CN114199574A - Solid rocket engine integration test tool - Google Patents
Solid rocket engine integration test tool Download PDFInfo
- Publication number
- CN114199574A CN114199574A CN202111597367.2A CN202111597367A CN114199574A CN 114199574 A CN114199574 A CN 114199574A CN 202111597367 A CN202111597367 A CN 202111597367A CN 114199574 A CN114199574 A CN 114199574A
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- test
- center frame
- solid rocket
- bearing pier
- rocket engine
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- 238000012360 testing method Methods 0.000 title claims abstract description 95
- 239000007787 solid Substances 0.000 title claims abstract description 24
- 230000010354 integration Effects 0.000 title claims description 11
- 238000011065 in-situ storage Methods 0.000 claims abstract description 18
- 238000006073 displacement reaction Methods 0.000 claims abstract description 3
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 8
- 238000012545 processing Methods 0.000 abstract description 7
- 238000010586 diagram Methods 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the field of solid rocket engine tests, in particular to a solid rocket engine integrated test tool. The method comprises the following steps: the arc seat, the front force-bearing pier, the rear force-bearing pier, the front center frame, the rear force-bearing pier, the small attached plate and the large attached plate are fixed on the upper surface of the bottom plate through bolts, the small attached plate is fixed on the large attached plate through bolts, and the large attached plate is fixed on the front force-bearing pier through bolts. The upper surface of the bottom plate is provided with a T-shaped groove. And a center frame bolt is arranged in the T-shaped groove to control the fixation and displacement of the front center frame and the rear center frame. The invention can realize the ground test and the in-situ calibration of engines with different lengths within the diameter range of 100-400mm, and has higher test precision. At present, a plate spring test frame with higher test precision is special test equipment, although the test precision is high, the processing cost is high, the processing period is longer, and the requirement of heavy test tasks at the present stage cannot be met.
Description
Technical Field
The invention relates to the field of solid rocket engine tests, in particular to a solid rocket engine integrated test tool.
Background
When the engine is used for ground test, the engine needs to be fixed on a test rack, and the test rack is placed on the guide rail. After the engine is ignited, the test rack moves on the guide rail simultaneously, and test parameters are collected. The method requires that all the test equipment are special test equipment, the motion of the test frame on the guide rail is rolling friction, and the heavier the test frame is, the larger the friction force is, the larger the influence on the collection of test parameters is. Meanwhile, with the increase of scientific research and production tasks, the processing and manufacturing period of the test equipment is required to be shortened, and the test cost is reduced. Ordinary test equipment satisfies the above-mentioned needs.
At present, multifunctional test process equipment applied to solid rocket engine tests is unavailable.
The engine test stand belongs to the special frock of engine, and the engine of different structure size need design not unidimensional test stand with it cooperation, and the uncontrollable test stand quantity of processing reduces test cost, and processing test stand needs certain time cycle simultaneously, wastes time and energy and takes money.
Disclosure of Invention
Technical problem to be solved by the invention
The invention provides an integrated test tool for a solid rocket engine, which aims to solve the technical problem that test process equipment cannot be universal in the engine test process. The test process equipment also has the capability of in-situ calibration, and meets the in-situ calibration requirements of ground tests of certain models.
Technical scheme adopted by the invention for solving technical problem
The utility model provides a solid rocket engine integration test fixture, includes: the arc seat, the front force-bearing pier, the rear force-bearing pier, the front center frame, the rear force-bearing pier, the small attached plate and the large attached plate are fixed on the upper surface of the bottom plate through bolts, the small attached plate is fixed on the large attached plate through bolts, and the large attached plate is fixed on the front force-bearing pier through bolts.
Furthermore, the upper surface of the bottom plate is provided with a T-shaped groove.
Furthermore, a center frame bolt is arranged in the T-shaped groove to control the fixation and displacement of the front center frame and the rear center frame.
Furthermore, the rear bearing pier is placed right side as a test bearing pier, and is rotated by 180 degrees to form a reverse bearing pier calibrated in situ.
Further, the front center frame and the rear center frame are adjusted back and forth and/or are radially stretched and contracted according to the size of the engine.
Further, the test tool bottom plate is a steel plate with the thickness of 60 mm.
Furthermore, the arc seat is also provided with a pressing belt for fixing the small-size engine.
Advantageous effects obtained by the present invention
The invention can realize the ground test and the in-situ calibration of engines with different lengths within the diameter range of 100-400mm, and has higher test precision. At present, a plate spring test frame with higher test precision is special test equipment, although the test precision is high, the processing cost is high, the processing period is longer, and the requirement of heavy test tasks at the present stage cannot be met.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1: the structure schematic diagram of the solid rocket engine integrated test tool;
FIG. 2: an in-situ calibration schematic diagram of a solid rocket engine integrated test;
FIG. 3: a ground test schematic diagram of a long engine for the solid rocket engine integrated test;
FIG. 4: a schematic diagram of an integrated test in-situ calibration component of the solid rocket engine;
FIG. 5: a solid rocket engine integrated test small engine ground test schematic diagram;
wherein: the method comprises the following steps of 1-a bottom plate, 2-an arc seat, 3-a backward bearing pier, 4-a rear center frame, 5-a front center frame, 6-a small attached plate, 7-a large attached plate, 8-a front bearing pier, 9-an in-situ calibration assembly, 10-a thrust sensor, 11-a reverse thrust frame, 12-a standard thrust sensor, 13-an oil cylinder, 14-an adapter and 15-a small-size engine.
Detailed Description
The invention provides multifunctional test process equipment for a solid rocket engine. The test equipment mainly comprises a bottom plate, a bearing pier, a center frame, a reverse bearing pier, an in-situ calibration assembly and the like, wherein the reverse bearing pier can be used as the bearing pier and can also be used as the reverse bearing pier for in-situ calibration. The test equipment is used for carrying out the ground test of the engine, and the ground test requirements of engines with different lengths within the diameter range of 100-400mm can be met.
In order to make the objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. It is obvious that the described embodiments are only some, not all embodiments of the proposed solution. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, 2 and 3, the solid rocket engine integrated test tool comprises a bottom plate 1, a front force-bearing pier 8, a front center frame 4, a rear center frame 5, a rear force-bearing pier 3, a large attachment plate 7 and a small attachment plate 6. The test stand has the functions of in-situ calibration of the engine, ground test of the long engine, ground test of the small-size engine and the like. The test stand bottom plate is the steel sheet of thickness 60mm, and during the engine ground test, the test stand can effectively reduce the test stand deflection when wholly bearing thrust. A T-shaped groove is reserved on the upper surface of the bottom plate and is specially used for connecting the center frame; meanwhile, a plurality of threaded holes are reserved as tool connecting interfaces, and the bearing pier is connected with the bottom plate through bolts. The large auxiliary plate is connected with the bearing pier through a bolt, and the upper position and the lower position of the large auxiliary plate can be adjusted to ensure the adjustment of the center height of the engine. The small attached plate is connected with the large attached plate through a bolt, and the left-right posture of the engine is adjusted through horizontal movement.
Example 1
As shown in fig. 5, the ignition test of the small tester was completed. The rear bearing pier 3 can be used as a test bearing pier and is arranged at the rear end of the bottom plate 1 to carry out an engine test with smaller length. The arc seat 2 and the rear bearing pier 3 are arranged on the upper surface of the base plate 1 through bolts, the arc seat 2 is provided with a press belt, the arc seat and the press belt are used during ground test of the small-size engine 15, and the arc seat and the press belt are used for holding the small-size engine 15 tightly for ground test. The test is suitable for models such as testers which do not need to test the thrust.
Example 2
As shown in fig. 3, in a schematic diagram of a ground test of a long engine, a front center frame 5 and a rear center frame 4 are selected as supporting devices of the ground test, and a T-shaped groove reserved on the upper surface of a bottom plate is of a penetrating structure, so that the center frames can move back and forth conveniently. And adjusting the span of the pivot of the central frame and adjusting the expansion amount of the guide wheel of the central frame according to the size of the engine. The long engine to be tested is supported on the front bearing pier 8 through the auxiliary plate.
Example 3
As shown in FIG. 2, the in-situ calibration schematic diagram of the solid rocket engine integration test is shown. The front and rear bearing piers and the front and rear support frames are fixed on the upper surface of the bottom plate, and the engine rear bearing pier is turned by 180 degrees to form a reverse bearing pier. As shown in fig. 4, the in-situ calibration device includes a reverse thrust frame 11, a standard thrust sensor 12, a cylinder 13, an adapter 14, and the like. One end of the thrust reverser is connected with the rear skirt of the engine, and the other end of the thrust reverser is connected with the standard sensor through the adapter. The standard sensor is connected with the oil cylinder through the adapter piece. The oil cylinder is connected with the reverse force bearing pier through the adapter by a bolt. During in-situ calibration, the engine is connected with the sensor and the force bearing pier through the center frame, the rear skirt of the engine and the rear force bearing pier are connected with the in-situ calibration device shown in the figure 4, a corresponding force value is applied to the engine through the oil cylinder 13, the force value is read by the standard thrust sensor to be used as a standard force value, and in-situ calibration of the force value of each step of the test sensor is carried out. After in-situ calibration, the long engine ground test can be directly carried out after the components 1 and 3 are removed as shown in fig. 3.
The invention has been successfully applied to the ground tests of the engines with different sizes, and the ground test of the engines is carried out by using the test device, thereby not only achieving the purposes of saving the cost and shortening the test period, but also having high test precision during the test. Has high application value.
Claims (7)
1. The utility model provides a solid rocket engine integration test fixture which characterized in that includes: the arc seat, the front force-bearing pier, the rear force-bearing pier, the front center frame, the rear force-bearing pier, the small attached plate and the large attached plate are fixed on the upper surface of the bottom plate through bolts, the small attached plate is fixed on the large attached plate through bolts, and the large attached plate is fixed on the front force-bearing pier through bolts.
2. The solid rocket engine integration test tool according to claim 1, characterized in that: the upper surface of the bottom plate is provided with a T-shaped groove.
3. The solid rocket engine integration test tool according to claim 2, characterized in that: and a center frame bolt is arranged in the T-shaped groove to control the fixation and displacement of the front center frame and the rear center frame.
4. The solid rocket engine integration test tool according to claim 1, characterized in that: the rear bearing pier is a testing bearing pier and is a reverse bearing pier calibrated in situ after being rotated by 180 degrees.
5. The solid rocket engine integration test tool according to claim 1, characterized in that: the front center frame and the rear center frame are adjusted forwards and backwards and/or are radially stretched and contracted according to the size of the engine.
6. The solid rocket engine integration test tool according to claim 1, characterized in that: the test tooling bottom plate is a steel plate with the thickness of more than 60 mm.
7. The solid rocket engine integration test tool according to claim 1, characterized in that: the arc seat is also provided with a pressing belt for fixing the small-size engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111597367.2A CN114199574A (en) | 2021-12-24 | 2021-12-24 | Solid rocket engine integration test tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111597367.2A CN114199574A (en) | 2021-12-24 | 2021-12-24 | Solid rocket engine integration test tool |
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| Publication Number | Publication Date |
|---|---|
| CN114199574A true CN114199574A (en) | 2022-03-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111597367.2A Pending CN114199574A (en) | 2021-12-24 | 2021-12-24 | Solid rocket engine integration test tool |
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| CN (1) | CN114199574A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5831155A (en) * | 1996-12-02 | 1998-11-03 | Atlantic Research Corporation | Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system |
| KR200443527Y1 (en) * | 2008-01-09 | 2009-02-20 | 이상기 | Safety Compass with protecting cap |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
| CN107907342A (en) * | 2017-12-18 | 2018-04-13 | 西安航天动力测控技术研究所 | The thrust calibrated in situ device that a kind of canted nozzle axially reinforces |
| KR101965579B1 (en) * | 2017-10-31 | 2019-04-04 | 주식회사 한화 | Conbustion test apparatus of rocket engine and thrust measurement method of rocket engine using the same |
| CN109580150A (en) * | 2018-12-03 | 2019-04-05 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket vibration test standard frock |
| CN109632171A (en) * | 2019-01-08 | 2019-04-16 | 陕西航天西诺美灵电气有限公司 | A kind of rocket engine micro-force measuring apparatus |
| WO2022068703A1 (en) * | 2020-10-04 | 2022-04-07 | 西安航天动力测控技术研究所 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
| CN216559724U (en) * | 2021-12-24 | 2022-05-17 | 内蒙航天动力机械测试所 | Solid rocket engine integration test tool |
| CN116818336A (en) * | 2023-05-29 | 2023-09-29 | 内蒙航天动力机械测试所 | Multi-degree-of-freedom adjustment test technological equipment for solid engine |
-
2021
- 2021-12-24 CN CN202111597367.2A patent/CN114199574A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5831155A (en) * | 1996-12-02 | 1998-11-03 | Atlantic Research Corporation | Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system |
| KR200443527Y1 (en) * | 2008-01-09 | 2009-02-20 | 이상기 | Safety Compass with protecting cap |
| CN205785819U (en) * | 2016-05-24 | 2016-12-07 | 华中科技大学 | A kind of test device for rocket engine ground firing |
| KR101965579B1 (en) * | 2017-10-31 | 2019-04-04 | 주식회사 한화 | Conbustion test apparatus of rocket engine and thrust measurement method of rocket engine using the same |
| CN107907342A (en) * | 2017-12-18 | 2018-04-13 | 西安航天动力测控技术研究所 | The thrust calibrated in situ device that a kind of canted nozzle axially reinforces |
| CN109580150A (en) * | 2018-12-03 | 2019-04-05 | 内蒙航天动力机械测试所 | A kind of solid propellant rocket vibration test standard frock |
| CN109632171A (en) * | 2019-01-08 | 2019-04-16 | 陕西航天西诺美灵电气有限公司 | A kind of rocket engine micro-force measuring apparatus |
| WO2022068703A1 (en) * | 2020-10-04 | 2022-04-07 | 西安航天动力测控技术研究所 | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
| CN216559724U (en) * | 2021-12-24 | 2022-05-17 | 内蒙航天动力机械测试所 | Solid rocket engine integration test tool |
| CN116818336A (en) * | 2023-05-29 | 2023-09-29 | 内蒙航天动力机械测试所 | Multi-degree-of-freedom adjustment test technological equipment for solid engine |
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