CN117163282A - Landing gear stowing control circuit - Google Patents
Landing gear stowing control circuit Download PDFInfo
- Publication number
- CN117163282A CN117163282A CN202311192238.4A CN202311192238A CN117163282A CN 117163282 A CN117163282 A CN 117163282A CN 202311192238 A CN202311192238 A CN 202311192238A CN 117163282 A CN117163282 A CN 117163282A
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- CN
- China
- Prior art keywords
- landing gear
- contact
- control circuit
- stowing
- circuit
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 238000006243 chemical reaction Methods 0.000 claims description 3
- 230000007935 neutral effect Effects 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
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Abstract
The invention discloses a landing gear retraction control circuit, and belongs to the field of landing gear retraction control system design in the aviation field. In the landing gear stowing control circuit, the interlocking of the wheel-mounted switch is added. When the aircraft wheel lands (the aircraft landing gear strut is in a compressed state), the loop of the landing gear stowing control circuit is disconnected, and the landing gear stowing electromagnetic valve is not powered even though the landing gear stowing is operated; when the aircraft wheel is not grounded (the aircraft landing gear strut is in a released state), the landing gear can be normally retracted. The landing gear locking device avoids the risk of collision with the landing gear strut mechanical locking device due to the fact that the landing gear operating switch is misoperation to retract and drop the landing gear when the aircraft wheel lands and the landing gear retracting and releasing actuating cylinder is used for compressing and retracting and dropping the landing gear.
Description
Technical Field
The invention belongs to the field of design of landing gear retraction control systems in the aviation field, and relates to a landing gear retraction control circuit.
Background
Landing gear control is divided into electrical control and mechanical control. The electrical control portion generally includes stow control circuitry and drop control circuitry for controlling stow and drop of the aircraft landing gear. The control circuit generally comprises a landing gear retraction control circuit power supply, a circuit breaker, a landing gear operating switch, a hydraulic electromagnetic valve, and other logic control switches (such as signals for controlling the hydraulic source oil level position, landing gear cabin door position, landing gear position and the like of retraction of the landing gear) in the landing gear circuit. The mechanical part is generally composed of a hydraulic source, a hydraulic electromagnetic valve, corresponding pipelines and the like.
The landing gear retraction control circuit supplies power to the landing gear control switch through the circuit device, when the landing gear control switch is retracted or put down, the retraction or put down circuit is switched on, the landing gear retraction or landing gear put down hydraulic electromagnetic valve is powered through other logic control switches, and after the hydraulic electromagnetic valve works, the mechanical control part hydraulic source drives the landing gear to retract or put down.
At present, the landing gear electric control part of various airplanes has no interlocking with the wheel-mounted switch, and when the airplane wheel lands, the landing gear operation switch is operated by mistake to retract and drop the landing gear, and the landing gear retraction actuator cylinder is used for pressing and retracting and dropping the landing gear, so that the landing gear is in conflict with the landing gear strut mechanical locking device. The technical problem to be solved by the invention is to technically avoid the risk.
Disclosure of Invention
In order to solve the above problems in the prior art, the present invention provides a landing gear stowing control circuit. In the landing gear stowing control circuit, interlocking of the wheel-mounted switch is added. When the aircraft wheel lands (the aircraft landing gear strut is in a compressed state), the loop of the landing gear stowing control circuit is disconnected, and the landing gear stowing electromagnetic valve is not powered even though the landing gear stowing is operated; when the aircraft wheel is not grounded (the aircraft landing gear strut is in a released state), the landing gear can be normally retracted.
The technical scheme of the invention is as follows:
a landing gear stowing control circuit comprises a landing gear control circuit, a protection circuit and a landing gear stowing circuit.
The landing gear control circuit comprises a landing gear control circuit power supply V1, a landing gear retraction control circuit breaker K1 and a landing gear control switch K2; wherein, K2 has 3 conversion states, namely neutral (A), put down (B) and stow (C). V1 is connected with movable contact O of K2 in series after passing through K1.
The protection circuit comprises 1 wheel-mounted switch W1, wherein a D, F contact of the W1 is a normally closed contact, and a E, H contact of the W1 is a normally open contact; when the aircraft wheel is grounded (the aircraft landing gear leg is in a compressed state), the E, H contact is open and the D, F contact is closed; when the aircraft wheel is not grounded (the aircraft landing gear leg is in the released state), the E, H contact is closed and the D, F contact is open.
The landing gear stowing circuit comprises a rest control logic circuit L1 in the landing gear stowing circuit and a landing gear stowing hydraulic electromagnetic valve D1. L1 and D1 are connected in series and then connected with 'GND', and the 'GND' is the power ground of a power supply V1 in the landing gear control circuit.
The landing gear stowing contact C of the landing gear operating switch K2 in the landing gear control circuit is connected with the normally open contact E of the wheel load switch W1 in the protection circuit, and the normally open contact H of the wheel load switch W1 is connected with the L1 in the landing gear stowing circuit. When the aircraft wheel is grounded (the aircraft landing gear leg is in a compressed state), since W1 is disconnected E, H, even if landing gear steering switch K2 is erroneously actuated to the retracted position (O is connected to C), landing gear retraction hydraulic solenoid valve D1 does not operate. The landing gear stow may be operated only when the aircraft wheels are not grounded (the aircraft landing gear leg is in the released state) and the E, H of the wheel load switch W1 is closed.
The invention has the beneficial effects that: according to the landing gear locking device, the interlocking of the wheel-mounted switch is added in the landing gear retraction circuit, so that the risk of collision with the landing gear strut mechanical locking device due to the fact that the landing gear operation switch is misoperated to retract and drop the landing gear and the landing gear retraction actuating cylinder is used for compressing and retracting and dropping the landing gear when the aircraft wheels land is avoided from design.
Drawings
FIG. 1 is a schematic diagram of the landing gear stow control circuit of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings.
As shown in fig. 1, the invention provides a landing gear stowing control circuit, which comprises a landing gear control circuit, a protection circuit and a landing gear stowing circuit.
The landing gear control circuit comprises a landing gear control circuit power supply V1, a landing gear retraction control circuit breaker K1 and a landing gear control switch K2; wherein, K2 has 3 conversion states, namely neutral (A), put down (B) and stow (C). V1 is connected with movable contact O of K2 in series after passing through K1.
The protection circuit comprises 1 wheel-mounted switch W1, wherein a D, F contact of the W1 is a normally closed contact, and a E, H contact of the W1 is a normally open contact; when the aircraft wheel is grounded (the aircraft landing gear leg is in a compressed state), the E, H contact is open and the D, F contact is closed; when the aircraft wheel is not grounded (the aircraft landing gear leg is in the released state), the E, H contact is closed and the D, F contact is open.
The landing gear retraction circuit comprises a rest control logic circuit L1 (such as signals for controlling the hydraulic source oil level position, the landing gear cabin door position, the landing gear position and the like for retraction and extension of the landing gear) and a landing gear retraction hydraulic electromagnetic valve D1. L1 and D1 are connected in series and then connected with 'GND', and the 'GND' is the power ground of a power supply V1 in the landing gear control circuit.
The landing gear stowing contact C of the landing gear operating switch K2 in the landing gear control circuit is connected with the normally open contact E of the wheel load switch W1 in the protection circuit, and the normally open contact H of the wheel load switch W1 is connected with the L1 in the landing gear stowing circuit. When the aircraft wheel is grounded (the aircraft landing gear leg is in a compressed state), since W1 is disconnected E, H, even if landing gear steering switch K2 is erroneously pushed to the retracted position (O is connected to C), landing gear retraction hydraulic solenoid valve D1 does not operate. The landing gear stow may be operated only when the aircraft wheels are not grounded (the aircraft landing gear leg is in the released state) and the E, H of the wheel load switch W1 is closed.
Claims (1)
1. The landing gear stowing control circuit is characterized by comprising a landing gear control circuit, a protection circuit and a landing gear stowing circuit;
the landing gear control circuit comprises a landing gear control circuit power supply V1, a landing gear retraction control circuit breaker K1 and a landing gear control switch K2; wherein, K2 has 3 conversion states, which are neutral A, down B and up C respectively; v1 is connected with movable contact O of K2 in series after passing through K1;
the protection circuit comprises 1 wheel-mounted switch W1, wherein a D, F contact of the W1 is a normally closed contact, and a E, H contact of the W1 is a normally open contact; when the airplane wheel lands, the E, H contact is opened, and the D, F contact is closed; when the airplane wheel is not grounded, the E, H contact is closed, and the D, F contact is opened;
the landing gear retraction circuit comprises a rest control logic circuit L1 and a landing gear retraction hydraulic electromagnetic valve D1 in the landing gear retraction circuit; l1 and D1 are connected in series and then connected with 'GND', wherein the 'GND' is the power ground of a power supply V1 in the landing gear control circuit;
the landing gear stowing contact C of the landing gear operating switch K2 in the landing gear control circuit is connected with the normally open contact E of the wheel load switch W1 in the protection circuit, and the normally open contact H of the W1 is connected with the L1 in the landing gear stowing circuit; when the aircraft wheel lands, E, H in W1 is disconnected, and even if the landing gear operating switch K2 is driven to the retracted position, the landing gear retraction hydraulic solenoid valve D1 does not work; landing gear stowage may be operated only when E, H of the wheel load switch W1 is closed when the aircraft wheels are not grounded.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311192238.4A CN117163282A (en) | 2023-09-15 | 2023-09-15 | Landing gear stowing control circuit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311192238.4A CN117163282A (en) | 2023-09-15 | 2023-09-15 | Landing gear stowing control circuit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117163282A true CN117163282A (en) | 2023-12-05 |
Family
ID=88944764
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311192238.4A Pending CN117163282A (en) | 2023-09-15 | 2023-09-15 | Landing gear stowing control circuit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117163282A (en) |
-
2023
- 2023-09-15 CN CN202311192238.4A patent/CN117163282A/en active Pending
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