CN105015801A - Undercarriage raising/lowering time detection device - Google Patents
Undercarriage raising/lowering time detection device Download PDFInfo
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- CN105015801A CN105015801A CN201510296389.3A CN201510296389A CN105015801A CN 105015801 A CN105015801 A CN 105015801A CN 201510296389 A CN201510296389 A CN 201510296389A CN 105015801 A CN105015801 A CN 105015801A
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- undercarriage
- activated switch
- light activated
- control
- lucifuge
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- Lighting Device Outwards From Vehicle And Optical Signal (AREA)
Abstract
The invention provides an undercarriage raising/lowering time detection device; and the device can judge and precisely record the undercarriage raising/lowering time according to a state of an indicator light. The device comprises an undercarriage state indicator light mounted on an airplane landing signal panel, a light shielding cavity, a photosensitive switch and a control system. The device realizes the measurement of the undercarriage raising/lowering time by the undercarriage state indicator light on the airplane landing signal panel, and has general applicability for accurate detection of the undercarriage raising/lowering time in a cockpit.
Description
Technical field
The application relates to the detection technique field of aircraft, particularly the detecting device of a kind of undercarriage control time.
Background technology
The time of undercarriage folding and unfolding is accurately that aviator judges the whether normal important evidence of undercarriage, in flight airmanship and training program, all have embodiment.
Undercarriage generally comprise left and right lead, front, when undercarriage is normal, within its folding and unfolding time is generally 10 seconds.Folding and unfolding state is generally most of in driving compartment to be identified on panel by the undercarriage control status indicator lamp on aircraft landing signal head, indicator lamp divides red and green two kinds, during the starting packing up, when putting down action of alighting gear, lamp is bright, when action completes, lamp goes out, indicator lamp only can show the different conditions packed up with putting down, and directly can not show the correct time required for its undercarriage control.The measurement of current most domestic type to this parameter is according to human eye vision and stopwatch, namely in driving compartment, look at the indicator lamp on gauge panel, according to LED status different during folding and unfolding, by stopwatch to determine the time of folding and unfolding action, accuracy and the precision of this method of measurement are lower, artifical influence factor is larger.
Along with the large stream of internationalization trend, airworthiness requirement aircraft all technical is tending towards unified gradually and requires more and more higher to measurement, the measurement undercarriage control time becomes necessary more accurately, realize this and measure requirement, just must improve or again find the method for measurement of undercarriage control time.
Summary of the invention
The object of the application is to provide a kind of device accurately measuring the undercarriage control time, and this device according to LED status, can judge and the folding and unfolding time of accurate record alighting gear.
For reaching above object, the application takes following technical scheme to be achieved:
A kind of undercarriage control time detection device, comprise the undercarriage indicator lamp, lucifuge cavity, light activated switch and the control system that are arranged on aircraft landing signal head panel, lucifuge cavity is the closed enclosure shaped piece of an opening, its inside be divided into difform multiple unit every, it is consistent with cell type part that each unit separates actinal surface; Each unit is corresponding with a undercarriage indicator lamp position every aperture position; Light activated switch is arranged on each unit every interior, and near opening surface one end; Control system is arranged on the outside of lucifuge cavity and is connected every interior light activated switch with each unit, and lucifuge cavity hatch face is connected with aircraft landing signal head panel; Light activated switch by the different conditions of the induction undercarriage control that flickers of landing gear light, and sends different status signals to control system, is calculated and record the undercarriage control time and be supplied to aviator by control system.Control system comprises PLC (logical editting control machine), HMI (touch display screen), light activated switch is flickered by undercarriage indicator lamp on photosensitive Interruption performance perception aircraft landing signal head panel, signal will be cut-off and be sent to PLC, by the variate-values such as main to gear up, a lowering time and left and right time difference being shown on HMI after logical calculated.
The advantage of the application is to achieve measures the undercarriage control time by the undercarriage indicator lamp on aircraft landing signal head panel, has general applicability for accurately detecting the undercarriage control time in driving compartment.And this apparatus structure is simple, be easy to install.
Accompanying drawing explanation
Fig. 1 aircraft landing signal head and undercarriage control time detection device annexation figure;
Fig. 2 aircraft landing signal head panel schematic diagram;
Fig. 3 undercarriage control time detection device constructional drawing.
In Fig. 1 ~ Fig. 2: 1, aircraft landing signal head panel; 2, detecting device; 4, undercarriage indicator lamp; 5, unit every; 6, lucifuge cavity; 7, expanded cellular rubber; 8, light activated switch;
Detailed description of the invention
See Fig. 2, aircraft landing signal head in driving compartment observable part by aircraft landing signal head panel 1 (hereinafter referred to as panel 1), undercarriage indicator lamp 4 (following indicator lamp 4).
In a particular application, see Fig. 3, a kind of undercarriage control time detection device, comprise the undercarriage indicator lamp be arranged on panel 1, lucifuge cavity 6, light activated switch 8 and control system, lucifuge cavity 6 is the closed enclosure shaped piece of an opening, its inside is divided into difform multiple unit every 5, and each unit is consistent with cell type part every 5 opening surfaces; Each unit is corresponding with a undercarriage indicator lamp position every 5 aperture positions; Light activated switch 8 is arranged on each unit in 5, and near opening surface one end; Control system is arranged on the outside of lucifuge cavity 6 and is connected with the light activated switch 8 of each unit in 5, and lucifuge cavity 6 opening surface is connected with panel 1; Light activated switch 8 by the different conditions of the induction undercarriage control that flickers of landing gear light, and sends different status signals to control system, is calculated and record the undercarriage control time and be supplied to aviator by control system.Control system comprises PLC (logical editting control machine), HMI (touch display screen), light activated switch is flickered by undercarriage indicator lamp on photosensitive Interruption performance perception aircraft landing signal head panel, signal will be cut-off and be sent to PLC, by the variate-values such as main to gear up, a lowering time and left and right time difference being shown on HMI after logical calculated.
Its logical calculated process is as follows:
The time that a, three indicator lamps 4 have indicator lamp 4 bright deducts the time that three indicator lamps 4 go out entirely and equals gear up, lowering time;
B, two, left and right indicator lamp 4 bright time difference equals the gear retraction time, and the time difference that left and right indicator lamp 4 goes out equals the gear down time.
This apparatus structure is simple, is easy to install, and measures the undercarriage control time by the indicator lamp 4 on panel 1, has general applicability for accurately detecting the undercarriage control time in driving compartment.
Claims (3)
1. a undercarriage control time detection device, comprise the undercarriage indicator lamp, lucifuge cavity, light activated switch and the control system that are arranged on aircraft landing signal head panel, it is characterized in that described lucifuge cavity is the closed enclosure shaped piece of an opening, described lucifuge inside cavity be divided into difform multiple unit every, it is consistent with cell type part that each unit separates actinal surface; Each unit is corresponding with a described undercarriage indicator lamp position every aperture position; Described light activated switch is arranged on each unit every interior, and near opening surface one end; Described control telltale is arranged on described lucifuge containment portion and is connected every interior light activated switch with each unit, and described lucifuge cavity hatch face is connected with aircraft landing signal head panel; Described light activated switch by the different conditions of the induction undercarriage control that flickers of landing gear light, and sends different status signals to control system, is calculated and record the undercarriage control time and be supplied to aviator by control system.
2. a undercarriage control time detection device, it is characterized in that described control system comprises PLC (logical editting control machine), HMI (touch display screen), described light activated switch is flickered by undercarriage indicator lamp on photosensitive Interruption performance perception aircraft landing signal head panel, signal will be cut-off and be sent to PLC, by the variate-values such as main to gear up, a lowering time and left and right time difference being shown on HMI after logical calculated.
3. a undercarriage control time detection device, is characterized in that described light activated switch is photodiode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510296389.3A CN105015801A (en) | 2015-06-02 | 2015-06-02 | Undercarriage raising/lowering time detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510296389.3A CN105015801A (en) | 2015-06-02 | 2015-06-02 | Undercarriage raising/lowering time detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105015801A true CN105015801A (en) | 2015-11-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510296389.3A Pending CN105015801A (en) | 2015-06-02 | 2015-06-02 | Undercarriage raising/lowering time detection device |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4916447A (en) * | 1983-05-13 | 1990-04-10 | Sundstrand Data Control, Inc. | Warning system for aircraft landing with landing gear up |
| CN2088518U (en) * | 1990-10-11 | 1991-11-13 | 成都飞机工业公司 | Sound indicator for the aeroplane landing gear in place |
| CN103852735A (en) * | 2012-11-29 | 2014-06-11 | 深圳市海洋王照明工程有限公司 | Lamp fixture discharge timing circuit |
| US20140252210A1 (en) * | 2013-03-08 | 2014-09-11 | Messier-Dowty Inc. | Proximity sensor |
| CN104062590A (en) * | 2013-03-21 | 2014-09-24 | 深圳市海洋王照明工程有限公司 | Battery charging time testing apparatus |
| CN204297071U (en) * | 2014-10-28 | 2015-04-29 | 中航通飞研究院有限公司 | A kind of amphibious aircraft wheel-retracting gear position warning device |
-
2015
- 2015-06-02 CN CN201510296389.3A patent/CN105015801A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4916447A (en) * | 1983-05-13 | 1990-04-10 | Sundstrand Data Control, Inc. | Warning system for aircraft landing with landing gear up |
| CN2088518U (en) * | 1990-10-11 | 1991-11-13 | 成都飞机工业公司 | Sound indicator for the aeroplane landing gear in place |
| CN103852735A (en) * | 2012-11-29 | 2014-06-11 | 深圳市海洋王照明工程有限公司 | Lamp fixture discharge timing circuit |
| US20140252210A1 (en) * | 2013-03-08 | 2014-09-11 | Messier-Dowty Inc. | Proximity sensor |
| CN104062590A (en) * | 2013-03-21 | 2014-09-24 | 深圳市海洋王照明工程有限公司 | Battery charging time testing apparatus |
| CN204297071U (en) * | 2014-10-28 | 2015-04-29 | 中航通飞研究院有限公司 | A kind of amphibious aircraft wheel-retracting gear position warning device |
Non-Patent Citations (2)
| Title |
|---|
| 印寅等: "多因素影响下的起落架收放系统性能分析", 《北京航空航天大学学报》 * |
| 郝劲松: "《活塞发动机飞机结构与系统》", 31 January 2007 * |
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Application publication date: 20151104 |