GB2612455A - Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection - Google Patents
Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection Download PDFInfo
- Publication number
- GB2612455A GB2612455A GB2216941.1A GB202216941A GB2612455A GB 2612455 A GB2612455 A GB 2612455A GB 202216941 A GB202216941 A GB 202216941A GB 2612455 A GB2612455 A GB 2612455A
- Authority
- GB
- United Kingdom
- Prior art keywords
- connecting plate
- solid rocket
- thrust
- rocket engine
- rear skirt
- 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
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Classifications
-
- 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
-
- 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
-
- 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
A thrust transfer apparatus for an ignition test of a solid rocket engine in a form of rear skirt connection, comprising a front end connecting plate (16), a base (20), a rear skirt connecting plate (14, 17), an arc-shaped seat (12), a connecting rod (11), and a hoop (13). The lower surface of the base is connected to a test movable/fixed frame platform; the front end connecting plate is fixed to one end of the base in a right-angle welding manner, and the front end connecting plate is connected to a force measuring assembly required by the test; the rear skirt connecting plate is connected to a rear skirt flange plate 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 (14) and a rear lower connecting plate (17), and the rear lower connecting plate is fixed to the other end of the base in a right-angle welding manner; the 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 having an aperture larger than the diameter of a cylinder at the rear skirt part of the fixed rocket engine to be tested; the arc-shaped seat is mounted on the base in a height-adjustable manner for directly supporting the solid rocket engine; and a detachable thrust connecting rod is mounted between the front end connecting plate and the rear skirt connecting plate.
Description
THRUST TRANSFER APPARATUS FOR IGNITION TEST OF SOLID
ROCKET ENGINE IN FORM OF REAR SKIRT CONNECTION
Technical Field
The present disclosure relates to the technical field of the ignition test of a solid rocket engine, and in particular, to a thrust transfer apparatus for the ignition test of a solid rocket engine in form of a rear skirt connection.
Background Art
The ground ignition test of a solid rocket engine is a key test that directly affects the model study and development and the product performance. The traditional ground ignition test of a solid rocket engine mostly adopts the test form that a front skirt of the solid rocket engine is connected to a transition frame which is then connected to 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 in the existing scheme, the squirrel-cage thrust frame is generally used for ground test, as shown in FIGS. 1 to 3. At present, the used squirrel-cage test device is mainly composed of a squirrel-cage thrust frame and a pair of arc-shaped seats connected to the movable fixing frame platform. The squirrel-cage thrust frame is composed of a front-end connecting plate, a rear-end connecting plate, a holding hoop and connecting rods. The front-end connecting plate and the rear-end connecting plate of the squirrel-cage thrust frame are integral structures respectively, and they are connected in a welding manner by a plurality of connecting rods which are parallel to each other, and the middle of the connecting rods is welded with two holding hoops. The integral annular rear-end connecting plate of the squirrel-cage thrust frame is connected to the rear skirt flange of the engine. A pair of arc-shaped seats connected to the movable fixing frame platform are responsible for supporting the two holding hoops welded at the middle of the connecting rods. The whole device is placed on the traditional movable fixing frame platform, and is used with a force measuring component and a bearing pier.
As the squirrel-cage thrust frame is a barrel-like integrated structure and connected to the rear skirt of the solid rocket engine, the engine is wrapped by the squirrel-cage thrust frame, so the engine cannot be directly installed horizontally. It is necessary to insert the engine upside down into the squirrel-cage thrust frame, as shown in FIG. 4. After installation, the two are turned over into a horizontal state, and then placed on a pair of arc-shaped seats to achieve a pre-test state. In this way, in addition to the cumbersome installation process, a special overturning device needs to be designed, which increases the design and processing costs. In addition, through the general assembly drawing, it can be found that there is only a matching relationship between the solid rocket engine and the test device at the rear skirt flange, and the whole barrel section of the engine at the front end is unsupported. A pair of arc-shaped seats only support the holding hoops welded on the squirrel cage, and thus there must be a gap between the arc-shaped seats and the barrel section shell of the engine. Therefore, the engine is similar to a cantilever beam in the squirrel cage, and the stress concentration caused by the bending moment caused by the dead weight of the engine at the connecting position will be more serious, leading to the deviation of the engine axis, which reduces the safety and accuracy of the test.
In addition, due to the test requirements, many sensors need to be attached to the surface of the barrel section shell of the solid rocket engine, and the existence of the squirrel cage makes the wiring of the sensors difficult, and its connecting rods hinder the operator to connect the cables of the sensors on the engine, which reduces the test efficiency.
Summary
In view of that in the existing ground ignition test of a solid rocket engine, the horizontal test method with a rear skirt connection is complicated, inefficient and difficult to implement, the present disclosure provides a thrust transfer apparatus for the ignition test of a solid rocket engine in form of a rear skirt connection, wherein the connection position with the rear skirt of the engine adopts an upper-lower split structure, and the horizontal installation of the engine can be quickly realized without the help of a squirrel cage and a overturning tooling. The arc-shaped seat is designed to be integrated with the device and adjustable, and directly supports the engine by adjusting the height, thus avoiding the stress concentration at the connection position of the rear skirt caused by the dead weight of the engine. The detachable thrust rod and holding hoop further facilitate the test, ensure the accurate installation of the engine, avoid the interference, and can be connected to different movable fixing frames to meet the test requirements for engines of different specifications. The device has the advantages of simple use, low cost, high efficiency, good safety and the like.
The technical solutions of the present disclosure are as follows.
A thrust transfer apparatus for the ignition test of a solid rocket engine in form of a rear skirt connection includes a front-end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, connecting rods and a holding hoop, wherein a lower surface of the base is connected to a movable fixing frame platform for a test; the front-end connecting plate is fixed at one end of the base by right-angle welding, a center of the front-end connecting plate is provided with an installation hole connected to a force measuring component, the front-end connecting plate is connected to the force measuring component required by the test, and the front-end connecting plate is further provided with a plurality of bolt through holes evenly distributed circumferentially and configured to connect the connecting rods; the rear skirt connecting plate is configured to connect a rear skirt flange of the solid rocket engine, the rear skirt connecting plate is in an upper-lower split structure and is divided into a rear upper connecting plate and a rear lower connecting plate, the rear lower connecting plate is fixed at the other end of the base by right-angle welding, the base, the front-end connecting plate and the rear lower connecting plate are welded and fixed into an integral structure, and corner ribs are arranged at right-angle welding positions of the base with the front-end connecting plate and the rear lower connecting plate; a center of the rear skirt connecting plate composed of the rear upper connecting plate and the rear lower connecting plate is provided with a central through hole with an aperture larger than a diameter of a barrel body at a rear skirt part of the solid rocket engine to be tested, an edge of the central through hole is provided with an installation hole connected to the rear skid flange of the solid rocket engine, and a plurality of bolt through holes for connecting the connecting rods are provided outside the installation hole connected to the rear skirt flange of the solid rocket engine, which correspond in position to the bolt through holes connected to the connecting rods on the front-end connecting plate; the arc-shaped seat is installed on the base in a height-adjustable manner and is configured to directly support the solid rocket engine; and detachable thrust connecting rods are installed between the front-end connecting plate and the rear skid connecting plate, and the detachable thrust connecting rods are assembled after the engine is installed in place and wiring is completed; after the thrust connecting rods are installed in place, a holding hoop is additionally installed at a periphery of the thrust connecting rods, and the holding hoop holds the thrust connecting rods tightly to reduce deformation of the thrust connecting rods.
Further, by changing an opening position and form of the base and the front-end connecting plate, different types of movable fixing frame platforms and force measuring components can be connected to meet test requirements of solid rocket engines of different specifications.
Further, an upper surface of the base is welded with a plurality of threaded joints, and a bottom of the arc-shaped seat is welded with threaded joints in an opposite direction to threaded joints of the base; the arc-shaped seat is connected to the base through a sleeve, and two sections of mutually opposite threads are provided in the sleeve, the threads are respectively connected to a threaded joint at a bottom of a lower arc seat and a threaded joint on the upper surface of the base, and a height of the arc-shaped seat can be adjusted by rotating the sleeve.
Further, front and rear ends of the thrust connecting rod are provided with screw holes, and both ends of the thrust connecting rod are flush with inner sides of the front-end connecting plate and the rear skirt connecting plate, and are connected to bolt through holes evenly distributed on the front-end connecting plate and the rear skirt connecting plate by bolts.
Further, during installation of the thrust transfer apparatus, the connecting rods, the holding hoop and the rear upper connecting plate are in a disassembled state first, a height of the arc-shaped seat is lowered, the solid rocket engine is hoisted horizontally, the rear skirt of the solid rocket engine and the rear lower connecting plate is threadedly connected, and then the height of the arc-shaped seat is adjusted to support the solid rocket engine, an engine sling is loosened, and the arc-shaped seat and the rear upper connecting plate are used to hold the solid rocket engine tightly; after a sensor is connected in place on a surface of the solid rocket engine, the thrust connecting rods are installed in place, and after the thrust connecting rods are installed, a holding hoop is additionally installed at a periphery of the thrust connecting rods.
Beneficial Effects The thrust transfer apparatus provided by the present disclosure can directly realize the horizontal installation of the solid rocket engine by using a detachable connecting rods, a holding hoop and a rear upper connecting plate. Compared with the currently adopted test scheme, the overturning process of the engine and the test device is avoided, and an overturning device is not required to be designed at the same time, so that the test cost is reduced. In addition, the built-in arc-shaped seat with an adjustable height can directly support the barrel section of the engine. Compared with the previous arc seat supporting the squirrel cage, the stress concentration at the rear skirt connection is further avoided, and thus the safety of the test is improved. The detachable connecting rods further facilitates the wiring work of an operator after the engine is installed in place, which improves the test efficiency and can be considered for subsequent promotion and use.
Additional aspects and advantages of the present disclosure will be set forth in part in the description which follows, and in part will be obvious from the following description, or can be learned by practice of the present disclosure.
Brief Description of the Drawings
The above and/or additional aspects and advantages of the present disclosure will become apparent and easy to understand from the description of embodiments taken in conjunction with the following drawings, in which: FIG. 1 shows a traditional squirrel-cage thrust transfer apparatus, in which: 1-squirrel-cage thrust frame; 2-arc-shaped seat; 3-solid rocket engine with only rear skirt connecting hole; FIG. 2 is a schematic diagram of the squirrel-cage thrust frame, in which: 44ront-end connecting plate; 5-holding hoop; 6-connecting rod; 7-rear-end connecting plate; FIG. 3 shows a squirrel-cage test device, in which: 84orce measuring component; 9-movable fixing frame platform; 10-squirrelcage thrust transfer apparatus; FIG. 4 is a schematic diagram of the engine installed upside down; FIG. 5 shows the thrust transfer apparatus of the present disclosure, in which: 11-connecting rod; 12-arc-shaped seat; 13-holding hoop; 14-rear upper connecting plate; 15-sleeve; FIG. 6 is a structure diagram of the base (the illustration of the through holes connected to the connecting rods are omitted in the figure), in which: 16-front-end connecting plate; 17-rear lower connecting plate; 18-rib plate; 19-threaded joint; 20-bottom plate; FIG. 7 is a schematic diagram of the rear upper connecting plate; FIG. 8 is a schematic diagram of a forward-and-reverse threaded sleeve; FIG. 9 is a schematic diagram of the arc-shaped seat, in which: 21-upper arc seat; 22-lower arc seat; 23-reverse threaded joint; FIG. 10 is a schematic diagram of the holding hoop; FIG. 11 is an installation diagram of the present disclosure, in which: (a) the ready state of the device before the engine is installed, (b) the engine is horizontally installed on the test frame, (c) the upper arc seat and the rear upper connecting plate are installed, (d) the connecting rods and the holding hoop are installed; and FIG. 12 shows a test device using the thrust transfer apparatus of the present disclosure, in which: 24-the thrust transfer apparatus provided by the present disclosure. Detailed Description of Embodiments Embodiments of the present disclosure are described in detail below, and the embodiments are exemplary and intended to illustrate the present disclosure, but should not be construed as limiting the present disclosure.
In the description of the present disclosure, it should be understood that the orientation or positional relationships indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", and "counterclockwise" are based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present disclosure and simplifying the description, rather than indicating or implying that the referred device or element must be in a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the present disclosure.
The present disclosure provides a new thrust transfer apparatus in form of a rear skirt connection for horizontal test, which is suitable for the ground test of a solid rocket engine with only the rear skirt being provided with a connecting hole (but the front skirt cannot be connected to tooling), and can be directly installed horizontally without turning the engine over. The arc-shaped seat directly supports the engine, and its height is adjustable, thus avoiding the stress concentration at the rear skirt of the engine. The force transmission connecting rod connects the front and rear end faces, and is detachable, which is convenient for the installation of the engine and the commissioning of the test device.
As shown in FIGS. 5 to 10, the thrust transfer apparatus of the present disclosure includes a front-end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, connecting rods and a holding hoop.
Herein, the base is used as the main supporting part, and the lower surface of the base is connected to the movable fixing frame platform for the test. The front-end connecting plate is fixed at one end of the base by right-angle welding, a center of the front-end connecting plate is provided with an installation hole connected to a force measuring component, and the front-end connecting plate is connected to the force measuring component required by the test to ensure the accurate measurement of the thrust. In addition, a plurality of bolt through holes connected to the connecting rods are evenly distributed circumferentially around the front-end connecting plate. By changing the position and the form of the connecting holes of the base and the front-end connecting plate, different types of movable fixing frame platforms and force measuring components can be connected to meet the test requirements of solid rocket engines of different specifications.
The upper surface of the base is welded with a plurality of threaded joints, which are configured to connect with the arc-shaped seat through a threaded sleeve.
The rear skirt connecting plate is configured to connect a rear skirt flange of the solid rocket engine. The rear skirt connecting plate has an upper-lower split structure and is divided into a rear upper connecting plate and a rear lower connecting plate, the rear lower connecting plate is fixed at the other end of the base by right-angle welding, thus the base, the front-end connecting plate and the rear lower connecting plate are welded and fixed into an integral structure, and corner ribs are evenly arranged at right-angle welding positions of the base with the front-end connecting plate and the rear lower connecting plate, which can reduce the stress concentration at the welding position.
A center of the whole rear skirt connecting plate composed of the rear upper connecting plate and the rear lower connecting plate is provided with a central through hole with an aperture larger than a diameter of a barrel body at a rear skirt part of the solid rocket engine to be tested, an edge of the central through hole is provided with an installation hole connected to the rear skirt flange of the solid rocket engine, and a plurality of bolt through holes for connecting the connecting rods are provided outside the installation hole connected to the rear skirt flange of the solid rocket engine, corresponding in position to the bolt through holes connected to the connecting rods on the front-end connecting plate.
The arc-shaped seat is divided into an upper part and a lower part, the upper arc seat and the lower arc seat are fixedly connected by bolts. The arc-shaped seat is installed on the bottom seat, and can directly support the solid rocket engine. In order to reduce the influence of installation error, the arc-shaped seat is designed to be height-adjustable, which is realized by the following method: a bottom of the lower arc seat is welded with threaded joints in an opposite direction to threaded joints of the base; the arc-shaped seat is connected to the base through sleeves, and two sections of mutually opposite threads are provided in the sleeve, the threads are respectively connected to a threaded joint at a bottom of a lower arc seat and a threaded joint on the upper surface of the base, and a height of the arc-shaped seat can be finely adjusted by rotating the sleeve, thus ensuring that the arc-shaped seat can closely support the engine after the connection and installation of the rear skirt of the engine is completed, so as to avoid the influence by stress concentration of the bending moment caused by the dead weight of the engine on the connection position to the rear skirt.
In terms of thrust transmission, different from the previous welding method, the thrust connecting rods are designed to be detachable in the present disclosure, that is, the front and rear ends of the connecting rods are provided with screw holes, both ends of the connecting rods are flush with the inner sides of the front-end connecting plate and the rear skirt connecting plate, and are connected to bolt through holes evenly distributed on the front-end connecting plate and the rear skirt connecting plate by bolts. The detachable thrust connecting rods are assembled after the engine is installed in place and the wiring is completed, thus avoiding possible interference problems in the installation process and ensuring that the arc-shaped seat can directly support the engine.
After the connecting rods are installed in place, a holding hoop is additionally installed at a periphery of the connecting rods to hold the connecting rods tightly, so as to reduce the deformation of the connecting rods. Especially for the engine with a large length-to-diameter ratio, it may be considered to additionally install multiple pairs of holding hoops to reduce the deformation of the connecting rods caused by thrust.
The operation and use process of the present disclosure is as follows.
During the test preparation, the front-end connecting plate, the base, the rear lower connecting plate, the rib plate and the threaded joint are welded into one piece, and the connecting rods, the holding hoop and the rear upper connecting plate are all in disassembled state. Before the engine is installed, the forward-and-reverse threaded sleeve and the lower arc seat are installed first on the base, the height of the lower arc seat is lowered, the engine is horizontally hoisted, the rear skirt of the engine is threadedly connected with the rear lower connecting plate first, then the height of the arc seat is adjusted to support the engine, the engine sling is loosened, and then the upper arc seat and the rear upper connecting plate are installed. After connecting all sensors in place on the engine surface, all the connecting rods are installed in place. After the connecting rods are installed, a pair of bolt-connected holding hoops are additionally installed to the middle part.
The whole device is placed on various movable fixing frame platforms commonly used in ground tests, and is used with a force measuring component and a bearing pier, so that the requirements of a formal ignition test for the device can be realized, and various parameters such as the test thrust can be measured. By changing the form of the connecting holes at the front end and bottom, different types of assemblies of force measuring components and movable fixing frames can be connected to meet the test requirements of engines of different specifications.
Although the embodiments of the present disclosure have been shown and described above, it is to be understood that the embodiments are exemplary but should not be construed as limiting the present disclosure, and those of ordinary skill in the art may make changes, modifications, substitutions and variations of the embodiments within the scope of the present disclosure.
Claims (5)
- What is claimed is: 1. A thrust transfer apparatus for an ignition test of a solid rocket engine in form of a rear skirt connection, comprising a front-end connecting plate, a base, a rear skirt connecting plate, an arc-shaped seat, connecting rods, and a holding hoop, wherein a lower surface of the base is connected to a movable fixing frame platform for a test; the front-end connecting plate is fixed at one end of the base by right-angle welding, a center of the front-end connecting plate is provided with an installation hole connected to a force measuring component, the front-end connecting plate is connected to the force measuring component required by the test, and the front-end connecting plate is further provided with a plurality of bolt through holes evenly distributed circumferentially and configured to connect the connecting rods; the rear skirt connecting plate is configured to connect a rear skirt flange of the solid rocket engine, the rear skirt connecting plate is in an upper-lower split structure and is divided into a rear upper connecting plate and a rear lower connecting plate, the rear lower connecting plate is fixed at the other end of the base by right-angle welding, the base, the front-end connecting plate and the rear lower connecting plate are welded and fixed into an integral structure, and corner ribs are arranged at right-angle welding positions of the base with the front-end connecting plate and the rear lower connecting plate; a center of the rear skirt connecting plate composed of the rear upper connecting plate and the rear lower connecting plate is provided with a central through hole with an aperture larger than a diameter of a barrel body at a rear skirt part of the solid rocket engine to be tested, an edge of the central through hole is provided with an installation hole connected to the rear skirt flange of the solid rocket engine, and a plurality of bolt through holes for connecting the connecting rods are provided outside the installation hole connected to the rear skirt flange of the solid rocket engine, which correspond in position to the bolt through holes connected to the connecting rods on the front-end connecting plate; the arc-shaped seat is installed on the base in a height-adjustable manner and is configured to directly support the solid rocket engine; and detachable thrust connecting rods are installed between the front-end connecting plate and the rear skirt connecting plate, and the detachable thrust connecting rods are assembled after the engine is installed in place and wiring is completed; after the thrust connecting rods are installed in place, a holding hoop is additionally installed at a periphery of the thrust connecting rods, and the holding hoop holds the thrust connecting rods tightly to reduce deformation of the thrust connecting rods.
- 2. The thrust transfer apparatus for an ignition test of a solid rocket engine in form of a rear skirt connection according to claim 1, wherein by changing an opening position and form of the base and the front-end connecting plate, different types of movable fixing frame platforms and force measuring components can be connected to meet test requirements of solid rocket engines of different specifications.
- 3. The thrust transfer apparatus for an ignition test of a solid rocket engine in form of a rear skirt connection according to claim 1, wherein an upper surface of the base is welded with a plurality of threaded joints, and a bottom of the arc-shaped seat is welded with threaded joints in an opposite direction to the threaded joints of the base; the arc-shaped seat is connected to the base through sleeves, and two sections of mutually opposite threads are provided in each of the sleeves, the threads are respectively connected to a threaded joint at a bottom of a lower arc seat and a threaded joint on the upper surface of the base, and a height of the arc-shaped seat is adjustable by rotating the sleeves.
- 4. The thrust transfer apparatus for an ignition test of a solid rocket engine in form of a rear skirt connection according to claim 1, wherein front and rear ends of the thrust connecting rods are provided with screw holes, and both ends of the thrust connecting rods are flush with inner sides of the front-end connecting plate and the rear skirt connecting plate, and are connected to the bolt through holes evenly distributed on the front-end connecting plate and the rear skirt connecting plate by bolts.
- 5. The thrust transfer apparatus for an ignition test of a solid rocket engine in form of a rear skirt connection according to claim 1, wherein during installation of the thrust transfer apparatus, the connecting rods, the holding hoop and the rear upper connecting plate are in a disassembled state first, a height of the arc-shaped seat is lowered, the solid rocket engine is hoisted horizontally, a rear skirt of the solid rocket engine and the rear lower connecting plate is threadedly connected, and then a height of the arc-shaped seat is adjusted to support the solid rocket engine, an engine sling is loosened, and the arc-shaped seat and the rear upper connecting plate are used to hold the solid rocket engine tightly; after a sensor is connected in place on a surface of the solid rocket engine, the thrust connecting rods are installed in place, and after the thrust connecting rods are installed, a holding hoop is additionally installed at a periphery of the thrust connecting rods.
Applications Claiming Priority (2)
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB202216941D0 GB202216941D0 (en) | 2022-12-28 |
| GB2612455A true GB2612455A (en) | 2023-05-03 |
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ID=73528116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2216941.1A Pending GB2612455A (en) | 2020-10-04 | 2021-09-25 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
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 |
|---|---|---|---|---|
| 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 |
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- 2020-10-04 CN CN202011066998.7A patent/CN112012853B/en active Active
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- 2021-09-25 WO PCT/CN2021/120509 patent/WO2022068703A1/en active Application Filing
- 2021-09-25 GB GB2216941.1A patent/GB2612455A/en active Pending
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| 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 |
| 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 |
| CN108590889A (en) * | 2018-05-09 | 2018-09-28 | 北京理工大学 | A kind of larynx hydrant change propulsive solid propellant rocket ground test device |
| CN112012853A (en) * | 2020-10-04 | 2020-12-01 | 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022068703A1 (en) | 2022-04-07 |
| GB202216941D0 (en) | 2022-12-28 |
| CN112012853B (en) | 2021-07-06 |
| CN112012853A (en) | 2020-12-01 |
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