Aircraft landing gear position state indicating system

Abstract

The invention belongs to the technical field of aircraft landing gears, and particularly relates to an aircraft landing gear position state indicating system which comprises a signal lamp box indicating subsystem, a signal lamp indicating subsystem and a mechanical indicating subsystem. The starting and lamp box indicating subsystem is characterized in that a main power supply is connected with a closing position microswitch and a putting position microswitch through a main circuit breaker and supplies power to the closing position microswitch and the putting position microswitch; the putting-down position microswitch and the putting-up position microswitch are connected with the landing signal lamp displayer and the parameter sending displayer. The signal lamp indication subsystem is characterized in that a standby power supply is connected with an up-position microswitch and a down-position microswitch through a standby circuit breaker and supplies power to the up-position microswitch and the down-position microswitch; the up-folding position microswitch and the down-folding position microswitch are further connected with a signal processor, and the output end of the signal processor is connected with a white indicating lamp. The mechanical indication subsystem comprises a main landing gear mechanical indication system consisting of a main shock strut, a pull rod transmission mechanism, a spring and a red mechanical indicator which are connected in sequence; the front shock strut, the foldable inclined strut mechanism and the position indicating pointer are connected in sequence, and the position indicating pointer is matched with the marking line area to form a nose landing gear mechanical indicating system.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft landing gears, and in particular relates to an aircraft landing gear position status indicating system. Background Art

[0002] The landing gear position indication system is an important part of the aircraft. It is used to determine the position of the landing gear during takeoff, landing and flight. It is related to the safety and reliability of the aircraft. With the continuous improvement of aircraft safety requirements, higher requirements are placed on the accuracy and reliability of the aircraft landing gear position indication system.

[0003] At present, the aircraft landing gear position status indication system mostly uses sensors to collect status information, and displays the landing gear position status in the cockpit after logical transformation. This position indication system has the following problems: 1) When the electrical control system fails or a false alarm occurs, the pilot cannot accurately determine the position of the aircraft landing gear; 2) During takeoff or landing, due to the numerous crew operating procedures, when the landing gear retraction / lowering indication is not observed, it is easy to cause safety hazards such as the landing gear being retracted or not being lowered in place, resulting in an increased probability of flight accident symptoms; 3) When the indication system fails, when the aircraft informs the tower of the landing gear status during approach, it is impossible to accurately determine whether the landing gear is lowered and locked by its own weight. Especially when flying at night, due to the limitation of night vision ability, the airport tower personnel cannot determine the landing gear position. When the landing gear position does not meet the requirements, it is impossible to warn the pilot. Therefore, in the case of a failure of the indication system, the psychological burden and operating burden of the pilot will be increased, which will have a great impact on flight safety and flight missions. Summary of the invention

[0004] Purpose of the invention: In view of the problems existing in the existing aircraft landing gear position status indication system, the present invention proposes an aircraft landing gear position status indication system, which adopts a light box indication system, a signal light indication system and a mechanical indication system to form a landing gear position status indication system. When the position indication function of any subsystem fails or a false alarm occurs, the position of the landing gear can be judged by observing the remaining systems, thereby improving the reliability and accuracy of the landing gear position indication and reducing the psychological work pressure of the pilot; during the take-off stage or landing process, if the landing gear position status is not in a safe position, the light box indication system can provide voice warning information to remind the pilot to adjust the driving operation in time to ensure the flight safety of the aircraft; airport tower personnel can judge the landing gear position status through the signal light indication system, especially when flying at night, the white indicator light can significantly improve the night vision observation ability of the tower personnel, and when the landing gear position does not meet the flight requirements, the pilot can be warned in time, thereby improving the tower personnel's guidance and guarantee capabilities for the aircraft.

[0006] An aircraft landing gear position status indication system includes: a light box indication subsystem, a signal light indication subsystem and a mechanical indication subsystem;

[0007] The launch and landing light box indication system includes a main power supply, a main circuit breaker, a retracted position micro switch, a lowered position micro switch, a landing signal light box display, and a launch and landing parameter display;

[0008] The main power supply is connected to the retracted position micro switch and the lowered position micro switch through the main circuit breaker and supplies power; the lowered position micro switch and the retracted position micro switch are connected to the landing signal light display and the transmission parameter display;

[0009] The signal light indication system includes a backup power supply, a backup circuit breaker, a micro switch for the retracted position, a micro switch for the lowered position, a signal processor, and a white indicator light.

[0010] The backup power supply is connected to the micro switch at the retracted position and the micro switch at the lowered position through the backup circuit breaker and supplies power; the micro switch at the retracted position and the micro switch at the lowered position are also connected to the signal processor, and the output end of the signal processor is connected to a white indicator light;

[0011] The mechanical indication system comprises a main landing gear mechanical indication system consisting of a main shock absorber strut, a pull rod transmission mechanism, a spring and a red mechanical indicator connected in sequence;

[0012] The mechanical indication system also includes a front shock absorber strut, a foldable strut mechanism and a position indication pointer which are connected in sequence, and the position indication needle cooperates with the marking line area to form a front landing gear mechanical indication system.

[0013] Furthermore, the light box indication subsystem, signal light indication subsystem and mechanical indication subsystem indicate independently. When any one indication function fails, the remaining indication systems are observed to determine the position of the landing gear.

[0014] Furthermore, in the engine and main landing gear light box indication subsystem, when the front and main landing gear are retracted, the landing gear squeezes the micro switch of the retracted position, and the trigger signal makes the red retracted indicator light on the engine and main landing gear display light up; when the front and main landing gear are lowered, the landing gear squeezes the micro switch of the lowered position, and the trigger signal makes the green lowered indicator light on the engine and main landing gear display light up.

[0015] Furthermore, in order to increase the reliability of the landing gear light box indication system, the retracted position microswitch and the lowered position microswitch are dual-way microswitches. When the landing gear is retracted or lowered, the microswitch is triggered to generate a backup indication signal, which is transmitted to the landing signal light box display. When the landing gear is retracted, the red indicator light of the landing signal light box display lights up, and when the landing gear is lowered, the green indicator light of the landing signal light box display lights up.

[0016] Furthermore, when any landing gear is not lowered during the landing process, the aircraft is below 500 meters above the ground and the throttle lever is in the low throttle position, the light box indication subsystem outputs a voice warning message to prompt the pilot to lower the landing gear;

[0017] When the aircraft takes off at a height greater than 500 meters above the ground and any landing gear is not retracted, the light box indication system will output a voice warning message to prompt the pilot to retract the landing gear.

[0018] Furthermore, the white indicator light of the signal light indication system is installed on the outside of the landing gear, and the microswitch signals of the signal light indication subsystem and the light box indication subsystem are interconnected. When the front and main landing gears are lowered, the microswitch in the lowered position is turned on, and the trigger signal passes through the signal processor to light up the white indicator light; when the front and main landing gears are retracted, the microswitch in the retracted position is disconnected, and the trigger signal passes through the signal processor to turn off the white indicator light.

[0019] Furthermore, when the main landing gear is retracted, the main shock absorber strut of the mechanical indication system drives the pull rod transmission mechanism, thereby compressing the spring, and the red mechanical indicator is retracted into the fairing; when the main landing gear is lowered, the compressed spring extends and pushes out the red mechanical indicator, and the pilot can observe the red mechanical indicator extending out of the fairing shape.

[0020] Furthermore, when the front landing gear is lowered, the front shock absorber strut of the mechanical indication system drives the foldable strut mechanism to move. When the foldable strut mechanism is straightened and locked, the pilot observes the position indication pointer entering the marked line area; when the front landing gear is retracted, the pilot observes the position indication pointer deviating from the marked line area.

[0021] The beneficial effects of this application are:

[0022] 1) Improve the reliability and accuracy of the landing gear position indication and reduce the work pressure of the pilots: The landing gear position indication system includes three subsystems: the engine light box indication system, the signal light indication system and the mechanical indication system. The pilot shall first observe the indication information of the engine light box indication system in the cockpit to determine the position status of the landing gear. He may also observe the position of the mechanical indication system outside the cockpit or contact the tower personnel to determine the position status of the landing gear through the signal light indication system when flying at low altitude. When any indication system fails, the remaining indication systems can be observed to determine the position information of the landing gear.

[0023] 2) Add landing gear position warning reminder to improve flight safety: By sending a voice warning function to the light box indication system, it can reduce errors caused by flight operations, improve flight safety margin, and avoid damage to the fuselage structure caused by the landing gear not being lowered or the impact on the aircraft's control stability caused by the landing gear not being retracted.

[0024] 3) Improve the tower personnel's ability to guide and support aircraft: The white indicator light of the signal light indication system is installed on the outside of the landing gear. During the takeoff and landing process of the aircraft, the tower personnel observe whether the white indicator light of the signal light indication system is on or off, and then judge the position status of the landing gear. When the landing gear position status is wrong, the tower personnel can promptly warn the pilot. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 The present invention is a schematic diagram of an aircraft landing gear position status indication system. DETAILED DESCRIPTION

[0026] The following will be combined with the accompanying drawings in the embodiments of the present invention to clearly describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present invention.

[0027] The terms "first", "second", etc. in the specification and claims of the present invention are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present invention can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. are generally of the same type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0028] This application takes the landing gear position status indication system of a certain type of aircraft as an example to further explain this application in detail. The landing gear position status indication system involved in the present invention is composed of three subsystems: a light box indication system, a signal light indication system and a mechanical indication system. The light box indication system contains a main power supply, a circuit breaker, a micro switch for the retracted position, a micro switch for the lowered position, a landing signal light box display, and a landing display, which are used for the front and main landing gear position indication; the signal light indication system contains a backup power supply, a circuit breaker, a micro switch for the retracted position, a micro switch for the lowered position, a signal processor and a white indicator light, which are used for the front and main landing gear position indication; the mechanical indication system contains a main landing gear mechanical indication system composed of a main shock absorber strut, a pull rod transmission mechanism, a spring, and a red mechanical indicator, and a front landing gear mechanical indication system composed of a front shock absorber strut, a foldable strut mechanism, a position indication pointer, and a marking line area.

[0029] During the flight, the pilot or airport tower personnel can observe the status of the light box indication system, mechanical indication system, and signal light indication system to analyze and determine the landing gear position as follows:

[0030] In the engine parameter display and landing signal light box display of the engine parameter light box indication system, the pilot judges the position status of the landing gear by observing the visual information on the interface of the engine parameter display and the landing signal light box display. When the pilot presses the retract button of the landing gear switch, the landing gear is retracted under the hydraulic force. When the front and main landing gears are retracted, the landing gear squeezes the retracted position micro switch, triggering a signal to light up the red retracted indicator light of the engine parameter display; when the pilot presses the lowering button of the landing gear switch, the landing gear is lowered, and the landing gear squeezes the lowered position micro switch, triggering a signal to light up the green lowered indicator light of the engine parameter display. In order to improve the safety margin of the engine parameter light box indication system, the retracted position micro switch and the lowered position micro switch use dual-channel micro switches, which generate backup indication signals when the landing gear is retracted or lowered, and transmit them to the landing signal light box display. When the landing gear is retracted in place, the red indicator light of the landing signal light box lights up, and when the landing gear is lowered in place, the green indicator light of the landing signal light box lights up.

[0031] At the same time, a voice warning method is adopted. When any landing gear is not lowered during the landing process of the aircraft, the aircraft altitude is less than 500 meters and the throttle lever is in the low throttle position, the light box indication system outputs a voice warning indication information to prompt the pilot to lower the landing gear to avoid the damage and damage to the aircraft body caused by the landing impact when the landing gear is not lowered; when the aircraft takes off and the altitude is greater than 500 meters, and any landing gear is not retracted, the light box indication system outputs a voice warning indication information to prompt the pilot to retract the landing gear to avoid the aerodynamic resistance formed by the landing gear under high-speed flight affecting the aircraft's control stability.

[0032] The airport tower personnel can observe the position status of the landing gear through the signal light indication system. Installing the white indicator light of the signal light indication system on the outside of the landing gear can improve the observation and guarantee guidance capabilities of the airport tower personnel. The microswitch signals of the signal light indication system and the transmission and participation light box indication system are interconnected. When the front and main landing gear are lowered, the microswitch of the lowering position of the transmission and participation light box indication system is turned on, and the trigger signal passes through the signal processor to light up the white indicator light. The airport tower personnel can judge that the landing gear has been lowered; when the front and main landing gear are retracted, the microswitch of the retracted position of the transmission and participation light box indication system is disconnected, and the trigger signal passes through the signal processor to turn off the white indicator light. The airport tower personnel can judge that the landing gear has been retracted.

[0033] The mechanical indicator system is installed on the outside of the cockpit. During flight, the pilot uses the mechanical indicator system through the observation window to determine the landing gear position. When the main landing gear is retracted, the main shock absorber strut drives the pull rod transmission mechanism, which in turn compresses the spring, and the red mechanical indicator is retracted into the fairing shape; when the main landing gear is lowered, the compressed spring extends and pushes out the red mechanical indicator, and the pilot can observe the red mechanical indicator extending out of the fairing shape; when the front landing gear is lowered, the front shock absorber strut drives the foldable strut mechanism to move, and when the foldable strut mechanism is straightened and locked, the pilot observes the position indicator pointer entering the marked line area; when the front landing gear is retracted, the pilot observes the position indicator pointer deviating from the marked line area.

[0034] It should be noted that, in this article, the terms "comprise", "include" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, an element defined by the sentence "comprises a ..." does not exclude the presence of other identical elements in the process, method, article or device including the element. In addition, it should be pointed out that the scope of the method and device in the embodiment of the present invention is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in reverse order according to the functions involved, for example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0035] Through the description of the above implementation modes, those skilled in the art can clearly understand that the above implementation modes can be implemented by means of software plus a necessary general hardware platform, and of course by means of hardware, but in many cases the former is a better implementation mode. The above describes the embodiments of the present invention in conjunction with the accompanying drawings, but the present invention is not limited to the above specific implementation modes, which are merely illustrative and not restrictive. Under the enlightenment of the present invention, those skilled in the art can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.

Claims

1. An aircraft landing gear position status indication system, characterized in that: The system includes: a light box indication subsystem, a signal light indication subsystem and a mechanical indication subsystem; The said launch and parameter light box indication subsystem is composed of the following: the main power supply is connected to the retracted position micro switch and the lowered position micro switch through the main circuit breaker and supplies power; the lowered position micro switch and the retracted position micro switch are connected to the landing signal light display and the launch parameter display; The signal light indication subsystem is composed of the following: the backup power supply is connected to the stowed position micro switch and the lowered position micro switch through the backup circuit breaker and supplies power; the stowed position micro switch and the lowered position micro switch are also connected to the signal processor, and the output end of the signal processor is connected to the white indicator light; The mechanical indication subsystem is composed of the following: a main landing gear mechanical indication system composed of a main shock absorber strut, a pull rod transmission mechanism, a spring and a red mechanical indicator connected in sequence; a front shock absorber strut, a foldable strut mechanism and a position indication pointer connected in sequence, which cooperate with the position indication needle and the marking line area to form a front landing gear mechanical indication system.

2. The landing gear position status indication system according to claim 1, characterized in that: The light box indication subsystem, signal light indication subsystem and mechanical indication subsystem indicate independently.

3. The landing gear position status indication system according to claim 2, characterized in that: In the engine control light box indication subsystem, when the front and main landing gear are retracted, the landing gear squeezes the micro switch in the retracted position, and the trigger signal makes the red retracted indicator light on the engine control display light up; when the front and main landing gear are lowered, the landing gear squeezes the micro switch in the lowered position, and the trigger signal makes the green lowered indicator light on the engine control display light up.

4. The landing gear position status indication system as claimed in claim 3, characterized in that: The retracted position microswitch and the lowered position microswitch are dual-way microswitches. When the landing gear is retracted or lowered, the microswitch is triggered to generate a backup indication signal, which is transmitted to the landing signal light box display. When the landing gear is retracted, the red indicator light on the landing signal light box display lights up, and when the landing gear is lowered, the green indicator light on the landing signal light box display lights up.

5. The landing gear position status indication system as claimed in claim 4, characterized in that: When any landing gear is not lowered during landing, the aircraft altitude is less than 500 meters and the throttle lever is in the low throttle position, the light box indication subsystem outputs a voice warning message to prompt the pilot to lower the landing gear; When the aircraft takes off at a height greater than 500 meters above the ground and any landing gear is not retracted, the light box indication system will output a voice warning message to prompt the pilot to retract the landing gear.

6. The landing gear position status indication system and method as claimed in claim 5, characterized in that: The signal light indication subsystem and the transmitter and light box indication subsystem share a set of up position micro switches and down position micro switches; The white indicator light of the signal light indication system is installed on the outside of the landing gear. When the front and main landing gears are lowered, the lowering position micro switch is turned on, and the trigger signal passes through the signal processor to light up the white indicator light. When the front and main landing gear are retracted, the micro switch in the retracted position is disconnected, and the trigger signal passes through the signal processor to turn off the white indicator light.

7. The landing gear position status indication system as claimed in claim 6, characterized in that: When the main landing gear is retracted, the main shock absorber strut of the mechanical indication system drives the pull rod transmission mechanism, thereby compressing the spring, and the red mechanical indicator is retracted into the fairing; when the main landing gear is lowered, the compressed spring extends and pushes out the red mechanical indicator, and the pilot can observe the red mechanical indicator extending out of the fairing shape.

8. The landing gear position status indication system as claimed in claim 7, characterized in that: When the front landing gear is lowered, the front shock absorber strut of the mechanical indication system drives the foldable strut mechanism to move. When the foldable strut mechanism is straightened and locked, the position indication pointer enters the marked line area; when the front landing gear is retracted, the position indication pointer deviates from the marked line area.

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