CN214582822U - Rod system connection carrier based on modular solid power system - Google Patents
Rod system connection carrier based on modular solid power system Download PDFInfo
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- CN214582822U CN214582822U CN202023331805.4U CN202023331805U CN214582822U CN 214582822 U CN214582822 U CN 214582822U CN 202023331805 U CN202023331805 U CN 202023331805U CN 214582822 U CN214582822 U CN 214582822U
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Abstract
The application discloses a rod system connection carrier based on a modularized solid power system, which is characterized by comprising a multi-stage power system, a fairing and a control cabin; the multi-stage power systems are fixedly connected, the control cabin is fixedly connected with the fairing, and the control cabin is fixedly connected with a designated power system in the multi-stage power systems. The method breaks through the limitation of the number of the binding boosting around the traditional core level, and realizes the optimal selection of the carrying capacity and the rocket scale. The first stage, the second stage and the third stage all adopt solid rocket engines, the power system is simple and mature, and the flight reliability of the carrier is greatly improved.
Description
Technical Field
The utility model relates to a rocket field especially relates to a delivery ware is connected to rod system based on modularization solid power system.
Background
In order to meet the requirements for launching different types of satellites, orbital vehicles and other spacecrafts, the development of vehicles with different carrying capacities is required. In order to shorten the development period, reduce the development cost and form a series type spectrum of the carrier rocket, the existing series rocket is usually used as a base, and boosters with different combinations are bound around a rocket core stage so as to achieve the effects of improving the carrying capacity and meeting the launching requirements of more effective loads. Liquid propellant is adopted at the core level of the domestic and foreign mainstream parallel carrier rockets, and liquid propellant or solid propellant is adopted for boosting. After the booster rocket finishes working, the booster and the rocket core stage are usually separated. However, in the existing carrier, the core level adopts liquid propellant, the liquid engine system is complex in composition, the technical difficulty is high, the reliability is low, the filling and ground testing are complex, the rocket launching response time is long, and the requirement on a firing ground guarantee facility is high. Meanwhile, the existing boosting parallel scheme can only select 2 or 4 boosters, and the rocket scale and the carrying capacity have faults, so that the carrying capacity is wasted to a certain extent, and the optimal design cannot be realized.
Therefore, how to provide a novel carrier that can ensure high reliability of products while inheriting the technical advancement is a problem that needs to be solved urgently by those skilled in the art.
SUMMERY OF THE UTILITY MODEL
The application provides a rod system connecting carrier based on a modularized solid power system, which breaks through the limitation of the number of binding boosts around the traditional core level and realizes the optimal selection of carrying capacity and rocket scale.
In order to solve the technical problem, the application provides the following technical scheme:
a rod system connection carrier based on a modular solid power system comprises a multi-stage power system, a fairing and a control cabin; the multi-stage power systems are fixedly connected, the control cabin is fixedly connected with the fairing, and the control cabin is fixedly connected with a designated power system in the multi-stage power systems.
The multi-stage power system comprises a primary power system, a secondary power system and a tertiary power system; the primary power system is fixedly connected with the secondary power system, and the secondary power system is fixedly connected with the tertiary power system; the control cabin is respectively connected with the three-stage power system and the fairing.
The primary power system comprises a plurality of primary solid rocket engines, and the plurality of primary solid rocket engines are connected through the binding mechanism.
The system comprises a primary power system, a secondary power system, a plurality of primary tail sections, a plurality of primary solid rocket engines and a secondary section, wherein the primary power system comprises a plurality of primary tail sections, a plurality of primary solid rocket engines and a secondary section; each first-stage solid rocket engine is connected with a corresponding first-stage tail section; the rear end surfaces of the plurality of primary solid rocket engines are respectively connected with the corresponding primary tail sections through bolts; the front end faces of the first-stage solid rocket engines are respectively connected with the rear end faces of the second-stage intermediate sections through bolts.
The system comprises a secondary power system, a secondary tail section, a secondary solid rocket engine and a secondary-tertiary stage section; the rear end face of the secondary solid rocket engine is connected with the secondary tail section through a bolt; the front end face of the second-stage solid rocket engine is connected with the rear end face of the second-stage section and the third-stage section through bolts.
The three-stage power system comprises a three-stage tail section and a three-stage solid rocket engine; the rear end face of the three-stage solid rocket engine is connected with the three-stage tail section through a bolt; the front end face of the three-stage solid rocket engine is connected with the control cabin through a bolt.
The two-stage intermediate lever system realizes connection and separation of the first-stage power system and the second-stage power system, and two end faces of the two-stage intermediate lever system are respectively connected with the two-stage intermediate section and the two-stage tail section.
The method as above, wherein the surface of a secondary spar system is wrapped around the skin structure.
The first-stage solid rocket engine and the second-stage solid rocket engine are the same type of engine.
The number of the plurality of the first-stage solid rocket engines is two or four.
The application has the following beneficial effects:
(1) the rod system connecting carrier based on the modularized solid power system breaks through the limitation of the number of binding boosts around the traditional core level, and realizes the optimal selection of carrying capacity and rocket scale. The first stage, the second stage and the third stage all adopt solid rocket engines, the power system is simple and mature, and the flight reliability of the carrier is greatly improved.
(2) The application provides a cargo carrier is connected to rod system based on modularization solid driving system, including a plurality of one-level solid rocket engines of the same model, can reduce the complexity that each system design and production were made, be convenient for realize structure and engine product furthest's batch production, furthest shortens research and development cycle and cost. In a primary power system, four or two solid rocket engines work simultaneously and are mutually assisted, so that the control difficulty caused by asynchronous thrust is reduced.
(3) The utility model provides a based on carrier is connected to modularization solid power system's rod system, the outer skin that sets up of rod system between the second grade carries out the rectification to at the thermal separation process of second grade and open the flame vent, guarantee separation and pneumatic environment's stability when guaranteeing structure bearing strength.
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 is obvious that the drawings in the following description are only some embodiments described in the present invention, and other drawings can be obtained by those skilled in the art according to the drawings.
FIG. 1 is a schematic structural diagram of a modular solid state power system based stick-connected vehicle provided by an embodiment of the present application;
FIG. 2 is a schematic structural diagram of yet another modular solid state power system based stick-connected vehicle provided by an embodiment of the present application;
reference numerals:
1-first stage tail section; 2-a first stage solid rocket engine; 3-a second stage solid rocket engine; 4-a secondary stage section; 5-a secondary interstage linkage; 6-second-order tail section; 7-a secondary solid rocket engine; 8-two three-level time section; 9-three-stage tail section; 10-three stage solid rocket engines; 11-a control cabin; 12-a fairing; 13-a third stage solid rocket engine; 14-fourth stage solid rocket engine.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below by referring to the drawings are exemplary only for explaining the present invention, and should not be construed as limiting the present invention.
The application provides a rod system connecting carrier based on a modularized solid power system, which breaks through the limitation of the number of binding boosts around the traditional core level and realizes the optimal selection of carrying capacity and rocket scale. By adopting the design ideas of modularization and generalization, the research and development period and the cost are shortened to the maximum extent, and the high reliability of the product is ensured while the technical advancement is inherited.
The modular solid state power system-based bar linkage connection vehicle provided by the embodiment specifically includes a multistage power system, a fairing 12 and a control cabin 11. The multi-stage power systems are fixedly connected, the control cabin 11 is fixedly connected with the fairing 14, and the control cabin 11 is fixedly connected with a designated power system in the multi-stage power systems.
Preferably, the diameter of the fairing is 4200mm, which can meet the emission requirement of the mainstream satellite in the market.
Preferably, the control cabin 11 is capable of performing rocket control, measurement, telemetry, etc., and has a length of 1960 mm.
The multi-stage power system comprises a primary power system, a secondary power system and a tertiary power system. Wherein, the first-stage power system is fixedly connected with the second-stage power system through bolts, and the second-stage power system is fixedly connected with the third-stage power system through bolts. The control cabin 11 is connected with a three-stage power system and a fairing 12 respectively.
Specifically, the primary power system comprises a plurality of primary solid rocket engines, and the plurality of primary solid rocket engines are connected through a binding mechanism.
Example one
Referring to fig. 1, the primary power system includes a plurality of primary tail sections 1, a first primary solid rocket engine 2, a second primary solid rocket engine 3, and a secondary section 4; the secondary power system comprises a secondary tail section 6, a secondary solid rocket engine 7 and a secondary and tertiary stage section 8; the three-stage power system comprises a three-stage tail section 9 and a three-stage solid rocket engine 10.
Preferably, the first stage solid rocket engine 2 and the second stage solid rocket engine 3 are transversely and parallelly bound through a binding connection structure, so that the transmission of axial force is realized. The binding connection structure comprises a front binding structure and a rear connecting rod structure, wherein the front binding structure is a main bearing structure and is positioned at the front parts of the first stage solid rocket engine and the second stage solid rocket engine and used for transmitting axial and transverse loads; the rear connecting rod structure is an auxiliary bearing structure, is positioned at the rear parts of the first stage solid rocket engine and the second stage solid rocket engine and is used for transferring transverse load and limiting the transverse relative position between the engines.
Specifically, each one-stage solid rocket engine is connected with a corresponding one-stage tail section, and in the one-stage power system, the number of the one-stage tail sections 4 is the same as that of the one-stage solid rocket engines. The rear end face of the first primary solid rocket engine 2 is connected with the corresponding first-stage tail section 1 through a bolt; the front end face of the first primary solid rocket engine 2 is connected with the rear end face of the second primary section 4 through bolts. The rear end face of the second stage solid rocket engine 3 is connected with the corresponding first stage tail section 1 through a bolt; the front end face of the second-stage solid rocket engine 3 is connected with the rear end face of the second-stage section 4 through bolts.
Specifically, in the secondary power system, the rear end face of the secondary solid rocket engine 7 is connected with the secondary tail section 6 through bolts; the front end face of the second-stage solid rocket engine 7 is connected with the rear end face of the second-stage section 8 through bolts.
The two end faces of the primary and secondary interstage rod systems 5 are respectively connected with the primary and secondary sections 4 and the secondary tail section 6, and connection and separation of the primary power system and the secondary power system are achieved.
In particular, a secondary stage 5 is used in a rocket with thermal separation between stages, and the secondary stage 5 is a space ring framework formed by connecting a plurality of inclined rods. The rod system is made of high-quality alloy steel in multiple choices, the rod is a seamless steel pipe, a plurality of inclined rods are connected in a vertically staggered mode, and the intersection points are welded together through joints to form a space annular framework. The upper joint and the lower joint are respectively connected with a secondary tail section 6 and a secondary section 4 through a ring frame and a bolt. The surface of the rod system is wrapped with a skin structure to play a role in rectification and give consideration to the function of flame exhaust in the two-stage separation process.
Preferably, the surface of the secondary lever system 5 is wrapped by a skin structure to play a role in rectification and take the function of flame exhaust into consideration in the secondary separation process.
Specifically, in the three-stage power system, the rear end face of a three-stage solid rocket engine 10 is connected with a three-stage tail section 9 through a bolt; the front end face of the three-stage solid rocket engine 10 is connected with the control cabin 11 through bolts.
Wherein, the third-level tail section 9 is also connected with the second-level and third-level section 8 for realizing the connection of the second-level and third-level power systems.
In the structure of the first embodiment, the two first-stage solid rocket engines are connected in parallel through the connecting structure between the second-stage section and the first-stage tail section, and the two first-stage solid rocket engines are not separated in the flying process.
Example two
Please refer to fig. 2, which is a schematic structural diagram of another carrier according to an embodiment of the present disclosure. The rocket specifically comprises a plurality of first-stage tail sections 1, a first primary solid rocket engine 2, a second primary solid rocket engine 3 and a second-stage section 4; the secondary power system comprises a secondary tail section 6, a secondary solid rocket engine 7 and a secondary and tertiary stage section 8; the three-stage power system comprises a three-stage tail section 9 and a three-stage solid rocket engine 10; a third stage solid rocket motor 13; and a fourth stage solid rocket engine.
Preferably, the first-stage solid rocket engine, the second-stage solid rocket engine and the fourth-stage solid rocket engine are bound in an encircling mode to form parallel connection, and axial force transmission is achieved.
Specifically, each first-stage solid rocket engine is respectively connected with a first-stage tail section and a second-stage section, and in the first-stage power system, the number of the first-stage tail sections 4 is the same as that of the first-stage solid rocket engines.
The rear end face of the first primary solid rocket engine 2 is connected with the corresponding first-stage tail section 1 through a bolt; the front end face of the first primary solid rocket engine 2 is connected with the rear end face of the second primary section 4 through bolts. The rear end face of the second stage solid rocket engine 3 is connected with the corresponding first stage tail section 1 through a bolt; the front end face of the second-stage solid rocket engine 3 is connected with the rear end face of the second-stage section 4 through bolts. The rear end face of the third stage solid rocket engine 13 is connected with the corresponding first stage tail section 1 through a bolt; the front end face of the third stage solid rocket motor 13 is connected with the rear end face of the second stage section 4 through bolts. The rear end face of the fourth stage solid rocket engine 14 is connected with the corresponding first stage tail section 1 through a bolt; the front end face of the fourth stage solid rocket engine 14 is connected with the rear end face of the second stage section 4 through bolts.
Specifically, in the secondary power system, the rear end face of the secondary solid rocket engine 7 is connected with the secondary tail section 6 through bolts; the front end face of the second-stage solid rocket engine 7 is connected with the rear end face of the second-stage section 8 through bolts.
The two end faces of the primary and secondary interstage rod systems 5 are respectively connected with the primary and secondary sections 4 and the secondary tail section 6, and connection and separation of the primary power system and the secondary power system are achieved.
Specifically, in the three-stage power system, the rear end face of a three-stage solid rocket engine 10 is connected with a three-stage tail section 9 through a bolt; the front end face of the three-stage solid rocket engine 10 is connected with the control cabin 11 through bolts.
Wherein, the third-level tail section 9 is also connected with the second-level and third-level section 8 for realizing the connection of the second-level and third-level power systems.
In the structure of the second embodiment, the four first-stage solid rocket engines are connected in parallel through the connecting structure between the second-stage section and the first-stage tail section, and the four first-stage solid rocket engines are not separated in the flying process.
Among other things, the present application is based on the design of a solid rocket engine having a diameter of 2650mm to complete a launch vehicle. The total length of the carrier is 39.5m, and the first-stage solid rocket engine and the second-stage solid rocket engine are both the same type engines. The diameters, the lengths and the loading quantities of the plurality of first-stage solid rocket engines are the same, and the diameters, the lengths and the loading quantities of the second-stage solid rocket engines are the same as those of the first-stage solid rocket engines.
Furthermore, the three-stage solid rocket engine also adopts a solid rocket engine with the diameter of 2650mm, and the diameters of the stage section and the tail section are 2650mm, so that the universal design and production of a structural system are facilitated.
Further, in the above structure, a length of the secondary stage is 1000 mm.
Preferably, the length of the first-stage tail section is 1330mm, and transverse loads between the engines are transmitted between the first-stage solid rocket engines through the rear connecting rod structure of the binding mechanism.
Preferably, the separation of the primary and secondary power systems adopts a thermal separation mode, and an opening is formed between the primary and secondary lever systems in the separation process, so that the flame is smoothly exhausted, and the bearing capacity of the structure is ensured. Wherein the length of the rod system is 2300mm, and the length of the secondary tail section is 740 mm.
Preferably, the separation of the second-level and third-level power systems adopts cold separation, and according to the length of the nozzle of the three-level solid rocket launcher and the separation scheme, the length of the third-level tail section is 1330mm, and the length of the second-level and third-level time sections is 1600 mm.
The application has the following beneficial effects:
(1) the rod system connecting carrier based on the modularized solid power system breaks through the limitation of the number of binding boosts around the traditional core level, and realizes the optimal selection of carrying capacity and rocket scale. The first stage, the second stage and the third stage all adopt solid rocket engines, the power system is simple and mature, and the flight reliability of the carrier is greatly improved.
(2) The application provides a cargo carrier is connected to rod system based on modularization solid driving system, including a plurality of one-level solid rocket engines of the same model, can reduce the complexity that each system design and production were made, be convenient for realize structure and engine product furthest's batch production, furthest shortens research and development cycle and cost. In a primary power system, four or two solid rocket engines work simultaneously and are mutually assisted, so that the control difficulty caused by asynchronous thrust is reduced.
(3) The utility model provides a based on carrier is connected to modularization solid power system's rod system, the outer skin that sets up of rod system between the second grade carries out the rectification to at the thermal separation process of second grade and open the flame vent, guarantee separation and pneumatic environment's stability when guaranteeing structure bearing strength.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application. It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (7)
1. A rod system connection carrier based on a modular solid power system is characterized by comprising a multi-stage power system, a fairing and a control cabin;
the multi-stage power systems are fixedly connected, the control cabin is fixedly connected with the fairing and fixedly connected with a designated power system in the multi-stage power systems;
the multistage power system comprises a primary power system, a secondary power system and a tertiary power system; the primary power system is fixedly connected with the secondary power system, and the secondary power system is fixedly connected with the tertiary power system; the control cabin is respectively connected with the three-stage power system and the fairing;
the secondary power system comprises a secondary tail section, a secondary solid rocket engine and a secondary and tertiary stage section;
the rear end face of the secondary solid rocket engine is connected with the secondary tail section through a bolt; the front end face of the second-stage solid rocket engine is connected with the rear end face of the second-stage section and the third-stage section through bolts;
the two end faces of the secondary interstage rod system are respectively connected with the secondary section and the secondary tail section.
2. The modular solid state power system based linkage-link vehicle of claim 1, wherein the primary power system comprises a plurality of primary solid state rocket motors, the plurality of primary solid state rocket motors being connected by a binding mechanism.
3. The modular solid state power system based stick connected launch vehicle of claim 1 wherein the primary power system comprises a plurality of primary tail sections, a plurality of primary solid rocket motors, and a secondary section; each first-stage solid rocket engine is connected with a corresponding first-stage tail section;
the rear end surfaces of the plurality of primary solid rocket engines are respectively connected with the corresponding primary tail sections through bolts; the front end faces of the first-stage solid rocket engines are respectively connected with the rear end faces of the second-stage intermediate sections through bolts.
4. The modular solid state power system based stick connected launch vehicle of claim 1 wherein the three stage power system comprises a three stage tail section and a three stage solid rocket engine;
the rear end face of the three-stage solid rocket engine is connected with the three-stage tail section through a bolt; the front end face of the three-stage solid rocket engine is connected with the control cabin through a bolt.
5. The modular solid state drive system based linkage connection carrier as claimed in claim 4, wherein a surface of an interstage linkage wraps a skin structure.
6. The modular solid state power system based stick connected vehicle of any one of claims 1-5, wherein the primary solid rocket engine and the secondary solid rocket engine are the same type of engine.
7. The modular solid state power system based stick connected launch vehicle of claim 1 wherein the number of the plurality of primary solid state rocket engines is two or four.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023331805.4U CN214582822U (en) | 2020-12-31 | 2020-12-31 | Rod system connection carrier based on modular solid power system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023331805.4U CN214582822U (en) | 2020-12-31 | 2020-12-31 | Rod system connection carrier based on modular solid power system |
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| CN214582822U true CN214582822U (en) | 2021-11-02 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113820095A (en) * | 2021-08-23 | 2021-12-21 | 北京强度环境研究所 | Wind tunnel scale model assembly of bundled rocket |
| CN115060122A (en) * | 2022-05-27 | 2022-09-16 | 火箭派(北京)航天科技有限公司 | Carrier rocket cabin section structure for modularized rapid assembly |
-
2020
- 2020-12-31 CN CN202023331805.4U patent/CN214582822U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113820095A (en) * | 2021-08-23 | 2021-12-21 | 北京强度环境研究所 | Wind tunnel scale model assembly of bundled rocket |
| CN113820095B (en) * | 2021-08-23 | 2023-05-23 | 北京强度环境研究所 | Binding rocket wind tunnel scaling model assembly |
| CN115060122A (en) * | 2022-05-27 | 2022-09-16 | 火箭派(北京)航天科技有限公司 | Carrier rocket cabin section structure for modularized rapid assembly |
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