CN114446112B - Landing gear handle fault simulation method and locking device - Google Patents
Landing gear handle fault simulation method and locking device Download PDFInfo
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- CN114446112B CN114446112B CN202210121525.5A CN202210121525A CN114446112B CN 114446112 B CN114446112 B CN 114446112B CN 202210121525 A CN202210121525 A CN 202210121525A CN 114446112 B CN114446112 B CN 114446112B
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- 238000000034 method Methods 0.000 title claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims description 24
- 230000000903 blocking effect Effects 0.000 claims description 20
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 19
- 230000033001 locomotion Effects 0.000 claims description 11
- 238000012549 training Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/085—Special purpose teaching, e.g. alighting on water, aerial photography
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/28—Simulation of stick forces or the like
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Abstract
The invention belongs to the technical field of flight simulation, and discloses a landing gear handle fault simulation method and a locking device. The method adopts a locking device, the locking device comprises a handle connecting piece and a locking piece, a landing gear handle is connected to the handle connecting piece, the locking piece is provided with a locking state and an unlocking state, when the locking piece is in the unlocking state, the handle connecting piece can normally move among an UP position, a middle position and a DOWN position, when the locking piece is in the locking state, the handle connecting piece can be locked in the UP position, the middle position or the DOWN position, and the landing gear handle fault simulation method comprises the following steps: s1, receiving a fault instruction; s2, judging the state of the handle connecting piece; s3, the handle connecting piece reaches a failure instruction appointed state, and the locking piece is locked. According to the method, by adopting the external locking device, fault simulation of the landing gear handle at the UP position, the middle position and the DOWN position can be realized, and the method is high in independence and universality.
Description
Technical Field
The invention relates to the technical field of flight simulation, in particular to a landing gear handle fault simulation method and a locking device.
Background
The full-automatic flight simulator simulates a real flight state through comprehensive application of a vision system, a motion system and an aviation simulation system, and is professional equipment for pilot initial refitting, retraining and fault flight training. Landing gear systems are one of the important systems of an aircraft, providing support for landing and taxiing of the aircraft. The requirement of the landing gear of the aircraft on the reliability is extremely high, the landing gear belongs to the aircraft system with the highest safety level, and serious flight safety accidents which are easy to cause due to improper fault treatment of the landing gear. Landing gear failure handling is therefore one of the important training items for simulated training of aircraft. Landing gear failure includes failure of various link mechanisms within the landing gear system and failure of the landing gear handle.
In the prior art, landing gear faults in a traditional full-motion flight simulator are mostly faults of a landing gear system. The connection mechanisms in the landing gear system are realized by controlling the hydraulic and electric control units through the sensors and the contactors, the fault simulation is logic simulation, and the design of the fault simulation can be completed by setting logic faults in the full-motion flight simulator. The landing gear handle is positioned at the front part of the cabin, has higher integration level and contains an electromagnetic mechanism and an electric control unit. Once the landing gear handle fails, its handling capability is limited, which can severely impact flight safety. At present, an electromagnetic mechanism inside a landing gear handle is usually adopted to lock to realize a fault simulation function. However, in this way, only the fault simulation of the landing gear handle in the UP position and the DOWN position can be realized, and the fault simulation of the middle position cannot be realized. In addition, the built-in electromagnetic structure drives, the independence is poor, the internal structure of the landing gear handle assembly needs to be damaged during installation, and the requirements on the model of an airplane are high, so that the suitability is poor.
It is therefore desirable to provide a landing gear handle failure simulation method to solve the above-mentioned problems.
Disclosure of Invention
The invention aims to provide a fault simulation method for a landing gear handle, which can realize fault simulation of the landing gear handle at three positions of an UP position, a middle position and a DOWN position by adopting an external locking device, and has the advantages of strong independence and high universality.
To achieve the purpose, the invention adopts the following technical scheme:
the landing gear handle fault simulation method adopts a locking device, the locking device comprises a handle connecting piece and a locking piece, the landing gear handle is connected to the handle connecting piece, the locking piece is provided with a locking state and an unlocking state, when the locking piece is in the unlocking state, the handle connecting piece can normally move among an UP position, a middle position and a DOWN position, when the locking piece is in the locking state, the handle connecting piece can be locked in the UP position, the middle position or the DOWN position, and the landing gear handle fault simulation method comprises the following steps:
s1, receiving a fault instruction;
s2, judging the state of the handle connecting piece;
s3, the handle connecting piece reaches the fault instruction appointed position, and the locking piece is locked. Alternatively, the process may be carried out in a single-stage,
optionally, the failure command is that the handle connection be locked to the UP bit or the intermediate bit or the DOWN bit.
Optionally, the locking of the handle connector to the intermediate position includes: after the handle connection member is moved from the UP position to the intermediate position, it cannot be moved from the intermediate position to the DOWN position; the handle coupler cannot move from the intermediate position to the UP position after moving from the DOWN position to the intermediate position.
Optionally, the determining the state of the handle connector includes determining a position of the handle connector and determining a movement path of the handle connector.
Another object of the present invention is to provide a landing gear handle failure simulation locking device, which is independently disposed with respect to the landing gear handle assembly, can achieve failure simulation of the landing gear handle in three positions, UP, middle and DOWN, and is convenient to install and highly versatile.
To achieve the purpose, the invention adopts the following technical scheme:
the landing gear handle fault simulation locking device is applicable to the landing gear handle fault simulation method, and comprises the following components:
the handle connecting piece is connected with the landing gear handle;
a locking member having a locked state and an unlocked state; when the handle is in a locking state, the handle can be fixed at an UP position, a middle position or a DOWN position, and when the handle is in the unlocking state, the handle can work normally;
the control mechanism is connected to the locking piece and can control the locking piece to be in the locking state or the unlocking state.
Optionally, the blocking part is arranged on the locking piece, and in the locking state, the blocking part can block the landing gear handle from moving.
Optionally, the device further comprises a bracket, the locking piece is rotatably connected with the bracket, and the control mechanism can control the locking piece to rotate around a connection point of the locking piece and the bracket, so that the locking piece is in the locking state or the unlocking state.
Optionally, the handle comprises a handle connecting piece, a locking piece and a connecting rod, wherein the handle connecting piece is connected with the connecting rod, and the locking piece can block the connecting rod from rotating.
Optionally, the control mechanism includes an electromagnetic switch connected to the locking member.
Optionally, the electromagnetic switch includes movable iron core and fixed sleeve that sets up, the sleeve cover is located movable iron core, movable iron core's output with the locking piece rotates to be connected.
The beneficial effects are that:
the method for simulating the faults of the handle of the undercarriage is used for simulating the faults of the undercarriage by adopting the external locking device. The locking device is connected to the landing gear handle through the handle connecting piece, and the handle connecting piece is locked through the locking piece, so that the movement of the landing gear handle is indirectly locked, and fault simulation is realized. The locking piece has locking state and unblock state, and in the unblock state, the undercarriage handle does not break DOWN, can normally work, and when the locking piece was in the locking state, can fix the undercarriage handle in any one of three positions in UP position, intermediate position or DOWN position. The method comprises the steps of firstly receiving a fault instruction, then judging whether the state of the handle connecting piece accords with the fault instruction, and locking the handle connecting piece by the locking piece when the handle connecting piece reaches the state designated by the fault instruction. Because the external locking device is adopted in the method, the structure inside the undercarriage handle assembly is not required to be damaged, the electromagnetic mechanism of the undercarriage handle assembly is not required to be adopted for driving, the independence is strong, meanwhile, the method can be conveniently connected with most undercarriage handles, has no specific requirements on the model of an airplane, belongs to a universal fault simulation mechanism, and has strong suitability. Fault simulation of the UP bit, the middle bit or the DOWN bit can be realized, and the fault condition of the undercarriage handle can be comprehensively simulated.
Drawings
FIG. 1 is a flow chart of a landing gear handle failure simulation method provided by the present invention;
FIG. 2 is a top view of the locking device provided by the present invention;
fig. 3 is a schematic structural view of the locking device in an unlocked state;
fig. 4 is a schematic structural view of the locking structure in a locked state.
In the figure:
10. UP bit; 20. a middle position; 30. a DOWN bit; 100. a handle connector; 110. a connecting rod; 200. a locking member; 210. a blocking portion; 300. a control mechanism; 310. a sleeve; 320. a movable iron core; 400. a bracket; 500. a base.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Wherein the terms "first location" and "second location" are two distinct locations and wherein the first feature is "above," "over" and "over" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is level above the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the invention.
See fig. 1 and 2. The method adopts a locking device, the locking device comprises a handle connecting piece 100 and a locking piece 200, a landing gear handle is connected to the handle connecting piece 100, the locking piece 200 is provided with a locking state and an unlocking state, when the locking piece 200 is in the unlocking state, the handle connecting piece 100 can normally move among an UP position 10, a middle position 20 and a DOWN position 30, when the locking piece 200 is in the locking state, the handle connecting piece 100 can be locked in the UP position 10, the middle position 20 or the DOWN position 30, and the landing gear handle fault simulation method comprises the following steps:
s1, receiving a fault instruction;
s2, judging the state of the handle connecting piece 100;
s3, the handle connector 100 reaches a failure instruction designated state, and the locking piece 200 is locked.
According to the method, the landing gear fault is simulated by adopting the external locking device. The locking device is connected to the landing gear handle through the handle connecting piece 100, and the handle connecting piece 100 is locked through the locking piece 200, so that the movement of the landing gear handle is indirectly locked, and fault simulation is realized. The lock 200 has a locked state in which the landing gear handle does not fail and can operate normally, and an unlocked state in which the landing gear handle can be fixed in any one of the UP position 10, the intermediate position 20, or the DOWN position 30 when the lock 200 is in the locked state. The method first needs to receive the fault instruction, then judges whether the state of the handle connector 100 is consistent with the fault instruction, and when the handle connector 100 reaches the state designated by the fault instruction, the locking piece 200 locks the handle connector 100. Because the external locking device is adopted in the method, the structure inside the undercarriage handle assembly is not required to be damaged, the electromagnetic mechanism of the undercarriage handle assembly is not required to be adopted for driving, the independence is strong, meanwhile, the method can be conveniently connected with most undercarriage handles, has no specific requirements on the model of an airplane, belongs to a universal fault simulation mechanism, and has strong suitability. Fault simulation of the UP bit 10, the middle bit 20 or the DOWN bit 30 can be realized, and the fault condition of the landing gear handle can be comprehensively simulated.
In this embodiment, the fault instruction may be that the handle connector 100 is locked at the UP position 10, that is, after the fault instruction is issued, when the handle connector 100 reaches the UP position 10 for the first time, the locking member 200 locks the handle connector 100; the fault instruction may also be that the handle connector 100 is locked in the middle position 20, that is, after the fault instruction is issued, when the handle connector 100 reaches the middle position 20 for the first time, the locking member 200 locks the handle connector 100; the failure command may also be that the handle connector 100 is locked in the DOWN position 30, i.e. after the failure command is issued, the lock 200 locks the handle connector 100 when the handle connector 100 reaches the DOWN position 30 for the first time. In other embodiments, the fault command may be that the handle connector 100 is locked in any of the UP bit 10, the middle bit 20, or the DOWN bit 30, i.e., after the fault command is issued, the lock 200 locks the handle connector 100 when the handle connector 100 reaches any of the UP bit 10, the middle bit 20, or the DOWN bit 30. Of course, the fault instruction is not limited to the above two types, and in practical application, the fault instruction may be set according to a function to be implemented by the locking device.
Further, according to two movement paths of the handle connector 100, locking the handle connector 100 to the intermediate position 20 includes: after the handle connector 100 is moved from the UP position 10 to the intermediate position 20, the lock member 200 is locked and the handle connector 100 cannot be moved from the intermediate position 20 to the DOWN position 30; after the handle coupler 100 is moved from the DOWN position 30 to the intermediate position 20, the lock member 200 is locked and the handle coupler 100 cannot be moved from the intermediate position 20 to the UP position 10. Accordingly, the fault instruction and the control method can be set accordingly.
It will be appreciated that since the handle connector 100 has two paths of movement, determining the status of the handle connector 100 includes determining the position of the handle connector 100 and determining the path of movement of the handle connector 100, thereby enabling simulation of all possible fault conditions.
The embodiment also provides a landing gear handle fault simulation locking device which can be used for the landing gear fault simulation method. The locking device includes a handle connector 100, a locking member 200, and a control mechanism 300. The handle connector 100 is connected to the handle landing gear. The lock member 200 has a locked state and an unlocked state, referring to fig. 2 and 3, when the lock member 200 is in the locked state, the handle connection member 100 can be locked in the UP position 10 or the middle position 20 or the DOWN position 30; referring to fig. 4, when the locking member 200 is in the unlocked state, the handle can be operated normally. The control mechanism 300 is connected to the lock member 200 and can control the lock member 200 to be in a locked state or an unlocked state.
The locking means that this embodiment provided is independent mechanism relative landing gear handle subassembly, adopts solitary control mechanism 300 to control, can design control scheme according to actual need, is connected to landing gear handle on landing gear handle subassembly external connection through handle connecting piece 100, need not to destroy the inner structure of landing gear handle subassembly during the assembly, and convenient connection does not have special requirement to the flight model, and is extensive in application. When the simulated landing gear handle is required to fail, the locking member 200 is kept in the unlocked state, the handle connector 100 can be normally switched between the UP position 10, the middle position 20 and the DOWN position 30, and when the simulated landing gear handle is required to fail, the control mechanism 300 controls the state of the locking member 200 to be in the locked state, and locks the handle connector 100 in the specified position, so that the situation that the simulated landing gear handle fails in the UP position 10, the middle position 20 and the DOWN position 30 is realized.
The locking device in this embodiment further includes a base, and other components such as the control mechanism 300 are fixed on the base according to actual needs. The locking device can be fixed in a proper area through the base according to the structure of the simulation machine.
It will be appreciated that the UP bit 10, the middle bit 20, and the DOWN bit 30 of the handle link 100 correspond to the positions of the landing gear handle in actual use, respectively. The handle connector 100 in this embodiment is a rod member having one end connected to the landing gear handle via a cable and the other end connected to a connecting rod 110. One end of the connecting rod 110 is rotatably connected to the handle connector 100, and the other end can be rotated around a fixed point. In the unlocked state, the landing gear handle is operated to drive the handle connector 100 to move, and the connecting rod 110 is driven by the handle connector 100 to rotate around the fixed point. When a simulated failure is required, the lock 200 locks the position of the handle connector 100 by preventing rotation of the connecting rod 110, thereby simulating a landing gear handle failure. In other embodiments, the structure and movement of the connecting rod 110 are not limited to those provided in the present embodiment, and of course, the fault simulation may also be implemented by adopting a structure form of directly locking the handle connector 100.
Further, the control mechanism 300 is crosslinked through an interface system of a relay and a simulator, and performs data acquisition and logic control through a simulation computer. The data acquisition and logic control method is a mature prior art, and will not be described in detail herein.
The control mechanism 300 includes an electromagnetic switch coupled to the lock member 200. The electromagnetic switch controls the locking piece 200 to switch between the locking state and the unlocking state according to the actual power-on or power-off requirement. Alternatively, the electromagnetic switch includes a movable iron core 320 and a fixedly arranged sleeve 310, the sleeve 310 is sleeved on the movable iron core 320, and the output end of the movable iron core 320 is rotationally connected with the locking member 200. When the electromagnetic switch is turned on, the movable iron core 320 is retracted upward, and the locking member 200 rotates and approaches the connecting rod 110, locking the connecting rod 110; when the electromagnetic switch is turned off, the movable iron core 320 protrudes downward, and the locking member 200 rotates and moves away from the connection rod 110, so that the connection rod 110 is unlocked.
Further, the locking device further comprises a bracket 400, the locking piece 200 is rotatably connected to the bracket 400, and the control mechanism 300 can control the locking piece 200 to rotate clockwise or anticlockwise around the connection point of the locking piece 200 and the bracket 400, so that the locking piece 200 is in a locking state or an unlocking state. Alternatively, the bracket 400 is fixed to the base by bolts. The bracket 400 is provided with a mounting groove, and the locking member 200 is inserted into the mounting groove and hinged with the bracket 400.
Further, the blocking part 210 is further provided on the locking member 200. The locking member 200 is a rod member, the output end of the movable iron core 320 is connected to one end of the locking member 200, the blocking portion 210 is disposed at the other end of the locking member 200, and the bracket 400 is connected between the two ends. Alternatively, the blocking portion 210 is a latch provided on the locking member 200, and in this embodiment, two latches are provided on the locking member 200 at intervals, so that three blocking positions, i.e., a first blocking position at the front end of the locking member 200, a second blocking position between the two latches, and a third blocking position near one side of the stand 400, respectively correspond to the UP position 10, the middle position 20, and the DOWN position 30 of the handle connection member 100. In other embodiments, the blocking portion 210 may be three latches, or may be configured to clamp or snap into the connecting rod 110, so long as the handle connector 100 is locked in the UP position 10, the middle position 20, or the DOWN position 30.
In this embodiment, the functions of the locking device are divided into the following five types according to the type of failure generated by the landing gear handle of the aircraft:
function one: landing gear handle normally works
The electromagnetic switch is turned off, the movable iron core 320 extends out, the front end of the locking piece 200 is lifted, the latch avoids the connecting rod 110, the locking piece 200 has no blocking effect on the connecting rod 110, and the connecting rod 110 and the handle connecting piece 100 can normally move.
And the function II: the landing gear handle creates a jam in the UP position 10 and cannot move from the UP position 10 to the intermediate position 20
When the interface system receives a fault instruction and the connecting rod 110 reaches the UP position 10, the electromagnetic switch is powered on, the movable iron core 320 is retracted, and drives the locking piece 200 to rotate clockwise around the connection point of the locking piece and the bracket 400, the connecting rod 110 is blocked in the first blocking position, and the landing gear handle cannot be removed from the UP position 10.
And the third function: landing gear handles create a jam in the middle position 20 and cannot move from the middle position 20 to the DOWN position 30
When the landing gear handle is in the UP position 10, the electromagnetic switch is in a closed state. The interface system receives the fault command, the interface system collects the signal that the landing gear handle is separated from the UP position 10, the electromagnetic switch is powered on, the movable iron core 320 is retracted, and drives the locking piece 200 to rotate clockwise around the connection point of the locking piece and the bracket 400, the connecting rod 110 is blocked between the second blocking positions, and the landing gear handle cannot be removed from the middle position 20. The signal transfer time is guaranteed to be far less than the movement time of the handle from the DOWN bit 30 to the middle bit 20, thereby achieving fault simulation.
Function IV: the landing gear handle creates a jam in the DOWN bit 30 and cannot move from the DOWN bit 30 to the intermediate bit 20
When the interface system receives the failure command and the handle landing gear is in the DOWN position 30, the electromagnetic switch is powered up, the movable iron core 320 is retracted, and drives the locking member 200 to rotate clockwise about its connection point with the bracket 400, the connecting rod 110 is blocked in the third blocking position of the locking member 200, and the landing gear handle cannot be removed from the DOWN position 30.
Function five: landing gear handles create a jam in the intermediate position 20 and cannot move from the intermediate position 20 to the UP position 10
The electromagnetic switch is in an off state when the landing gear handle is in the DOWN position 30. The interface system receives the failure command, the interface system collects the signal that the landing gear handle is out of the DOWN position 30, the electromagnetic switch is powered on, the movable iron core 320 is retracted, and drives the locking member 200 to rotate clockwise around its connection point with the bracket 400, the connecting rod 110 is blocked in the second blocking position, and the landing gear handle cannot be removed from the middle 20. The signal transmission time is ensured to be far less than the movement time of the handle from the intermediate 20 to the UP 10, so that fault simulation is realized.
It is to be understood that the above examples of the present invention are provided for clarity of illustration only and are not limiting of the embodiments of the present invention. Various obvious changes, rearrangements and substitutions can be made by those skilled in the art without departing from the scope of the invention. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the invention are desired to be protected by the following claims.
Claims (9)
1. A landing gear handle fault simulation method, which is characterized by adopting a locking device, wherein the locking device comprises a handle connecting piece (100) and a locking piece (200), the landing gear handle is connected to the handle connecting piece (100), the locking piece (200) has a locking state and an unlocking state, when the locking piece (200) is in the unlocking state, the handle connecting piece (100) can normally move among an UP position (10), an intermediate position (20) and a DOWN position (30), when the locking piece (200) is in the locking state, the handle connecting piece (100) can be locked to the UP position (10) or the intermediate position (20) or the DOWN position (30), and the landing gear handle fault simulation method comprises the following steps:
s1, receiving a fault instruction;
the fault instruction is that the handle connector is locked at the UP position (10), the handle connector is locked at the middle position (20), or the handle connector is locked at the DOWN position (30);
s2, judging the state of the handle connecting piece (100);
s3, the handle connecting piece (100) reaches the fault instruction appointed position, and the locking piece (200) is locked.
2. The landing gear handle failure simulation method according to claim 1, wherein the handle connection (100) being locked to the intermediate position (20) comprises: -after the handle connection (100) is moved from the UP position (10) to the intermediate position (20), it cannot be moved from the intermediate position (20) to the DOWN position (30); the handle connection (100) cannot be moved from the intermediate position (20) to the UP position (10) after being moved from the DOWN position (30) to the intermediate position (20).
3. The landing gear handle failure simulation method of claim 1, wherein the determining the state of the handle connector (100) includes determining a position of the handle connector (100) and determining a path of movement of the handle connector (100).
4. A landing gear handle fail-safe locking device adapted for use in a landing gear handle fail-safe method as claimed in any one of claims 1 to 3, the landing gear handle fail-safe locking device comprising:
a handle connection (100), the handle connection (100) being connected to the landing gear handle;
a locking member (200), the locking member (200) having a locked state and an unlocked state; when the handle is in the locking state, the handle can be fixed at an UP position (10), a middle position (20) or a DOWN position (30), and when the handle is in the unlocking state, the handle can work normally;
and the control mechanism (300) is connected to the locking piece (200) and can control the locking piece (200) to be in the locking state or the unlocking state.
5. The landing gear handle failure simulation locking device according to claim 4, wherein a blocking portion (210) is provided on the locking member (200), and the blocking portion (210) is capable of blocking the landing gear handle from moving in the locked state.
6. The landing gear handle failure simulation locking device according to claim 4, further comprising a bracket (400), wherein the locking member (200) is rotatably connected to the bracket (400), and wherein the control mechanism (300) is capable of controlling the locking member (200) to rotate about a connection point of the locking member (200) to the bracket (400) such that the locking member (200) is in the locked state or the unlocked state.
7. The landing gear handle failsafe locking arrangement of claim 4, further comprising a connecting rod (110), the connecting rod (110) being rotatable about a fixed point, the handle connector (100) being connected to the connecting rod (110), the locking member (200) being capable of blocking rotation of the connecting rod (110).
8. The landing gear handle failsafe locking arrangement of claim 4, wherein the control mechanism (300) includes an electromagnetic switch connected to the locking member (200).
9. The landing gear handle fault simulation locking device according to claim 8, wherein the electromagnetic switch comprises a movable iron core (320) and a fixedly arranged sleeve (310), the sleeve (310) is sleeved on the movable iron core (320), and the output end of the movable iron core (320) is rotatably connected with the locking piece (200).
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| CN202210121525.5A CN114446112B (en) | 2022-02-09 | 2022-02-09 | Landing gear handle fault simulation method and locking device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210121525.5A CN114446112B (en) | 2022-02-09 | 2022-02-09 | Landing gear handle fault simulation method and locking device |
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