CN104949839A - Adaptor frame structure of thrust vector testing device - Google Patents
Adaptor frame structure of thrust vector testing device Download PDFInfo
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- CN104949839A CN104949839A CN201510412450.6A CN201510412450A CN104949839A CN 104949839 A CN104949839 A CN 104949839A CN 201510412450 A CN201510412450 A CN 201510412450A CN 104949839 A CN104949839 A CN 104949839A
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- change
- over frame
- flange
- adaptor frame
- testing device
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Abstract
The invention provides an adaptor frame structure applied to an attitude/orbit control engine thrust vector testing device. A tested engine mounting flange surface, a far-end calibration flange mounting surface, a near-end calibration mounting flange surface and lifting bolt holes are designed on an adaptor frame. Corresponding positioning pin holes are designed in all the flange surfaces of the adaptor frame, so that the positioning precision for mounting is guaranteed, the mounting accuracy of test pieces is improved, and the operation difficulty is reduced. By the aid of the adaptor frame, the thrust vector testing device can perform calibration tests at two ends of the adaptor frame respectively, and the precision of the testing device is guaranteed while engine mounting conditions are met.
Description
Technical field
The invention belongs to sensor and measurement and control area thereof, particularly appearance/precise tracking thrust vectoring field tests.
Background technology
Along with the development of Aero-Space cause, the controllability that rocket appearance/precise tracking thrust vectoring test controls for spacecraft flight, reliability and even satisfactorily completing of space mission have great significance.The thrust vectoring test experiments of engine all needs to be realized by proving installation, because the mounting interface of engine and the mounting interface of proving installation there are differences, therefore needs to be installed by Change-over frame.
Traditional propulsion test device is horizontal type device, Change-over frame only ensures that the switching of engine is installed, increase the distance that engine outwards overhangs, addition of the impact of moment of torsion, make the performance of the test macro after installing engine, compared with calibration result before installing, larger change occur, add systematic error.
Therefore the design of Change-over frame not only will install location to engine accurately, facilitates suspention and the installation of engine.Also to provide installing space for calibration structure simultaneously, make proving installation can carry out demarcation operation respectively at the two ends of Change-over frame.The calibration result at Change-over frame two ends can reflect the impact of additional torque on proving installation performance, thus ensures that test macro can reach higher precision.In addition, Change-over frame will ensure that enough rigidity and intensity reduce the impact on proving installation dynamic perfromance equally.
Summary of the invention
The technical problem to be solved in the present invention is the Change-over frame structure that design a kind ofly accurately can be located, lifted conveniently, structural strength is enough, ensures that engine is accurately installed.
The technical solution used in the present invention is: a kind of thrust vectoring proving installation Change-over frame structure, and its main body is for being provided with reinforcement cylinder mode, and two ends are for demarcating flange installed surface; Flange installed surface is demarcated through fine grinding process in rear end, and its inner circle side is provided with rear end positioning boss, ensures the registration in the axle center of rear end positioning boss and the geometry axle center of Change-over frame structure, is convenient to install location; Demarcate flange and be provided with pin-and-hole, ensure the circumferential precision of installing; Test block mounting flange face is positioned at Change-over frame front end, and for installation testing part, the location and installation hole on it coordinates with pin, locates for circumference; Front end is demarcated inside flange installed surface front end positioning boss, ensures the registration in the geometry axle center of boss and Change-over frame; Both sides, test block mounting flange face are provided with lifting threaded hole, for installing lifting bolt.
Must ensure after described Change-over frame machines that flange installed surface is demarcated in rear end, flange installed surface is demarcated in front end, the axle center in test block mounting flange face has enough registrations, between installed surface, enough depth of parallelisms will be ensured; The advantage of this Change-over frame is the feasibility greatly improving test block installation, easy and simple to handle, accurate positioning.
Accompanying drawing explanation
Fig. 1 is Change-over frame structure front schematic view.
Fig. 2 is Change-over frame structured rear surface schematic diagram.
In figure: 1 Change-over frame main body; Flange installed surface is demarcated in a rear end; Flange installed surface is demarcated in b front end; C test block mounting flange face; D rear end positioning boss; E, e' rear end pin-and-hole; F, f ' location and installation hole; G front end positioning boss, h, h ' front end pin-and-hole; I, i' lift threaded hole.
Embodiment
Concrete installation method of the present invention is described in detail by reference to the accompanying drawings: as shown in Figure 1 with technical scheme, front end is demarcated flange and be installed on front end demarcation flange installed surface b, pin is inserted front end pin-and-hole h, h during installation ' location, ensure after bolt tightening that pin can from front end pin-and-hole h, h ' to extract smoothly.Change-over frame is installed on the mounting flange face of engine, is docked by test block mounting flange face c.', bolt is through all the other holes on flange face and tighten, and is then extracted by pin with bolt through location and installation hole f, f ' has tightened docking of engine and Change-over frame first pin to be inserted location and installation hole f, f during installation.Bolt will be lifted and screw in lifting threaded hole i, i ', Change-over frame is together sling together with engine.By the assembly horizontal after slinging, rear end is demarcated flange installed surface a and demarcate flange with the rear end be arranged on proving installation in advance and fit, pin is inserted rear end pin-and-hole e, e', assembly is fixed on proving installation by bolt of screwing on.Finally need to ensure that pin can be extracted smoothly from rear end pin-and-hole e, e', illustrate and accurate positioning is installed, can test.
Although the present invention to invention has been detailed description, not limits the present invention with above-described embodiment with above-mentioned preferred embodiment.Those skilled in the art should recognize when the technical characteristic do not departed from given by the present invention and scope, the increase done technology, with the replacement of some same contents of this area, all should belong to protection scope of the present invention.
Claims (1)
1. a thrust vectoring proving installation Change-over frame structure, is characterized in that, this thrust vectoring proving installation Change-over frame main structure body is for being provided with reinforcement cylinder mode, and two ends are for demarcating flange installed surface; Flange installed surface is demarcated through fine grinding process in rear end, and its inner circle side is provided with rear end positioning boss, ensures the registration in the axle center of rear end positioning boss and the geometry axle center of Change-over frame structure, is convenient to install location; Demarcate flange and be provided with pin-and-hole, ensure the circumferential precision of installing; Test block mounting flange face is positioned at Change-over frame front end, and for installation testing part, the location and installation hole on it coordinates with pin, locates for circumference; Front end is demarcated inside flange installed surface front end positioning boss, ensures the registration in the geometry axle center of boss and Change-over frame; Both sides, test block mounting flange face are provided with lifting threaded hole, for installing lifting bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412450.6A CN104949839A (en) | 2015-07-13 | 2015-07-13 | Adaptor frame structure of thrust vector testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510412450.6A CN104949839A (en) | 2015-07-13 | 2015-07-13 | Adaptor frame structure of thrust vector testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104949839A true CN104949839A (en) | 2015-09-30 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510412450.6A Pending CN104949839A (en) | 2015-07-13 | 2015-07-13 | Adaptor frame structure of thrust vector testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104949839A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525438A (en) * | 2016-11-03 | 2017-03-22 | 北京航天试验技术研究所 | Planar annular heavy load force bearing device for liquid rocket power system test |
| CN107421684A (en) * | 2017-07-28 | 2017-12-01 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107607293A (en) * | 2017-08-28 | 2018-01-19 | 湖北三江航天万峰科技发展有限公司 | A kind of connection component for optical seeker dynamic performance and testing |
| CN107806950A (en) * | 2017-10-24 | 2018-03-16 | 大连理工大学 | A kind of high thrust vector vertical device for testing structure |
| CN108181046A (en) * | 2017-12-21 | 2018-06-19 | 大连理工大学 | A kind of controllable force source generating device for thrust vector measuring system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56132540A (en) * | 1980-03-22 | 1981-10-16 | Toyota Motor Corp | Power transmission mechanism in testing apparatus for internal combustion engine |
| CN1632368A (en) * | 2004-12-28 | 2005-06-29 | 沈阳工业大学 | Connector of online detectors for oil gas pipelines |
| CN102280963A (en) * | 2011-08-31 | 2011-12-14 | 重庆长安汽车股份有限公司 | Driving motor of pure electric automobile |
-
2015
- 2015-07-13 CN CN201510412450.6A patent/CN104949839A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56132540A (en) * | 1980-03-22 | 1981-10-16 | Toyota Motor Corp | Power transmission mechanism in testing apparatus for internal combustion engine |
| CN1632368A (en) * | 2004-12-28 | 2005-06-29 | 沈阳工业大学 | Connector of online detectors for oil gas pipelines |
| CN102280963A (en) * | 2011-08-31 | 2011-12-14 | 重庆长安汽车股份有限公司 | Driving motor of pure electric automobile |
Non-Patent Citations (1)
| Title |
|---|
| 邢勤: "姿控火箭发动机脉动推力测试系统的研制", 《中国优秀硕士学位论文全文数据库·工程科技Ⅱ辑》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106525438A (en) * | 2016-11-03 | 2017-03-22 | 北京航天试验技术研究所 | Planar annular heavy load force bearing device for liquid rocket power system test |
| CN107421684A (en) * | 2017-07-28 | 2017-12-01 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107421684B (en) * | 2017-07-28 | 2019-06-07 | 大连理工大学 | Multidimensional Composite Nozzle device unit thrust calculation method |
| CN107607293A (en) * | 2017-08-28 | 2018-01-19 | 湖北三江航天万峰科技发展有限公司 | A kind of connection component for optical seeker dynamic performance and testing |
| CN107806950A (en) * | 2017-10-24 | 2018-03-16 | 大连理工大学 | A kind of high thrust vector vertical device for testing structure |
| CN108181046A (en) * | 2017-12-21 | 2018-06-19 | 大连理工大学 | A kind of controllable force source generating device for thrust vector measuring system |
| CN108181046B (en) * | 2017-12-21 | 2019-10-29 | 大连理工大学 | A kind of controllable force source generating device for thrust vector measuring system |
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Application publication date: 20150930 |