CN112455662A - Aircraft landing gear warning initiation and cancellation circuitry and method - Google Patents
Aircraft landing gear warning initiation and cancellation circuitry and method Download PDFInfo
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- CN112455662A CN112455662A CN202010988925.7A CN202010988925A CN112455662A CN 112455662 A CN112455662 A CN 112455662A CN 202010988925 A CN202010988925 A CN 202010988925A CN 112455662 A CN112455662 A CN 112455662A
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- 230000000977 initiatory effect Effects 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title claims abstract description 25
- 230000008030 elimination Effects 0.000 claims abstract description 19
- 238000003379 elimination reaction Methods 0.000 claims abstract description 19
- 230000003213 activating effect Effects 0.000 claims description 5
- 230000009977 dual effect Effects 0.000 claims description 2
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/26—Control or locking systems therefor
- B64C25/28—Control or locking systems therefor with indicating or warning devices
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Abstract
The application provides a circuit and a method for initiating and eliminating aircraft landing gear warning, and relates to the field of civil aviation. An aircraft undercarriage warning initiation and elimination circuit comprises an undercarriage lowering in-place switch, a warning device, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first accelerator position switch, a second accelerator position switch, a flap in-place switch and a warning elimination device, wherein the warning device is connected with the flap warning logic control relay and the first warning control relay, and the flap warning logic control relay is connected with the flap in-place switch and the second warning control relay; the first warning control relay is connected with the second warning control relay; the warning cancellation means connects the first warning control relay and the second warning control relay. The warning and eliminating logic that this application can satisfy CCAR23 airworthiness regulation requirement solves the complicated problem of traditional warning circuit to have characteristics such as simple structure, high reliability, with low costs.
Description
Technical Field
The application relates to the field of civil aviation, in particular to a circuit and a method for initiating and eliminating aircraft landing gear warning.
Background
The CCAR23.729(f) landing gear warning of the general aviation administration airworthiness regulation in China stipulates that for land aircraft, the following audible or equivalent landing gear warning devices must be provided:
(1) the device will sound continuously when one or more of the throttles are retracted beyond the normal landing approach without the landing gear fully down and locked. The throttle stop must be used as an audible device. If the warning device specified in this article is provided with a manual stopping measure, the warning system must be designed such that: when the warning has been suspended after retraction of one or more of the throttles, and subsequent reduction of either throttle to (or beyond) the normal landing approach position, the warning device will be activated;
(2) when using a normal landing procedure, the device will sound continuously when the flaps are lowered to a flap position beyond maximum approach, while the landing gear is not fully lowered and locked. The device must not be provided with manual sound stopping measures. The flap position sensor may be mounted at any suitable location. The device system may use any part of the device system (including the audible warning device) defined in clause (f) (1).
In the prior art, the Chinese invention patent 'an amphibious aircraft landing gear retraction mechanism position warning device' (application number: 201410588929.0) discloses an amphibious aircraft landing gear retraction mechanism position warning device, which comprises a flight warning computer, a radio altimeter, a flap control system and a landing gear retraction system, wherein the flight warning computer comprehensively processes collected information according to a warning logic judgment flow and drives a warning device to provide warning for a unit. The technology has the following defects: [1] the warning circuit is designed for an amphibious learning machine, and the warning logic is complex; [2] a special alarm computer is needed, and a hardware system is complex; [3] it has no versatility.
Therefore, a need exists for a warning initiation and elimination circuit for a universal aircraft landing gear, which is simple and has good universality on the basis of meeting the warning conditions of CCAR23.729(f) landing gears in China civil aviation administration airworthiness regulations.
Disclosure of Invention
Based on the circuit and the method, the warning initiation and elimination circuit and the warning initiation and elimination method for the aircraft landing gear can meet warning and elimination logics required by airworthiness regulations, solve the problem that a traditional warning circuit is complex, and have the characteristics of simple structure, high reliability, low cost and the like.
According to one aspect of the application, an aircraft landing gear warning initiation and elimination circuit is provided, comprising a landing gear lowering in-place switch, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in-place switch, and a warning elimination device, wherein,
the first end of the alarm is connected with a power supply, the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay, the flap warning logic control relay is connected with the first end of the first throttle position switch, the first end of the second throttle position switch, the first end of the flap in-place switch and the second warning control relay, the second end of the first throttle position switch is connected with the first warning control relay, the second end of the second throttle position switch is connected with the second warning control relay, and the second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear lowering position switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear put-in-place switch is grounded; the warning cancellation means connects the first warning control relay and the second warning control relay.
According to a second aspect of the present application, there is provided an aircraft landing gear warning initiation and cancellation method comprising:
when the first accelerator is retracted to exceed the normal landing approach position, so that the first accelerator position is opened and closed and at least one switch is not closed in the landing gear put-down position switch, the alarm is connected with the ground through the first warning control relay, the first accelerator position switch and the landing gear put-down position switch in the non-closed position to give an alarm; and
activating the alarm eliminating device triggers the change of the internal connection mode of the first alarm control relay, so that the alarm is eliminated without a grounding path.
When the first accelerator is retracted to exceed the normal landing entrance position and the second accelerator is retracted to exceed the normal landing entrance position, so that the second accelerator position is switched on and off and at least one switch is not switched on in the landing gear lowering in-place switch, the alarm is switched on to the ground through the second warning control relay, the second accelerator position switch and the landing gear lowering in-place switch in the non-closed position to give an alarm;
the alarm cannot be cleared by activating the alarm clearing means.
According to a third aspect of the present application, there is provided an aircraft landing gear warning initiation method comprising:
detecting whether the condition that the flap lowering exceeds the normal landing approach position so that the flap in-place switch is closed and at least one switch is not closed exists in the landing gear lowering in-place switch is met; and
in the event that the condition is met, the alarm is connected to ground to sound an alarm by a flap warning logic control relay and landing gear down position switch in the non-closed position.
The alarm cannot be cleared by activating the alarm clearing means.
The circuit and the method for initiating and eliminating the warning of the aircraft landing gear have the characteristics of clear control logic, simple circuit structure and high reliability, have universality and are suitable for initiating and eliminating the warning of the aircraft landing gear of common models.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without exceeding the protection scope of the present application.
FIG. 1 is a schematic block diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application.
FIG. 2 is a block diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application. FIG. 3 is a flow chart of an aircraft landing gear warning initiation and elimination method according to an embodiment of the application.
Detailed Description
The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some, but not all, embodiments of the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
According to one aspect of the present application, an aircraft landing gear warning initiation and cancellation circuit is provided. FIG. 1 is a schematic block diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application. As shown in FIG. 1, the aircraft landing gear warning initiation and elimination circuit comprises an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in-position switch, a landing gear down in-position switch, and a warning elimination device.
In fig. 1, a first end of an alarm is connected with a power supply, a second end of the alarm is connected with a flap warning logic control relay and a first warning control relay, the flap warning logic control relay is connected with a first end of a first throttle position switch, a first end of a second throttle position switch, a first end of a flap in-place switch and a second warning control relay, a second end of the first throttle position switch is connected with the first warning control relay, a second end of the second throttle position switch is connected with the second warning control relay, and a second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear lowering position switch is connected with a flap warning logic control relay, the first end of the first accelerator position switch, the first end of the second accelerator position switch and the second warning control relay; the second end of the landing gear lowering in-place switch is grounded; the warning cancellation means connects the first warning control relay and the second warning control relay.
In fig. 1, the number of landing gear down position switches may be one, two, three, etc. In one particular embodiment, the number of landing gear down position switches is 3, such as in particular a nose landing gear down position switch, a left landing gear down position switch, and a right landing gear down position switch. Thus, according to the circuit shown in fig. 1, the first end of the nose landing gear lowering in-place switch, the first end of the left landing gear lowering in-place switch, and the first end of the right landing gear lowering in-place switch are respectively connected to the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch, and the second warning control relay, and the second end of the nose landing gear lowering in-place switch, the second end of the left landing gear lowering in-place switch, and the second end of the right landing gear lowering in-place switch are respectively grounded.
In fig. 1, the first and second throttle position switches may be embodied as left and right throttle position switches of the aircraft or right and left throttle position switches of the aircraft. The alarm includes a buzzer. The flap warning logic control relay comprises an electromagnetic relay, such as 1432875-1 from TE corporation. The first or second warning control relay comprises a dual coil electromagnetic relay, for example, a loose DS2E-ML2-DC 24V. The gear-down-position switch, the first throttle position switch, and the second throttle position switch comprise travel switches, such as 1SE1 from honeywell.
FIG. 2 is a block diagram of an aircraft landing gear warning initiation and cancellation circuit according to one embodiment of the present application. As shown in fig. 2, the aircraft landing gear warning initiation and cancellation circuit includes a power supply, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap-in-position switch, a landing gear-down-in-position switch, and a warning cancellation device.
In fig. 2, the power source is embodied as a +28V bus bar. The first end of the alarm is connected with a power supply, and the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay. Specifically, in the embodiment shown in FIG. 2, the second end of the alarm is connected to pin 87 of the flap warning logic control relay and pin 11 of the first warning control relay.
In fig. 2, the flap warning logic control relay is connected to a first terminal of the first throttle position switch, a first terminal of the second throttle position switch, a first terminal of the flap in-position switch, and the second warning control relay. Specifically, in the embodiment shown in fig. 2, pin 30 of the flap warning logic control relay is connected to a first terminal (terminal C) of the first throttle position switch, a first terminal (terminal C) of the second throttle position switch, and pin 4 of the second warning control relay; pin 85 of the flap warning logic control relay is connected to a first (C) terminal of the flap in position switch.
In fig. 2, the second end of the first throttle position switch is connected to the first warning control relay, the second end of the second throttle position switch is connected to the second warning control relay, and the second end of the flap-in-place switch is grounded. Specifically, in the embodiment shown in fig. 2, the NC terminal of the first throttle position switch is connected to the first warning control relay pin 15, the NO terminal of the first throttle position switch is connected to the first warning control relay pin 13, the NC terminal of the second throttle position switch is connected to the second warning control relay pin 15, and the NO terminal of the second throttle position switch is connected to the second warning control relay pin 13.
In fig. 2, the first warning control relay is connected to the second warning control relay. Specifically, in the embodiment shown in fig. 2, pins 1, 2, 4, and 8 of the first warning control relay are connected to pins 1, 2, 8, and 11 of the second warning control relay, respectively.
The first end of the landing gear lowering position switch is connected with a flap warning logic control relay, the first end of the first accelerator position switch, the first end of the second accelerator position switch and the second warning control relay; the second end of the landing gear down position switch is grounded. Specifically, in the embodiment shown in fig. 2, a first end (NC terminal) of the landing gear down position switch is connected to pin 30 of the flap warning logic control relay, a first end (C terminal) of the first throttle position switch, a first end (C terminal) of the second throttle position switch, and pin 4 of the second warning control relay; the second (C) end of the landing gear down position switch is grounded.
In the embodiment shown in fig. 2, the number of landing gear down position switches is 3: nose gear down-in-place switch S1, left gear down-in-place switch S3, and right gear down-in-place switch S4. It should be noted that although the nose gear down-in-place switch, the left gear down-in-place switch, and the right gear down-in-place switch are respectively one in fig. 2, i.e., S1, S3, and S4, the number of the nose gear down-in-place switch, the left gear down-in-place switch, and the right gear down-in-place switch may be two or more, respectively. In practical application, the states of the closed positions and the non-closed positions of the plurality of nose landing gear put-down position switches are kept consistent, the states of the closed positions and the non-closed positions of the plurality of left landing gear put-down position switches are kept consistent, and the states of the closed positions and the non-closed positions of the plurality of right landing gear put-down position switches are also kept consistent. According to the circuit shown in fig. 2, the first end (NC end) of the nose landing gear lowering in-place switch, the first end (NC end) of the left landing gear lowering in-place switch, and the first end (NC end) of the right landing gear lowering in-place switch are connected to the pin 30 of the flap warning logic control relay, the first end (C end) of the first throttle position switch, the first end (C end) of the second throttle position switch, and the pin 4 of the second warning control relay, respectively, and the second end (C end) of the nose landing gear lowering in-place switch, the second end (C end) of the left landing gear lowering in-place switch, and the second end (C end) of the right landing gear lowering in-place switch are grounded, respectively.
In fig. 2, the warning cancellation means connects the first warning control relay and the second warning control relay. Specifically, in the embodiment shown in fig. 2, the warning cancellation device is connected with one end connected to the power supply and the other end connected to the pin 1 of the first warning control relay and the pin 1 of the second warning control relay.
In the embodiment shown in fig. 2, the NO terminals and NC terminals of the first throttle position switch, the second throttle position switch, the flap-in-place switch, and the landing gear down-in-place switch respectively represent the closed state and the non-closed state of the corresponding switches, wherein the closed states of the first throttle position switch, the second throttle position switch, and the flap-in-place switch respectively represent that the first throttle position, the second throttle position, and the flap position exceed the normal landing approach position, and the closed state of the landing gear down-in-place switch represents that the landing gear is down in place; the unclosed states of the first throttle position switch, the second throttle position switch and the flap in-place switch respectively represent that the positions of the first throttle, the second throttle and the flap do not exceed the normal landing approach position, and the unclosed state of the landing gear put-down in-place switch represents that the landing gear is not put down in place.
The embodiment shown in fig. 2 shows the specific arrangement and connection relationship of the circuit components, in particular the pin arrangement and connection relationship of the flap warning logic control relay, the first warning control relay and the second warning control relay. However, it should be noted that the pin arrangement and connection relationships of the circuit components of fig. 2, especially the flap warning logic control relay, the first warning control relay and the second warning control relay are not unique or fixed, and those skilled in the art can select other components, other pin arrangements and other connection relationships that can be used as the flap warning logic control relay, the first warning control relay and the second warning control relay as long as the landing gear warning condition and warning logic of CCAR23.729(f) item of general aviation regulation in china can be satisfied, and all of these are within the scope covered by the present application.
The operation of the aircraft landing gear warning initiation and cancellation circuit is described in detail below with reference to the above-described block diagrams of the aircraft landing gear warning initiation and cancellation circuit shown in fig. 1 and 2.
As shown in fig. 2, when the first throttle retraction exceeds the normal landing approach position to trigger the first throttle position switch S5 to be in the closed position, and thus there is at least one of the nose landing gear down position switch S1, the left landing gear position switch S3 and the right landing gear position switch S4 that is not closed, i.e., there is a C terminal connected to the NC terminal, the "-" terminal of the alarm is connected to ground through the 11 and 13 pins of the first warning control relay, the NO and C terminals of the first throttle position switch S5, and the NC and C terminals of some landing gear down position switch together, and since the "+" terminal of the alarm is always connected to the +28V power supply, the alarm sounds a continuous warning tone at this time.
When the alarm eliminating device K1 is pressed, the SET coil of the first alarm control relay is electrified, the pin 13 is connected with the pin 9, the pin 8 is connected with the pin 4, and the "-" pole of the alarm has no passage to the ground, the buzzer stops sounding, and the alarm is eliminated.
At this time, when the second throttle retraction exceeds the normal landing approach position to trigger the second throttle position switch S6 to be in the closed position, the alarm is again continuously sounded with an alarm sound through the "minus" pole of the alarm via the 11 and 13 feet of the second alarm control relay, the NO and C feet of the second throttle position switch S6, and the NC and C ends of the landing gear down position switch.
Under the condition that the first throttle and the second throttle are retracted to exceed the normal landing approach position to trigger the first throttle position switch S5 and the second throttle position switch S6 to be in the closed position, the warning eliminating device K1 is started, SET coils of the first warning control relay and the second warning control relay are electrified, respective 13 feet and 9 feet are communicated, 8 feet and 4 feet are communicated, a '-' pole of the alarm is communicated with the ground through the 8 feet and 4 feet of the first warning control relay, the 8 feet and 4 feet of the second warning control relay, and NC and C ends of a certain landing frame and the landing position switch, and warning sound of the alarm cannot be eliminated.
The operation process of the aircraft landing gear warning initiation and elimination circuit under the condition of firstly receiving the first throttle and then receiving the second throttle is described above, and the process of firstly receiving the second throttle and then receiving the first throttle is similar to the process described above, and the description is not repeated.
When the flap is put down to exceed the normal landing approach position, namely the flap in-place switch S7 is closed, the flap warning logic control relay is closed, if at the moment, at least one landing gear put-down in-place switch among the nose landing gear put-down in-place switch S1, the left landing gear put-in-place switch S3 and the right landing gear put-in-place switch S4 is not closed, namely the C end is communicated with the NC end, the < - > pole of the warning buzzer is communicated with the ground through the 87 and 30 feet of the flap warning logic control relay and the NC and C feet of a certain landing gear put-down in-place switch, and the alarm gives continuous warning sound and cannot be turned off through the warning eliminating device.
As can be seen from the above description, when there is at least one of the landing gear down position switches that is not closed, a warning sound is emitted when one of the first and second throttles exceeds the normal landing approach position, and the warning can be removed; when the positions of the first throttle and the second throttle exceed the normal landing approach position, a warning sound is given out, and the warning cannot be eliminated; when the flap position exceeds the normal landing approach position, a warning tone is sounded regardless of the position of the first throttle and the second throttle, and the warning cannot be eliminated. It can be seen that the aircraft landing gear warning initiation and cancellation circuitry meets the warning and cancellation logic required by airworthiness regulations.
According to another aspect of the present application, an aircraft landing gear warning initiation and elimination method is provided. FIG. 3 is a flow chart of an aircraft landing gear warning initiation and elimination method according to an embodiment of the application. As shown in fig. 3, the method includes the following steps.
And S301, when the first accelerator is retracted to exceed the normal landing entrance position, so that the first accelerator position switch is closed and at least one switch in the landing gear put-down position switch is not closed, the alarm is connected with the ground through the first warning control relay, the first accelerator position switch and the landing gear put-down position switch in the non-closed position to give an alarm.
According to the embodiment shown in FIG. 2, when the first throttle retraction exceeds the normal landing approach position triggering the first throttle position switch S5 to be in the closed position, such that there is at least one of the nose gear-down in-position switch S1, the left gear-in-position switch S3 and the right gear-in-position switch S4 that is not closed, i.e., there is a C terminal connected to the NC terminal, the "-" terminal of the alarm is connected to ground through the 11 and 13 terminals of the first warning control relay, the NO and C terminals of the first throttle position switch S5, and the NC and C terminals of a certain landing gear-down in-position switch, and the alarm sounds a continuous warning tone at this time since the "+" terminal of the alarm is always connected to +28V power.
Step S302, starting an alarm eliminating device to trigger the change of the internal connection mode of the first alarm control relay, so that the alarm is eliminated without a grounding path.
According to the embodiment shown in fig. 2, when the alarm cancellation device K1 is pressed, the SET coil of the first alarm control relay is energized, pin 13 is connected with pin 9, pin 8 is connected with pin 4, and the "-" pole of the alarm is not connected to the ground, the buzzer is turned off, and the alarm is cancelled.
And step S303, when the second accelerator is retracted to exceed the normal landing entrance position, so that the second accelerator position switch is closed and at least one switch in the landing gear put-down position switch is not closed, the alarm is connected with the ground through the second warning control relay, the second accelerator position switch and the landing gear put-down position switch in the non-closed position to give an alarm.
According to the embodiment shown in FIG. 2, when the second throttle retraction exceeds the normal landing approach position triggering the second throttle position switch S6 to be in the closed position, the alarm continues to sound again by the "-" pole of the alarm through the 11 and 13 feet of the second warning control relay, the NO and C feet of the second throttle position switch S6, and the NC and C ends of the landing gear down position switch being again connected to ground.
Step S304, starting the warning eliminating device to trigger the change of the internal connection mode of the first warning control relay and the second warning control relay, so that the alarm is connected with the ground through the first warning control relay, the second warning control relay and the landing gear put-down-to-position switch in the non-closed position, and the alarm continues to give an alarm.
According to the embodiment shown in fig. 2, in the case that the first throttle and the second throttle are both retracted beyond the normal landing approach position to trigger the first throttle position switch S5 and the second throttle position switch S6 to be in the closed position, the warning eliminating device K1 is started, the SET coils of the first warning control relay and the second warning control relay are powered on, the respective 13 feet and 9 feet are connected, the 8 feet and 4 feet are connected, the "-" pole of the alarm passes through the 8 feet and 4 feet of the first warning control relay, the 8 feet and 4 feet of the second warning control relay, and the NC end and the C end of a certain landing frame lowering position switch are connected with the ground, and the warning sound of the alarm cannot be eliminated.
And S305, when the flap is lowered beyond the normal landing approach position so that the flap in-place switch is closed and at least one switch in the landing gear in-place switch is not closed, the alarm gives an alarm by switching on the flap warning logic control relay and the landing gear in the non-closed position in the landing gear in-place switch.
When the flap position exceeds the normal landing approach position, a warning tone is sounded regardless of the position of the first throttle and the second throttle, and the warning cannot be eliminated. Thus, the present application also provides an aircraft landing gear warning initiation method:
detecting whether the condition that the flap lowering exceeds the normal landing approach position so that the flap in-place switch is closed and at least one switch is not closed exists in the landing gear lowering in-place switch is met; and
in the event that the condition is met, the alarm is connected to ground to sound an alarm by a flap warning logic control relay and landing gear down position switch in the non-closed position.
According to the embodiment shown in fig. 2, when the flap is lowered beyond the normal landing approach position, namely the flap in-place switch S7 is closed, the flap warning logic control relay is closed, if at the moment, at least one landing gear down-in-place switch among the nose landing gear down-in-place switch S1, the left landing gear in-place switch S3 and the right landing gear in-place switch S4 is not closed, namely the C end is connected with the NC end, the '-' pole of the warning buzzer is connected with the ground through the 87 and 30 feet of the flap warning logic control relay and the NC and C feet of a certain landing gear down-in-place switch, and the alarm gives a continuous warning sound and cannot be turned off through the warning elimination device.
The circuit and the method for initiating and eliminating the warning of the aircraft landing gear have the characteristics of clear control logic, simple circuit structure and high reliability, have universality and are suitable for initiating and eliminating the warning of the aircraft landing gear of common models.
The foregoing detailed description of the embodiments of the present application has been presented to illustrate the principles and implementations of the present application, and the description of the embodiments is only intended to facilitate the understanding of the methods and their core concepts of the present application. Meanwhile, a person skilled in the art should, according to the idea of the present application, change or modify the embodiments and applications of the present application based on the scope of the present application. In view of the above, the description should not be taken as limiting the application.
Claims (10)
1. An aircraft landing gear warning initiation and elimination circuit comprises a landing gear lowering in-place switch, an alarm, a flap warning logic control relay, a first warning control relay, a second warning control relay, a first throttle position switch, a second throttle position switch, a flap in-place switch and a warning elimination device, wherein,
the first end of the alarm is connected with a power supply, the second end of the alarm is connected with the flap warning logic control relay and the first warning control relay, the flap warning logic control relay is connected with the first end of the first throttle position switch, the first end of the second throttle position switch, the first end of the flap in-place switch and the second warning control relay, the second end of the first throttle position switch is connected with the first warning control relay, the second end of the second throttle position switch is connected with the second warning control relay, and the second end of the flap in-place switch is grounded; the first warning control relay is connected with the second warning control relay; the first end of the landing gear lowering position switch is connected with the flap warning logic control relay, the first end of the first throttle position switch, the first end of the second throttle position switch and the second warning control relay; the second end of the landing gear put-in-place switch is grounded; the warning cancellation means connects the first warning control relay and the second warning control relay.
2. The circuit of claim 1, wherein the landing gear down in place switch comprises a nose gear down in place switch, a left landing gear down in place switch, and a right landing gear down in place switch, wherein a first end of the nose gear down in place switch, a first end of the left landing gear down in place switch, and a first end of the right landing gear down in place switch are connected to the flap warning logic control relay, a first end of the first throttle position switch, a first end of the second throttle position switch, and the second warning control relay, respectively, and wherein a second end of the nose gear down in place switch, a second end of the left landing gear down in place switch, and a second end of the right landing gear down in place switch are connected to ground, respectively.
3. The circuit of claim 1, wherein the alarm comprises a buzzer.
4. The circuit of claim 1, wherein the flap warning logic control relay comprises an electromagnetic relay.
5. The circuit of claim 1, wherein the first or second alert control relay comprises a dual coil electromagnetic relay.
6. The circuit of claim 1, wherein the gear-down-position switch, the first throttle position switch, and the second throttle position switch comprise travel switches.
7. An aircraft landing gear warning initiation and elimination method, comprising:
when the first accelerator is retracted to exceed the normal landing approach position, so that the first accelerator position is opened and closed and at least one switch is not closed in the landing gear put-down position switch, the alarm is connected with the ground through the first warning control relay, the first accelerator position switch and the landing gear put-down position switch in the non-closed position to give an alarm; and
activating the alarm eliminating device triggers the change of the internal connection mode of the first alarm control relay, so that the alarm is eliminated without a grounding path.
8. The method of claim 7, further comprising:
when the first accelerator is retracted to exceed the normal landing entrance position, the second accelerator is retracted to exceed the normal landing entrance position so that the second accelerator position switch is closed and at least one switch in the landing gear down-to-place switch is not closed, the alarm is connected with the ground through a second warning control relay, the second accelerator position switch and the landing gear down-to-place switch in the non-closed position to give an alarm; and
and activating the warning elimination device to trigger the change of the internal connection mode of the first warning control relay and the second warning control relay, so that the alarm is connected with the ground through the first warning control relay, the second warning control relay and the landing gear in the non-closed position, and the alarm continues to give an alarm.
9. The method of claim 7 or 8, further comprising:
when the flap is lowered beyond the normal landing approach position so that the flap-in-place switch is closed and at least one switch in the landing gear-in-place-down switch is not closed, the alarm is communicated with the ground through the flap warning logic control relay and the landing gear-in-place-down switch in the non-closed position to give an alarm.
10. An aircraft landing gear warning initiation method, comprising:
detecting whether the condition that the flap lowering exceeds the normal landing approach position so that the flap in-place switch is closed and at least one switch is not closed exists in the landing gear lowering in-place switch is met; and
in the event that the condition is met, the alarm is connected to ground to sound an alarm by a flap warning logic control relay and landing gear down position switch in the non-closed position.
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| CN112455662B (en) | 2024-02-02 |
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