CN104773288A - Skid type landing gear wheel loaded signal device - Google Patents
Skid type landing gear wheel loaded signal device Download PDFInfo
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- CN104773288A CN104773288A CN201510161334.1A CN201510161334A CN104773288A CN 104773288 A CN104773288 A CN 104773288A CN 201510161334 A CN201510161334 A CN 201510161334A CN 104773288 A CN104773288 A CN 104773288A
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- micro
- switch
- landing gear
- microswitch
- gear wheel
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Abstract
The invention discloses a skid type landing gear wheel loaded signal device which is simple in structure and stable in performance. The device comprises a microswitch bracket, a microswitch, a clamping hoop, a rubber pad, a touch pad and a strippable washer, wherein the microswitch is fixed on a fuselage structure through the microswitch bracket; the strippable washer is fixed with the touch pad; the touch pad is arranged on a skid transverse beam through the clamping hoop and the rubber pad; the touch pad is arranged right below the touch point of the microswitch; when the skid transverse beam deforms, the touch point of the microswitch is in touch with the strippable washer; when the skid transverse beam does not deform, the touch point of the microswitch is at a free state. The skid type landing gear wheel loaded signal device is simple in structure; the deformation of the landing gear during landing or taking off is sensed through the microswitch, the performance is stable and later maintenance is convenient.
Description
Technical field
The present invention relates to Landing Gear Design technology, particularly relate to a kind of skid landing gear wheel load signalling apparatus.
Background technology
The wheel load signal of Aircraft landing gear system is the unique signal of interest carrying out vacant lot condition adjudgement as the most system of aircraft, must meet the safe reliability requirement that each system proposes, and therefore, carries out test analysis very necessary to the wheel load signal of Landing Gear System.
At present, the wheel load signal measurement apparatus of other forms of aircraft is measured by sensor, and sensor is arranged on alighting gear urceolus, and the target of sensor is arranged on toggle or from arm, measures.But for skid landing gear, due to the difference of alighting gear and alighting gear surrounding structure, above-mentioned wheel load signal measurement apparatus cannot directly use; And said apparatus structure is comparatively complicated, poor stability.
Summary of the invention
The technical problem to be solved in the present invention: the object of the present invention is to provide a kind of structure simple and the skid landing gear wheel load signalling apparatus for helicopter field of stable performance.
Technical scheme of the present invention: the present invention proposes a kind of skid landing gear wheel load signalling apparatus, and comprise, micro-switch support, micro-switch, clip, rubber pad, touch panel, strippable gasket, micro-switch is fixed on airframe structure by micro-switch support; Strippable gasket and touch panel are fixed together, and touch panel is arranged on sled crossbeam by clip and rubber pad; Touch panel is positioned at immediately below micro-switch contact; When sled crossbeam is not out of shape, the contact of micro-switch is in by strippable gasket triggering conditions, and when sled beam deformation, the contact of micro-switch is in free state.
Further preferably, the center of touch panel below the contact alignment of micro-switch.
Beneficial effect of the present invention: a kind of skid landing gear wheel load signalling apparatus that the present invention proposes mainly changes the contacts status of micro-switch to realize goal of the invention by the deformation of sled crossbeam, structure of the present invention is simple, stable performance and convenient later maintenance.
Accompanying drawing explanation
Fig. 1 is skid landing gear wheel load signalling apparatus isometric views of the present invention;
Fig. 2 is skid landing gear wheel load signalling apparatus fundamental diagram of the present invention;
Fig. 3 is I enlarged schematic partial view in Fig. 2.
Wherein, 1 be micro-switch support, 2 be micro-switch, 3 be clip, 4 be rubber pad, 5 be touch panel, 6 for strippable gasket.
Detailed description of the invention
Embodiment 1:
A kind of skid landing gear wheel load signalling apparatus that the present invention proposes, as shown in Figure 1, comprises, micro-switch support 1, micro-switch 2, clip 3, rubber pad 4, touch panel 5, strippable gasket 6.
First micro-switch support 1 is arranged on the airframe structure 7 directly over sled crossbeam 8 center, then micro-switch 2 is bolted on micro-switch support 1, then by cementing for strippable gasket 6 on touch panel 5, again touch panel 5 is fixed on sled crossbeam 8 by rubber pad 4 and clip 3, now should ensure that micro-switch 2 contact is aimed at strippable gasket 6 center, the thickness finally by adjustment strippable gasket 6 regulates the distance δ between micro-switch 2 contact and strippable gasket 6.
Of the present inventionly make principle as shown in Figures 2 and 3, sled crossbeam 8 is in free state (now sled crossbeam 8 is for shown in solid line in Fig. 2) after aircraft is liftoff; When after aircraft landing, sled crossbeam 8 produces distortion δ (now sled crossbeam 8 is that in Fig. 2, dotted line is shown) under the effect of fuselage gravity G, being out of shape δ by sled crossbeam 8 makes touch panel 5 drive strippable gasket 6 position to change, thus makes the triggering of micro-switch 2.That is to say, when sled crossbeam 8 is out of shape, micro-switch 2 contact is in the state of being touched.
After aircraft is liftoff, sled crossbeam 8 restores to the original state, and not triggering of micro-switch 2, is in free state.That is to say, under the non-deformation of sled crossbeam 8, micro-switch 2 contact is in free state.
Preferably, the center of touch panel 5 below the contact alignment of micro-switch 2, this kind of set-up mode can reduce other uncorrelated factor to the impact of the contact closure condition of micro-switch 2.
Skid landing gear wheel load signalling apparatus structure of the present invention is simple, by micro-switch 2 to aircraft landing or when taking off the deformation of alighting gear carry out perception, performance is more stable, and convenient later maintenance.
Claims (2)
1. a skid landing gear wheel load signalling apparatus, it is characterized in that: comprise, micro-switch support (1), micro-switch (2), clip (3), rubber pad (4), touch panel (5), strippable gasket (6), described micro-switch (2) is fixed on airframe structure by micro-switch support (1); Described strippable gasket (6) and touch panel (5) are fixed together, and described touch panel (5) is arranged on sled crossbeam by described clip (3) and rubber pad (4); Described touch panel (5) is positioned at immediately below micro-switch (2) contact;
When described sled beam deformation, the contact of described micro-switch (2) is in by strippable gasket (6) triggering conditions;
When sled crossbeam is not out of shape, the contact of described micro-switch (2) is in free state.
2. skid landing gear wheel load signalling apparatus according to claim 1, is characterized in that: the center of described touch panel (5) below the contact alignment of described micro-switch (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161334.1A CN104773288A (en) | 2015-04-07 | 2015-04-07 | Skid type landing gear wheel loaded signal device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510161334.1A CN104773288A (en) | 2015-04-07 | 2015-04-07 | Skid type landing gear wheel loaded signal device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104773288A true CN104773288A (en) | 2015-07-15 |
Family
ID=53615128
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510161334.1A Pending CN104773288A (en) | 2015-04-07 | 2015-04-07 | Skid type landing gear wheel loaded signal device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104773288A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108032998A (en) * | 2017-12-20 | 2018-05-15 | 中国科学院工程热物理研究所 | Recoil simulator is carried based on the unmanned plane undercarriage wheel of shock strut and toggle |
-
2015
- 2015-04-07 CN CN201510161334.1A patent/CN104773288A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108032998A (en) * | 2017-12-20 | 2018-05-15 | 中国科学院工程热物理研究所 | Recoil simulator is carried based on the unmanned plane undercarriage wheel of shock strut and toggle |
| CN108032998B (en) * | 2017-12-20 | 2023-07-07 | 中国科学院工程热物理研究所 | Unmanned aerial vehicle undercarriage wheel-load signal device based on shock strut and torque arm |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150715 |