CN216424787U - Airplane pneumatic deicing control function testing device - Google Patents
Airplane pneumatic deicing control function testing device Download PDFInfo
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- CN216424787U CN216424787U CN202122984056.3U CN202122984056U CN216424787U CN 216424787 U CN216424787 U CN 216424787U CN 202122984056 U CN202122984056 U CN 202122984056U CN 216424787 U CN216424787 U CN 216424787U
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Abstract
The utility model discloses a pneumatic deicing control function testing arrangement of aircraft, this pneumatic deicing control function testing arrangement of aircraft includes: the adapter plug seat S1, the adapter plug seat S2, the adapter plug seat S3, the signal indicator lamps L1-L9 and the switch K1; the adapter plug seat S1, the adapter plug seat S2 and the adapter plug seat S3 are respectively connected in series to the rear ends of the machine element plug seats of an air inlet deicing timer and an airfoil deicing timer in the aircraft pneumatic deicing circuit through cross-linked test cables. The embodiment of the utility model provides a pneumatic deicing control function testing arrangement of aircraft is shown the order of pneumatic deicing system work with light signal's form when the engine is not in operation, reaches direct monitoring light signal and judges the working sequence who draws flow control valve to can inspect the pneumatic deicing control function of aircraft fast, easy operation has reduced the operation degree of difficulty, and audio-visual display effect is also showing the accuracy that has promoted the detection.
Description
Technical Field
The utility model relates to an airborne vehicle maintains technical field, especially relates to a pneumatic deicing control function testing arrangement of aircraft.
Background
Before the aircraft starts, generally need to check functions such as pneumatic deicing system, in traditional inspection mode, when the engine was not in operation, can not provide the air supply for pneumatic deicing system, when static circular telegram was examined this system, whether effective circulation of deicing timer procedure was judged through the sound that draws the work of flow control valve, very not directly perceived, the artificial error of judgement appears moreover often, and the operation is complicated.
SUMMERY OF THE UTILITY MODEL
In order to overcome the not enough of relevant product among the prior art, the utility model provides a pneumatic deicing control function testing arrangement of aircraft solves current pneumatic deicing system inspection mode complicacy, and the problem that the result shows that directly visual accuracy that leads to is low.
The utility model provides a pneumatic deicing control function testing arrangement of aircraft, include: the adapter plug seat S1, the adapter plug seat S2, the adapter plug seat S3, the signal indicator lamps L1-L9 and the switch K1; the adapter plug seat S1, the adapter plug seat S2 and the adapter plug seat S3 are respectively connected in series to the rear ends of the machine part plug seats of an air inlet deicing timer and an airfoil deicing timer in the aircraft pneumatic deicing circuit through cross-linked test cables; the adapter plug socket S1 comprises 12 pins, pins 1-6 and pins 11-16, and the adapter plug socket S2 and the adapter plug socket S3 have the same structure and respectively comprise 6 pins E-K; one end of the signal indicator lamp L1 is respectively connected with pins 2 and 16 of the adapter plug socket S1, the other end of the signal indicator lamp L1 is respectively connected with pin E of the adapter plug socket S2 and the switch K1, and the other end of the switch K1 is connected with pin J of the adapter plug socket S3; one end of the signal indicator lamp L2 is connected with pins 3 and 11 of the adapter plug seat S1 respectively, and the other end of the signal indicator lamp L2 is connected with pin K of the adapter plug seat S2 and pin H of the adapter plug seat S3 respectively; one end of the signal indicator lamp L3 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L3 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L4 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L4 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L5 is connected with pins 6 and 14 of the adapter plug seat S1 respectively, and the other end of the signal indicator lamp L5 is connected with pin G of the adapter plug seat S2 and pin E of the adapter plug seat S3 respectively; one end of the signal indicator lamp L6 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L6 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L7 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L7 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L8 is respectively connected with pins 2 and 11 of the adapter plug seat S1, and the other end of the signal indicator lamp L8 is respectively connected with pin K of the adapter plug seat S2 and pin J of the adapter plug seat S3; one end of the signal indicator lamp L9 is respectively connected with pins 1 and 15 of the adapter plug seat S1, and the other end of the signal indicator lamp L9 is respectively connected with pin F of the adapter plug seat S2 and pin K of the adapter plug seat S3;
signal indicator lamp L1 is left intake duct signal indicator lamp, signal indicator lamp L2 is flat interior signal indicator lamp, signal indicator lamp L3 is two signal indicator lamps in left outer wing, signal indicator lamp L4 is a left outer wing signal indicator lamp, signal indicator lamp L5 is central wing signal indicator lamp, signal indicator lamp L6 is a right outer wing signal indicator lamp, signal indicator lamp L7 is two signal indicator lamps in right outer wing, signal indicator lamp L8 is flat outer, perpendicular signal indicator lamp, signal indicator lamp L9 is right intake duct signal indicator lamp.
Compared with the prior art, the utility model discloses there is following advantage:
the embodiment of the utility model provides a pneumatic deicing control function testing arrangement of aircraft is shown the order of pneumatic deicing system work with light signal's form when the engine is not in operation, reaches direct monitoring light signal and judges the working sequence who draws flow control valve to can inspect the pneumatic deicing control function of aircraft fast, easy operation has reduced the operation degree of difficulty, and audio-visual display effect is also showing the accuracy that has promoted the detection.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is the schematic structural diagram of the pneumatic deicing control function testing device of the aircraft of the utility model.
Detailed Description
In order to make the technical field person understand the scheme of the present invention better, the following will combine the drawings in the embodiments of the present invention to clearly and completely describe the technical scheme in the embodiments of the present invention. It is to be understood that the embodiments described are merely exemplary of some, and not all embodiments of the invention, and that the preferred embodiments of the invention are shown in the drawings. The present invention may be embodied in many different forms and is not limited to the embodiments described herein, which are provided for the purpose of providing a more thorough understanding of the present disclosure.
Referring to fig. 1, the aircraft pneumatic deicing control function testing device comprises a patch plug socket S1, a patch plug socket S2, a patch plug socket S3, signal indicator lamps L1-L9 and a switch K1; the adapter plug seat S1, the adapter plug seat S2 and the adapter plug seat S3 are respectively connected in series to the rear ends of the machine part plug seats of an air inlet deicing timer and an airfoil deicing timer in the aircraft pneumatic deicing circuit through cross-linked test cables; the adapter plug socket S1 comprises 12 pins, pins 1-6 and pins 11-16, and the adapter plug socket S2 and the adapter plug socket S3 have the same structure and respectively comprise 6 pins E-K; one end of the signal indicator lamp L1 is respectively connected with pins 2 and 16 of the adapter plug socket S1, the other end of the signal indicator lamp L1 is respectively connected with pin E of the adapter plug socket S2 and the switch K1, and the other end of the switch K1 is connected with pin J of the adapter plug socket S3; one end of the signal indicator lamp L2 is respectively connected with pins 3 and 11 of the adapter plug seat S1, and the other end of the signal indicator lamp L2 is respectively connected with pin K of the adapter plug seat S2 and pin H of the adapter plug seat S3; one end of the signal indicator lamp L3 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L3 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L4 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L4 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L5 is respectively connected with pins 6 and 14 of the adapter plug seat S1, and the other end of the signal indicator lamp L5 is respectively connected with a pin G of the adapter plug seat S2 and a pin E of the adapter plug seat S3; one end of the signal indicator lamp L6 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L6 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L7 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L7 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L8 is respectively connected with pins 2 and 11 of the adapter plug seat S1, and the other end of the signal indicator lamp L8 is respectively connected with pin K of the adapter plug seat S2 and pin J of the adapter plug seat S3; one end of the signal indicator lamp L9 is connected with pins 1 and 15 of the adapter plug seat S1 respectively, and the other end of the signal indicator lamp L9 is connected with pin F of the adapter plug seat S2 and pin K of the adapter plug seat S3 respectively;
the embodiment of the utility model provides an in, signal indicator lamp L1 is left intake duct signal indicator lamp, signal indicator lamp L2 is flat interior signal indicator lamp, signal indicator lamp L3 is two signal indicator lamps of left outer wing, signal indicator lamp L4 is a left outer wing signal indicator lamp, signal indicator lamp L5 is central wing signal indicator lamp, signal indicator lamp L6 is a right outer wing signal indicator lamp, signal indicator lamp L7 is two signal indicator lamps of right outer wing, signal indicator lamp L8 is flat outer, perpendicular signal indicator lamp, signal indicator lamp L9 is right intake duct signal indicator lamp.
The embodiment of the utility model provides a test work process of aircraft pneumatic deicing control function testing arrangement specifically as follows:
when the test of the air inlet deicing timer is carried out:
1. connecting the adapter plug seat S1 and the adapter plug seat S2 in series at the rear end of the plug seat of the machine part of the air inlet deicing timer by using a cross-linked test cable, and simultaneously switching on a button switch of a left air channel on the test box;
2. the direct current power supply ON the machine is switched ON, the circuit breaker of related equipment is ensured to be in a closed state, the emergency deicing switch ON the deicing control panel is arranged at an NORM (normal) position, when the air inlet channel deicing switch is arranged at an ON (ON) position, the air inlet channel deicing timer works normally, and the air inlet channel deicing timer works in a 1min cycle according to the following sequence: left engine intake duct (L1) → right engine intake duct (L9). In the working process, the left and right air inlet channel indicating signal lamps (L1 and L9) on the test box are sequentially lighted in the sequence, and each side is lighted for about 6 seconds;
3. the emergency deicing switch is arranged at the position of INTAKE TIMER (air inlet timer), the engine and empennage deicing switch are arranged at the position of OFF, the air inlet deicing switch is arranged at the position of ON, the work of the wing, the stabilizing surface and the air inlet deicing system is simultaneously controlled by the air inlet deicing timer, and the emergency deicing switch works in 1min of one cycle in sequence: the left engine air inlet duct (L1) → the right engine air inlet duct (L9) → the center wing leading edge (L5) → the No. 1 outer wing leading edge (L4, L6) → the No. 2 outer wing leading edge (L3, L7) → the horizontal stabilizer leading edge inside (L2) and the horizontal stabilizer leading edge outside and the vertical stabilizer leading edge (L8), and the indicator lights sequentially light up in this order in the working process, and each group lights up for about 6 s.
When testing the airfoil de-icing timer:
1. using a cross-linked test cable to serially connect the adapter plug socket S1 and the adapter plug socket S3 at the rear end of the plug socket of the airfoil deicing timer mechanism, and simultaneously disconnecting a button switch of a left air channel on the test box;
2. and switching on a direct-current power supply on the machine to ensure that a breaker of related equipment is in a closed state, and placing an emergency deicing switch on a deicing control board in a NORM (normal) position to perform normal-state working inspection on the airfoil deicing system.
3. The deicing switches of the airplane and the empennage are arranged at a HIGH position, the deicing system works in a cycle of 1min, each group works once, and the time is 6 s.
4. The deicing switches of the airplane and the empennage are arranged at a LOW (slight icing) position, the deicing system works in a cycle of 3min, each group works once, and the time is 6 s.
5. During normal operation, for two states of severe icing and slight icing, the deicing system of the wing and the stabilizing surface circularly operates according to the following sequence: the center leading edge (L5) → No. 1 outer leading edge (L4, L6) → No. 2 outer leading edge (L3, L7) → horizontal stabilizer leading edge inside (L2) → horizontal stabilizer outer leading edge, vertical stabilizer leading edge (L8). And indicating signal lamps sequentially lighten according to the sequence in the working process, wherein each pair of lightening lamps is about 6 s.
6. The emergency deicing switch is arranged at a WING & TAIL TIMER (tail WING timer), a button switch of a left air passage on the test box is switched on, the emergency state working inspection is carried out on the air inlet channel deicing system, and at the moment, the WING surface deicing timer controls the work of the engine, the tail WING and the air inlet channel deicing system at the same time. The air inlet channel deicing switch is arranged at an OFF position, the machine and empennage deicing switches are arranged at a HIGH (severe icing) or LOW (slight icing) position, the whole machine deicing sleeve works in 1min of one cycle, and the working sequence is as follows: the center airfoil leading edge (L5) → No. 1 airfoil leading edge (L4, L6) → No. 2 airfoil leading edge (L3, L7) → horizontal stabilizer leading edge inside (L2) → horizontal stabilizer leading edge outside, vertical stabilizer leading edge (L8), and left engine intake duct (L1) → right engine intake duct (L9). And indicating signal lamps are sequentially lightened according to the sequence in the working process, and each group is lightened for about 6 seconds.
The embodiment of the utility model provides a pneumatic deicing control function testing arrangement of aircraft is shown the order of pneumatic deicing system work with light signal's form when the engine is not in operation, reaches direct monitoring light signal and judges the working sequence who draws flow control valve to can inspect the pneumatic deicing control function of aircraft fast, easy operation has reduced the operation degree of difficulty, and audio-visual display effect is also showing the accuracy that has promoted the detection.
Those not described in detail in this specification are within the skill of the art. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing detailed description, or equivalent replacements may be made for some of the technical features of the embodiments. All utilize the equivalent structure that the content of the utility model discloses a specification and attached drawing was done, direct or indirect application is in other relevant technical field, all is in the same way the utility model discloses within the patent protection scope.
Claims (1)
1. A pneumatic deicing control function testing device for an aircraft is characterized by comprising: the adapter plug seat S1, the adapter plug seat S2, the adapter plug seat S3, the signal indicator lamps L1-L9 and the switch K1; the adapter plug seat S1, the adapter plug seat S2 and the adapter plug seat S3 are respectively connected in series to the rear ends of the machine part plug seats of an air inlet deicing timer and an airfoil deicing timer in the aircraft pneumatic deicing circuit through cross-linked test cables; the adapter plug socket S1 comprises 12 pins, pins 1-6 and pins 11-16, and the adapter plug socket S2 and the adapter plug socket S3 have the same structure and respectively comprise 6 pins E-K; one end of the signal indicator lamp L1 is respectively connected with pins 2 and 16 of the adapter plug socket S1, the other end of the signal indicator lamp L1 is respectively connected with pin E of the adapter plug socket S2 and the switch K1, and the other end of the switch K1 is connected with pin J of the adapter plug socket S3; one end of the signal indicator lamp L2 is respectively connected with pins 3 and 11 of the adapter plug seat S1, and the other end of the signal indicator lamp L2 is respectively connected with pin K of the adapter plug seat S2 and pin H of the adapter plug seat S3; one end of the signal indicator lamp L3 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L3 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L4 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L4 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L5 is respectively connected with pins 6 and 14 of the adapter plug seat S1, and the other end of the signal indicator lamp L5 is respectively connected with a pin G of the adapter plug seat S2 and a pin E of the adapter plug seat S3; one end of the signal indicator lamp L6 is respectively connected with pins 5 and 13 of the adapter plug seat S1, and the other end of the signal indicator lamp L6 is respectively connected with pin H of the adapter plug seat S2 and pin F of the adapter plug seat S3; one end of the signal indicator lamp L7 is connected with pins 4 and 12 of the adapter plug socket S1, and the other end of the signal indicator lamp L7 is connected with pin J of the adapter plug socket S2 and pin G of the adapter plug socket S3; one end of the signal indicator lamp L8 is respectively connected with pins 2 and 11 of the adapter plug seat S1, and the other end of the signal indicator lamp L8 is respectively connected with pin K of the adapter plug seat S2 and pin J of the adapter plug seat S3; one end of the signal indicator lamp L9 is respectively connected with pins 1 and 15 of the adapter plug seat S1, and the other end of the signal indicator lamp L9 is respectively connected with pin F of the adapter plug seat S2 and pin K of the adapter plug seat S3;
signal indicator lamp L1 is left intake duct signal indicator lamp, signal indicator lamp L2 is flat interior signal indicator lamp, signal indicator lamp L3 is two signal indicator lamps in left outer wing, signal indicator lamp L4 is a left outer wing signal indicator lamp, signal indicator lamp L5 is central wing signal indicator lamp, signal indicator lamp L6 is a right outer wing signal indicator lamp, signal indicator lamp L7 is two signal indicator lamps in right outer wing, signal indicator lamp L8 is flat outer, perpendicular signal indicator lamp, signal indicator lamp L9 is right intake duct signal indicator lamp.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122984056.3U CN216424787U (en) | 2021-11-29 | 2021-11-29 | Airplane pneumatic deicing control function testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122984056.3U CN216424787U (en) | 2021-11-29 | 2021-11-29 | Airplane pneumatic deicing control function testing device |
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| Publication Number | Publication Date |
|---|---|
| CN216424787U true CN216424787U (en) | 2022-05-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122984056.3U Active CN216424787U (en) | 2021-11-29 | 2021-11-29 | Airplane pneumatic deicing control function testing device |
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| CN (1) | CN216424787U (en) |
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2021
- 2021-11-29 CN CN202122984056.3U patent/CN216424787U/en active Active
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