CN103115716A - Thrust block device of six-component test stand - Google Patents
Thrust block device of six-component test stand Download PDFInfo
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- CN103115716A CN103115716A CN2013100285919A CN201310028591A CN103115716A CN 103115716 A CN103115716 A CN 103115716A CN 2013100285919 A CN2013100285919 A CN 2013100285919A CN 201310028591 A CN201310028591 A CN 201310028591A CN 103115716 A CN103115716 A CN 103115716A
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- circular hole
- thrust block
- thrust
- top board
- block device
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Abstract
The invention discloses a thrust block device of a six-component test stand. The thrust block device comprises a top plate 1, two upright plates, rib plates 3 and a bottom plate 4. The two upright plates 2 are perpendicularly welded on the upper surface of the bottom plate 4 and are parallel to each other, the top plate 1 is placed on the two upright plates 2 and is fixedly welded, and a cavity 5 is formed by the top plate 1, the two upright plates 2 and the bottom plate 4; the corresponding rib plates 3 are welded on the outer side of each upright plate 2; a circular hole I 6, a circular hole II 7 and a circular hole III 8 are sequentially arranged on the top plate 1 along straight line directions perpendicular to the upright plates 2, and the axis of the circular hole I 6, the axis of the circular hole II 7 and the axis of the circular hole III 8 are perpendicular to the bottom plate 4; and the bottom plate 4 is in contact with a foundation completely and is fixed to the foundation, and surfaces of the top plate 1 are parallel to the foundation. The thrust block device has the advantages that the thrust block device can effectively and safely bear the total weight including the weight of a six-component testing system and the weight of a rocket engine, and brings convenience for mounting a main thrust testing hydraulic cylinder of the rocket engine.
Description
Technical field
The present invention relates to the thrust of solid propellant rocket, the vertical fields of measurement of side direction force and moment, particularly a kind of six component testing table thrust block devices.
Background technology
The thrust of rocket engine is a space vector, and it does not overlap with the geometrical axis of rocket engine.In the rocket engine course of work, its size, direction and position of action point are all constantly to change in time.Measure the important content that above-mentioned thrust eccentric or thrust vectoring are Solid Rocket Motor Ground Tests, for the performance of determining solid propellant rocket, and then develop high performance solid propellant rocket and have great importance.
Time series analysis is measured Thrust of Solid Rocket Motor vector main device over time just, and wherein thrust block will bear the gravity of rocket engine thrust, moving frame and rocket engine etc., and it is made a concerted effort more than 30T.The present thrust block device that extensively adopts is directly the cement platform mostly or is connected with ground by 4 root posts: directly adopt the cement platform to be difficult for the main thrust hydraulic jack is installed as the thrust block device, cause the demarcation difficulty of main thrust sensor and test result error larger; There is security hidden danger by 4 upright supports that are connected with ground.Therefore, be necessary the thrust block device of six component testing tables is improved.
Summary of the invention
Technical matters solved by the invention be to provide a kind of can effective and safe ground support the gross weight that comprises six minutes force test systems and rocket engine, and be convenient to install six component testing table thrust block devices of rocket engine main thrust testing hydraulic oil cylinder.
The technical solution that realizes the object of the invention is: a kind of six component testing table thrust block devices, comprise top board 1, riser 2, gusset 3, base plate 4, two risers 2 of base plate 4 upper surface vertical welding wherein, and two risers 2 are parallel to each other, top board 1 is positioned on two risers 2 and is welded and fixed, and top board 1, two risers 2 and base plate 4 form cavitys 5; The outside of every riser 2 is welded with gusset 3; On top board 1, be provided with successively circular hole I 6, circular hole II 7 and circular hole III 8 along the rectilinear direction perpendicular to riser 2.
The present invention's six component testing table thrust block devices, described base plate 4 contacts fully and fixes with ground.
The present invention's six component testing table thrust block devices, the surface of described top board 1 is parallel with ground surface.
The present invention compared with prior art, its remarkable advantage is: (1) thrust block device can bear the gross weight that comprises rocket engine thrust, moving frame and rocket engine weight safely and effectively, its base plate can significantly reduce to act on the pressure on concrete foundation, ground is not damaged; (2) space that is surrounded by top board, 2 risers and base plate is used for the main thrust hydraulic jack is installed, and reaches the purpose of installation, demarcation and the test of simplifying the main thrust sensor.
Description of drawings
Fig. 1 is the front view of the present invention's six component testing table thrust block devices.
Fig. 2 is the vertical view of the present invention's six component testing table thrust block devices.
Wherein: 1-top board, 2-riser, 3-gusset, 4-base plate, 5-space, 6-circular hole I, 7-circular hole II, 8-circular hole III
Embodiment
Below in conjunction with drawings and the specific embodiments, the present invention is described in further detail.
In conjunction with Fig. 1, Fig. 2, the present invention's six component testing table thrust block devices, comprise top board 1, riser 2, gusset 3, base plate 4, two risers 2 of base plate 4 upper surface vertical welding wherein, and two risers 2 are parallel to each other, top board 1 is positioned on two risers 2 and is welded and fixed, and top board 1, two risers 2 and base plate 4 form cavitys 5; The outside of every riser 2 is welded with gusset 3; On top board 1, be provided with successively circular hole I 6, circular hole II 7 and circular hole III 8 along the rectilinear direction perpendicular to riser 2.
The present invention's six component testing table thrust block devices, described base plate 4 contacts fully and fixes with ground.
The present invention's six component testing table thrust block devices, the surface of described top board 1 is parallel with ground surface.
The present invention is the important device of support vertical rocket engine Time series analysis test macro, describes details and the working condition of the concrete device that proposes according to the present invention in detail below in conjunction with Fig. 1.
The present invention's six component testing table thrust block devices, comprise top board 1, riser 2, gusset 3, base plate 4, it is fixing that wherein base plate 4 is placed in concrete foundation, two risers 2 of base plate 4 upper surface vertical welding, and two risers 2 are parallel to each other, top board 1 is positioned on two risers 2 and is welded and fixed, and top board 1, two risers 2 and base plate 4 surround cavity 5, and cavity 5 is in order to install the main thrust hydraulic jack; For strengthening the stability of thrust block, in the outside of cavity 5, three gussets 3 are welded respectively in the outside of every riser 2, amount to 6 gussets 3; As shown in Figure 2, in the middle of top board 1, be provided with successively circular hole I 6, circular hole II 7 and circular hole III 8 along the rectilinear direction perpendicular to riser 2, wherein circular hole I 6 and circular hole III 8 are used for penetrating of moving frame bar, and circular hole II 7 is used for installing main thrust and transmits bar.
For the top board of assurance thrust block device and the depth of parallelism on ground, at first base plate 4 is contacted fully with concrete foundation, reach the sufficiently high depth of parallelism by making top board 1 and ground surface after adjusting, then deposit concrete makes base plate 4 and ground be completely fixed.
The specific works process of the present invention's six component testing table thrust block devices is as follows: after rocket motor ignition enters the test link, engine gravity and thrust are on the moving frame bar, the moving frame bar passes circular hole I 6, circular hole III 8 is transmitted bar with main thrust and is connected, main thrust is delivered on the main thrust bar, be connected with the main thrust sensor on the main thrust bar, the other end of main thrust sensor passes circular hole II 7 and is connected on thrust block, and the large I of main thrust is recorded by the main thrust sensor thus.The power on thrust block of acting on by the larger base plate 4 of area after, the normal stress that acts on concrete foundation reduces greatly, has avoided the impaired of ground.
Facts have proved, thrust block can bear the gross weight that comprises rocket engine thrust, moving frame and rocket engine weight, and relies on 1400 * 800mm
2The rectangle base plate significantly reduce to act on pressure on concrete foundation; Surround cavity 5 by top board 1, two risers 2 and base plate 4 and be used for the main thrust hydraulic jack is installed, reach the purpose of installation, demarcation and the test of simplifying the main thrust sensor.
Claims (3)
1. component testing table thrust block device, it is characterized in that, comprise top board (1), riser (2), gusset (3), base plate (4), base plate (4) two risers of upper surface vertical welding (2) wherein, and two risers (2) are parallel to each other, top board (1) is positioned over two risers (2) and goes up and be welded and fixed, and top board (1), two risers (2) and base plate (4) form cavity (5); The outside of every riser (2) is welded with gusset (3); On top board (1), be provided with successively circular hole I (6), circular hole II (7) and circular hole III (8) along the rectilinear direction perpendicular to riser (2).
2. six component testing table thrust block devices according to claim 1, is characterized in that, described base plate (4) contacts fully and fixes with ground.
3. six component testing table thrust block devices according to claim 1 and 2, it is characterized in that: the surface of described top board (1) is parallel with ground surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100285919A CN103115716A (en) | 2013-01-25 | 2013-01-25 | Thrust block device of six-component test stand |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013100285919A CN103115716A (en) | 2013-01-25 | 2013-01-25 | Thrust block device of six-component test stand |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103115716A true CN103115716A (en) | 2013-05-22 |
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ID=48414137
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013100285919A Pending CN103115716A (en) | 2013-01-25 | 2013-01-25 | Thrust block device of six-component test stand |
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| Country | Link |
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| CN (1) | CN103115716A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3301038A (en) * | 1964-01-02 | 1967-01-31 | North American Aviation Inc | Thrust measurement calibrator |
| CN102323000A (en) * | 2011-05-30 | 2012-01-18 | 哈尔滨工业大学 | Safe force-coupling-free six-dimensional force sensor |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| 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 |
| CN102889953A (en) * | 2011-07-19 | 2013-01-23 | 马格纳斯泰尔汽车技术两合公司 | Measuring element, force sensor and measuring assembly for measuring forces |
| CN203116900U (en) * | 2013-01-25 | 2013-08-07 | 南京理工大学 | Six-component testing stand thrust pier device |
-
2013
- 2013-01-25 CN CN2013100285919A patent/CN103115716A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3301038A (en) * | 1964-01-02 | 1967-01-31 | North American Aviation Inc | Thrust measurement calibrator |
| CN102323000A (en) * | 2011-05-30 | 2012-01-18 | 哈尔滨工业大学 | Safe force-coupling-free six-dimensional force sensor |
| CN102889953A (en) * | 2011-07-19 | 2013-01-23 | 马格纳斯泰尔汽车技术两合公司 | Measuring element, force sensor and measuring assembly for measuring forces |
| CN102680238A (en) * | 2012-05-29 | 2012-09-19 | 西北工业大学 | Non-contact engine thrust testing method and device |
| 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 |
| CN203116900U (en) * | 2013-01-25 | 2013-08-07 | 南京理工大学 | Six-component testing stand thrust pier device |
Non-Patent Citations (1)
| Title |
|---|
| 张强等: "航空发动机推力直接测试技术试验与研究", 《测控技术》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| 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 |
| GB2612455A (en) * | 2020-10-04 | 2023-05-03 | Xian Aerospace Propulsion Testing Tech Research Institute | Thrust transfer apparatus for ignition test of solid rocket engine in form of rear skirt connection |
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Application publication date: 20130522 |