8 is fixedly connected to the first separating cylinder 5 and the second separating cylinder 11 by at least one shield bolt 16.
When the protective cover bolt 16 is inserted into the connecting hole of the heat-proof protective cover 8, a protective cover spring washer and a protective cover flat washer are further arranged between the protective cover bolt 16 and the heat-proof protective cover 8.
In this embodiment, a cable outlet hole is formed in the first separation cylinder 5, one end of the explosive bolt cable 7 is arranged in the first separation cylinder 5 through the cable outlet hole, the explosive bolt cable 7 is electrically connected with a control device of an explosive bolt 10 entering the first separation cylinder 5, the other end of the explosive bolt cable 7 is connected with a flight control system, the flight control system sends a detonation instruction to the explosive bolt 10 through the explosive bolt cable 7 when in use, and the explosive bolt 10 explodes after receiving the detonation instruction, so that the explosive bolt is separated from the explosive bolt nut 9, and the first separation cylinder 5 is separated from the second separation cylinder 11;
in this embodiment, the heat protection shield 8 is designed to ensure that the explosive bolt cable 7 can maintain a normal working temperature during flight.
The assembling process of the binding connecting rod mechanism of the rocket booster in the embodiment is as follows: firstly, one end of an explosion bolt cable 7 penetrates into a first separation barrel 5 through a cable outlet hole and penetrates through an explosion bolt nut 9 to be connected with a control device of an explosion bolt 10 in a second separation barrel 11, then the first separation barrel 5 and the second separation barrel 11 are fixedly connected through the explosion bolt 10 and the explosion bolt nut 9, then the first energy absorption block 6 is installed inside the first pull lug 4, the second end of the first pull lug 4 is fixedly connected with the first separation barrel 5, the second energy absorption block 14 is installed inside the second pull lug 15, the second pull lug 15 is fixedly connected with the second separation barrel 11 through an adjusting barrel 13, the first end of the first pull lug 4 is fixedly connected with a rocket booster, the first end of the second pull lug 15 is fixedly connected with the core-grade rocket, the length of a connecting rod mechanism is adjusted to a proper length through the adjusting barrel 13 after installation is finished, and finally the heat-proof protective cover 8 is fixedly connected with the first separation barrel 5 and the first separation barrel 11 through at least one bolt 16.
And (3) a separation process: when the rocket flies to the rocket booster and needs to detach the core-level rocket, the flight control system sends out a detonation instruction through the explosion bolt cable 7, the explosion bolt 10 explodes after receiving the detonation instruction, and therefore the first separating cylinder 5 and the second separating cylinder 11 are separated at the separating surface 20, and the rocket booster and the core-level rocket are separated.
The binding connecting rod mechanism of the rocket booster adopts the explosive bolt 10 as a separation mode, has reliable separation, is provided with a length adjusting mechanism, can adjust assembly errors during the assembly of a large rocket, meets the requirement of axial displacement difference between the booster and a core-level rocket in the flight process, and has the advantages of small mass, simple structure, convenience in installation and the like.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. A binding linkage mechanism of a rocket booster, comprising:
a first pull lug (4) used for connecting with the rocket booster;
the first separating cylinder (5) is fixedly connected with the first pull lug (4);
a second separating cylinder (11) detachably connected to the first separating cylinder (5);
the adjusting cylinder (13) is fixedly connected with the second separating cylinder (11);
and the second pulling lug (15) is fixedly connected with the adjusting cylinder (13), and the second pulling lug (15) is used for being connected with the core-level rocket.
2. The rocket motor tie linkage according to claim 1,
the second separating cylinder (11) is provided with left-handed threads, and the second pull lug (15) is provided with right-handed threads;
the adjusting cylinder (13) and the second separating cylinder (11) are connected through a left-handed thread, and the second pull lug (15) is connected through a right-handed thread.
3. The rocket booster tie linkage according to claim 2, wherein the first splitter cylinder (5) is detachably connected to the second splitter cylinder (11) by means of an explosion bolt (10) and an explosion bolt nut (9).
4. The binding linkage mechanism of a rocket booster according to claim 3, wherein an explosion bolt washer (12) is arranged in a clamping gap between the second separation barrel (11) and the explosion bolt (10).
5. The rocket booster tie linkage according to claim 1, wherein the first pull tab (4) and the second pull tab (15) are placed at 90 °.
6. The rocket booster tie linkage according to claim 1, wherein a first energy-absorbing block (6) is arranged inside the first pull tab (4); and a second energy absorption block (14) is arranged in the second pull lug (15).
7. The binding linkage mechanism of the rocket booster according to claim 1, wherein the first pull lug (4) is fixedly connected with the rocket booster through a first pin bolt (1) and a first self-locking nut (2); and the first end of the second pull lug (15) is fixedly connected with the core-level rocket through a second pin bolt (21) and a second self-locking nut (22).
8. The rocket motor tie linkage according to claim 3, further comprising: explosion bolt cables (7) on the first and second separation barrels (5, 11), the explosion bolt cables (7) being electrically connected with the explosion bolts (10);
covering a heat protection shield (8) of the explosive bolt cable (7), the heat protection shield (8) with a first separation barrel (5) and a second separation barrel (11) fixed connection.
9. The binding linkage of a rocket booster according to claim 8, wherein said heat shield (8) is fixedly connected to said first and second splitter cylinder (5, 11) by at least one shield bolt (16).
10. The binding link mechanism of a rocket motor according to claim 9, wherein a protective cover spring washer and a protective cover flat washer are further provided between the protective cover bolt (16) and the heat-proof protective cover (8) when the protective cover bolt (16) is inserted into the connecting hole of the heat-proof protective cover (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310044909.6A CN115790294A (en) | 2023-01-30 | 2023-01-30 | Binding connecting rod mechanism of rocket booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310044909.6A CN115790294A (en) | 2023-01-30 | 2023-01-30 | Binding connecting rod mechanism of rocket booster |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115790294A true CN115790294A (en) | 2023-03-14 |
Family
ID=85429183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310044909.6A Pending CN115790294A (en) | 2023-01-30 | 2023-01-30 | Binding connecting rod mechanism of rocket booster |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115790294A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02241900A (en) * | 1989-03-15 | 1990-09-26 | Nissan Motor Co Ltd | Fitting device for booster rocket lower end section |
| CN107585329A (en) * | 2017-08-10 | 2018-01-16 | 大连理工大学 | A kind of carrier rocket wire type bundlees separator |
| CN110949695A (en) * | 2018-12-20 | 2020-04-03 | 中国船舶重工集团应急预警与救援装备股份有限公司 | Booster and core-level rocket binding butt joint vertical direction adjusting system |
| US20200309183A1 (en) * | 2019-03-25 | 2020-10-01 | United States Of America, As Represented By The Secretary Of The Navy | Doubly-Separating Explosively Releasable Bolt |
| CN113955139A (en) * | 2021-10-29 | 2022-01-21 | 中国运载火箭技术研究院 | Adjustable rocket boosting structure and method suitable for unmanned aerial vehicle |
| CN115265293A (en) * | 2022-08-10 | 2022-11-01 | 北京凌空天行科技有限责任公司 | Rocket booster connection structure |
-
2023
- 2023-01-30 CN CN202310044909.6A patent/CN115790294A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02241900A (en) * | 1989-03-15 | 1990-09-26 | Nissan Motor Co Ltd | Fitting device for booster rocket lower end section |
| CN107585329A (en) * | 2017-08-10 | 2018-01-16 | 大连理工大学 | A kind of carrier rocket wire type bundlees separator |
| CN110949695A (en) * | 2018-12-20 | 2020-04-03 | 中国船舶重工集团应急预警与救援装备股份有限公司 | Booster and core-level rocket binding butt joint vertical direction adjusting system |
| US20200309183A1 (en) * | 2019-03-25 | 2020-10-01 | United States Of America, As Represented By The Secretary Of The Navy | Doubly-Separating Explosively Releasable Bolt |
| CN113955139A (en) * | 2021-10-29 | 2022-01-21 | 中国运载火箭技术研究院 | Adjustable rocket boosting structure and method suitable for unmanned aerial vehicle |
| CN115265293A (en) * | 2022-08-10 | 2022-11-01 | 北京凌空天行科技有限责任公司 | Rocket booster connection structure |
Non-Patent Citations (1)
| Title |
|---|
| 陆友人等: "大型运载器捆绑连接技术的综合分析" * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP1950414B1 (en) | Separable blade for wind turbine | |
| EP2538035B1 (en) | Joint assembly | |
| US7509903B2 (en) | Separable structure material | |
| CN103673786B (en) | Impact reducing tail-section linear explosion separating device for small-diameter assisted takeoff rocket | |
| US10640232B2 (en) | Conductive fastening system for composite structures | |
| RU2428356C2 (en) | Nut system and aircraft engine strut with said system | |
| CN112815789A (en) | Fairing horizontal throwing separation device with spring pushing and punching functions | |
| CN107031871A (en) | A kind of cutting separator of fiber-reinforced composite materials structures | |
| CN110143297B (en) | Reduce towards and bury a structure suitable for great unit of heat conduction demand on spacecraft | |
| CN106123709A (en) | Flight Vehicle Stage Separation device | |
| CN115790294A (en) | Binding connecting rod mechanism of rocket booster | |
| RU2493413C2 (en) | Device to suppress transverse forces by separation of reactive jet acting at jet engine nozzle, and jet engine nozzle | |
| CN113847851A (en) | Linear separation structure suitable for decoupling large-pressure load and small-tension load | |
| US3204515A (en) | Explosively releasable nut assembly | |
| RU2401414C1 (en) | Device for rocket separation | |
| US6925939B2 (en) | Low shock separation bolt | |
| US20130034437A1 (en) | Fastening device particularly suitable for the fastening between an air intake and an engine of an aircraft nacelle | |
| CN113340159A (en) | Self-adjusting type rotating throwing fairing separating mechanism | |
| US20030173456A1 (en) | Device for recovery of forces generated by an aircraft engine | |
| KR101063843B1 (en) | Horizontal Separation System of Space Launch Vehicle Separator | |
| CN111674575B (en) | Cabin section connecting structure and aircraft | |
| CN112082437B (en) | Aircraft clamping block type interstage separation structure | |
| WO2021207955A1 (en) | Point-type separation satellite-rocket butt joint structure | |
| CN114018099A (en) | Device is shed to shrapnel | |
| CN113587741B (en) | Small-size tactics guided missile boosting separator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |