CN214397207U - Undercarriage control device that receive and releases - Google Patents
Undercarriage control device that receive and releases Download PDFInfo
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- CN214397207U CN214397207U CN202022965495.5U CN202022965495U CN214397207U CN 214397207 U CN214397207 U CN 214397207U CN 202022965495 U CN202022965495 U CN 202022965495U CN 214397207 U CN214397207 U CN 214397207U
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Abstract
The utility model discloses an aircraft undercarriage receive and releases controlling means, including power, switch, undercarriage receive and release solenoid valve, through undercarriage receive and release solenoid valve carries out the receive and release action of undercarriage, a serial communication port, including two parallel receiving and releasing control circuits between switch and the undercarriage receive and release solenoid valve, one is computer control's normal receiving and releasing control circuit, and another is backup receiving and releasing control circuit, be equipped with backup undercarriage switch on the backup receiving and releasing control circuit, through the disconnection and the closure of backup undercarriage switch, realize the switching of normal receiving and releasing control and backup receiving and releasing control. According to the airplane undercarriage retraction control device, the two control systems can be switched back and forth by backing up the retraction rack switch. The state of the undercarriage system is monitored through the electromechanical computer, so that the fault detection rate is improved, the development cost of the airplane is saved, and the development period is shortened.
Description
Technical Field
The utility model relates to an aviation electrical control technical field especially relates to an undercarriage control device that receive and releases.
Background
The landing gear system of the airplane is the only part for supporting the weight of the whole airplane, and the normal folding and unfolding of the landing gear system directly influences the flight safety. A common aircraft landing gear system adopts two redundancy designs, one is a mode depending on traditional electric control, and the other is a mode depending on high-pressure nitrogen control. In the domestic aircraft, the traditional electrical control is mostly realized by still adopting a large number of relays to build a control logic, the control logic is simple and single, the monitoring on the state of the undercarriage system is insufficient, the fault detection rate is low, and the maintainability is poor. If the control conditions are changed, the control is realized at a large expense (the development cost of the airplane is increased, and the development period is prolonged). Under the condition that the traditional electrical control fails or fails, the aircraft only selects the landing gear which is controlled by the high-pressure nitrogen in an emergency release mode, but according to the judgment standard of accident signs of military aircraft, the situations are defined as accident signs, and the accident signs have great influence on the flight quality evaluation of the aircraft.
Disclosure of Invention
The utility model aims at solving current aircraft undercarriage and being two redundancy designs, being not enough to undercarriage system state control, the fault detection rate is low, and the poor technical problem of maintainability provides an aircraft undercarriage control device that receive and releases, monitors undercarriage system state through electromechanical computer, has promoted the fault detection rate, has practiced thrift the development cost of aircraft, has shortened the development cycle.
In order to solve the technical problem, the utility model provides an undercarriage control device that receive and releases, include: the landing gear control system comprises a power supply, a power switch and a landing gear retracting and releasing electromagnetic valve, wherein the landing gear retracting and releasing action of the landing gear is executed through the landing gear retracting and releasing electromagnetic valve; the landing gear retraction control system is characterized in that two parallel retraction control circuits are arranged between the power switch and the landing gear retraction electromagnetic valve, one is a normal retraction control circuit controlled by a computer, the other is a backup retraction control circuit, a backup landing gear switch is arranged on the backup retraction control circuit, and switching between normal retraction control and backup retraction control is realized by opening and closing the backup landing gear switch.
In an optional embodiment of the present application, the aircraft landing gear retraction control device further includes an emergency retraction control system, and the emergency retraction control system is a mechanical control system.
In an optional embodiment of the present application, the normal retraction control circuit comprises a landing gear operating switch, an electromechanical management computer; and when the undercarriage is normally retracted, the power supply, the power switch, the undercarriage control switch, the electromechanical management computer and the undercarriage retraction electromagnetic valve are electrically connected in sequence.
In an optional embodiment of the present application, the backup retraction control circuit comprises a backup landing gear switch and a backup landing gear relay; when the backup is retracted, the power supply, the power switch, the backup landing gear relay and the landing gear retraction electromagnetic valve are electrically connected in sequence.
In an optional embodiment of the present application, one end of the backup undercarriage relay is connected to the backup undercarriage switch, and the other end of the backup undercarriage relay is grounded, and the other two contact ends are respectively connected to the undercarriage control switch input end and the undercarriage retraction solenoid valve input end.
In an optional embodiment of the present application, the emergency retraction control system comprises an emergency landing gear switch, a cold air emergency valve, a nose gear uplock actuator, a left landing gear uplock actuator, a right landing gear uplock actuator, a nose gear uplock, a left landing gear uplock, a right landing gear uplock, a nose gear hydraulic oil lock, a left landing gear hydraulic oil lock, a right landing gear hydraulic oil lock, a nose landing gear actuator, a left landing gear actuator, and a right landing gear actuator; when the landing gear is in emergency retraction, the landing gear operating switch is arranged at a 'down' position, the emergency landing gear switch in the cabin is opened, high-pressure nitrogen enters the front landing gear uplock actuator cylinder, the left landing gear uplock actuator cylinder and the right landing gear uplock actuator cylinder respectively after passing through the cold air emergency valve, and the front landing gear uplock, the left landing gear uplock and the right landing gear uplock are opened respectively; after the lock is unlocked, high-pressure nitrogen respectively enters the nose landing gear actuator cylinder, the left landing gear actuator cylinder and the right landing gear actuator cylinder through the nose landing gear hydraulic oil lock, the left landing gear hydraulic oil lock and the right landing gear hydraulic oil lock, and the nose landing gear, the left landing gear and the right landing gear are put down in an emergency mode respectively.
The utility model provides an aircraft undercarriage control device that receive and releases, including power, switch, undercarriage receive and releases the solenoid valve, through undercarriage receive and releases the action that receive and releases of solenoid valve execution undercarriage, a serial communication port, including two parallel receiving and releasing control circuits between switch and the undercarriage receive and release the solenoid valve, one is computer control's normal receiving and releasing control circuit, and another is backup receiving and releasing control circuit, be equipped with backup undercarriage switch on the backup receiving and releasing control circuit, through the disconnection and the closure of backup undercarriage switch, realize normal receiving and releasing control and backup receiving and releasing control's switching.
The undercarriage retraction control device is provided with a normal retraction control system and a backup retraction control system, wherein the normal retraction control system collects state information of undercarriage switch signals (an undercarriage down end switch, an undercarriage up end switch and an undercarriage landing end switch) through an electromechanical management computer, and outputs corresponding control signals to an undercarriage retraction electromagnetic valve to realize the control retraction of the undercarriage after analysis. When the control system of the electromechanical management computer fails, the backup retraction control system controlled by the traditional circuit is operated, and the back-and-forth switching of the two control systems can be realized through the backup retraction landing switch. The state of the undercarriage system is monitored through the electromechanical computer, so that the fault detection rate is improved, the development cost of the airplane is saved, and the development period is shortened.
Furthermore, the undercarriage control device that receive and releases in this application adopts the design of three redundancy control, except normal receive and releases control system, the backup receive and releases control system, still is equipped with emergent receive and release control system, and under the circumstances that two kinds of control system all became invalid, the emergent receive and release control system that adopts high-pressure nitrogen gas control operates, on the basis that does not influence flight quality aassessment, has also promoted the reliability and the security of aircraft.
Drawings
In order to clearly illustrate the embodiments or technical solutions of the present invention, the drawings used in the description of the embodiments or the prior art 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 for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic diagram illustrating a principle of normal retraction and backup retraction in an aircraft landing gear retraction and extension control device provided in an embodiment of the present application.
Fig. 2 is a schematic diagram of an emergency retraction working principle of the undercarriage retraction control device provided in the embodiment of the present application.
Detailed Description
In order to make the technical field better understand the solution of the present invention, the following detailed description of the present invention is provided with reference to the accompanying drawings and the detailed description. It is to be understood that the embodiments described are only some embodiments of the invention, and not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
As shown in fig. 1, fig. 1 is a schematic diagram illustrating a principle of normal retraction and backup retraction in an aircraft landing gear retraction and extension control device provided in an embodiment of the present application, where the aircraft landing gear retraction and extension control device includes: the undercarriage control system comprises a power supply 1, a power switch 2 and an undercarriage retracting electromagnetic valve 3, wherein the undercarriage retracting electromagnetic valve 3 executes the retracting action of the undercarriage. The power switch 2 and the undercarriage retraction electromagnetic valve 3 comprise two parallel retraction control circuits, one is a normal retraction control circuit controlled by a computer, the other is a backup retraction control circuit, a backup undercarriage switch 6 is arranged on the backup retraction control circuit, and switching between normal retraction control and backup retraction control is realized by opening and closing the backup undercarriage switch 6.
Furthermore, the normal retraction control circuit comprises a landing gear operating switch 4 and an electromechanical management computer 5; and when the undercarriage is normally retracted, the power supply 1, the power switch 2, the undercarriage control switch 4, the electromechanical management computer 5 and the undercarriage retraction electromagnetic valve 3 are electrically connected in sequence. The state information of landing gear switch signals (a landing gear lowering terminal switch, a landing gear retracting terminal switch and a landing gear landing terminal switch) is collected by the electromechanical management computer 5, and corresponding control signals are output to the landing gear retracting electromagnetic valve 3 after analysis so as to realize the controlled retraction of the landing gear.
Further, the backup retraction control circuit comprises a backup landing gear switch 6 and a backup landing gear relay 7; when the backup is retracted, the power supply 1, the power switch 2, the backup undercarriage switch 6, the backup undercarriage relay 7 and the undercarriage retraction electromagnetic valve 3 are electrically connected in sequence.
The undercarriage retraction control device is provided with a normal retraction control system and a backup retraction control system, wherein the normal retraction control system collects state information of undercarriage switch signals (an undercarriage down end switch, an undercarriage up end switch and an undercarriage landing end switch) through an electromechanical management computer 5, and outputs corresponding control signals to an undercarriage retraction electromagnetic valve 3 after analysis to realize the control retraction of the undercarriage. When the control system of the electromechanical management computer 5 fails, a backup retraction control system controlled by a traditional circuit is arranged for operation, and the back-and-forth switching of the two control systems can be realized through the backup retraction frame switch 6. The state of the undercarriage system is monitored through the electromechanical computer 5, the fault detection rate is improved, the development cost of the airplane is saved, and the development period is shortened.
It should be noted that, in this embodiment, the normal retraction control circuit and the backup retraction control circuit are not limited to the above forms, as long as the switching between the two control circuits can be realized, and are not limited specifically.
In another embodiment of the present application, one end of the backup landing gear relay 7 is connected to the backup landing gear switch 6, and the other end is grounded, and the other two contact ends are respectively connected to the input end of the landing gear operating switch 4 and the input end of the landing gear retraction electromagnetic valve 3.
In another embodiment of the present application, the aircraft landing gear retraction control device further includes an emergency retraction control system, and the emergency retraction control system is a mechanical control system.
Further, as shown in fig. 2, fig. 2 is a schematic diagram of an emergency retraction working principle in the undercarriage retraction control device according to the embodiment of the present application. The emergency retraction control system is a high-pressure nitrogen control system and comprises an emergency landing gear switch 301, a cold air emergency valve 302, a nose gear uplock actuator cylinder 303, a left landing gear uplock actuator cylinder 304, a right landing gear uplock actuator cylinder 305, a nose gear uplock 306, a left landing gear uplock 307, a right landing gear uplock 308, a nose gear hydraulic oil lock 309, a left landing gear hydraulic oil lock 310, a right landing gear hydraulic oil lock 311, a nose gear actuator cylinder 312, a left landing gear actuator cylinder 313 and a right landing gear actuator cylinder 314; when in emergency retraction, the undercarriage control switch 4 is arranged at a 'down' position, an emergency undercarriage switch 301 in the cabin is opened, high-pressure nitrogen enters a nose undercarriage uplock actuator cylinder 303, a left undercarriage uplock actuator cylinder 304 and a right undercarriage uplock actuator cylinder 305 after passing through a cold air emergency valve 302, and a nose undercarriage uplock 306, a left undercarriage uplock 307 and a right undercarriage uplock 308 are opened respectively; after unlocking, the high-pressure nitrogen respectively enters the nose landing gear actuator cylinder 312, the left landing gear actuator cylinder 313 and the right landing gear actuator cylinder 314 through the nose landing gear hydraulic oil lock 309, the left landing gear hydraulic oil lock 310 and the right landing gear hydraulic oil lock 311, and the nose landing gear, the left landing gear and the right landing gear are put down in an emergency mode respectively.
According to the aircraft undercarriage retraction control device, a three-redundancy control design is adopted, an emergency retraction control system is further arranged besides a normal retraction control system and a backup retraction control system, the emergency retraction control system controlled by high-pressure nitrogen is adopted to operate under the condition that the two control systems fail, and reliability and safety of an aircraft are improved on the basis that flight quality assessment is not influenced.
The working principle of various retraction control systems is specifically analyzed below.
1) Working principle of normal retraction of undercarriage
As shown in fig. 1, the power switch 2 is turned on, the landing gear operating switch 4 is turned on in the retracting position, the landing gear releasing backup switch 6 is kept in the off state, the direct current of the power supply 1 sequentially passes through a wire [ 1Q1 ], a wire [ 1Q3 ], a contact 2 of the landing gear releasing backup relay 7, a contact 1 of the landing gear releasing backup relay 7, a wire [ 4Q3 ], a hole B of the landing gear operating switch 4, a hole D of the landing gear operating switch 4, a wire [ 4Q1 ], and a hole D of the electromechanical management computer 5, and at this time, the electromechanical management computer 5 analyzes according to the collected information of the on-landing gear switch state, judges whether the landing gear retracting command can be executed, and if the landing gear retracting command cannot be executed, the command is not output; if the undercarriage control system can be executed, current is output, and the undercarriage retracting and releasing electromagnetic valve 3 is driven to actuate through the hole A of the electromechanical management computer 5, a lead (6Q 1) and the hole 2 of the undercarriage retracting and releasing electromagnetic valve 3, so that the undercarriage retracting and releasing instruction is executed.
2) Working principle of landing gear
As shown in fig. 1, the power switch 2 is turned on, the "down" position of the landing gear operating switch 4 is turned on, the backup landing gear releasing switch 6 is kept in the off state, the direct current of the power supply 1 sequentially passes through a wire [ 1Q1 ], a wire [ 1Q3 ], a contact 2 of the backup landing gear releasing relay 7, a contact 1 of the backup landing gear releasing relay 7, a wire [ 4Q3 ], a hole B of the landing gear operating switch 4, a hole C of the landing gear operating switch 4, a wire [ 4Q2 ], and a hole C of the electromechanical management computer 5, and the electromechanical management computer 5 analyzes according to the collected on-landing gear switch state information to judge whether the landing gear command "down" can be executed, and if the landing gear command cannot be executed, the electromechanical management computer does not output the command; if the landing gear control system can be executed, current is output, and the landing gear control system drives the landing gear retraction electromagnetic valve 3 to operate through a hole B of the electromechanical management computer 5, a lead (5Q 3), a lead (6Q 2) and 3 holes of the landing gear retraction electromagnetic valve 3 to execute a landing gear lowering command.
3) Working principle of 'normal retraction' switching 'backup retraction' of undercarriage
As shown in fig. 1, the power switch 2 is turned on, the contact 2 of the backup landing gear releasing switch 6 is communicated with the contact 1, the direct current of the power supply 1 sequentially passes through a wire (1Q 1), a wire (1Q 2), the contact 2 of the backup landing gear releasing switch 6, the contact 1 of the backup landing gear releasing switch 6, a wire (2Q 1) and the backup landing gear releasing relay 7, at this time, the backup landing gear releasing relay 7 works, the contacts 1 and 2 of the backup landing gear releasing relay 7 are disconnected, the contacts 2 and 3 are contacted, under the condition, a direct current signal which flows from the power supply 1 to the holes 1 and 3 of the landing gear retraction electromagnetic valve 3 through the landing gear operating switch 4 is interrupted, and at the moment, no matter the landing gear operating switch 4 is in a 'down' position or a 'retracting' position, the electromechanical management computer 5 cannot receive a command signal, and cannot output an electric signal to drive the landing gear retraction electromagnetic valve 3 to actuate to execute 'retracting' and 'retracting' commands. And simultaneously, the contacts 2 and 3 of the landing gear releasing relay 7 are backed up to be contacted, so that the trend of the current is changed into: the landing gear control system comprises a direct current power supply 1, a lead (1Q 1), a lead (1Q 3), a contact 2 of a backup landing gear releasing relay 7, a contact 3 of the backup landing gear releasing relay 7, a lead (6Q 3), a lead (6Q 2), 3 holes of a landing gear releasing electromagnetic valve 3 and a drive landing gear releasing electromagnetic valve 3 to actuate, and a landing gear releasing instruction is executed.
4) Principle of 'backup release' switching 'normal release and retraction' of undercarriage
As shown in fig. 1, when the power switch 2 is turned on, the contact 2 of the backup landing gear releasing switch 6 is disconnected from the contact 1, at this time, the direct current supplied from the power supply 1 to the backup landing gear releasing relay is interrupted, the backup landing gear releasing relay 7 stops working, the contacts 1 and 2 of the backup landing gear releasing relay are in contact, and the contacts 2 and 3 are disconnected, in this case, the direct current signal supplied from the power supply 1 and flowing to the hole 1 of the landing gear releasing solenoid valve 3 through the contacts 2 and 3 of the backup landing gear releasing relay 7 is interrupted, and at the same time, the contacts 1 and 2 of the backup landing gear releasing relay 7 are in contact, at this time, the current passes through the wire [ 1Q1 ], the wire [ 1Q3 ], the contact 2 of the backup landing gear releasing relay 7, the contact 1 of the backup landing gear releasing relay 7, the wire [ 4Q3 ], the hole B ] of the landing gear operating switch 4, and at this time, no matter whether the landing gear operating switch 4 is placed in "put down" or "put down", corresponding current passes through the electromechanical management computer 5, the electromechanical management computer 5 analyzes according to the collected on-undercarriage switch state information, and outputs current to drive the undercarriage retraction electromagnetic valve 3 to actuate so as to execute an undercarriage extension instruction or an undercarriage retraction instruction.
5) Working principle of emergency landing gear
As shown in fig. 2, when the landing gear is released in emergency, the landing gear operating switch 4 is set to the "down" position, the landing gear switch 301 in the cabin is opened, the high-pressure nitrogen in the gas cylinder of the strut passes through the cold air emergency valve 302 and then enters the nose gear uplock actuator cylinder 303, the left landing gear uplock actuator cylinder 304 and the right landing gear uplock actuator cylinder 305 respectively, and the nose gear uplock 306, the left landing gear uplock 307 and the right landing gear uplock 308 are opened respectively; after unlocking, the high-pressure nitrogen respectively enters the nose landing gear actuator cylinder 312, the left landing gear actuator cylinder 313 and the right landing gear actuator cylinder 314 through the nose landing gear hydraulic oil lock 309, the left landing gear hydraulic oil lock 310 and the right landing gear hydraulic oil lock 311, and the nose landing gear, the left landing gear and the right landing gear are put down in an emergency mode respectively.
In the aircraft landing gear retraction control device in the embodiment of the application, when the contacts 1 and 2 of the backup landing gear retraction switch 6 are disconnected, normal retraction can be executed; when the contacts 1 and 2 of the backup landing gear releasing switch 6 are switched on, the backup releasing and releasing can be executed, and the two modes can be switched back and forth. When the two modes are invalid, the emergency retraction can be executed, and the emergency retraction is not influenced by electrical faults and is controlled by a mechanical system. The safety of the landing gear system is guaranteed to the maximum extent by the aid of the three-redundancy design, and the reliability of the airplane is improved.
It should be noted that, in this specification, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the present invention are conventionally placed in when used, and are used only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
It should also be noted that, unless expressly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" are intended to be construed broadly, as they may be fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include elements inherent in the list. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element. In addition, parts of the above technical solutions provided in the embodiments of the present application, which are consistent with the implementation principles of corresponding technical solutions in the prior art, are not described in detail so as to avoid redundant description.
The principles and embodiments of the present invention have been explained herein using specific examples, and the above descriptions of the embodiments are only used to help understand the method and its core ideas of the present invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.
Claims (6)
1. The utility model provides an aircraft undercarriage receive and releases controlling means, includes power, switch, undercarriage receive and releases the solenoid valve, through undercarriage receive and releases the action of receiving and releasing of solenoid valve execution undercarriage, its characterized in that, including two parallel receive and release control circuits between switch and the undercarriage receive and release solenoid valve, one is computer control's normal receive and release control circuit, and another is backup receive and release control circuit, be equipped with backup undercarriage switch on the backup receive and release control circuit, through the disconnection and the closure of backup undercarriage switch, realize the switching of normal receive and release control and backup receive and release control.
2. An aircraft landing gear retraction control according to claim 1, further comprising an emergency retraction control system, the emergency retraction control system being a mechanical control system.
3. An aircraft landing gear retraction control according to claim 1 or claim 2, wherein said normal retraction control circuit includes a landing gear operating switch, an electromechanical management computer; and when the undercarriage is normally retracted, the power supply, the power switch, the undercarriage control switch, the electromechanical management computer and the undercarriage retraction electromagnetic valve are electrically connected in sequence.
4. An aircraft landing gear retraction control device according to claim 1 or claim 2, wherein said back-up retraction control circuit includes a back-up landing gear switch and a back-up landing gear relay; when the backup is retracted, the power supply, the power switch, the backup landing gear relay and the landing gear retraction electromagnetic valve are electrically connected in sequence.
5. An aircraft landing gear retraction control according to claim 4, wherein the backup landing gear relay has one end connected to the backup landing gear switch and one end connected to ground, and two other contact terminals connected to the landing gear operating switch input and the landing gear retraction solenoid input, respectively.
6. The aircraft landing gear retraction control device according to claim 2, wherein the emergency retraction control system includes an emergency landing gear switch, a cold air emergency valve, a nose gear uplock actuator, a left landing gear uplock actuator, a right landing gear uplock actuator, a nose gear uplock, a left landing gear uplock, a right landing gear uplock, a nose gear hydraulic oil lock, a left landing gear hydraulic oil lock, a right landing gear hydraulic oil lock, a nose gear actuator, a left landing gear actuator, and a right landing gear actuator; when the landing gear is in emergency retraction, the landing gear operating switch is arranged at a 'down' position, the emergency landing gear switch in the cabin is opened, high-pressure nitrogen enters the front landing gear uplock actuator cylinder, the left landing gear uplock actuator cylinder and the right landing gear uplock actuator cylinder respectively after passing through the cold air emergency valve, and the front landing gear uplock, the left landing gear uplock and the right landing gear uplock are opened respectively; after the lock is unlocked, high-pressure nitrogen respectively enters the nose landing gear actuator cylinder, the left landing gear actuator cylinder and the right landing gear actuator cylinder through the nose landing gear hydraulic oil lock, the left landing gear hydraulic oil lock and the right landing gear hydraulic oil lock, and the nose landing gear, the left landing gear and the right landing gear are put down in an emergency mode respectively.
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| CN202022965495.5U CN214397207U (en) | 2020-12-12 | 2020-12-12 | Undercarriage control device that receive and releases |
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| CN202022965495.5U CN214397207U (en) | 2020-12-12 | 2020-12-12 | Undercarriage control device that receive and releases |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4215437A1 (en) * | 2022-01-24 | 2023-07-26 | Airbus Operations Limited | An aircraft control system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4215437A1 (en) * | 2022-01-24 | 2023-07-26 | Airbus Operations Limited | An aircraft control system |
| GB2615072A (en) * | 2022-01-24 | 2023-08-02 | Airbus Operations Ltd | An aircraft control system |
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