CN204064660U - A kind of engine wobble test unit - Google Patents
A kind of engine wobble test unit Download PDFInfo
- Publication number
- CN204064660U CN204064660U CN201420405498.5U CN201420405498U CN204064660U CN 204064660 U CN204064660 U CN 204064660U CN 201420405498 U CN201420405498 U CN 201420405498U CN 204064660 U CN204064660 U CN 204064660U
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- China
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- actuator
- linkage assembly
- engine
- transition frame
- sliding seat
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- Expired - Lifetime
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- 238000012360 testing method Methods 0.000 title claims abstract description 20
- 230000007704 transition Effects 0.000 claims abstract description 12
- 230000008859 change Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- Testing Of Engines (AREA)
Abstract
The utility model proposes a kind of engine wobble test unit, comprise actuator, linkage assembly, sliding platform and transition frame; Rocket engine front end is fixedly connected with transition frame one end, and the transition frame other end coordinates with outside Fixed-point Motion of A; Rocket engine rear end is arranged on the sliding seat of sliding platform; Actuator output terminal is fixedly connected with linkage assembly one end, and the linkage assembly other end is connected with sliding seat; Actuator is controlled to move back and forth, and is amplified by reciprocating stroke by linkage assembly, and drives sliding seat to move on sliding platform, and then drives rocket engine to carry out radial reciprocating-oscillation.Actuator is used for engine wobble test by the utility model, accurately can realize multiple swing requirement by servo-control system to the control of actuator.Because actuator stroke is less, by linkage assembly, its stroke is carried out amplifying to reach the object increasing engine wobble amplitude.Test shows, the utility model can apply radial overload to below 1000kg engine.
Description
Technical field
The utility model relates to Test System for Rocket Engine Test technical field, is specially a kind of engine wobble test unit, and this device can as requested, realize the quick swing of below 1000Kg engine, and stable action, sequential be accurate.
Background technology
Rocket engine has all needed overload test; current rocket engine overload test mainly adopts the mode such as hydro-extractor, rocket sledge; but these current test units are also applicable to the radial overload test of rocket engine; and radial overload sudden change usually can cause rocket engine to occur the special feelings such as sudden change of pressure surface in flight course, so be necessary that the new test unit of design carries out the radial overload test of rocket engine.
Summary of the invention
Technical scheme of the present invention is:
Described a kind of engine wobble test unit, is characterized in that: comprise actuator, linkage assembly, sliding platform and transition frame; Rocket engine front end is fixedly connected with transition frame one end, and the transition frame other end coordinates with outside Fixed-point Motion of A; Rocket engine rear end is arranged on the sliding seat of sliding platform; Actuator output terminal is fixedly connected with linkage assembly one end, and the linkage assembly other end is connected with sliding seat; Actuator is controlled to move back and forth, and is amplified by reciprocating stroke by linkage assembly, and drives sliding seat to move on sliding platform, and then drives rocket engine to carry out radial reciprocating-oscillation.
Beneficial effect
Actuator is used for engine wobble test by the utility model, and its advantage is accurately to realize multiple swing requirement by servo-control system to the control of actuator, such as changes amplitude of fluctuation and hunting frequency etc.Because actuator stroke is less, by linkage assembly, its stroke is carried out amplifying to reach the object increasing engine wobble amplitude.Test shows, the utility model to below 1000kg engine applying radial direction overload, and can realize the technical requirement such as overload sudden change, the steady safety of swing.
Accompanying drawing explanation
Fig. 1: oscillation testing device structural representation.
1-transition frame, 2-engine, 3-actuator, 4-linkage assembly, 5-sliding platform and safe spacing.
Embodiment
Now the invention will be further described by reference to the accompanying drawings:
With reference to accompanying drawing 1, a kind of engine wobble test unit in the present embodiment, comprises actuator 3, linkage assembly 4, sliding platform and transition frame 1.Rocket engine front end is fixedly connected with transition frame one end, and the transition frame other end coordinates with outside Fixed-point Motion of A; Rocket engine rear end is arranged on the sliding seat of sliding platform; Actuator output terminal is fixedly connected with linkage assembly one end, and the linkage assembly other end is connected with sliding seat; Actuator is controlled to move back and forth, and is amplified by reciprocating stroke by linkage assembly, and drives sliding seat to move on sliding platform, and then drives rocket engine to carry out radial reciprocating-oscillation.
Actuator is connected with the servo energy and servo-control system, by writing specific control program to servo-control system, actuator pistons bar can be controlled with sine wave, triangular wave, the form to-and-fro movements such as square wave, but actuator stroke is less, by linkage assembly, its stroke is amplified, make it that 4 meters of how long engines can be driven to carry out significantly reciprocally swinging, the accurate control to the radial overload quantity of engine can be realized by the control program rewriting servo-control system, thus the multiple radial overload conditions that simulated engine runs in practical flight process.
Claims (1)
1. an engine wobble test unit, is characterized in that: comprise actuator, linkage assembly, sliding platform and transition frame; Rocket engine front end is fixedly connected with transition frame one end, and the transition frame other end coordinates with outside Fixed-point Motion of A; Rocket engine rear end is arranged on the sliding seat of sliding platform; Actuator output terminal is fixedly connected with linkage assembly one end, and the linkage assembly other end is connected with sliding seat; Actuator is controlled to move back and forth, and is amplified by reciprocating stroke by linkage assembly, and drives sliding seat to move on sliding platform, and then drives rocket engine to carry out radial reciprocating-oscillation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420405498.5U CN204064660U (en) | 2014-07-22 | 2014-07-22 | A kind of engine wobble test unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420405498.5U CN204064660U (en) | 2014-07-22 | 2014-07-22 | A kind of engine wobble test unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204064660U true CN204064660U (en) | 2014-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420405498.5U Expired - Lifetime CN204064660U (en) | 2014-07-22 | 2014-07-22 | A kind of engine wobble test unit |
Country Status (1)
| Country | Link |
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| CN (1) | CN204064660U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104807646A (en) * | 2015-05-21 | 2015-07-29 | 中国工程物理研究院总体工程研究所 | Installation device for centrifugal overload test of solid rocket engine |
| CN104977169A (en) * | 2015-04-15 | 2015-10-14 | 北京宇航系统工程研究所 | Rocket engine cold swinging digital test method |
| RU167873U1 (en) * | 2016-02-29 | 2017-01-11 | Михаил Николаевич Ларин | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATION MODES OF THE ROCKET ENGINE OF THE FUEL FUEL |
| RU183978U1 (en) * | 2018-01-15 | 2018-10-11 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ Военная академия Ракетных войск стратегического назначения имени Петра Великого МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATION MODES OF A LIQUID ROCKET ENGINE |
| CN109236499A (en) * | 2018-11-02 | 2019-01-18 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
| CN109268442A (en) * | 2018-10-30 | 2019-01-25 | 中国船舶重工集团公司第七〇九研究所 | A kind of integration active vibration isolation actuator |
| CN111121703A (en) * | 2019-12-11 | 2020-05-08 | 西安航天发动机有限公司 | Swing interference detection system for liquid rocket engine |
| RU200539U1 (en) * | 2020-07-07 | 2020-10-28 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ Военная академия Ракетных войск стратегического назначения имени Петра Великого МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATING MODES OF A ROCKET ENGINE FOR SOLID FUEL |
-
2014
- 2014-07-22 CN CN201420405498.5U patent/CN204064660U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104977169A (en) * | 2015-04-15 | 2015-10-14 | 北京宇航系统工程研究所 | Rocket engine cold swinging digital test method |
| CN104807646A (en) * | 2015-05-21 | 2015-07-29 | 中国工程物理研究院总体工程研究所 | Installation device for centrifugal overload test of solid rocket engine |
| CN104807646B (en) * | 2015-05-21 | 2017-06-09 | 中国工程物理研究院总体工程研究所 | Solid propellant rocket is centrifuged the erecting device of overload test |
| RU167873U1 (en) * | 2016-02-29 | 2017-01-11 | Михаил Николаевич Ларин | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATION MODES OF THE ROCKET ENGINE OF THE FUEL FUEL |
| RU183978U1 (en) * | 2018-01-15 | 2018-10-11 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ Военная академия Ракетных войск стратегического назначения имени Петра Великого МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATION MODES OF A LIQUID ROCKET ENGINE |
| CN109268442A (en) * | 2018-10-30 | 2019-01-25 | 中国船舶重工集团公司第七〇九研究所 | A kind of integration active vibration isolation actuator |
| CN109236499A (en) * | 2018-11-02 | 2019-01-18 | 西安航天动力测控技术研究所 | A kind of solid propellant rocket varied angle centrifugation overload point fire test device and test method |
| CN111121703A (en) * | 2019-12-11 | 2020-05-08 | 西安航天发动机有限公司 | Swing interference detection system for liquid rocket engine |
| CN111121703B (en) * | 2019-12-11 | 2021-08-13 | 西安航天发动机有限公司 | Swing interference detection system for liquid rocket engine |
| RU200539U1 (en) * | 2020-07-07 | 2020-10-28 | ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ КАЗЕННОЕ ВОЕННОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ Военная академия Ракетных войск стратегического назначения имени Петра Великого МИНИСТЕРСТВА ОБОРОНЫ РОССИЙСКОЙ ФЕДЕРАЦИИ | BALLISTIC PENDULUM FOR DEMONSTRATION OF OPERATING MODES OF A ROCKET ENGINE FOR SOLID FUEL |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141231 |
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| CX01 | Expiry of patent term |