CN219584473U - Ground anti-misoperation sound warning circuit for aircraft landing gear based on isolation protection - Google Patents
Ground anti-misoperation sound warning circuit for aircraft landing gear based on isolation protection Download PDFInfo
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- CN219584473U CN219584473U CN202320546645.XU CN202320546645U CN219584473U CN 219584473 U CN219584473 U CN 219584473U CN 202320546645 U CN202320546645 U CN 202320546645U CN 219584473 U CN219584473 U CN 219584473U
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Abstract
The utility model relates to an isolation protection-based landing gear ground anti-misoperation sound-receiving warning circuit of an aircraft, which comprises a relay, an isolation diode, a freewheel diode and a landing gear warning buzzer, wherein the relay is connected with the isolation diode; the positive electrode of the isolation diode is connected with the port of the control end 85 of the relay, and the negative electrode of the isolation diode is connected with the port C of the right pillar electric door S13; the port of a controlled end 87 of the relay is connected with the negative electrode of the landing gear warning buzzer, and the port of a control end 86 is connected with the port C of the left pillar electric valve S7 and the port UP of the landing gear control handle; the positive pole of the freewheel diode is connected with the control end 85 port of the relay, and the negative pole of the freewheel diode is connected with the control end 86 port of the relay. The landing gear control handle is arranged on the ground in a folding way, and the landing gear control handle is arranged on the ground in a folding way.
Description
Technical Field
The utility model relates to the technical field of electric control, in particular to an aircraft landing gear ground anti-misoperation sounding warning circuit based on isolation protection.
Background
Sometimes, an aircraft sometimes receives an undercarriage mistake in a take-off and running stage, and then the aircraft nose is sunk, the aircraft is damaged due to the ground contact and running, the existing aircraft model (such as DA42 model) does not have an undercarriage mistake-prevention sound warning device, only an unsafe warning lamp is indicated when an undercarriage handle is in ground misoperation, the warning lamp is influenced by the installation position and the ambient brightness and is easily ignored by a machine set, and potential safety hazards exist, so that the problem is needed to be considered at present.
It should be noted that the information disclosed in the above background section is only for enhancing understanding of the background of the present disclosure and thus may include information that does not constitute prior art known to those of ordinary skill in the art.
Disclosure of Invention
The utility model aims to overcome the defects of the prior art, provides an aircraft landing gear ground anti-false sound warning circuit based on isolation protection, and solves the problems caused by the fact that some aircraft types do not have landing gear anti-false sound warning devices.
The aim of the utility model is achieved by the following technical scheme: an aircraft landing gear ground anti-misoperation sound warning circuit based on isolation protection comprises a relay R1, an isolation diode D1, a freewheel diode D2 and a landing gear warning buzzer;
the positive electrode of the isolation diode D1 is connected with the port of the control end 85 of the relay R1, the negative electrode of the isolation diode D1 is connected with the port C of the right pillar electric door S13, the port NC of the right pillar electric door S13 is grounded, and the isolation diode D1 is used for isolating a plurality of components or systems connected with the port C of the right pillar electric door S13, so that the landing gear control circuit is prevented from being interfered by other components or systems under specific conditions;
the port of a controlled end 87 of the relay R1 is connected with the negative electrode of the landing gear warning buzzer, the port of a controlled end 30 of the relay R1 is grounded, and the port of a control end 86 is connected with the port C of the left pillar electric door S7 and the port UP of the landing gear control handle; the positive pole of the freewheel diode D2 is connected with the control end 85 port of the relay R1, the negative pole of the freewheel diode D2 is connected with the control end 86 port of the relay R1, and the freewheel diode D2 is used for preventing the control coil of the relay R1 from generating instant high voltage when being electrified or powered off, and protecting elements in a circuit from being broken down or burnt by induced voltage.
The landing gear warning buzzer is characterized in that the anode of the landing gear warning buzzer is connected with a left main bus bar of the aircraft, the other end of the landing gear control handle is connected with the left main bus bar of the aircraft, and the NO port of the left pillar electric valve S7 is connected with the winding and unwinding electromagnetic valve.
When the landing gear of the aircraft is put down and the ground of the aircraft wheel bears load, the C port of the right pillar electric valve S13 is communicated with the NC port, and the C port of the left pillar electric valve S7 is connected with the NC port.
The utility model has the following advantages: the utility model provides an aircraft landing gear ground prevents mistake and receives sound warning circuit based on keep apart protection, under the circumstances that does not change the original circuit of DA42 model, make full use of the control characteristics of two existing landing gear pillar electric gates of aircraft, through install a relay (need parallelly connected installation freewheel diode) additional in instrument board rear portion, an isolation diode and relevant electrical wire, under the circumstances that guarantees not influencing landing gear system normal work, realize ground mistake and put landing gear control handle in "receipts" position, trigger landing gear stereo warning, improve aircraft safety margin, have the practicality.
Drawings
FIG. 1 is a schematic circuit diagram of the present utility model;
FIG. 2 is a block diagram of the circuit of the present utility model;
fig. 3 is a logic control block diagram of the circuit of the present utility model.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present utility model more apparent, the technical solutions of the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments. The components of the embodiments of the present utility model generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Accordingly, the following detailed description of the embodiments of the utility model, as presented in conjunction with the accompanying drawings, is not intended to limit the scope of the utility model as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be made by a person skilled in the art without making any inventive effort, are intended to be within the scope of the present utility model. The utility model is further described below with reference to the accompanying drawings.
As shown in fig. 1 and 2, the utility model relates to an anti-misoperation sound warning circuit for the ground of an undercarriage based on isolation protection, which is used for providing an audible warning to remind operators of the error in setting the position of the handle of the undercarriage when the handle of the undercarriage is misoperation to a 'retracted' position on the ground of the undercarriage; the device comprises a relay R1, an isolation diode D1, a freewheel diode D2 and an undercarriage warning buzzer;
the positive electrode of the isolation diode D1 is connected with a port of the control end 85 of the relay R1, the negative electrode of the isolation diode D1 is connected with a port C of the right pillar electric gate S13, the NC port of the right pillar electric gate S13 is grounded, the right pillar electric gate S13 provides public space signals for a plurality of systems of the aircraft, and the isolation diode D1 plays an isolation protection role on the right pillar electric gate S13;
the port of a controlled end 87 of the relay R1 is connected with the negative electrode of the landing gear warning buzzer, the port of a controlled end 30 of the relay R1 is grounded, and the port of a control end 86 is connected with the port C of the left pillar electric door S7 and the port UP of the landing gear control handle; the positive pole of the freewheel diode D2 is connected with the control end 85 port of the relay R1, and the negative pole of the freewheel diode D2 is connected with the control end 86 port of the relay R1, so that the control coil of the relay R1 is prevented from generating instant high voltage when being electrified or powered off.
Further, the positive pole of the landing gear warning buzzer is connected with a left main bus bar of the aircraft, the other end of the landing gear control handle is connected with the left main bus bar of the aircraft, and the NO port of the left pillar electric valve S7 is connected with the winding and unwinding electromagnetic valve.
Further, the C port of the right pillar electric door S13 communicates with the NC port, and the C port of the left pillar electric door S7 is connected with the NC port.
As shown in fig. 3, the working process of the utility model is as follows: when the aircraft is on the ground, the aircraft is electrified, the landing gear handle is at the DOWN position, the landing gear is in a normal DOWN state, no current flows through a control circuit of the control relay R1, the relay R1 does not work, the audible warning circuit is open, and no warning trigger exists;
when the aircraft is on the ground (the wheels bear weight), the aircraft is electrified, the landing gear handle is placed in the 'UP' position, the pillar electric door S7 on the left landing gear is in a disconnected state (as shown in figure 1, the C end is connected with the NC end), and the landing gear cannot be retracted; at this time, the right pillar electric door S13 is in a closed state (as shown in fig. 1, the C and NC ends are connected and conducted), the control circuit of the relay R1 works, the relay is attracted to make the 30 port and the 87 port connected and conducted, and the grounding circuit of the warning buzzer forms a passage to trigger an audible warning;
when the aircraft is in the air, the pillar switch S13 on the right landing gear is in the off state (as shown in fig. 1, the C and NO ends are connected), at which time, regardless of whether the landing gear handle is in the up or down position, the relay R1 control line is open, the relay is inactive, and the anti-false audible warning circuit is inactive.
According to the utility model, under the condition that the original circuit of the DA42 type is not changed, the control characteristics of the existing two landing gear pillar electric doors of the aircraft are fully utilized, and by additionally arranging a relay (a freewheel diode is required to be installed in parallel), an isolation diode and related electric wires at the rear part of an instrument board, landing gear control handles are mistakenly placed in the 'retracted' position on the ground under the condition that normal operation of a landing gear system is not influenced, landing gear acoustic warning is triggered, the safety margin of the aircraft is improved, and the landing gear electric door has practicability.
In practical application, the isolation diode D1, the freewheeling diode D2, the relay R1 and related electrical wires are all arranged at the rear part of the instrument panel, and the relay and the diode with the same specification are adopted. The landing gear control handle can trigger the landing gear acoustic warning when the landing gear control handle is placed on the 'retracted' position by mistake on the ground under the condition that the normal operation of the landing gear system is not affected and the safety of an airplane is guaranteed, and the safety of the airplane is guaranteed.
The foregoing is merely a preferred embodiment of the utility model, and it is to be understood that the utility model is not limited to the form disclosed herein but is not to be construed as excluding other embodiments, but is capable of numerous other combinations, modifications and environments and is capable of modifications within the scope of the inventive concept, either as taught or as a matter of routine skill or knowledge in the relevant art. And that modifications and variations which do not depart from the spirit and scope of the utility model are intended to be within the scope of the appended claims.
Claims (3)
1. An aircraft landing gear ground anti-misoperation sound warning circuit based on isolation protection is characterized in that: the device comprises a relay R1, an isolation diode D1, a freewheel diode D2 and an undercarriage warning buzzer;
the positive electrode of the isolation diode D1 is connected with the port of the control end 85 of the relay R1, the negative electrode of the isolation diode D1 is connected with the port C of the right pillar electric door S13, and the port NC of the right pillar electric door S13 is grounded, so that the grounding can be provided for a plurality of parts or systems of the aircraft; isolating the plurality of components or systems connected to the C port of the right pillar electric door S13 by an isolation diode D1;
the port of a controlled end 87 of the relay R1 is connected with the negative electrode of the landing gear warning buzzer, the port of a controlled end 30 of the relay R1 is grounded, and the port of a control end 86 is connected with the port C of the left pillar electric door S7 and the port UP of the landing gear control handle;
the positive pole of the freewheel diode D2 is connected with the control end 85 port of the relay R1, the negative pole of the freewheel diode D2 is connected with the control end 86 port of the relay R1, and the freewheel diode D2 is used for preventing the control coil of the relay R1 from generating instant high voltage when being electrified or powered off, and protecting elements in a circuit from being broken down or burnt by induced voltage.
2. An aircraft landing gear ground anti-false sound warning circuit based on isolation protection as claimed in claim 1, wherein: the landing gear warning buzzer is characterized in that the anode of the landing gear warning buzzer is connected with a left main bus bar of the aircraft, the other end of the landing gear control handle is connected with the left main bus bar of the aircraft, and the NO port of the left pillar electric valve S7 is connected with the winding and unwinding electromagnetic valve.
3. An aircraft landing gear ground anti-false sound warning circuit based on isolation protection as claimed in claim 1, wherein: when the landing gear of the aircraft is put down and the ground of the aircraft wheel bears load, the C port of the right pillar electric valve S13 is communicated with the NC port, and the C port of the left pillar electric valve S7 is connected with the NC port.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320546645.XU CN219584473U (en) | 2023-03-20 | 2023-03-20 | Ground anti-misoperation sound warning circuit for aircraft landing gear based on isolation protection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320546645.XU CN219584473U (en) | 2023-03-20 | 2023-03-20 | Ground anti-misoperation sound warning circuit for aircraft landing gear based on isolation protection |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219584473U true CN219584473U (en) | 2023-08-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320546645.XU Active CN219584473U (en) | 2023-03-20 | 2023-03-20 | Ground anti-misoperation sound warning circuit for aircraft landing gear based on isolation protection |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219584473U (en) |
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2023
- 2023-03-20 CN CN202320546645.XU patent/CN219584473U/en active Active
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