CN201555719U - Detection device for aircraft anti-skid braking system - Google Patents
Detection device for aircraft anti-skid braking system Download PDFInfo
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- CN201555719U CN201555719U CN2009202747273U CN200920274727U CN201555719U CN 201555719 U CN201555719 U CN 201555719U CN 2009202747273 U CN2009202747273 U CN 2009202747273U CN 200920274727 U CN200920274727 U CN 200920274727U CN 201555719 U CN201555719 U CN 201555719U
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Abstract
The utility model relates to a detection device for an aircraft anti-skid braking system, which comprises a rotating speed sensor, an anti-skid control device, a main undercarriage damping signal acquisition device, a brake valve and a tester, wherein the tester comprises an amplifier, a bandpass filter, a detector, a first conditioning circuit, a second conditioning circuit, a third conditioning circuit, a logic comparison circuit and an electric stop watch, the rotating speed sensor, the amplifier, the bandpass filter, the detector and the logic comparison circuit are connected in sequence; the anti-skid control device, the first conditioning circuit and the logic comparison circuit are connected in sequence; the brake valve, the second conditioning circuit and the logic comparison circuit are connected in sequence; the main undercarriage damping signal acquisition device, the third conditioning circuit and the logic comparison circuit are connected in sequence; and the logic comparison circuit is connected with the electric stop watch. Compared with the prior art, the detection device has the advantages of improving the performance testing accuracy of an anti-skid system, and the like.
Description
Technical field
The utility model relates to the pick-up unit of airplane brake system, especially relates to a kind of pick-up unit that is used for Aircraft Anti-skid Break Control.
Background technology
In order to prevent that aircraft from skidding or the phenomenon of drift off the runway in the landing mission brake process; on certain type coach anti-skid brake system (ABS) is housed; this system comprises two wheel rotary frequency sensors; an anti-skidding control assembly; and two electro-hydraulic valves; its work relationship is: the wheel frequency sensor is experienced the airplane wheel rotating speed; the various situations of change of rotating speed are real-time transmitted to anti-skidding control assembly; control assembly produces anti-skidding control signal according to the compressed signal of change in rotational speed situation and undercarriage leg vibroshock; the control electro-hydraulic valve is switched on or switched off; realize the function of brake locking or release; reach the unallowed purpose of skidding and when the pilot brakes in advance, forbidding wheel braking (realizing landing defencive function) when eliminating the wheel braking, satisfy skid-resistance requirements.
The present domestic special inspecting equipment that do not have carries out in situ detection to anti-skidding electric control system.When aircraft antiskid system in-situ test, to run for simulated aircraft is sliding, common way is with aircraft jack-up, rotate with dragging the tire device to drag wheel, reach certain rotating speed roughly, step on brake again, whether artificial impression has the generation of antiskid action, simply judges the serviceability of antiskid system with this.There are a lot of drawbacks and limitation, the first, dragging the tire device to drag wheel is very big wearing and tearing to wheel, and each test is all exerted an influence to tyre life, the second, dragging speed is rough, can only whether judge antiskid system work to a certain extent.The 3rd, test event is limited, can not satisfy test for the anti-skidding projects such as protection delay time, brake block signal releasing speed of landing.
Summary of the invention
The purpose of this utility model is exactly to provide a kind of pick-up unit that is used for Aircraft Anti-skid Break Control that improves antiskid system performance test precision for the defective that overcomes above-mentioned prior art existence.
The purpose of this utility model can be achieved through the following technical solutions:
A kind of pick-up unit that is used for Aircraft Anti-skid Break Control, it is characterized in that, this device comprises speed probe, anti-skidding control device, main landing gear damping signal pickup assembly, brake valve, exerciser, described exerciser comprises amplifier, bandpass filter, wave detector, first modulate circuit, second modulate circuit, the 3rd modulate circuit, logic comparator circuit, electrical secondmeter, described speed probe, amplifier, bandpass filter, wave detector, logic comparator circuit connects successively, described anti-skidding control device, first modulate circuit, logic comparator circuit connects successively, described brake valve, second modulate circuit, logic comparator circuit connects successively, described main landing gear damping signal pickup assembly, the 3rd modulate circuit, logic comparator circuit connects successively, and described logic comparator circuit is connected with electrical secondmeter.
Described amplifier, bandpass filter, wave detector, first modulate circuit, logic comparator circuit, electrical secondmeter are 2.
Compared with prior art, the utlity model has following advantage:
Avoided going round and round a millstone and decreasing the drawback of tire with dragging the tire device to drag wheel; rotation speed source rotary speed precision height; utilize the rotation speed source test to improve antiskid system performance test precision; exerciser makes test event cover system's all properties substantially for sampling processing, the logical transition control of various types of signal, protects delay time, brake block signal releasing speed also can satisfy test for anti-skidding landing.
Description of drawings
Fig. 1 is a kind of panel construction synoptic diagram that is used for the pick-up unit of Aircraft Anti-skid Break Control of the utility model;
Fig. 2 is a kind of structural representation that is used for the pick-up unit of Aircraft Anti-skid Break Control of the utility model;
The theory diagram of the exerciser of the pick-up unit that Fig. 3 is used for Aircraft Anti-skid Break Control for the utility model is a kind of.
Embodiment
Below in conjunction with the drawings and specific embodiments the utility model is elaborated.
As shown in Figure 1, a kind of panel of the pick-up unit that is used for Aircraft Anti-skid Break Control is as shown in the table:
| Sequence number | | Mark | Function | |
| 1 | | RESET | 2 | Clicking reset button electrical |
| 2 | | TIME | 2 | The right brake of the record pine delay time of stopping |
| 3 | | LIGHT | 2 | The right brake of indication pine is stopped |
| 4 | | LIGHT | 1 | Brake pine in an indication left side is stopped |
| 5 | | TIME | 1 | The record left side brake pine delay time of stopping |
| 6 | | RESET | 1 | Clicking reset button |
| 7 | Power switch | POWER | The |
|
| 8 | The simulation brake switch | BRAKE | Connect the simulation brake switch, the anti-skidding control device power supply of Б Э A | |
| 9 | Fuse | 1A | The |
|
| 10 | Power | DC | 28V | Power supply input cable socket, |
| 11 | Test socket | TEST | The detection streamer socket, the input detection signal |
As shown in Figure 2, speed-frequency signal Uf1, the Uf2 of speed probe are by cable on the machine, be connected to anti-skidding control device, by the threeway detection streamer, exerciser is experienced this signal simultaneously, the control signal U of the brake analog switch simulation brake valve in the exerciser is to anti-skidding control device, and main landing gear damping signal Uw is connected to anti-skidding control device by cable on the machine, also delivers to exerciser simultaneously.Liquid electricity valve events signal U1, the U2 of anti-skidding control device output are connected to exerciser via the threeway cable.
As shown in Figure 3, frequency signal Uf1, Uf2 that speed probe produces amplify through amplifier, and bandpass filter is carried out filtering, and wave detector carries out detection, divide to be clipped to logic comparator circuit and brake valve pilot lamp signal U lamp 1, U lamp 2 through nursing one's health; Operating voltage signal U1, U2; Undercarriage electric switch signal Uw compares.Result relatively controls electrical secondmeter respectively and carries out timing.
The function of amplifier is that sinusoidal signal Uf1, Uf2 that sensor is exported are amplified, and satisfies sinusoidal signal Uf1, Uf2 amplitude 〉=0.2V, can drive the electrical secondmeter timing;
The function of bandpass filter is that sensor frequency signal Uf1, Uf2 are carried out filtering, makes Uf1, Uf2 drive the frequency values of timing between 1000 ± 100Hz;
Wave detector converts effective frequency values to DC voltage, becomes logic level, participates in logical operation.
U1, U2 are meant the antiskid action signal, and promptly the actuating signal of liquid electricity valve is the DC28V direct current signal, directly show that with the pilot lamp simulation first modulate circuit is to convert this direct current signal to 5V TTL logic level by relay in the exerciser, participate in logical operation.
U signal is anti-skidding power supply, and after the trampling brake, the control device energized is the DC28V direct current signal in the aircraft system, and second modulate circuit becomes 5V TTL logic level by voltage division processing, participates in logical operation.
The Uw signal is a main landing gear damping signal, and for connecting DC28V+, normal after the aircraft landing the 3rd modulate circuit did not become 5V TTL logic level by voltage division processing in order to disconnect DC28V+, participates in logical operation when aircraft landed.
Logic comparator circuit carries out computing to above logic respectively, forms the left and right anti-skidding path action timing logic of antiskid system.Control electrical secondmeter starting and stop.Accurately measure the anti-skidding closed-circuit working time under the different situations.
Detection is landed defencive function and is detected:
1, after the normal main wheel of detection lands, time-delay 2.5 ± 0.5s wheel braking.
1.1 simulate aerial state, (connection of Uw main landing gear damping signal).
1.2 the brake analog switch BRAKE on the call through test device (U signal connection), this moment, two pilot lamp LIGHT1, LIGHT2 ignited simultaneously, (U1, U2 refer to the establishment of antiskid action signal).
1.3 simulation landing state (disconnection of Uw main landing gear damping signal), electrical secondmeter picks up counting, and goes out (U1, U2 refer to the antiskid action blackout) until pilot lamp LIGHT1, LIGHT2, and timing stops, and delay time should be 2.5 ± 0.5s.
2, detect protection electric switch fault (Uw main landing gear damping signal can not disconnect), (when wheel rises to rotating speed 110km/h, 2.5 ± 0.5s wheel braking).
2.1 simulate aerial state, (connection of Uw main landing gear damping signal).
2.2 the brake analog switch BRAKE on the call through test device (U signal connection), this moment, two pilot lamp LIGHT1, LIGHT2 ignited simultaneously, (U1, U2 refer to the establishment of antiskid action signal).
Back Uw main landing gear damping signal can not disconnect 2.3 land, the analog machine wheel speed reaches (110km/h), rotation speed source is set rotating speed 3663 (frequency signal Uf1, Uf2 that speed probe produces are between 1000 ± 100Hz), electrical secondmeter picks up counting, go out (U1, U2 refer to the antiskid action blackout) until pilot lamp LIGHT1, LIGHT2, timing stops, and delay time is answered 2.5 ± 0.5s.
Claims (2)
1. pick-up unit that is used for Aircraft Anti-skid Break Control, it is characterized in that, this device comprises speed probe, anti-skidding control device, main landing gear damping signal pickup assembly, brake valve, exerciser, described exerciser comprises amplifier, bandpass filter, wave detector, first modulate circuit, second modulate circuit, the 3rd modulate circuit, logic comparator circuit, electrical secondmeter, described speed probe, amplifier, bandpass filter, wave detector, logic comparator circuit connects successively, described anti-skidding control device, first modulate circuit, logic comparator circuit connects successively, described brake valve, second modulate circuit, logic comparator circuit connects successively, described main landing gear damping signal pickup assembly, the 3rd modulate circuit, logic comparator circuit connects successively, and described logic comparator circuit is connected with electrical secondmeter.
2. a kind of pick-up unit that is used for Aircraft Anti-skid Break Control according to claim 1 is characterized in that described amplifier, bandpass filter, wave detector, first modulate circuit, logic comparator circuit, electrical secondmeter are 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202747273U CN201555719U (en) | 2009-12-17 | 2009-12-17 | Detection device for aircraft anti-skid braking system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009202747273U CN201555719U (en) | 2009-12-17 | 2009-12-17 | Detection device for aircraft anti-skid braking system |
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| Publication Number | Publication Date |
|---|---|
| CN201555719U true CN201555719U (en) | 2010-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009202747273U Expired - Lifetime CN201555719U (en) | 2009-12-17 | 2009-12-17 | Detection device for aircraft anti-skid braking system |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102135775A (en) * | 2010-12-28 | 2011-07-27 | 江西洪都航空工业集团有限责任公司 | Test method and tester for electronic skid control box of airplane |
| CN102556365A (en) * | 2011-12-21 | 2012-07-11 | 西安航空制动科技有限公司 | Accelerated life test method of aircraft brake system |
| CN102103170B (en) * | 2009-12-17 | 2012-12-26 | 上海凯迪克航空工程技术有限公司 | In-situ detection device of anti-skidding electrical control system |
| CN103853148A (en) * | 2013-05-09 | 2014-06-11 | 西安航空制动科技有限公司 | Method of anti-skidding brake control box low-temperature stepping test |
| CN104494815A (en) * | 2014-11-18 | 2015-04-08 | 西安航空制动科技有限公司 | Landing protection method for anti-skid brake system of airplane |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
| CN105807167A (en) * | 2016-05-09 | 2016-07-27 | 赵红军 | Airplane wheel anti-skid braking system detection simulator |
| CN110657970A (en) * | 2019-09-27 | 2020-01-07 | 蚌埠和能信息科技有限公司 | Signal conditioning device for aircraft brake test system |
-
2009
- 2009-12-17 CN CN2009202747273U patent/CN201555719U/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102103170B (en) * | 2009-12-17 | 2012-12-26 | 上海凯迪克航空工程技术有限公司 | In-situ detection device of anti-skidding electrical control system |
| CN102135775A (en) * | 2010-12-28 | 2011-07-27 | 江西洪都航空工业集团有限责任公司 | Test method and tester for electronic skid control box of airplane |
| CN102556365A (en) * | 2011-12-21 | 2012-07-11 | 西安航空制动科技有限公司 | Accelerated life test method of aircraft brake system |
| CN102556365B (en) * | 2011-12-21 | 2014-01-01 | 西安航空制动科技有限公司 | Accelerated life test method of aircraft brake system |
| CN103853148A (en) * | 2013-05-09 | 2014-06-11 | 西安航空制动科技有限公司 | Method of anti-skidding brake control box low-temperature stepping test |
| CN103853148B (en) * | 2013-05-09 | 2016-04-06 | 西安航空制动科技有限公司 | The method of antiskid braking control box low temperature Step test |
| CN104494815A (en) * | 2014-11-18 | 2015-04-08 | 西安航空制动科技有限公司 | Landing protection method for anti-skid brake system of airplane |
| CN105000173A (en) * | 2015-08-11 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Ground protection system and method for airplane brake |
| CN105807167A (en) * | 2016-05-09 | 2016-07-27 | 赵红军 | Airplane wheel anti-skid braking system detection simulator |
| CN105807167B (en) * | 2016-05-09 | 2019-12-06 | 烟台军融万通光电科技有限公司 | airplane wheel anti-skid braking system detection simulator |
| CN110657970A (en) * | 2019-09-27 | 2020-01-07 | 蚌埠和能信息科技有限公司 | Signal conditioning device for aircraft brake test system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20100818 Effective date of abandoning: 20091217 |
|
| RGAV | Abandon patent right to avoid regrant |