CN107226200A - A kind of landing gear position optical indicating device - Google Patents
A kind of landing gear position optical indicating device Download PDFInfo
- Publication number
- CN107226200A CN107226200A CN201610177474.2A CN201610177474A CN107226200A CN 107226200 A CN107226200 A CN 107226200A CN 201610177474 A CN201610177474 A CN 201610177474A CN 107226200 A CN107226200 A CN 107226200A
- Authority
- CN
- China
- Prior art keywords
- locking bar
- lower locking
- eyepiece
- lock rod
- landing gear
- 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.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
- B64C25/28—Control or locking systems therefor with indicating or warning devices
Abstract
The invention provides a kind of landing gear position optical indicating device, upper lock rod (1) including undercarriage down lock, lower locking bar (2), upper lock rod (1), lower locking bar (2) is arranged on undercarriage, the two is hinged, it is characterized in that, it is additionally provided with surveillance mirror (10), surveillance mirror (10) is by object lens (5), image-carrying fiber bundle (6) and eyepiece (7) composition, object lens (5) end of surveillance mirror (10) is arranged on and upper lock rod (1), on the relative landing gear compartment wallboard (8) of lower locking bar (2), eyepiece (7) end of surveillance mirror (10) is arranged on cabin wallboard (9), upper lock rod (1) and lower locking bar (2) are provided with alignment mark (3), object lens (5) image in the target image of alignment mark (3) on the end face of coherent fiber bundle, light is transferred to by eyepiece (7) by image-carrying fiber bundle (6) again, target image just can be observed through eyepiece (7).
Description
Technical field
The present invention relates to airborne vehicle field of optical device technology
Background technology
The positional information of undercarriage is indicated more than existing Aircraft landing gear system using contact microswitch or proximity transducer, and
Power-supply system and other electric systems is intact on this machine that places one's entire reliance upon.Once generation electric loop breaks down, just
The accuracy of landing gear position information may be had influence on, danger is brought to flight operation.Therefore the landing gear position of many aircrafts refers to
It is redundancy design to show system, and which again increases system complexity, adds weight and cost.
The content of the invention
The backup of system is electrically indicated as general undercarriage, the purpose of landing gear position optical indicating device is to provide height can
Function is indicated by property, landing gear position simple in construction.It is both independent of power supply, while again without machine driven system, structure
Simply, reliability is high.
By setting cue mark on undercarriage strut/locking bar, by image-carrying fiber bundle, by strut, the relative position figure of locking bar
As information transmission is to cabin, make whether unit can put down locking with accurate observation to undercarriage.
The technical scheme is that a kind of landing gear position optical indicating device, including undercarriage down lock upper lock rod (1),
Lower locking bar (2), upper lock rod (1), lower locking bar (2) are arranged on undercarriage, and the two is hinged, it is characterised in that
Surveillance mirror (10) is additionally provided with, surveillance mirror (10) is made up of object lens (5), image-carrying fiber bundle (6) and eyepiece (7),
Object lens (5) end of surveillance mirror (10) is arranged on the landing gear compartment wallboard (8) relative with upper lock rod (1), lower locking bar (2),
Eyepiece (7) end of surveillance mirror (10) is arranged on cabin wallboard (9).
Upper lock rod (1) and lower locking bar (2) are provided with alignment mark (3),
Object lens (5) image in the target image of alignment mark (3) on the end face of coherent fiber bundle, then pass through image-carrying fiber bundle (6)
Light is transferred to eyepiece (7), target image just can be observed through eyepiece (7).
Further, alignment mark (3) is a colour band, upper and lower locking bar half and half, when upper lock rod (1) and lower locking bar (2)
During into locking state, the colour band alignment in upper lock rod (1) and lower locking bar (2) is in line.
Further, colour band is by rare earth aluminate luminescent coating brushing, available for the instruction in the case of night darkness.
Optical fiber image transmission beam is closely concerned with an orderly manner by hundreds thousand of optical fibers to be arranged, gathers bunchy, is made through two ends solidification rubbing down,
Image can be intactly transmitted, and can arbitrarily be bent, the complicated space arrangement requirement of landing gear compartment is met.
Landing gear position optical indicating device of the present invention, when gear down and when locking, positioned at upper lock rod (1) and lower locking bar
(2) alignment mark (3) colour band alignment on is in line, object lens (5), image transmission optical fibre of this image through surveillance mirror (10)
Beam (6) and eyepiece (7), by observer it was observed that.If not observing, colour band alignment is in line, and illustrates that undercarriage is not located
In putting down lock-out state.
Under landing gear compartment non-illuminated conditions, removed after being irradiated several seconds by surveillance mirror (10) with external light source such as flashlight,
By the colour band of rare earth aluminate luminescent coating brushing by continuous illumination, it can be observed by eyepiece (7).
Brief description of the drawings
State shown in Fig. 1 is the connection of upper lock rod (1) and lower locking bar (2), and colour band setting form.
Fig. 2 show the structure of surveillance mirror (10).
Fig. 3 show the arrangement of surveillance mirror (10).
Embodiment
A kind of landing gear position optical indicating device, includes upper lock rod 1, the lower locking bar 2 of undercarriage down lock, upper lock rod 1, under
Locking bar 2 is arranged on undercarriage, and the two is hinged, it is characterised in that
Surveillance mirror 10 is additionally provided with, surveillance mirror 10 is made up of object lens 5, image-carrying fiber bundle 6 and eyepiece 7, the object lens of surveillance mirror 10
5 ends are arranged on the landing gear compartment wallboard 8 relative with upper lock rod 1, lower locking bar 2, and the end of eyepiece 7 of surveillance mirror 10 is arranged on machine
In bulkhead plate 9.
Upper lock rod 1 and lower locking bar 2 are provided with alignment mark 3,
Object lens 5 image in the target image of alignment mark 3 on the end face of coherent fiber bundle, then are passed light by image-carrying fiber bundle 6
It is defeated to arrive eyepiece 7, target image just can be observed through eyepiece 7.
Alignment mark 3 is colour band, upper and lower locking bar half and half, when upper lock rod 1 and lower locking bar 2 are into locking state, is located at
Colour band alignment in upper lock rod 1 and lower locking bar 2 is in line.
Colour band is by rare earth aluminate luminescent coating brushing, available for the instruction in the case of night darkness.
Gear down and when locking, in line, this image is through seeing for the colour band alignment in upper lock rod 1 and lower locking bar 2
Survey mirror 10 object lens 5, image-carrying fiber bundle 6 and eyepiece 7, by observer it was observed that.If not observing, colour band is aligned to always
Line, then illustrate that undercarriage is not on putting down lock-out state.
Under landing gear compartment dark condition, removed after several seconds can be irradiated by surveillance mirror 10 with external light source such as flashlight, by
The colour band of rare earth aluminate luminescent coating brushing can observe continuous illumination by eyepiece 7.
The present invention is electrically to indicate that system breaks down in undercarriage can not normally indicate when putting down locking of undercarriage, utilizes pure light
Whether system, observation undercarriage down lock is in locking state, realizes the accurate judgement to landing gear position, it is ensured that aircraft is pacified
It is complete to land.
Claims (3)
1. a kind of landing gear position optical indicating device, includes upper lock rod (1), the lower locking bar (2) of undercarriage down lock, locks
Bar (1), lower locking bar (2) are arranged on undercarriage, and the two is hinged, it is characterised in that
Surveillance mirror (10) is additionally provided with, surveillance mirror (10) is made up of object lens (5), image-carrying fiber bundle (6) and eyepiece (7),
Object lens (5) end of surveillance mirror (10) is arranged on the landing gear compartment wallboard (8) relative with upper lock rod (1), lower locking bar (2),
Eyepiece (7) end of surveillance mirror (10) is arranged on cabin wallboard (9),
Upper lock rod (1) and lower locking bar (2) are provided with alignment mark (3),
Object lens (5) image in the target image of alignment mark (3) on the end face of coherent fiber bundle, then pass through image-carrying fiber bundle (6)
Light is transferred to eyepiece (7), target image just can be observed through eyepiece (7).
2. landing gear position optical indicating device according to claim 1, it is characterised in that alignment mark (3) is one
Bar colour band, upper and lower locking bar half and half, when upper lock rod (1) and lower locking bar (2) are into locking state, positioned at upper lock rod (1) and
Colour band alignment on lower locking bar (2) is in line.
3. landing gear position optical indicating device according to claim 2, it is characterised in that colour band is by rare earth aluminate night
Optical coating brushing, available for the instruction in the case of night darkness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177474.2A CN107226200B (en) | 2016-03-25 | 2016-03-25 | A kind of landing gear position optical indicating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177474.2A CN107226200B (en) | 2016-03-25 | 2016-03-25 | A kind of landing gear position optical indicating device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107226200A true CN107226200A (en) | 2017-10-03 |
| CN107226200B CN107226200B (en) | 2019-11-15 |
Family
ID=59932625
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610177474.2A Active CN107226200B (en) | 2016-03-25 | 2016-03-25 | A kind of landing gear position optical indicating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107226200B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202863759U (en) * | 2012-07-13 | 2013-04-10 | 哈尔滨飞机工业集团有限责任公司 | Stay bar structure of retractable nose landing gear |
| US20150101480A1 (en) * | 2013-10-11 | 2015-04-16 | Goodrich Corporation | Shrink strut landing gear system, method, and apparatus |
| CN104613397A (en) * | 2013-11-04 | 2015-05-13 | 西安飞豹科技发展公司 | Aircraft landing gear putting in-place indicator light |
-
2016
- 2016-03-25 CN CN201610177474.2A patent/CN107226200B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202863759U (en) * | 2012-07-13 | 2013-04-10 | 哈尔滨飞机工业集团有限责任公司 | Stay bar structure of retractable nose landing gear |
| US20150101480A1 (en) * | 2013-10-11 | 2015-04-16 | Goodrich Corporation | Shrink strut landing gear system, method, and apparatus |
| CN104613397A (en) * | 2013-11-04 | 2015-05-13 | 西安飞豹科技发展公司 | Aircraft landing gear putting in-place indicator light |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107226200B (en) | 2019-11-15 |
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| GR01 | Patent grant |