CN209023161U - A kind of aircraft slow test nose-gear loaded member - Google Patents
A kind of aircraft slow test nose-gear loaded member Download PDFInfo
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- CN209023161U CN209023161U CN201821559971.XU CN201821559971U CN209023161U CN 209023161 U CN209023161 U CN 209023161U CN 201821559971 U CN201821559971 U CN 201821559971U CN 209023161 U CN209023161 U CN 209023161U
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- side plate
- load
- loaded member
- nose
- slow test
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Abstract
The utility model is to apply simulating piece for implementing nose-gear load in a kind of aircraft slow test, and in particular to a kind of aircraft slow test nose-gear loaded member can simultaneously serve as the gripping clamping apparatus of flight load situation slow test.In the full machine slow test of aircraft, full machine is supported by main landing gear bogusware and nose-gear loaded member static determinacy, and nose-gear loaded member is used as gripping clamping apparatus.The aircraft slow test nose-gear loaded member of the utility model, generally frame structure, the frame structure includes opposite side plate, side plate itself is that lateral load applies connector, there is connecting plate, undercarriage damper leg attachment base and wheel shaft connecting flange between side plate, in the lower end of side plate there is vertical load to apply connector, in the upper end of side plate there is course load to apply connector, also with the connecting hole of the wheel shaft connecting flange on side plate.Low with manufacturing cost, installation and load such as are easy to implement at the characteristics.
Description
Technical field
The utility model is to apply simulating piece for implementing nose-gear load in a kind of aircraft slow test, and in particular to
A kind of aircraft slow test nose-gear loaded member, can simultaneously serve as the gripping clamping apparatus of flight load situation slow test.
Background technique
In the full machine slow test of aircraft, for landing load situation, rises and carry before needing to apply by nose-gear loaded member
Lotus；For flight load situation, apply full machine trim load, full machine passes through main landing gear bogusware and nose-gear loaded member static determinacy
It supports, nose-gear loaded member is used as gripping clamping apparatus.
Summary of the invention
The utility model provide it is a kind of convenient for applying nose-gear load, as test when flight load situation slow test
The nose-gear loaded member of support.
A kind of aircraft slow test nose-gear loaded member, the loaded member generally frame structure, the frame structure include
Opposite side plate, side plate itself are that lateral load applies connector, have connecting plate, undercarriage damper leg attachment base between side plate
And wheel shaft connecting flange, in the lower end of side plate there is vertical load to apply connector, applies in the upper end of side plate with course load
Connector, also with the connecting hole of the wheel shaft connecting flange on side plate.
The side plate is approximately " L " type.
There is the link slot of vertical direction on the side plate.
The vertical load applies the connecting plate that connector is horizontal direction, there is several connecting holes on it.
The course load applies the connecting plate that connector is vertical direction, there is the link slot of vertical direction on it.
The wheel shaft connecting flange is cylindrical structure, across between the side plates.
This nose-gear loaded member upper design and undercarriage damper leg, wheel shaft jointing, are used for and nose-gear
Connection.In course, lateral and vertical devise course, lateral load connector and Plumb load connector.Course load connector is used for
Apply course load, the design of slot can apply the course load of different height position；Lateral load connector is lateral for applying
Load, the design of slot can apply the lateral load of different height position；Plumb load connector is for applying vertical load.Currently
When undercarriage loaded member is as test gripping clamping apparatus, it is connect by bottom-loaded connector with test-bed.
The utility model has the advantages that this nose-gear loaded member has manufacturing cost low, peace by multiple slow test using verifying
Dress and load such as are easy to implement at the characteristics.
Detailed description of the invention
Fig. 1 is the general assembly drawing of nose-gear loaded member.
Specific embodiment
The utility model is described in further detail with specific embodiment with reference to the accompanying drawing:
A kind of aircraft slow test nose-gear loaded member, the loaded member generally frame structure, the frame structure include
Opposite side plate 1, side plate 1 itself are that lateral load applies connector, and there is connecting plate, undercarriage damper leg to connect between side plate 1
Joint chair 2 and wheel shaft connecting flange 6, in the lower end of side plate 1 there is vertical load to apply connector 4, have course in the upper end of side plate 1
Load applies connector 5, also with the connecting hole 3 of the wheel shaft connecting flange 6 on side plate 1.
The side plate 1 is approximately " L " type.There is the link slot of vertical direction on the side plate 1.The vertical load application connects
First 4 be the connecting plate of horizontal direction, there is several connecting holes on it.The course load applies the company that connector 5 is vertical direction
Fishplate bar has the link slot of vertical direction on it.The wheel shaft connecting flange 6 is cylindrical structure, across between side plate 1.
By upper connection and undercarriage damper leg, wheel axis connection, for being connect with nose-gear.Course load applies
For connector 5 for applying undercarriage course load, the design of link slot can apply the course load of different height position；Side plate 1
It can be used in applying lateral load, the design of link slot can apply the lateral load of different height position；Vertical load applies
Connector 4 is for applying vertical load.When nose-gear loaded member is as test gripping clamping apparatus, connector is applied by vertical load
4 connect with test-bed.
Claims (6)
1. a kind of aircraft slow test nose-gear loaded member, it is characterised in that: the loaded member generally frame structure, the frame
Structure includes opposite side plate (1), and side plate (1) itself is that lateral load applies connector, has connecting plate between side plate (1), rises
Frame damper leg attachment base (2) and wheel shaft connecting flange (6) are fallen, in the lower end of side plate (1) there is vertical load to apply connector
(4), in the upper end of side plate (1) there is course load to apply connector (5), also there is the wheel shaft connecting flange on side plate (1)
(6) connecting hole (3).
2. aircraft slow test nose-gear loaded member according to claim 1, it is characterised in that: the side plate (1) is close
It is seemingly " L " type.
3. aircraft slow test nose-gear loaded member according to claim 2, it is characterised in that: on the side plate (1)
There is the link slot of vertical direction.
4. aircraft slow test nose-gear loaded member according to claim 3, it is characterised in that: the vertical load is applied
Adjunction head (4) is the connecting plate of horizontal direction, there is several connecting holes on it.
5. aircraft slow test nose-gear loaded member according to claim 4, it is characterised in that: the course load is applied
Adjunction head (5) is the connecting plate of vertical direction, there is the link slot of vertical direction on it.
6. aircraft slow test nose-gear loaded member according to claim 5, it is characterised in that: the wheel shaft connection method
Blue (6) are cylindrical structure, across between side plate (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821559971.XU CN209023161U (en) | 2018-09-25 | 2018-09-25 | A kind of aircraft slow test nose-gear loaded member |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821559971.XU CN209023161U (en) | 2018-09-25 | 2018-09-25 | A kind of aircraft slow test nose-gear loaded member |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209023161U true CN209023161U (en) | 2019-06-25 |
Family
ID=66904012
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821559971.XU Active CN209023161U (en) | 2018-09-25 | 2018-09-25 | A kind of aircraft slow test nose-gear loaded member |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209023161U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595755A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Main landing gear loading test device with single wheel and inclined angle |
| CN110641733A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Loading mechanism forming fixed angle with rotating surface |
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
| CN113800005A (en) * | 2021-11-10 | 2021-12-17 | 中航飞机起落架有限责任公司 | Emergency breaking test bed and test method for main landing gear of airplane |
-
2018
- 2018-09-25 CN CN201821559971.XU patent/CN209023161U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595755A (en) * | 2019-09-29 | 2019-12-20 | 中国直升机设计研究所 | Main landing gear loading test device with single wheel and inclined angle |
| CN110641733A (en) * | 2019-09-29 | 2020-01-03 | 中国直升机设计研究所 | Loading mechanism forming fixed angle with rotating surface |
| CN110815078A (en) * | 2019-11-14 | 2020-02-21 | 昌河飞机工业（集团）有限责任公司 | Undercarriage strut test clamping device and method |
| CN111409853A (en) * | 2020-04-12 | 2020-07-14 | 中国飞机强度研究所 | Structure is applyed to undercarriage intensity test tire ground point load |
| CN113800005A (en) * | 2021-11-10 | 2021-12-17 | 中航飞机起落架有限责任公司 | Emergency breaking test bed and test method for main landing gear of airplane |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |