CN202987530U - Aircraft turning testing device - Google Patents
Aircraft turning testing device Download PDFInfo
- Publication number
- CN202987530U CN202987530U CN2012206830816U CN201220683081U CN202987530U CN 202987530 U CN202987530 U CN 202987530U CN 2012206830816 U CN2012206830816 U CN 2012206830816U CN 201220683081 U CN201220683081 U CN 201220683081U CN 202987530 U CN202987530 U CN 202987530U
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- aircraft
- overturning
- test platform
- hinged
- pressurized strut
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Abstract
The utility model discloses an aircraft turning testing device which comprises a testing platform and a support for supporting the testing platform, an aircraft hinging supporting connector used for being hinged with the aircraft nose is arranged at the front end of the upper surface of the testing platform; the turned aircraft nose is hinged with the aircraft hinging supporting connector; upright columns are arranged on the two sides of the testing platform; a pulley in contact with an aircraft body, an inertial load loading mechanism and a friction force loading mechanism are arranged on each upright column. The device really simulates the turning gesture of the aircraft, and ensures the accurate squeezing load of the contact between the turned aircraft and the ground.
Description
Technical field
The utility model relates to the Flight Vehicle Design field, specifically, discloses a kind of aircraft overturning experimental set-up.
Background technology
According to the requirement of CCAR-23 section of China Administration of Civil Aviation, during the aircraft emergency landing, if can not guarantee that aircraft overturning can not occur when emergency landing, structure must be designed to protect the occupant when the complete overturning of aircraft.If inexperience shows structure design and can protect the occupant when the complete overturning of aircraft, must be by the accordance of its structure of overturning verification experimental verification, present domestic this type of test of not yet carrying out.
Fig. 1 shows suffered load condition after the aircraft overturning, in figure, to the right arrow represents the trend that slides after the aircraft overturning, after overturning, Aircraft Main will bear downward inertia loading PW and frictional ground force Pf, mainly has following technical barrier by its real bearing state of overturning test simulation:
1. how to simulate the overturning attitude;
2. how to apply downward inertia loading and frictional ground force, the frictional ground force (CCAR-23 regulation friction coefficient is 0.5) of especially simulation regulation friction coefficient;
3. fastening aircraft and do not increase again superfluous constraint how.
The utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art, the needs that adapt to reality, a kind of aircraft overturning experimental set-up is provided, be intended to real simulation overturning attitude as far as possible, and apply according to the rules downward inertia loading and frictional ground force, can be good at simultaneously fastening aircraft and do not increase superfluous constraint.
In order to realize the purpose of this utility model, the technical solution adopted in the utility model is:
A kind of aircraft overturning experimental set-up, comprise test platform and the support that is used for supporting test platform, the front end of described test platform upper surface is provided with for adding hinged joint with the hinged machine of plane nose, it is hinged that plane nose after overturning and described machine add hinged joint, the both sides of described test platform are provided with column, described column is provided with the pulley that contacts with airframe, also is provided with the inertia loading load maintainer, and the friction force load maintainer.
In this device, the side of described test platform is provided with altogether four root posts and is divided into both sides.
In this device, described inertia loading load maintainer comprises the vertical cable wire that is connected on airframe, also comprises lever and vertically loads pressurized strut, and described vertical cable wire applies pulling force by vertical loading pressurized strut.
In this device, described friction force load maintainer comprises the horizontal cable that is connected in passenger cabin earth point on airframe, comprises that also level loads pressurized strut, and described horizontal cable loads pressurized strut by level and applies pulling force.
The beneficial effects of the utility model are:
1. domestic initiation is tested after with the complete overturning of aircraft, simulated aircraft overturning attitude so really, and guaranteed after the aircraft overturning accuracy with ground contact point extruding stand under load;
2. add hinged joint by machine plane nose is hinged on test platform, can prevent effectively that aircraft from sliding and not increasing superfluous constraint; By column being set near aircraft, can prevent the aircraft side on oscillation, and contact with aircraft by pulley, can prevent extra frrction load; Initiatively apply by steel cable stretching force the accuracy that friction force can guarantee load at the passenger cabin earth point, solve and accurately to simulate the problem of friction coefficient by the passive generation friction force of relative sliding.
Description of drawings
Fig. 1 is suffered load condition after the aircraft overturning.
Fig. 2 is use principle schematic diagram of the present utility model.
The specific embodiment
Below in conjunction with drawings and Examples, the utility model is further illustrated:
Embodiment: referring to Fig. 1, Fig. 2.
Fig. 1 shows suffered load condition after the aircraft overturning, and in figure, G is the center of gravity of airplane, P
w-downward inertia loading; P
f-passenger cabin earth point friction force; In figure, the aircraft horizontal datum be used for to indicate the horizontal surface of aircraft, will be with other position of horizontal datum demarcation for referencial use during test, and such as stress intensity point, displacement measurement point position etc.In figure, direction shown in arrow is the line of travel after the aircraft overturning.
Aircraft overturning experimental set-up of the present utility model has been shown in Fig. 2.
A kind of aircraft overturning experimental set-up, comprise test platform 2 and the support 8 that is used for supporting test platform 2, the front end of described test platform 2 upper surfaces is provided with for adding hinged joint 9 with the hinged machine of aircraft 1 head, it is hinged that aircraft 1 head after overturning and described machine add hinged joint 9, the both sides of described test platform 2 are provided with column 6, described column 6 is provided with the pulley 7 that contacts with aircraft 1 fuselage, also is provided with the inertia loading load maintainer, and the friction force load maintainer.
Because the fuselage of aircraft 1 has downward deformation tendency, if plane contact between column 6 and fuselage, having force of sliding friction inhibition fuselage is out of shape downwards, artificial increase extra frrction load, be not inconsistent with time of day, and adopt the pulley contact, generation be friction of rolling, but friction force is very little, can ignore.
As preferred embodiment a kind of, in this device, the side of described test platform 2 is provided with altogether four root posts 6 and is divided into both sides, and every limit arranges two root posts, is conducive to the loaded load of relative equilibrium.
In this device, described inertia loading load maintainer comprises the vertical cable wire 5 that is connected on aircraft 1 fuselage, also comprises lever 4 and vertically loads pressurized strut 3, and described vertical cable wire 5 applies pulling force by vertical loading pressurized strut 3.
In this device, described friction force load maintainer comprises the horizontal cable 11 that is connected in passenger cabin earth point on aircraft 1 fuselage, comprises that also level loads pressurized strut 10, and described horizontal cable 11 loads pressurized strut 10 by level and applies pulling force.
The aircraft overturning test method that adopts experimental installation of the present utility model to carry out comprises the steps:
A., a test platform 2 is set, and fitting machine adds hinged joint 9 on test platform 2, is used for hinged with aircraft 1 head;
B. will be placed on test platform 2 after aircraft 1 overturning, and it is hinged that the machine on aircraft 1 head and test platform 2 is added hinged joint 9;
C. the airframe both sides on test platform 2 arrange column 6, and on column 6, pulley 7 are installed, and pulley 7 installs with airframe and contacts;
D., inertia loading load maintainer and friction force load maintainer are set.
Whether satisfy the requirement of seaworthiness clause according to take off data analysis after test, if the test results that adopts this testing program to obtain satisfies the requirement of seaworthiness test criterion, this test just can be passed through seaworthiness.
Claims (4)
1. aircraft overturning experimental set-up, it is characterized in that: comprise test platform and the support that is used for supporting test platform, the front end of described test platform upper surface is provided with for adding hinged joint with the hinged machine of plane nose, it is hinged that plane nose after overturning and described machine add hinged joint, the both sides of described test platform are provided with column, described column is provided with the pulley that contacts with airframe, also is provided with the inertia loading load maintainer, and the friction force load maintainer.
2. aircraft overturning experimental set-up according to claim 1, it is characterized in that: the side of described test platform is provided with altogether four root posts and is divided into both sides.
3. aircraft overturning experimental set-up according to claim 1, it is characterized in that: described inertia loading load maintainer comprises the vertical cable wire that is connected on airframe, also comprise lever and vertically load pressurized strut, described vertical cable wire applies pulling force by vertical loading pressurized strut.
4. aircraft overturning experimental set-up according to claim 1, it is characterized in that: described friction force load maintainer comprises the horizontal cable that is connected in passenger cabin earth point on airframe, comprise that also level loads pressurized strut, described horizontal cable loads pressurized strut by level and applies pulling force.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012206830816U CN202987530U (en) | 2012-12-12 | 2012-12-12 | Aircraft turning testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012206830816U CN202987530U (en) | 2012-12-12 | 2012-12-12 | Aircraft turning testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202987530U true CN202987530U (en) | 2013-06-12 |
Family
ID=48558734
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012206830816U Withdrawn - After Issue CN202987530U (en) | 2012-12-12 | 2012-12-12 | Aircraft turning testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202987530U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103029849A (en) * | 2012-12-12 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Airplane overturn testing device and airplane overturn testing method |
| CN109407684A (en) * | 2017-08-18 | 2019-03-01 | 昊翔电能运动科技(昆山)有限公司 | Rotor wing unmanned aerial vehicle attitude control method and system |
-
2012
- 2012-12-12 CN CN2012206830816U patent/CN202987530U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103029849A (en) * | 2012-12-12 | 2013-04-10 | 江西洪都航空工业集团有限责任公司 | Airplane overturn testing device and airplane overturn testing method |
| CN109407684A (en) * | 2017-08-18 | 2019-03-01 | 昊翔电能运动科技(昆山)有限公司 | Rotor wing unmanned aerial vehicle attitude control method and system |
| CN109407684B (en) * | 2017-08-18 | 2022-08-19 | 昊翔电能运动科技(昆山)有限公司 | Rotor unmanned aerial vehicle attitude control method and system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20130612 Effective date of abandoning: 20141210 |
|
| RGAV | Abandon patent right to avoid regrant |