CN203405683U - tool for controlling stability augmentation system - Google Patents
tool for controlling stability augmentation system Download PDFInfo
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- CN203405683U CN203405683U CN201320474507.1U CN201320474507U CN203405683U CN 203405683 U CN203405683 U CN 203405683U CN 201320474507 U CN201320474507 U CN 201320474507U CN 203405683 U CN203405683 U CN 203405683U
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- breaker
- tool
- machine
- isolating switch
- test
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Abstract
The utility model is applicable to a test of a helicopter general assembly, and relates to original position detection. The breaker <{EN0}>tool for controlling a stability augmentation system comprises a breaker, a breaker box, a connector and a cable socket terminal. The breaker box comprises a breaker connecting hole and a powered state indicating lamp. The breaker adopts a "T"-shaped structure whose three points are communicated with each other, and test points are reserved. With development of the tester, relevant components controlling the stability augmentation system do not needed to be detached or installed repetitively and a wiring diagram does not need to be consulted by workers in the powered process of a general assembly so that operation is facilitated and working strength is reduced. With application of the tool breaker, the test points can be searched rapidly so that workload is reduced and burning of finished products caused by shorting due to mis-operation can be avoided simultaneously. Besides, fault simulation can be performed via the breaker tool so that relevant operations do not need to be performed on conductive wires of a machine and integrity of circuits of the machine is ensured.
Description
Technical field
The present invention is applicable to helicopter general assembly test, relates in situ detection.
Background technology
Technical development over nearly 20 years, there is larger variation in flight control system, the inapplicable control augmentation stability system energising needs that newly grind of former French Experiment in Introduction equipment.
In general assembly galvanization, need to power distribution, ground connection distribution, simulating signal, digital signal etc. be checked and be monitored.From the connection of airborne equipment, be mainly divided into two kinds: a kind of A of being equipment is directly connected to B equipment by cable on machine; Another kind is that A equipment is connected to B equipment by interconnecting module, specifically sees Fig. 1; On machine, all do not reserve test point, this measurement to signal brings inconvenience.For to power supply, ground connection and various types of signal test, can only take following means at work: 1) equipment of connection is pulled down, by attachment plug, tested; 2) by interconnecting module, test; Although taked measure as mentioned above, but still had the following disadvantages:
1), for test signal, need repeated disassembled and assembled finished product;
2) directly measure plug each point, careless manipulation, easily causes short circuit, burns finished product;
3) the full machine of each component distribution of control augmentation stability system, needs constantly mobile test equipment everywhere;
4) the finished product signal testing connecting by interconnecting module all needs to search test point according to drawing at every turn;
5) easily cable on machine is damaged;
6) for after system normal operation, the part control signal of generation cannot be tested.As direct-connected equipment, if dismantle certain equipment, will cause system not work or work undesired, cause the signal cannot to gather and gather inaccurate phenomenon.
Summary of the invention
The technical problem to be solved in the present invention:
Control augmentation stability system isolating switch frock is by having proposed solution for how realizing signal testing, by frock, introduce test point, realized controlling and increased steady in-situ test, can solve that working strength is large, technical risk is high, the not congruent problem of test signal, can meet general assembly energising and check needs, outside drawing refers to Fig. 2.
Technical scheme of the present invention:
This isolating switch frock adopts the design of T-shape breaking rings, on machine, between cable and tested finished product, introduces test point, by the test point on breaking rings, can realize signal measurement and monitoring, specifically refers to Fig. 3.
Control augmentation stability system isolating switch frock, comprise: isolating switch, circuit breaker case, connector and cable socket end, wherein, comprise isolating switch connecting hole and power-up state pilot lamp on circuit breaker case, isolating switch adopts " T " structure of 3 intercommunications, leaves test point.
Beneficial effect of the present invention:
This frock has been taked and aircraft design means one to one.
This frock adopts home position testing method design, and equipment need not dismantled from aircraft.
This frock possesses the indication of working power state.
The development of this exerciser, makes workman in general assembly galvanization, not need control augmentation stability system associated components repeated disassembled and assembled and consult wiring diagram, has facilitated operation, has reduced working strength; Can fast finding measurement point by frock isolating switch, reduced workload, can avoid maloperation to cause that short circuit burns finished product simultaneously; By isolating switch frock, carry out fault simulation, do not need machine upper conductor to carry out associative operation, guaranteed the integrity of circuit on machine.
Contrast before and after switching on by general assembly, improves general assembly energising efficiency 30%～40%; This exerciser panel simple and clear, simple to operate, use reliably, can meet use needs simultaneously.
Accompanying drawing explanation
Fig. 1 is original airborne equipment connection diagram;
Fig. 2 profile schematic diagram of the present invention;
Fig. 3 is design concept figure of the present invention;
Fig. 4 is circuit diagram of the present invention;
Fig. 5 is the connection layout of the present invention while using.
Embodiment
The utility model is by cable on machine and tested finishing room serial connection isolating switch frock, connection/disconnection by breaking rings has realized the path/isolation in signal transmission, the breaking rings test point that utilization is introduced in circuit and isolating switch connecting hole, realized the Quick Acquisition of signal and measured and fault isolation analysis.When control augmentation stability system energising checks, breaking rings is connected with isolating switch connecting hole on panel, and on machine, cable and tested finished product are in conducting connection status; When for fault analysis, also the breaking rings of corresponding signal and isolating switch connecting hole can be disconnected, realize isolation and the fault simulation of signal.
Isolating switch frock mainly comprises three parts: isolating switch, circuit breaker case, connector and cable (S plug end, P socket end).Wherein on circuit breaker case, comprise isolating switch connecting hole and power-up state pilot lamp.
1) isolating switch
Isolating switch is the main devices of frock, and every wire all interconnects by breaking rings, isolates each other.Breaking rings contact stud diameter 2mm, has Self-fastening function, spacing 12mm, and test point 2mm, the key technical indexes of breaking rings:
Maximum current: 7A (20 ℃)
Withstand voltage: 2000Vrms50Hz
Voltage: 500Vrms50Hz
Insulation resistance: be not less than 5000M Ω
Mechanical property: be greater than 10000 times
Working temperature :-40 ℃～70 ℃
Isolating switch adopts " T " structure of 3 intercommunications, leaves test point, and cable and tested finished product short circuit are got up, after system powers on or works, on machine, signal conducts to breaking rings test point by wire, by test point connecting test equipment, carries out measurement of correlation.By plug, carry out path and open-circuit operation, realize collection analysis and the fault isolation of signal.Refer to B in Fig. 3.
2) circuit breaker case
Circuit breaker case adopts metal construction, and the connecting hole insulating with casing is installed above, and connecting hole aperture 2mm, evenly arranges; System power supply status indicator lamp is also installed on casing, for the indication of system power supply state, refers to Fig. 2 (outside drawing) and Fig. 3.After system normally powers on, 3,6,5 of 16Cb plug and 3,6,5 corresponding 28VDC, 26VAC/400Hz, 115VAC/400Hz pilot lamp of 16Cc plug ignite, and schematic diagram refers to Fig. 4.The conventional pilot lamp that the rated voltage that 115VAC/400Hz power light adopts is 250V, because 115V alternating voltage is higher, for preventing static current transformer and machine on short circuit infringement machine, therefore, in frock circuit, seal in resistance R 1, C1 and R2, C2, for current limliting and rectification.R1=R2=56KΩ,1/4W,115V;C1=C2=0.1μF,250V。
3) connector and cable
In the selection of connector, with on machine and consistent on finished product, have good connectivity, S end, P end are connected with tested finished product respectively at cable on machine, two ends correspondence one by one in signal definition; The wire that cable adopts is consistent with on machine, and for the transmission of signal, the wire diameter of employing is 0.38mm2, to guarantee that isolating switch frock has good electrical characteristics.Because control augmentation stability system is one of most important, complication system of helicopter, this system comprises: control and increase 24 parts altogether such as steady computing machine, amplifier, steering wheel, connect more nearly more than 800 roots of wire, between parts, reception/output signal mostly is simulating signal, therefore, associated tracks has been carried out to shielding processing, made isolating switch frock there is good Electro Magnetic Compatibility.
Concrete energising check test step is as follows:
1) before test, prepare
A. system support is complete, and short-circuiting device connects in place reliable, wire without opening circuit, short circuit.
2) test routine
A. closing control stability augmentation system power supply;
B. isolating switch frock is connected in series between cable on machine and airborne equipment, S end is connected with cable on machine, and P end is connected with airborne equipment on machine, and the reliability of inspection connection;
C. breaking rings is connected with the connecting hole on panel, breaking rings holds wire and S end finished product corresponding lead to couple together P, form path, realize signal take out pilot measurement and try by the test point on breaking rings on machine between cable and tested finished product, breaking rings is connected reliably with the connecting hole on panel; Refer to Fig. 3;
D. connecting test equipment on the breaking rings of tested pilot, refers to Fig. 5;
E. after system powers on, on panel, for 28VDC, 26VAC/400Hz, 115VAC/400Hz working power status indicator lamp, ignite, illustrate that control augmentation stability system powers on normally.
F. by energising, check that file checks control augmentation stability system, signal transmission is tested;
G. when control augmentation stability system breaks down, can, by disconnecting breaking rings, signal source is judged and fault isolation, or additional simulating signal be carried out ground validation test; The use of isolating switch frock can be avoided line taking operation on machine, is convenient to troubleshooting, has simplified operation, has improved security.
Facts have proved, control augmentation stability system isolating switch frock can better meet control augmentation stability system general assembly demand and flight-line service demand.
Claims (1)
1. control augmentation stability system isolating switch frock, is characterized in that, comprising: isolating switch, circuit breaker case, connector and cable socket end, wherein, on circuit breaker case, comprise isolating switch connecting hole and power-up state pilot lamp, isolating switch adopts " T " structure of 3 intercommunications, leaves test point.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320474507.1U CN203405683U (en) | 2013-08-05 | 2013-08-05 | tool for controlling stability augmentation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320474507.1U CN203405683U (en) | 2013-08-05 | 2013-08-05 | tool for controlling stability augmentation system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203405683U true CN203405683U (en) | 2014-01-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320474507.1U Expired - Fee Related CN203405683U (en) | 2013-08-05 | 2013-08-05 | tool for controlling stability augmentation system |
Country Status (1)
| Country | Link |
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| CN (1) | CN203405683U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300366A (en) * | 2014-07-08 | 2016-02-03 | 哈尔滨飞机工业集团有限责任公司 | Radio compass self-checking test device |
-
2013
- 2013-08-05 CN CN201320474507.1U patent/CN203405683U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105300366A (en) * | 2014-07-08 | 2016-02-03 | 哈尔滨飞机工业集团有限责任公司 | Radio compass self-checking test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140122 Termination date: 20190805 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |