CN211543940U - Aircraft fuel system test bench - Google Patents
Aircraft fuel system test bench Download PDFInfo
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- CN211543940U CN211543940U CN201922394915.6U CN201922394915U CN211543940U CN 211543940 U CN211543940 U CN 211543940U CN 201922394915 U CN201922394915 U CN 201922394915U CN 211543940 U CN211543940 U CN 211543940U
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- actuating cylinders
- mounting platform
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- tank mounting
- upright post
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Abstract
The invention belongs to the technical field of aviation, and relates to an aircraft fuel system test bed which comprises an oil tank mounting platform, a foundation, a support structure and a hydraulic drive system, wherein the support structure comprises a main upright post, two pitching actuating cylinders and two rolling actuating cylinders, the test bed frame structure adopts a five-point support and four-point drive mode, the main upright post is a main bearing structure, the four actuating cylinders are driving elements and auxiliary bearing structures, and a pitching/rolling rotating shaft is a rack rotating shaft. The test bed has wide structure gravity center range, stable structure, high safety, simultaneous rotation of pitch and roll, 25T rack load, single-degree-of-freedom rotation range of pitch and roll of +/-40 degrees and compound rotation range of +/-15 degrees.
Description
Technical Field
The application belongs to the technical field of aviation, and relates to a design for a structural form of a ground simulation test bench of an aircraft fuel system.
Background
The aircraft fuel system test bed usually contains oil tank mounting platform, ground, bearing structure and hydraulic system, and bearing structure's upper end is connected with oil tank mounting platform through hooke's hinge, and bearing structure's lower extreme articulates on the ground, and current bearing structure includes a main column, a roll driving cylinder and a every single move driving cylinder, adopts three point support, two point drive's structural style, and this kind of structural style focus scope is little, and the atress is unreasonable, and rack safety and stability is not high.
Disclosure of Invention
The application aims at providing an aircraft fuel system test bench, the gravity center scope of the aircraft fuel system ground simulation test bench is enlarged, the actuating cylinder only bears pressure, and the test bench bears reasonable force.
The test bed adopts a five-point supporting and four-point driving structural form, the actuating cylinders are symmetrically arranged by taking the main upright post as the center, the main upright post is a main bearing structure, and the gravity center of the test bed is in a quadrangle formed by four actuating cylinder supporting points, so that the gravity center range of the test bed is large, the stress is reasonable, and the safety and the stability of the test bed are improved.
The aircraft fuel system test bed is characterized in that the support structure comprises a main stand column, two pitching actuating cylinders and two rolling actuating cylinders, the upper end of the main stand column is connected to the geometric center of the fuel tank mounting platform through a hook hinge, the lower end of the main stand column is vertically fixed on the foundation, the two rolling actuating cylinders are symmetrically arranged on the two sides of the main stand column in a left-right mode, the upper ends of the two rolling actuating cylinders are fixed on the long axis of the fuel tank mounting platform through a hook hinge, the two pitching actuating cylinders are symmetrically arranged on the two sides of the main stand column in a front-back mode, the upper ends of the two pitching actuating cylinders are fixed on the short axis of the fuel tank mounting platform through a hook hinge, and the lower ends of the two rolling actuating cylinders and the two pitching actuating cylinders are respectively and vertically hinged to the foundation.
The main upright post of the supporting structure and the hook joints at the upper ends of the two pitching actuating cylinders form a rolling rotating shaft of the oil tank mounting platform, the main upright post and the hook joints at the upper ends of the two pitching actuating cylinders form a pitching rotating shaft of the oil tank mounting platform, and the rolling rotating shaft and the pitching rotating shaft are perpendicular to each other and are positioned on the same plane.
When the oil tank mounting platform is at a zero angle, the planes of the roll rotating shaft and the pitching rotating shaft are parallel to the horizontal plane.
The two rolling actuating cylinders are controlled by a hydraulic system to move synchronously, and the extension directions of piston rods of the actuating cylinders are opposite.
The two pitching actuating cylinders are controlled by a hydraulic system to move synchronously, and the extension directions of piston rods of the actuating cylinders are opposite.
The lower ends of the two rolling actuating cylinders and the two pitching actuating cylinders are vertically hinged on the foundation through a single-lug double-lug rotating shaft mechanism respectively.
The beneficial effect of this application lies in: the gravity center of the oil tank mounting platform is in a quadrangle formed by the four actuating cylinder supporting points, the gravity center range of the oil tank mounting platform is large, the application range is wide, and the requirement on the gravity center of a tested object is not strict. The actuating cylinder is only stressed, the oil tank mounting platform is reasonably stressed, and the safety and the stability of the test are improved. The range of the rotation angle of the oil tank mounting platform is large, the flight state of an airplane with a large oil surface angle can be simulated, the oil tank mounting platform can rotate by +/-40 degrees in pitching and +/-40 degrees in rolling by taking the pitching shaft and the rolling shaft as axes, and the rotation of +/-15 degrees in a pitching and rolling composite angle can be realized.
The present application is described in further detail below with reference to the accompanying drawings of embodiments:
drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic diagram of the layout of the relative positions of the supporting structures.
The numbering in the figures illustrates: the device comprises an oil tank mounting platform 1, a hooke joint 2, a main upright post 3, a rolling actuator cylinder 4, a pitching actuator cylinder 5, a foundation 6 and a single-lug double-lug rotating shaft mechanism 7.
Detailed Description
Referring to the attached drawings, the aircraft fuel system test bed comprises an oil tank mounting platform 1, a foundation 6, a support structure and a hydraulic drive system, and is characterized in that the support structure comprises a main upright post 3, two pitching actuating cylinders 5 and two rolling actuating cylinders 4, the upper end of the main upright post 3 is connected to the geometric center of the oil tank mounting platform 1 through a Hooke hinge 2, the lower end of the main upright post 3 is vertically fixed on the foundation 6, the two rolling actuating cylinders 4 are symmetrically arranged on the two sides of the main upright post 3 in a left-right mode, the upper ends of the two rolling actuating cylinders 4 are fixed on the major axis line of the oil tank mounting platform 1 through the Hooke hinge 2, the two pitching actuating cylinders 5 are symmetrically arranged on the two sides of the main upright post 3 in a front-back mode, the upper ends of the two pitching actuating cylinders 5 are fixed on the minor axis line of the oil tank mounting platform 1 through the Hooke hinge 2, the lower ends of the two rolling actuating cylinders 4 and the two pitching actuating cylinders 5 are respectively and vertically hinged on the foundation, the roll ram 4 and the pitch ram 5 are each connected to a hydraulic drive system.
In implementation, the main upright post 3 and the hooke joints 2 at the upper ends of the two pitching actuating cylinders 5 of the supporting structure form a rolling rotating shaft of the oil tank mounting platform 1, the main upright post 3 and the hooke joints 2 at the upper ends of the two rolling actuating cylinders 4 form a pitching rotating shaft of the oil tank mounting platform 1, and the rolling rotating shaft and the pitching rotating shaft are perpendicular to each other and are located on the same plane. When the oil tank mounting platform 1 is at a zero angle, the planes of the roll rotating shaft and the pitching rotating shaft are parallel to the horizontal plane.
The two rolling actuating cylinders 4 are controlled by a hydraulic system to move synchronously, and the extension directions of piston rods of the actuating cylinders are opposite.
The two pitching actuating cylinders 5 are controlled by a hydraulic system to move synchronously, and the extension directions of piston rods of the actuating cylinders are opposite.
The lower ends of the two rolling actuating cylinders 4 and the two pitching actuating cylinders 5 are vertically hinged on the foundation through a single-lug double-lug rotating shaft mechanism 7 respectively.
In implementation, the oil tank mounting platform 1 is of a truss structure and is formed by welding sectional materials, the lower surface of the oil tank mounting platform is provided with a mounting surface of a Hooke hinge 2, and the oil tank mounting platform is connected with the Hooke hinge 2 through bolts. The upper end of the main upright post 3 is welded into a honeycomb structure by plates and is connected with the Hooke's hinge 2 by bolts. The upper ends of the rolling actuating cylinder 4 and the pitching actuating cylinder 5 are plate type square flanges and are fixedly connected with the Hooke hinge 2 through bolts. The lower ends of the rolling actuating cylinder 4 and the pitching actuating cylinder 5 are fixed with a foundation 6 through a single-lug double-lug rotating shaft mechanism 7, and the main upright post 3 is directly fixed on the foundation 6. Foundation 6 is in the form of a ground rail. The rolling actuator cylinders 4 are arranged in a left-right symmetrical mode with the main upright post 3 as the center, the distance is 4000mm, and the pitching actuator cylinders 5 are arranged in a front-back symmetrical mode with the main upright post 3 as the center, and the distance is 3600 mm. The rolling actuator cylinder 4 and the pitching actuator cylinder 5 are driven by hydraulic pressure to realize the rotation of the oil tank mounting platform.
When the oil tank mounting platform 1 needs to complete pitching rotation, pressure oil is introduced into the lower cavity of the pitching actuator cylinder at the front side of the main upright post 3, oil is directly returned from the lower cavity of the pitching actuator cylinder at the rear side of the main upright post 3, and pitching head-up rotation is realized. If the lower cavity of the pitching actuator cylinder at the front side of the main upright post 3 is allowed to return oil directly, the lower cavity of the pitching actuator cylinder at the rear side of the main upright post 3 is communicated with pressure oil, and pitching head-lowering rotation is realized. Similarly, if the oil tank mounting platform 1 needs to realize the rolling rotation, the lower cavity of the rolling actuator cylinder on the left side of the main upright post 3 is communicated with pressure oil, and the lower cavity of the rolling actuator cylinder on the right side of the main upright post 3 is directly returned with oil, so that the rotation of lifting the right side of the rolling is realized. If the lower cavity of the rolling actuator cylinder on the left side of the main upright post 3 is directly returned, the lower cavity of the rolling actuator cylinder on the right side of the main upright post 3 is communicated with pressure oil, so that the left side of the rolling is lifted and rotated.
Claims (6)
1. An aircraft fuel system test bed comprises an oil tank mounting platform, a foundation, a supporting structure and a hydraulic driving system, it is characterized in that the supporting structure comprises a main upright post, two pitching actuating cylinders and two rolling actuating cylinders, the upper end of the main upright post is connected with the geometric center of the oil tank mounting platform through a Hooke hinge, the lower end of the main upright post is vertically fixed on the foundation, the two rolling actuating cylinders are symmetrically arranged at the two sides of the main upright post, the upper ends of the two rolling actuating cylinders are fixed on the long axis of the oil tank mounting platform through Hooke joints, the two pitching actuating cylinders are symmetrically arranged at the two sides of the main upright post in the front-back direction, the upper ends of the two pitching actuating cylinders are fixed on a short axis of the oil tank mounting platform through Hooke hinges, the lower ends of the two rolling actuating cylinders and the lower ends of the two pitching actuating cylinders are vertically hinged on a foundation respectively, and the rolling actuating cylinders and the pitching actuating cylinders are connected with a hydraulic driving system respectively.
2. An aircraft fuel system test bed as claimed in claim 1, wherein the main column of the support structure and the hooke joints at the upper ends of the two pitch cylinders form a roll axis of the tank mounting platform, the main column and the hooke joints at the upper ends of the two roll cylinders form a pitch axis of the tank mounting platform, and the roll axis and the pitch axis are perpendicular to each other and are in the same plane.
3. An aircraft fuel system test rig according to claim 1, wherein the plane of the roll and pitch axes is parallel to the horizontal plane when the tank mounting platform is at zero degrees.
4. An aircraft fuel system test rig according to claim 1, wherein the two roll rams are controlled by a hydraulic system to move in synchronism and the ram piston rods are retracted in opposite directions.
5. An aircraft fuel system test rig according to claim 1, wherein the two pitch rams are controlled by a hydraulic system to move in synchronism and the ram piston rods are caused to extend and retract in opposite directions.
6. An aircraft fuel system test stand according to claim 1, wherein the lower ends of said two roll and pitch rams are vertically hinged to the ground by a single lug and double lug pivot mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922394915.6U CN211543940U (en) | 2019-12-26 | 2019-12-26 | Aircraft fuel system test bench |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922394915.6U CN211543940U (en) | 2019-12-26 | 2019-12-26 | Aircraft fuel system test bench |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211543940U true CN211543940U (en) | 2020-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922394915.6U Active CN211543940U (en) | 2019-12-26 | 2019-12-26 | Aircraft fuel system test bench |
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| Country | Link |
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| CN (1) | CN211543940U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581490A (en) * | 2021-07-28 | 2021-11-02 | 中国商用飞机有限责任公司 | Water counter weight system test platform and test system |
-
2019
- 2019-12-26 CN CN201922394915.6U patent/CN211543940U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581490A (en) * | 2021-07-28 | 2021-11-02 | 中国商用飞机有限责任公司 | Water counter weight system test platform and test system |
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