CN2749784Y - Automatic anti-misoperation device for undercarriage - Google Patents
Automatic anti-misoperation device for undercarriage Download PDFInfo
- Publication number
- CN2749784Y CN2749784Y CN 200420080068 CN200420080068U CN2749784Y CN 2749784 Y CN2749784 Y CN 2749784Y CN 200420080068 CN200420080068 CN 200420080068 CN 200420080068 U CN200420080068 U CN 200420080068U CN 2749784 Y CN2749784 Y CN 2749784Y
- Authority
- CN
- China
- Prior art keywords
- undercarriage
- switch
- aircraft
- circuit
- micro
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000005484 gravity Effects 0.000 description 4
- 230000006378 damage Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 239000006096 absorbing agent Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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- Mechanical Control Devices (AREA)
Abstract
The utility model discloses an automatic mistake receipts device that prevents of aircraft undercarriage, its key feature is that a fine motion switch of establishing ties in the control circuit is received to the undercarriage, and the ejector pin top of fine motion switch sets up a connecting rod, and the other end of connecting rod is connected with the arm of turning round of preventing of aircraft main undercarriage, and the circuit is received in the fine motion switch pressurized switch-on when the aircraft takes off, breaks off under the spring action when the aircraft lands and receives the circuit. The utility model discloses fundamentally has solved the undercarriage mistake that causes because of the human factor and has received the accident.
Description
Background technology
The utility model belongs to the anti-error receiving apparatus of undercarriage.
Technical field
As everyone knows, existing undercarriage extension and retraction system, because of human element, all have on ground and lead to when pressing, the safety factor hidden danger of mistake gear up, for this reason, once had much at anti-error receipts measure of this situation design-calculated alighting gear or device, still, these devices still need certain artificial attention, so still the factor that exists artificial mistake to receive, receive insurance card as existing mistake,, still need artificial the recovery after this insurance card is opened though played certain safety effect, will open this card before the aviator is taking off when flight simultaneously, then this moment, this insurance card did not just have safety effect yet.So present measures also is not very perfect, still need further to improve and improve.
Summary of the invention
The purpose of this utility model provides the anti-error receiving apparatus of a kind of new undercarriage, and it can prevent the mistake gear up automatically according to the operating mode of taking off of aircraft.
The technical solution of the utility model is: the take-off and landing device according to present generation aircraft has all been equipped the shock absorber that rises and falls, i.e. the alighting gear damper leg.Aircraft is ground connection and when liftoff like this, damper leg all can cause the change of amount of compression because of the difference of bearing gravity, that is: during ground contact, damper leg is compressed because of needs bear aircraft weight, and when aircraft is liftoff, damper leg is because of no longer bearing aircraft weight, and the high pressure gas of portion's filling within it and weight effect own are stretched out down fully, so just can utilize this phenomenon to change the work of the undercarriage stowage control setup of aircraft.The control landing-gear system is undercarriage control circuit and alighting gear electro hydraulic valve, the principle of work and the circuit of this cover circuit are also fairly simple, the circuit of wherein controlling undercarriage stowage is a switch circuit, both one positive one negative two followed line to receive upward electromagnet power supply for the alighting gear electro hydraulic valve, the alighting gear electro hydraulic valve is received gone up the loop connection, alighting gear just can received under the oil liquid pressure effect of hydraulic efficiency pressure system, if this circuit disconnects, alighting gear electromagnetism liquid is received and is gone up the electromagnet dead electricity, alighting gear electro hydraulic valve receipts go up the loop and just disconnect, and alighting gear just can not received.Thus, concrete scheme of the present utility model is: micro-switch of series connection is with the switching of control undercarriage stowage control circuit in the undercarriage stowage control circuit of being made up of undercarriage stowage electro hydraulic valve, undercarriage control switch, micro-switch is fixed on the urceolus of aircraft main landing gear damper leg, its push rod and the anti-last arm contact of turning round arm, the micro-switch pressurized is connected to receive and is gone up circuit when taking off, and disconnects receiving circuit when aircraft landing under acting force of the spring.
Its principle of work is as follows:
As aircraft ground connection, the alighting gear damper leg causes deformation because of bearing gravity, to the micro-switch above it be moved to disconnect the undercarriage stowage circuit, the alighting gear electro hydraulic valve is received upward, and electromagnet just can be in power failure state, the electro hydraulic valve receipts go up the loop will be in off-state all the time, also can pressure mistiming gear up not arranged in system even artificially receive landing gear switch on ground so by mistake.Simultaneously, as long as aircraft is liftoff, the alighting gear damper leg does not bear aircraft gravity, and the alighting gear damper leg is upheld fully so, drives the micro-switch action, connects the undercarriage stowage circuit, thereby does not influence the normal folding and unfolding of aircraft alighting gear when liftoff.When design can also be avoided aircraft landing like this to the impact damage of micro-switch.
Good effect of the present utility model is:
1, aircraft has adopted this kind device, the grave accident of the mistake gear up in the time of can stopping ground contact fully.
When 2, having adopted this kind device, when aircraft is liftoff, do not stretch out fully if damper leg hinders for some reason, alighting gear just can not received, and will avoid the great bodily injury that this moment, gear up caused the undercarriage cabin like this.
Description of drawings
Below in conjunction with drawings and Examples the utility model is further described
Accompanying drawing is the utility model circuit and structural representation
Among the figure: 1, electro hydraulic valve, electromagnet on the 1-1 receipts, 1-2 puts down electromagnet, and 2, the undercarriage control switch, 3, micro-switch, 4, push rod, 5, urceolus, 6, the anti-arm of turning round, 7, spring, 8, wheel, 9, the main landing gear damper leg.
The specific embodiment
With reference to accompanying drawing, the anti-error receiving apparatus of undercarriage comprises has on the receipts electromagnet (1-1) and one put down electromagnet (1-2) on an alighting gear electro hydraulic valve (1), the electro hydraulic valve (1), the micro-switch (3) of in the circuit of electro hydraulic valve (1) and undercarriage control switch (2), having connected, in the present embodiment, micro-switch (3) be 2 open in usual, promptly be in normally open under the effect of spring (7) when aircraft is walked, circuit disconnects on the receipts.Micro-switch (3) is contained on the urceolus (5) of aircraft main landing gear damper leg (9), the anti-last arm contact of turning round arm (6) of push rod of micro-switch (4) and main landing gear damper leg (9).When take off liftoff after, the alighting gear damper leg does not bear aircraft gravity, damper leg is upheld fully, drives anti-arm (6) upper arm of turning round and rotates counterclockwise compressing push rod (4) to moving down, and connects the undercarriage stowage circuit, alighting gear just can artificially be controlled and pack up this moment.
Claims (2)
1, the automatic anti-error receiving apparatus of a kind of undercarriage, comprise by alighting gear electro hydraulic valve (1), the undercarriage stowage control circuit that undercarriage control switch (2) is formed, it is characterized in that the switching of a micro-switch of series connection (3) control undercarriage stowage control circuit in the undercarriage stowage control circuit, micro-switch (3) is fixed on the urceolus (5) of aircraft main landing gear damper leg (9), the anti-last arm contact of turning round arm (6) of its push rod (4) and aircraft main landing gear, connect to receive and go up circuit when taking off when liftoff the micro-switch pressurized, when aircraft landing ground connection, under spring (7) application force, disconnect and receive upward circuit.
2, require the automatic anti-error receiving apparatus of 1 described a kind of undercarriage according to patent, it is characterized in that described micro-switch be 2 open in usual.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420080068 CN2749784Y (en) | 2004-09-30 | 2004-09-30 | Automatic anti-misoperation device for undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420080068 CN2749784Y (en) | 2004-09-30 | 2004-09-30 | Automatic anti-misoperation device for undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2749784Y true CN2749784Y (en) | 2006-01-04 |
Family
ID=35823175
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420080068 Expired - Fee Related CN2749784Y (en) | 2004-09-30 | 2004-09-30 | Automatic anti-misoperation device for undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2749784Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102060104A (en) * | 2010-11-19 | 2011-05-18 | 陕西飞机工业（集团）有限公司 | Micro-switch assembly |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN113335506A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Method and device for adjusting micro-switch of undercarriage |
-
2004
- 2004-09-30 CN CN 200420080068 patent/CN2749784Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102060104A (en) * | 2010-11-19 | 2011-05-18 | 陕西飞机工业（集团）有限公司 | Micro-switch assembly |
| CN102060104B (en) * | 2010-11-19 | 2013-03-06 | 陕西飞机工业（集团）有限公司 | Micro-switch assembly |
| CN105151282A (en) * | 2015-09-14 | 2015-12-16 | 江西洪都航空工业集团有限责任公司 | Control method for reliable ground locking of landing gear of airplane |
| CN113335506A (en) * | 2020-03-02 | 2021-09-03 | 中航西飞民用飞机有限责任公司 | Method and device for adjusting micro-switch of undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |