CN203069380U - Pipeline connection structure used for reducing thrust measurement binding force in rocket engine test - Google Patents
Pipeline connection structure used for reducing thrust measurement binding force in rocket engine test Download PDFInfo
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- CN203069380U CN203069380U CN 201220633636 CN201220633636U CN203069380U CN 203069380 U CN203069380 U CN 203069380U CN 201220633636 CN201220633636 CN 201220633636 CN 201220633636 U CN201220633636 U CN 201220633636U CN 203069380 U CN203069380 U CN 203069380U
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- pipeline
- rocket engine
- engine test
- thrust measurement
- thrust
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Abstract
The utility model provides a pipeline connection structure used for reducing the thrust measurement binding force in a rocket engine test. The technical problems can be solved and the impact of the fluid force on the thrust of an engine can be controlled to a bare minimum. The pipeline connection structure used for reducing the thrust measurement binding force in a rocket engine test comprises a pipeline support, a flexible component and front and rear sections of pipelines, wherein the front and rear sections of pipelines are respectively fixed on a movable frame and a fixed frame of a test bench through the pipeline support so as to ensure that the pipeline fixing direction is perpendicular to the axis of the thrust of the engine, namely, the pipeline fixing direction is in the radial direction, and the front and rear sections of pipelines are connected by the flexible component in a welded or flanged connection mode.
Description
Technical field
The present invention relates to a kind of pipeline jointing construction for rocket engine test minimizing thrust measurement constraining force, belong to liquid-propellant rocket engine test field.
Background technology
As the important parameter of rocket engine performance, need before taking a flight test to adopt the mode of test that thrust is accurately measured, truly reflect the performance of engine.In liquid-propellant rocket engine test, need peel off the influence that propellant temperature, pressure, fluid impact are measured motor power.Especially the pipeline big to bore, that pressure is high, pipeline type of attachment have determined the influence degree that its internal liquid propellant is measured motor power.Tradition thrust measurement medium caliber pipeline big, that pressure is high directly connects engine, and pipeline causes involves power and motor power intercouples, and error can't be peeled off, and has reduced the measuring accuracy of engine.
Therefore, invent a kind of pipeline connecting method that reduces the thrust measurement constraining force, by moving, deciding to adopt respectively on the frame fixed form, guarantee that the pipeline trend is perpendicular to the motor power axis, making the acting force of pipeline fluid is zero at the component of thrust axis direction, the thrust axis acting force is limited within the moving frame, cancels out each other as internal force, thereby the fluid function influence is down to minimum.
Summary of the invention
The invention provides a kind of pipeline jointing construction for rocket engine test minimizing thrust measurement constraining force, can solve the problems of the technologies described above, make fluid force influence control in minimum to motor power.
The pipeline jointing construction that the rocket engine test reduces the thrust measurement constraining force be should be used for, pipeline bearing, flexible piece and front and rear sections pipeline comprised; Forward and backward two sections pipelines are fixed on the moving frame of testing table by the pipeline bearing respectively and decide on the frame, guarantee pipeline fixed-direction and motor power axis normal, namely radially move towards; Adopt flexible piece to connect between forward and backward two sections pipelines, connected mode is welding or flange connection.
Flexible piece adopts corrugated tube or Ω tube side formula.
Beneficial effect of the present invention:
1, the present invention adopts radial symmetry to move towards mode at the pipeline of deciding between frame and the moving frame, and the acting force that makes the pipeline fluid enter moving frame is zero at the component of thrust axis direction.
2, decide among the present invention that pipeline is connected the flexible structure that adopts between frame and the moving frame, can the compensation conduit influence that Zona transformans is given moving frame on engine is radial and axial.
3, adopt pipeline connecting method of the present invention, thrust axis to the bend pipe pipeline will all concentrate on moving frame, the inner fluid force conduct that produce and the thrust axially parallel of pipeline is moved frame internal force and is cancelled out each other, thereby has peeled off the influence of pipeline to thrust measurement in principle.
Description of drawings
Fig. 1 is heavy caliber pipeline type of attachment structural representation;
1 liquid-propellant rocket engine wherein, 2 corrugated tubes, 3 pipelines, 4 pipeline bearings, 5 decide frame, 6 moving framves;
Fig. 2 is pressure duct type of attachment structural representation;
4 pipeline bearings wherein, 5 decide frame, 6 moving framves, 7 Ω pipe.
Embodiment
Embodiment 1: heavy caliber pipeline connected mode
Shown in figure one, liquid-propellant rocket engine 1 is installed on the moving frame 6, and extraneous pipeline 3 is introduced moving frame 6 by deciding frame 5.For reducing the pipeline constraining force to the influence of thrust measurement, moving frame 6 and the pipeline of deciding between the frame 5 adopt radially mode of entrance, and the acting force that makes the pipeline fluid enter moving frame 6 is zero at the component of thrust axis direction.Decide on frame 5 and the moving frame 6 fixingly by two pipeline bearings 4 respectively, adopt corrugated tube 2 to connect between two sections pipelines, can compensate the influence that Zona transformans is given moving frame 6 on engine is radial and axial.Pipeline on moving frame 6 carries out 90 ° of bendings, and its inner fluid force with the thrust axially parallel that produces is cancelled out each other as pipeline internal force, thereby has peeled off the influence of pipeline to thrust measurement in principle.
Embodiment 2: the pressure duct connected mode
In the pressure duct application scenario, moving frame 6 and this pipeline connecting mode of pipeline of deciding between the frame 5 also adopt radially mode of entrance.But decide can not directly adopt straight tube to be connected between frame 5 and the moving frame 6, can adopt the Ω shown in the figure two to manage 7 connected modes, the two ends of Ω pipe 7 are fixed on by pipeline bearing 4 respectively decides on frame 5 and the moving frame 6.Utilize symmetrical structure and the bend pipe self-deformation of Ω pipe, eliminate high-pressure fluid and impact moving the influence that frame and motor power are measured.
Claims (2)
1. be used for the pipeline jointing construction that the rocket engine test reduces the thrust measurement constraining force, it is characterized in that: comprise pipeline bearing, flexible piece and front and rear sections pipeline; Forward and backward two sections pipelines are fixed on the moving frame of testing table by the pipeline bearing respectively and decide on the frame, guarantee pipeline fixed-direction and motor power axis normal, namely radially move towards; Adopt flexible piece to connect between forward and backward two sections pipelines, connected mode is welding or flange connection.
2. the pipeline jointing construction for rocket engine test minimizing thrust measurement constraining force as claimed in claim 1 is characterized in that: flexible piece employing corrugated tube or Ω tube side formula.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220633636 CN203069380U (en) | 2012-11-26 | 2012-11-26 | Pipeline connection structure used for reducing thrust measurement binding force in rocket engine test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220633636 CN203069380U (en) | 2012-11-26 | 2012-11-26 | Pipeline connection structure used for reducing thrust measurement binding force in rocket engine test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203069380U true CN203069380U (en) | 2013-07-17 |
Family
ID=48768154
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220633636 Expired - Fee Related CN203069380U (en) | 2012-11-26 | 2012-11-26 | Pipeline connection structure used for reducing thrust measurement binding force in rocket engine test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203069380U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110307105A (en) * | 2019-07-31 | 2019-10-08 | 西安航天动力研究所 | It is a kind of to determine thrust rocket engine or motor power room performance testing device |
| CN110595791A (en) * | 2019-08-20 | 2019-12-20 | 南京理工大学 | Thrust measurement experiment table for solid fuel stamping connecting pipe experiment |
-
2012
- 2012-11-26 CN CN 201220633636 patent/CN203069380U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110307105A (en) * | 2019-07-31 | 2019-10-08 | 西安航天动力研究所 | It is a kind of to determine thrust rocket engine or motor power room performance testing device |
| CN110307105B (en) * | 2019-07-31 | 2020-06-09 | 西安航天动力研究所 | Testing device |
| CN110595791A (en) * | 2019-08-20 | 2019-12-20 | 南京理工大学 | Thrust measurement experiment table for solid fuel stamping connecting pipe experiment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130717 Termination date: 20161126 |