CN102991725A - Pole restraint device - Google Patents
Pole restraint device Download PDFInfo
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- CN102991725A CN102991725A CN2012105216376A CN201210521637A CN102991725A CN 102991725 A CN102991725 A CN 102991725A CN 2012105216376 A CN2012105216376 A CN 2012105216376A CN 201210521637 A CN201210521637 A CN 201210521637A CN 102991725 A CN102991725 A CN 102991725A
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- pressurized strut
- constraint
- screw rod
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Abstract
The invention belongs to an aircraft test piece constraint technology, and relates to a pole restraint device. The pole restraint device comprises a binaural joint, a connecting screw rod, a spiral pad, a load sensor, and a false actuating cylinder, wherein the binaural joint is fixed on a test piece constraint part and connected with the connecting screw rod in a hinge manner; the spiral pad is added to the threaded connection part between the load sensor and the false actuating cylinder, and the load sensor is connected with the control system. The pole restraint device disclosed by the invention can regulate the gesture of a testing machine by regulating the telescopic length of a connecting steel tube of the false actuating cylinder; and constraint of a 'two-force bar' structure in rigid connection under a shutdown state is still reliable and valid. Therefore, the existing testing equipment is effectively utilized, and reliable horizontal constraint is also achieved.
Description
Technical field
The invention belongs to aircraft testing part restriction technique, relate to a kind of Jackstay type restraint device.
Background technology
In complete aircraft structural static/fatigue test, the static determinacy that is constrained to of experimental engine retrains, and generally chooses three vertical constraints, and other three are constrained to horizontal restraint (comprising course constraint and sidewise restraint).Half adopts crowbar or suspension type constraint vertical the way of restraint, and horizontal restraint then adopts joint, pulley, chute and column constraint, Bidirectional differential soft-constraint or the control constraint of control pressurized strut position, position.Adopt joint, pulley, chute and column form, do not limit the aircraft vertical deviation, and retrain vector, side travel, because pulley and chute are gapped, the situation of course, sidewise restraint inefficacy can occur in test; When adopting the Bidirectional differential soft-constraint, need two to monitor passage, calculate the feedback load of this constraint by the feedback of two passages.
When obligatory point feedback load is larger, need to apply the validity that larger predetermincd tension retrains in can warranty test two soft-constraints, but for the examination at experimental engine constraint position, predetermincd tension be fict examination to drawing; When adopting position control pressurized strut as obligatory point, can not guarantee effective displacement in non-test condition (pressurized strut is without the oil pressure state) pressurized strut, at first can adjust the experimental engine attitude after the pressurization, in this process, may cause the overproof protection of other load(ing) points.
Summary of the invention
The objective of the invention is: propose in the static(al)/fatigue test of complete aircraft structure, effectively utilize existing test facility, realize the Jackstay type restraint device of failure-free horizontal restraint.
Technical scheme of the present invention is: a kind of Jackstay type restraint device, it comprises ears joint, connecting screw rod, spiral pad, load transducer, false pressurized strut, described ears joint is fixed on the test article constraint position, adopt articulated manner to be connected with connecting screw rod, spiral pad is installed on being threaded between load transducer and the false pressurized strut, and described load transducer is connected with control system.
Described false pressurized strut by joint steel pipe and the minus thread adapter substitute and the right-hand screw thread adapter substitute that are screwed onto respectively the steel pipe two ends form.
The pressurized strut base is fixed on the column, adopts articulated manner to be connected with false pressurized strut.
Technique effect of the present invention is: Jackstay type restraint device of the present invention can be adjusted the experimental engine attitude by the joint steel pipe collapsing length of adjusting false pressurized strut; and rigid connection " two power bars " structure retrains still effectively reliably when stopped status, and has following advantage:
● effectively utilize existing test facility, realized the failure-free horizontal restraint;
● processing parts only has false pressurized strut, has saved cost;
● adopt " two power bars " system of rigid connection only to take a control channel;
● screw type false pressurized strut can be regulated connecting length, changes constrained displacement, thereby adjusts the purpose of experimental engine attitude.
Description of drawings
Fig. 1 is the structural representation of Jackstay type restraint device of the present invention;
Fig. 2 is false pressurized strut structural representation,
Wherein, minus thread adapter substitute 1, ears joint 2, connecting screw rod 3, spiral pad 4, load transducer 5, false pressurized strut 6, pressurized strut base 7, column 8.
The specific embodiment
The present invention is described further below in conjunction with drawings and Examples:
As shown in Figure 1, Jackstay type restraint device of the present invention comprises ears joint 2, connecting screw rod 3, spiral pad 4, load transducer 5, false pressurized strut 6, pressurized strut base 7.Described ears joint 2 is fixed on the test article constraint position, adopts articulated manner to be connected with connecting screw rod 3, for a whole set of restraint device provides side direction (or course) degree of freedom.Spiral pad is installed on being threaded between load transducer 5 and the false pressurized strut 6, eliminates the gap that is threaded, described load transducer 5 is connected with control system, for the magnitude of load of Feedback Constrained point.Pressurized strut base 7 is fixed on the column 8, adopts articulated manner to be connected with false pressurized strut 6, and the vertical freedom degree of package unit is provided.
See also Fig. 2, it is the structural representation of false pressurized strut.Described false pressurized strut 6 by joint steel pipe and the minus thread adapter substitute 1 and the right-hand screw thread adapter substitute that are screwed onto respectively the steel pipe two ends form.By the rotary connection steel pipe, extending or shorten false pressurized strut connecting length, thus the equipment interference region is extended in constraint, can rotate adjusting length, adjust the experimental engine attitude.
During test condition, utilize pressurized strut base oscillating bearing function, form rigid connected system by joint, false pressurized strut, load transducer and column etc.Provide a direction degree of freedom by joint is hinged, by the hinged other direction degree of freedom that provides of pressurized strut base, so that this rigid connected system is " two-force-rod series system ", guaranteed the horizontal displacement (course, side travel) of constraint aircraft, and do not limit the aircraft vertical deviation, and can monitor by load transducer the feedback of obligatory point.
Can adjust the experimental engine attitude by the joint steel pipe collapsing length of adjusting false pressurized strut, and rigid connection " two power bars " structure retrains when stopped status still effectively reliable.
Claims (3)
1. Jackstay type restraint device, it is characterized in that: comprise ears joint, connecting screw rod, spiral pad, load transducer, false pressurized strut, described ears joint is fixed on the test article constraint position, adopt articulated manner to be connected with connecting screw rod, spiral pad is installed on being threaded between load transducer and the false pressurized strut, and described load transducer is connected with control system.
2. Jackstay type restraint device according to claim 1 is characterized in that: described false pressurized strut by joint steel pipe and the minus thread adapter substitute and the right-hand screw thread adapter substitute that are screwed onto respectively the steel pipe two ends form.
3. Jackstay type restraint device according to claim 2, it is characterized in that: the pressurized strut base is fixed on the column, adopts articulated manner to be connected with false pressurized strut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210521637.6A CN102991725B (en) | 2012-12-07 | 2012-12-07 | A kind of Pole restraint device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210521637.6A CN102991725B (en) | 2012-12-07 | 2012-12-07 | A kind of Pole restraint device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102991725A true CN102991725A (en) | 2013-03-27 |
| CN102991725B CN102991725B (en) | 2016-02-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210521637.6A Active CN102991725B (en) | 2012-12-07 | 2012-12-07 | A kind of Pole restraint device |
Country Status (1)
| Country | Link |
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| CN (1) | CN102991725B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625653A (en) * | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Included angle constraining method for full-scale fatigue test |
| CN103645054A (en) * | 2013-12-17 | 2014-03-19 | 北京航天益森风洞工程技术有限公司 | Force generator for hydraulically driving thrust rack |
| CN106347704A (en) * | 2016-09-06 | 2017-01-25 | 深圳电航空技术有限公司 | Flight control testing device |
| CN110789735A (en) * | 2019-12-05 | 2020-02-14 | 中国飞机强度研究所 | Force-controllable double-beam clamping device |
| CN111409851A (en) * | 2020-04-09 | 2020-07-14 | 中国飞机强度研究所 | Vertical restraint of aircraft and protection device |
| CN111409856A (en) * | 2020-04-17 | 2020-07-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test constraint system |
| CN111547265A (en) * | 2020-05-26 | 2020-08-18 | 中国飞机强度研究所 | Course restraining device for right main landing gear of airplane |
| CN113173260A (en) * | 2021-04-20 | 2021-07-27 | 中国飞机强度研究所 | Full-aircraft static support device and method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08159938A (en) * | 1994-12-07 | 1996-06-21 | Mitsubishi Heavy Ind Ltd | Load testing device |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
-
2012
- 2012-12-07 CN CN201210521637.6A patent/CN102991725B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08159938A (en) * | 1994-12-07 | 1996-06-21 | Mitsubishi Heavy Ind Ltd | Load testing device |
| CN201575950U (en) * | 2009-12-14 | 2010-09-08 | 中国飞机强度研究所 | Tension and compression pad-lever loading device |
Non-Patent Citations (1)
| Title |
|---|
| 薛彩军等: "民用飞机发动机吊挂静力试验技术研究", 《实验力学》, vol. 26, no. 6, 31 December 2011 (2011-12-31), pages 736 - 742 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625653A (en) * | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Included angle constraining method for full-scale fatigue test |
| CN103645054A (en) * | 2013-12-17 | 2014-03-19 | 北京航天益森风洞工程技术有限公司 | Force generator for hydraulically driving thrust rack |
| CN106347704A (en) * | 2016-09-06 | 2017-01-25 | 深圳电航空技术有限公司 | Flight control testing device |
| CN106347704B (en) * | 2016-09-06 | 2019-04-26 | 深圳一电航空技术有限公司 | Fly control test device |
| CN110789735A (en) * | 2019-12-05 | 2020-02-14 | 中国飞机强度研究所 | Force-controllable double-beam clamping device |
| CN111409851A (en) * | 2020-04-09 | 2020-07-14 | 中国飞机强度研究所 | Vertical restraint of aircraft and protection device |
| CN111409856A (en) * | 2020-04-17 | 2020-07-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test constraint system |
| CN111547265A (en) * | 2020-05-26 | 2020-08-18 | 中国飞机强度研究所 | Course restraining device for right main landing gear of airplane |
| CN113173260A (en) * | 2021-04-20 | 2021-07-27 | 中国飞机强度研究所 | Full-aircraft static support device and method |
| CN113173260B (en) * | 2021-04-20 | 2024-04-09 | 中国飞机强度研究所 | All-machine statically indeterminate supporting device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102991725B (en) | 2016-02-10 |
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