CN105644804B - A kind of complete aircraft structural test constrained system - Google Patents
A kind of complete aircraft structural test constrained system Download PDFInfo
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- CN105644804B CN105644804B CN201410728114.8A CN201410728114A CN105644804B CN 105644804 B CN105644804 B CN 105644804B CN 201410728114 A CN201410728114 A CN 201410728114A CN 105644804 B CN105644804 B CN 105644804B
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- constraint
- restraint device
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- undercarriage
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Abstract
The invention provides a kind of complete aircraft structural test constrained system, it is characterized in that, including restained beam (2), top connection equipment (3), lever (4), upwards upward restraint device (5), constraint sensor (6), downwards downward restraint device (7), constraint sensor (8) and ground fixing equipment (9) are supported, restained beam (2) above connects equipment (3) with supporting lever (4) hanging to be connected by top；Lever (4) one end is supported to be connected by the upward restraint device (5) of adjustable stroke with ground fixing equipment (9), the other end is connected by constraining force snesor (6) upwards with undercarriage vacation wheel (1) upper end, forms vertical upward constraint；The downward restraint device (7) that undercarriage vacation wheel (1) lower end passes sequentially through constraint force snesor (8) and adjustable stroke downwards is connected with ground fixing equipment (9), forms vertical downward constraint.
Description
Technical field
The invention belongs to airplane ground strength test technology, it is related to a kind of complete aircraft structural test constrained system.
Background technology
In complete aircraft structural static/fatigue test, typically by nose-gear, left and right main starting falls frame realization and hung down
Xiang Sandian is constrained, while supplementing two sidewise restraints and a course constraint or two courses of a sidewise restraint at undercarriage
Constraint, reaches the requirement of full machine static determinacy constraint.Wherein, the vertical constraint of undercarriage lifts vacation typically by column-crowbar device
Take turns and realized the false mode for taking turns ground connection using connector, such as Fig. 1.
In process of the test, undercarriage is deformed by that can produce lateral or course by dynamic loading, corresponding to produce lateral or boat
To additional constraint.For undercarriage and the larger aircraft of fuselage bonding pad rigidity, undercarriage deformation very little, the shadow of additional constraint
Sound can be ignored, and Fig. 1 the way of restraint is applicable.For undercarriage and the less aircraft of fuselage bonding pad rigidity, rise
Fall frame deformation larger, if using Fig. 1 the way of restraint, due to undercarriage vacation wheel tie point and lever end tie point distance compared with
Small, additional constraint influence is obvious, and full machine is in indeterminate restrained condition, influences the accuracy of result of the test.
The content of the invention
Goal of the invention
It is an object of the invention to provide a kind of complete aircraft structural static/vertical constrained system of fatigue test, for rising
Fall frame and the less aircraft of fuselage bonding pad rigidity, effectively reduce the influence of additional constraint, it is ensured that the accuracy of result of the test.
Inventive technique solution
The present invention is achieved through the following technical solutions：A kind of complete aircraft structural test constrained system, it is characterised in that
Including restained beam (2), top connection equipment (3), support lever (4), upward restraint device (5), upwards constraint sensor (6),
Downward restraint device (7), downwards constraint sensor (8) and ground fixing equipment (9).
Restained beam (2) above connects equipment (3) with supporting lever (4) hanging to be connected by top, supports lever
(4) one end is connected by the upward restraint device (5) of adjustable stroke with ground fixing equipment (9), and the other end is by upwards about
Beam force sensor (6) is connected with undercarriage vacation wheel (1) upper end, forms vertical upward constraint；Undercarriage vacation wheel (1) lower end leads to successively
The downward restraint device (7) for crossing constraint force snesor (8) and adjustable stroke downwards is connected with ground fixing equipment (9), is formed
Vertical downward constraint.
Further, top connection equipment (3) passes through peace by the turnbuckle (3-1) of upper end and the arm-tie (3-1) of lower end
Fill hole and bolt connection composition.
Have the advantage that compared with prior art or good effect
A) equipment (3) is connected by restained beam (2), top and supports lever (4) to generate longer constraint distance, effectively
Reduce the influence of additional constraint；
B) equipment (3), upward restraint device (5) and the conveniently adjusted constraint of downward restraint device (7) are connected by top
System altitude and aspect；
C) simple in construction, easy for installation, saving space；
D) production of the special equipments such as column, crowbar is avoided, experimentation cost is saved.
Brief description of the drawings
The conventional vertical the way of restraint schematic diagram of Fig. 1 undercarriages；
The vertical constrained system schematic diagram of Fig. 2 undercarriages.
Embodiment
Refering to accompanying drawing 1 to 2, complete aircraft structural test constrained system of the invention, it is characterised in that including restained beam
2nd, top connection equipment 3, support lever 4, upward restraint device 5, upwards constraint sensor 6, downward restraint device 7, downwards about
Beam sensor 8 and ground fixing equipment 9.
When the constrained system of aircraft structure test of the present invention is installed, restained beam 2 above connects equipment 3 by top
With supporting lever 4 to be connected, fulcrum is provided for the vertical constraint of undercarriage；Support the one end of lever 4 by adjustable stroke upwards about
Beam device 5 is connected with ground fixing equipment 9, and the other end is connected by constraining force snesor 6 upwards with 1 upper end of undercarriage vacation wheel,
Form vertical upward constraint；Undercarriage vacation wheel 1 lower end pass sequentially through downwards constraint force snesor 8 and adjustable stroke downwards about
Beam device 7 is connected with ground fixing equipment 9, forms vertical downward constraint.
Top connection equipment 3 passes through mounting hole and bolt connection group by the turnbuckle 3-1 of upper end and the arm-tie 3-1 of lower end
Into.
Constrained system of the present invention makes undercarriage vacation wheel about 1 to pull-shaped into differential soft-constraint；In the middle of connection equipment
Upward constraint sensor 6, downwards constraint sensor 8 in real time monitoring force feedback, for experiment provides constrain feedback data.
The present invention connects the company of the adjustable stroke in equipment 3, upward restraint device 5, downward restraint device 7 by top
Connect the constraint height of equipment adjustment constrained system and the posture of aircraft.
The present invention applies pretightning force by the differential soft-constraint of undercarriage vacation wheel about 1, to ensure the reliability of constrained system.
Claims (2)
1. a kind of complete aircraft structural test constrained system, it is characterised in that including restained beam (2), top connection equipment
(3) lever (4), upward restraint device (5), are supported, constraint sensor (6), downward restraint device (7), constraint downwards are passed upwards
Sensor (8) and ground fixing equipment (9),
Restained beam (2) above connects equipment (3) with supporting lever (4) hanging to be connected by top；Support lever (4) one
End is connected by the upward restraint device (5) of adjustable stroke with ground fixing equipment (9), and the other end is passed by upward restraining force
Sensor (6) is connected with undercarriage vacation wheel (1) upper end, forms vertical upward constraint；Undercarriage vacation wheel (1) lower end is passed sequentially through downwards
Constraint force snesor (8) and the downward restraint device (7) of adjustable stroke are connected with ground fixing equipment (9), formation it is vertical to
Lower constraint.
2. complete aircraft structural test constrained system according to claim 1, it is characterised in that top connects equipment
(3) it is made up of the turnbuckle (3-1) of upper end and the arm-tie (3-2) of lower end mounting hole and bolt connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410728114.8A CN105644804B (en) | 2014-12-03 | 2014-12-03 | A kind of complete aircraft structural test constrained system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410728114.8A CN105644804B (en) | 2014-12-03 | 2014-12-03 | A kind of complete aircraft structural test constrained system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105644804A CN105644804A (en) | 2016-06-08 |
| CN105644804B true CN105644804B (en) | 2017-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410728114.8A Active CN105644804B (en) | 2014-12-03 | 2014-12-03 | A kind of complete aircraft structural test constrained system |
Country Status (1)
| Country | Link |
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| CN (1) | CN105644804B (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109324627B (en) * | 2018-09-07 | 2021-08-17 | 中国飞机强度研究所 | Attitude control method in full-mechanical static test |
| CN110104207B (en) * | 2019-05-09 | 2022-11-01 | 中国飞机强度研究所 | Differential loading method and system |
| CN110108544A (en) * | 2019-05-09 | 2019-08-09 | 中国飞机强度研究所 | Radial lever load system space initial position determines method |
| CN111409851B (en) * | 2020-04-09 | 2023-06-02 | 中国飞机强度研究所 | Vertical restraint and protection device of aircraft |
| CN111409856B (en) * | 2020-04-17 | 2023-03-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test restraint system |
| CN111452994B (en) * | 2020-04-22 | 2023-03-24 | 中国飞机强度研究所 | Aircraft nose landing gear supporting device |
| CN111572813B (en) * | 2020-05-26 | 2023-06-23 | 中国飞机强度研究所 | Upward loading device for airplane |
| CN111547265B (en) * | 2020-05-26 | 2023-06-23 | 中国飞机强度研究所 | Course restraint device for right main landing gear of airplane |
| CN112242053B (en) * | 2020-10-16 | 2022-06-28 | 中国飞机强度研究所 | Multi-type test data optimized transmission system and method |
| CN113176143B (en) * | 2021-03-30 | 2023-10-24 | 中国飞机强度研究所 | Full-size aircraft structural test double round restraint system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2559670B2 (en) * | 1994-03-03 | 1996-12-04 | 川崎重工業株式会社 | Sliding work floor |
| CN102991727B (en) * | 2012-12-10 | 2015-08-26 | 中国飞机强度研究所 | A kind of constrained system of aircraft structure test |
| CN103625653B (en) * | 2013-12-04 | 2016-06-01 | 中国飞机强度研究所 | A kind of angle constrained procedure for full machine fatigue test |
| CN104044752B (en) * | 2014-06-24 | 2016-08-17 | 中国飞机强度研究所 | The differential constrained procedure of a kind of test |
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2014
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| CN105644804A (en) | 2016-06-08 |
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