CN112012853B - Solid rocket engine of back skirt connection form thrust transmission device for ignition test - Google Patents
Solid rocket engine of back skirt connection form thrust transmission device for ignition test Download PDFInfo
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- CN112012853B CN112012853B CN202011066998.7A CN202011066998A CN112012853B CN 112012853 B CN112012853 B CN 112012853B CN 202011066998 A CN202011066998 A CN 202011066998A CN 112012853 B CN112012853 B CN 112012853B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
Abstract
The invention provides a thrust transfer device for a solid rocket engine ignition test in a rear skirt connection mode, which comprises a front end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, a connecting rod and a hoop, wherein the front end connecting plate is fixedly connected with the base; the rear skirt connecting plate is in a vertically split mode, and horizontal installation of the engine can be quickly realized without a squirrel cage and a turnover tool; the arc-shaped seat is designed to be height-adjustable integrated with the device, and the engine is directly supported by adjusting the height, so that the stress concentration at the connecting position of the rear skirt caused by the dead weight of the engine is avoided; the detachable thrust connecting rod and the embracing ring are convenient for the test, the accurate installation of the engine is ensured, the occurrence of interference is avoided, and the detachable thrust connecting rod and the embracing ring can be connected with different movable and fixed frames to meet the test requirements of engines with different specifications. The device has the advantages of simple and convenient use, low cost, high efficiency, good safety and the like.
Description
Technical Field
The invention relates to the technical field of solid rocket engine ignition tests, in particular to a thrust transfer device for a solid rocket engine ignition test in a rear skirt connection mode.
Background
The ground ignition test of the solid rocket engine is a key test directly influencing model development and product performance. The traditional solid rocket engine ground ignition test mostly adopts a test mode that a front skirt of the solid rocket engine is connected with a transition frame and then connected with a sensor, and the engine is supported on an arc seat. For some specially designed solid rocket engines, only the rear skirt connection is provided, and the squirrel cage thrust frame is generally adopted in the prior art for ground tests, as shown in fig. 1 to 3. The cage type test device adopted at present mainly comprises a cage type thrust frame and a pair of arc-shaped seats connected with a same moving and fixed frame platform. The squirrel-cage thrust frame consists of a front end connecting plate, a rear end connecting plate, a hoop and a connecting rod; the front end connecting plate and the rear end connecting plate of the squirrel-cage thrust frame are of integral structures respectively, the front end connecting plate and the rear end connecting plate are connected through a plurality of parallel connecting rods in a welding mode, and two embracing rings are welded in the middle of each connecting rod. The integral annular rear end connecting plate of the squirrel-cage thrust frame is connected with a rear skirt flange of the engine; a pair of arc seats connected with the movable fixed frame platform are responsible for supporting two hoops welded in the middle of the connecting rod, and the whole device falls on the traditional movable fixed frame platform and is matched with a force measuring assembly and a force bearing pier for use.
The squirrel-cage thrust frame is of a cylindrical integrated structure and is connected with the rear skirt of the solid rocket engine, and the engine is wrapped by the squirrel-cage thrust frame, so that the squirrel-cage thrust frame cannot be directly and horizontally installed, the engine is required to be inserted into the squirrel-cage thrust frame in an inverted mode, and after the installation is finished, the engine and the squirrel-cage thrust frame are turned into a horizontal state together and fall on a pair of arc seats, and the pre-test state can be achieved. Thus, in addition to the troublesome installation process, a special turnover device needs to be designed, and the design and processing cost is increased. In addition, the assembly diagram shows that only the rear skirt flange between the solid rocket engine and the test device is in a matching relationship, and the whole engine cylinder section at the front end is in a suspended state; the pair of arc-shaped seats is only supported at the position of the embracing ring welded on the squirrel cage, and a gap is inevitably formed between the pair of arc-shaped seats and the engine cylinder section shell, so that the engine is similar to a cantilever beam in the squirrel cage, the stress concentration formed by bending moment caused by the dead weight of the engine borne by the connecting position is more serious, the axis of the engine deviates, and the safety and the accuracy of the test are reduced.
In addition, due to the requirement of testing, a plurality of sensors are required to be attached to the surface of the shell of the cylinder section of the solid rocket engine, the wiring of the sensors is difficult due to the existence of the squirrel cage, cables for connecting the sensors on the engine by operating workers are influenced, and the testing efficiency is reduced.
Disclosure of Invention
In consideration of the fact that the rear skirt connection horizontal test mode is complex, low in efficiency and high in implementation difficulty in the ground ignition test of the existing solid rocket engine, the invention provides the thrust transmission device for the ignition test of the solid rocket engine in the rear skirt connection mode, wherein the connection part of the thrust transmission device and the rear skirt of the engine is in a vertically split mode, and horizontal installation of the engine can be quickly realized without a squirrel cage and a turnover tool; the arc-shaped seat is designed to be adjustable and integrated with the device, and the engine is directly supported by adjusting the height, so that the stress concentration at the connecting position of the rear skirt caused by the dead weight of the engine is avoided; the detachable thrust rod piece and the embracing ring also facilitate the test, the accurate installation of the engine is ensured, the occurrence of interference condition is avoided, and the detachable thrust rod piece and the embracing ring can be connected with different movable and fixed frames to meet the test requirements of engines with different specifications. The device has the advantages of simple and convenient use, low cost, high efficiency, good safety and the like.
The technical scheme of the invention is as follows:
the thrust transfer device for the ignition test of the solid rocket engine in the rear skirt connection mode comprises a front end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, a connecting rod and a hoop;
the lower surface of the base is connected with a test movable and fixed frame platform;
the front end connecting plate is fixed at one end of the base in a right-angle welding manner, a mounting hole connected with the force measuring assembly is formed in the center of the front end connecting plate, and the front end connecting plate is connected with the force measuring assembly required by the test; the front end connecting plate is also provided with a plurality of bolt through holes which are uniformly distributed in the circumferential direction and used for connecting the connecting rod;
the rear skirt connecting plate is used for connecting a rear skirt flange of the solid rocket engine; the rear skirt connecting plate is of an upper-lower split structure and is divided into a rear upper connecting plate and a rear lower connecting plate, the right angle of the rear lower connecting plate is welded and fixed at the other end of the base, and the base, the front end connecting plate and the rear lower connecting plate are welded and fixed into an integral structure; and the right-angle welding positions of the base and the front end connecting plate and the rear lower connecting plate are provided with angle ribs;
the center of a rear skirt connecting plate consisting of a rear upper connecting plate and a rear lower connecting plate is provided with a central through hole with the diameter larger than the diameter of a cylinder body at the rear skirt part of the fixed rocket engine to be tested, the edge of the central through hole is provided with a mounting hole connected with a rear skirt flange of the fixed rocket engine, and the outer side of the mounting hole connected with the rear skirt flange of the fixed rocket engine is also provided with a plurality of bolt through holes for connecting rods, and the bolt through holes correspond to the bolt through holes of the connecting rods on the front end connecting plate;
the arc-shaped seat is arranged on the base in a height-adjustable mode and is used for directly supporting the solid rocket engine;
a detachable thrust connecting rod is arranged between the front end connecting plate and the rear skirt connecting plate, and the detachable thrust connecting rod is assembled after the engine is installed in place and the wiring is finished; after the thrust connecting rod is installed in place, the outer ring of the thrust connecting rod is provided with the embracing ring which embraces the thrust connecting rod tightly, so that the deformation of the thrust connecting rod is reduced.
Furthermore, the position and the form of the holes of the base and the front end connecting plate are changed, so that the movable and fixed frame platform and the force measuring assembly in different forms can be connected, and the test requirements of solid rocket engines in different specifications are met.
Furthermore, a plurality of threaded joints are welded on the upper surface of the base, and threaded joints opposite to the threaded joints of the base are welded at the bottom of the arc-shaped base; through muffjoint between arc seat and the base, the sleeve embeds two sections screw threads that are each other for the reversal, connects the screwed joint of arc seat bottom and the screwed joint of base upper surface down respectively, can realize the adjustment of arc seat height through rotatory sleeve.
Furthermore, screw holes are formed in the front end and the rear end of the thrust connecting rod, the two ends of the thrust connecting rod are flush with the inner sides of the front end connecting plate and the rear skirt connecting plate, and are connected with bolt through holes uniformly distributed in the front end connecting plate and the rear skirt connecting plate through bolts.
Furthermore, when the thrust transmission device is installed, the connecting rod, the hoop and the rear upper connecting plate are firstly in a disassembly state, the height of the arc-shaped seat is reduced, the solid rocket engine is horizontally hoisted, the rear skirt of the solid rocket engine is in threaded connection with the rear lower connecting plate, then the height of the arc-shaped seat is adjusted to support the solid rocket engine, the engine sling is loosened, the solid rocket engine is tightly embraced by the arc-shaped seat and the rear upper connecting plate, the thrust connecting rod is installed in place after the sensor is connected in place on the surface of the solid rocket engine, and the hoop is additionally installed on the outer ring of the thrust connecting rod after the thrust connecting rod is installed.
Advantageous effects
The thrust transmission device provided by the invention can directly realize the horizontal installation of the solid rocket engine by utilizing the detachable connecting rod, the hoop and the rear upper connecting plate, and compared with the currently adopted test scheme, the thrust transmission device avoids the overturning process of the engine and the test device, and simultaneously does not need to design an overturning device, thereby reducing the test cost; in addition, the built-in height-adjustable arc seat can directly support the engine cylinder section, and compared with the traditional arc seat for supporting a squirrel cage, the built-in height-adjustable arc seat also avoids stress concentration at the joint of the rear skirt and improves the safety of the test; the detachable connecting rod is convenient for the wiring work of operators after the engine is installed in place, the test efficiency is improved, and the subsequent popularization and use can be considered.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: conventional squirrel cage thrust transfer devices;
wherein: 1. a squirrel cage thrust frame; 2. an arc-shaped seat; 3. a solid rocket engine with only rear skirt connecting holes;
FIG. 2: a squirrel cage thrust frame schematic diagram;
wherein: 4. a front end connecting plate; 5. encircling; 6. a connecting rod; 7. a rear end connecting plate;
FIG. 3: a squirrel cage test device;
wherein: 8. a force measuring assembly; 9. a movable and fixed frame platform; 10. a squirrel cage thrust transfer device;
FIG. 4: an inverted engine mount schematic;
FIG. 5: the thrust transfer device of the present invention;
wherein: 11. a connecting rod; 12. an arc-shaped seat; 13. encircling; 14. a connecting plate is arranged on the back; 15. a sleeve;
FIG. 6: a base structure diagram; (the illustration of the through hole connecting to the connecting rod is omitted in the figure)
Wherein: 16. a front end connecting plate; 17. a rear lower connecting plate; 18. a rib plate; 19. a threaded joint; 20. a base plate;
FIG. 7: a rear upper connecting plate schematic view;
FIG. 8: a schematic view of a forward and reverse threaded sleeve;
FIG. 9: an arc seat schematic diagram;
wherein: 21. an upper arc seat; 22. a lower arc seat; 23. a reverse threaded joint;
FIG. 10: a schematic diagram of a hoop;
FIG. 11: the installation of the invention is illustrated schematically; (a) the device is in a ready state before the engine is installed, (b) the engine is horizontally installed on a test frame, (c) an upper arc seat and a rear upper connecting plate are installed; (d) mounting a connecting rod and a hoop;
FIG. 12: the invention relates to a test device of a thrust transmission device;
wherein: 24. the invention provides a thrust transmission device.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
The novel horizontal test thrust transfer device in the form of rear skirt connection is suitable for a solid rocket engine ground test in which only the rear skirt is provided with a connecting hole and the front skirt cannot be connected with a tool, and can be directly and horizontally installed without turning over the engine; the engine is directly supported by the arc-shaped seat, the height is adjustable, and stress concentration at the rear skirt of the engine is avoided; the force transmission connecting rod is detachable and is convenient for installation of an engine and debugging of a testing device.
As shown in fig. 5 to 10, the thrust transfer device of the present invention includes a front end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, a connecting rod, and a hoop.
Wherein the base is used as a main bearing part, and the lower surface of the base is connected with a test movable and fixed frame platform. The right angle welding of the front end connecting plate is fixed at one end of the base, a mounting hole connected with the force measuring assembly is formed in the center of the front end connecting plate, the front end connecting plate is connected with the force measuring assembly required by the test so as to guarantee accurate measurement of thrust, and a plurality of bolt through holes for connecting rods are uniformly distributed around the front end connecting plate along the circumferential direction. The movable and fixed frame platform and the force measuring assembly in different forms can be connected by changing the positions and the forms of the connecting holes of the base and the front end connecting plate so as to meet the test requirements of solid rocket engines with different specifications.
The upper surface of the base is welded with a plurality of screwed joints which are used for being connected with the arc-shaped seat through the threaded sleeve.
The rear skirt connecting plate is used for connecting a rear skirt flange of the solid rocket engine. The back skirt is even the board is split type structure from top to bottom, is divided into even board and back lower even board on the back, and even board right angle welding is fixed at the base other end under the back, and base, front end even board and back lower even board welded fastening are overall structure like this, and even distribution has the angle muscle in base and front end even board and back lower even board right angle welding department, and the stress concentration of reducible welding position department.
The whole center of the rear skirt connecting plate consisting of the rear upper connecting plate and the rear lower connecting plate is provided with a central through hole with the diameter larger than the diameter of a cylinder body at the rear skirt part of the fixed rocket engine to be tested, the edge of the central through hole is provided with a mounting hole connected with a rear skirt flange of the fixed rocket engine, and the outer side of the mounting hole connected with the rear skirt flange of the fixed rocket engine is also provided with a plurality of bolt through holes for connecting rods, and the bolt through holes correspond to the bolt through holes of the connecting rods on the front end connecting plate.
The arc seat is divided into an upper part and a lower part, the upper arc seat is fixedly connected with the lower arc seat through bolts, and the arc seat is installed on the base and can directly support the solid rocket engine. In order to reduce installation error's influence, the arc seat design is height-adjustable festival formula, and the implementation is: the bottom of the lower arc seat is welded with a threaded joint in the direction opposite to that of the threaded joint of the base; through muffjoint between arc seat and the base, the built-in two sections of sleeve are reverse screw thread each other, connect the screwed joint of arc seat bottom and the screwed joint of base upper surface down respectively, can realize the fine setting of arc seat height through rotatory sleeve to guarantee that the engine back skirt is connected the installation and is accomplished the back arc seat and can closely support the engine, stress concentration influence that the moment of flexure that leads to in order to avoid the engine dead weight brought the back skirt junction.
In the thrust transmission aspect, different from the traditional welding form, the thrust connecting rod is designed to be detachable, namely screw holes are formed in the front end and the rear end of the connecting rod, the two ends of the connecting rod are flush with the inner sides of the front end connecting plate and the rear skirt connecting plate and are connected with bolt through holes uniformly distributed on the front end connecting plate and the rear skirt connecting plate through bolts, and the detachable thrust connecting rod is assembled after the engine is installed in place and wiring is completed, so that the problem of interference possibly occurring in the installation process is avoided, and the arc-shaped seat can be guaranteed to directly support the engine.
After the connecting rod is installed in place, the outer ring of the connecting rod is provided with the embracing ring to tightly embrace the connecting rod so as to reduce the deformation of the connecting rod, and particularly for an engine with a large length-diameter ratio, the problem of deformation of the connecting rod caused by thrust can be solved by additionally arranging a plurality of pairs of embracing rings.
The operation and use process of the invention is as follows:
when the test is ready, the front end connecting plate, the base, the rear lower connecting plate, the rib plate and the threaded connector are welded into a whole, the connecting rod, the hoop and the rear upper connecting plate are all in a detachable state, a forward and reverse threaded sleeve and a lower arc seat are installed on the base before the engine is installed, the height of the lower arc seat is reduced, the engine is hoisted horizontally, the rear skirt of the engine is connected with the rear lower connecting plate through threads, the height of the arc seat is adjusted to support the engine, the engine sling is loosened, the upper arc seat and the rear upper connecting plate are installed, all the connecting rods are installed in place one by one after the sensors are connected in place on the surface of the engine, and a pair of hooping rings connected through bolts are additionally installed in the middle of the installed connecting rods.
The whole device is placed on various movable and fixed frame platforms commonly used in ground tests, and is matched with a force measuring assembly and a force bearing pier for use, so that requirements of formal ignition tests on the device can be met, and various parameters such as test thrust and the like can be measured. By changing the connecting hole form of the front end and the bottom, the force measuring assembly and the movable and fixed frame assembly of different types can be connected so as to meet the test requirements of engines of different specifications.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (4)
1. A solid rocket engine of back skirt connection form thrust transmission device for ignition test which characterized in that: comprises a front end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, a connecting rod and a hoop;
the lower surface of the base is connected with a test movable and fixed frame platform;
the front end connecting plate is fixed at one end of the base in a right-angle welding manner, a mounting hole connected with the force measuring assembly is formed in the center of the front end connecting plate, and the front end connecting plate is connected with the force measuring assembly required by the test; the front end connecting plate is also provided with a plurality of bolt through holes which are uniformly distributed in the circumferential direction and used for connecting the connecting rod;
the rear skirt connecting plate is used for connecting a rear skirt flange of the solid rocket engine; the rear skirt connecting plate is of an upper-lower split structure and is divided into a rear upper connecting plate and a rear lower connecting plate, the right angle of the rear lower connecting plate is welded and fixed at the other end of the base, and the base, the front end connecting plate and the rear lower connecting plate are welded and fixed into an integral structure; and the right-angle welding positions of the base and the front end connecting plate and the rear lower connecting plate are provided with angle ribs;
the center of a rear skirt connecting plate consisting of a rear upper connecting plate and a rear lower connecting plate is provided with a central through hole with the diameter larger than the diameter of a cylinder body at the rear skirt part of the fixed rocket engine to be tested, the edge of the central through hole is provided with a mounting hole connected with a rear skirt flange of the fixed rocket engine, and the outer side of the mounting hole connected with the rear skirt flange of the fixed rocket engine is also provided with a plurality of bolt through holes for connecting rods, and the bolt through holes correspond to the bolt through holes of the connecting rods on the front end connecting plate;
the arc-shaped seat is arranged on the base in a height-adjustable mode and is used for directly supporting the solid rocket engine;
a detachable thrust connecting rod is arranged between the front end connecting plate and the rear skirt connecting plate, and the detachable thrust connecting rod is assembled after the engine is installed in place and the wiring is finished; after the thrust connecting rod is installed in place, the outer ring of the thrust connecting rod is provided with the embracing ring which embraces the thrust connecting rod tightly, so that the deformation of the thrust connecting rod is reduced.
2. The thrust force transmission device for the ignition test of the solid rocket engine with the rear skirt connection type as claimed in claim 1, wherein: the upper surface of the base is welded with a plurality of threaded joints, and the bottom of the arc-shaped base is welded with threaded joints in the direction opposite to that of the threaded joints of the base; the arc seat is connected with the base through the sleeve, two sections of threads which are opposite to each other are arranged in the sleeve and are respectively connected with the threaded joint at the bottom of the lower arc seat and the threaded joint on the upper surface of the base, and the height of the arc seat is adjusted by rotating the sleeve.
3. The thrust force transmission device for the ignition test of the solid rocket engine with the rear skirt connection type as claimed in claim 1, wherein: screw holes are formed in the front end and the rear end of the thrust connecting rod, the two ends of the thrust connecting rod are flush with the inner sides of the front end connecting plate and the rear skirt connecting plate, and are connected with bolt through holes uniformly distributed in the front end connecting plate and the rear skirt connecting plate through bolts.
4. The thrust force transmission device for the ignition test of the solid rocket engine with the rear skirt connection type as claimed in claim 1, wherein: when the thrust transmission device is installed, the connecting rod, the hoop and the rear upper connecting plate are firstly in a disassembly state, the height of the arc-shaped seat is reduced, the solid rocket engine is horizontally hoisted, the rear skirt of the solid rocket engine is in threaded connection with the rear lower connecting plate, then the height of the arc-shaped seat is adjusted to support the solid rocket engine, the engine sling is loosened, the arc-shaped seat and the rear upper connecting plate are adopted to hold the solid rocket engine tightly, the thrust connecting rod is installed in place after the sensor is connected in place on the surface of the solid rocket engine, and the hoop is installed on the outer ring of the thrust connecting rod after the thrust connecting rod is installed.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011066998.7A CN112012853B (en) | 2020-10-04 | 2020-10-04 | Solid rocket engine of back skirt connection form thrust transmission device for ignition test |
| PCT/CN2021/120509 WO2022068703A1 (en) | 2020-10-04 | 2021-09-25 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
| GB2216941.1A GB2612455A (en) | 2020-10-04 | 2021-09-25 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011066998.7A CN112012853B (en) | 2020-10-04 | 2020-10-04 | Solid rocket engine of back skirt connection form thrust transmission device for ignition test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112012853A CN112012853A (en) | 2020-12-01 |
| CN112012853B true CN112012853B (en) | 2021-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011066998.7A Active CN112012853B (en) | 2020-10-04 | 2020-10-04 | Solid rocket engine of back skirt connection form thrust transmission device for ignition test |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN112012853B (en) |
| GB (1) | GB2612455A (en) |
| WO (1) | WO2022068703A1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112012853B (en) * | 2020-10-04 | 2021-07-06 | 西安航天动力测控技术研究所 | Solid rocket engine of back skirt connection form thrust transmission device for ignition test |
| CN113638822B (en) * | 2021-06-30 | 2023-12-29 | 西安航天动力测控技术研究所 | Mechanical arm type interstage separation test device for rear skirt connection of solid rocket engine |
| CN114184386B (en) * | 2021-11-29 | 2023-07-21 | 西安航天动力测控技术研究所 | Spherical solid rocket engine testing device |
| CN114856867B (en) * | 2022-05-27 | 2024-02-06 | 哈尔滨工程大学 | Active vibration damper of solid rocket engine |
| CN115184028B (en) * | 2022-08-25 | 2023-09-01 | 芜湖中科飞机制造有限公司 | Fixing device for aeroengine detection |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6032545A (en) * | 1998-04-17 | 2000-03-07 | California Polytechnic State University Foundation | Nozzle flow thrust vector measurement |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103115716A (en) * | 2013-01-25 | 2013-05-22 | 南京理工大学 | Thrust block device of six-component test stand |
| CN104019994A (en) * | 2014-04-24 | 2014-09-03 | 北京理工大学 | Overload testing device and method of solid rocket engine |
| US9140215B2 (en) * | 2012-03-14 | 2015-09-22 | Aerojet Rocketoyne Of De, Inc. | Rocket engine pressure sense line |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108590889B (en) * | 2018-05-09 | 2020-04-14 | 北京理工大学 | Throat bolt type variable thrust solid rocket engine ground testing device |
| CN112012853B (en) * | 2020-10-04 | 2021-07-06 | 西安航天动力测控技术研究所 | Solid rocket engine of back skirt connection form thrust transmission device for ignition test |
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2020
- 2020-10-04 CN CN202011066998.7A patent/CN112012853B/en active Active
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2021
- 2021-09-25 GB GB2216941.1A patent/GB2612455A/en active Pending
- 2021-09-25 WO PCT/CN2021/120509 patent/WO2022068703A1/en active Application Filing
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6032545A (en) * | 1998-04-17 | 2000-03-07 | California Polytechnic State University Foundation | Nozzle flow thrust vector measurement |
| US9140215B2 (en) * | 2012-03-14 | 2015-09-22 | Aerojet Rocketoyne Of De, Inc. | Rocket engine pressure sense line |
| CN102818671A (en) * | 2012-08-16 | 2012-12-12 | 北京航空航天大学 | High-precision liquid or gas rocket engine thrust rack |
| CN103115716A (en) * | 2013-01-25 | 2013-05-22 | 南京理工大学 | Thrust block device of six-component test stand |
| CN104019994A (en) * | 2014-04-24 | 2014-09-03 | 北京理工大学 | Overload testing device and method of solid rocket engine |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
| CN107100761A (en) * | 2017-06-29 | 2017-08-29 | 湖北三江航天江河化工科技有限公司 | A kind of test engine |
Also Published As
| Publication number | Publication date |
|---|---|
| GB202216941D0 (en) | 2022-12-28 |
| WO2022068703A1 (en) | 2022-04-07 |
| CN112012853A (en) | 2020-12-01 |
| GB2612455A (en) | 2023-05-03 |
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