Signal testing device and signal testing method
By using signal testing devices and methods in the aircraft take-off and landing system and using indicator signal lights to detect aircraft signals, the problem of lack of real-time detection in the field test of the aircraft take-off and landing system is solved, and fast and accurate fault judgment and isolation are achieved.
Patent Information
- Application Number
- CN202411940802.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-26
- Publication Date
- 2025-04-04
AI Technical Summary
The lack of real-time detection devices in the field test of the aircraft take-off and landing system, which makes the fault search time-consuming and labor-intensive, inefficient and inaccurate.
Provide a signal testing device and method, which detects the aircraft takeoff and landing signal through several indicator lights, determines whether the working order is normal, and realizes rapid fault judgment and isolation.
The aircraft take-off and landing signal is displayed through the light signal, and the fault is quickly and accurately judged and isolated, improving the detection efficiency and accuracy of the aircraft take-off and landing system.
Smart Images
Figure CN119749870A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aircraft signal testing, and in particular to a signal testing device and a signal testing method. Background Art
[0002] Takeoff and landing are the two most critical stages in the flight process, which are directly related to the safety performance of the aircraft. With the rapid development of the aviation industry, the requirements for aircraft takeoff and landing systems are becoming higher and higher. In order to ensure that the aircraft can take off and land safely in various complex environments, strict field tests are required to verify the stability and reliability of the system.
[0003] At present, there is a lack of special detection equipment to perform real-time detection of the take-off and landing system test process during the field test of the aircraft take-off and landing system. When a fault is detected, continuous testing is required to find the fault point, which is time-consuming and labor-intensive, inefficient, and the fault point is not accurately found.
[0004] Therefore, there is an urgent need for a signal testing device and a signal testing method, which can determine whether the working sequence of take-off and landing is normal through light signals, so as to quickly determine and isolate faults. Summary of the invention
[0005] In view of this, it is necessary to provide a signal testing device and a signal testing method, which can determine whether the take-off and landing working sequence is normal through light signals, so as to quickly determine and isolate faults.
[0006] In order to achieve the above-mentioned object, on the one hand, the present invention provides a signal testing device for testing aircraft take-off and landing signals, the device comprising: an input adapter socket head, a signal receiving adapter socket head and a plurality of indicator signal lights; The two ends of the plurality of indicator signal lights are respectively connected to one end of the input adapter socket head and one end of the signal receiving adapter socket head; When performing a signal test, the other end of the input adapter socket head is connected to the input end of the signal device that generates the aircraft take-off and landing signal through a cable, and the other end of the signal receiving adapter socket head is connected to the output end of the signal device that generates the aircraft take-off and landing signal through a cable; the action execution state of at least one target part when the aircraft takes off and lands is detected according to the signal states of the several indicator signal lights.
[0007] In a possible implementation, the target parts include a left landing gear, a front landing gear, a right landing gear and a flap of an aircraft; The action execution state includes the retracted and lowered state of the landing gear and the flap deployment angle state; The plurality of indicator light indicators include eight indicator light indicators; The first signal indicator light is a left landing gear lowering signal light, the second signal indicator light is a left landing gear retracting signal light, the third signal indicator light is a front landing gear lowering signal light, the fourth signal indicator light is a front landing gear retracting signal light, the fifth signal indicator light is a right landing gear retracting signal light, the sixth signal indicator light is a right landing gear lowering signal light, the seventh signal indicator light is a flap lowering signal light, and the eighth signal indicator light is a landing gear lowering signal light; The signal state of the indicator signal light includes a lit state and an extinguished state.
[0008] In a possible implementation, the input adapter socket head includes eight input pins, and the signal receiving adapter socket head includes eight receiving pins; Each pair of input pins is connected in sequence with its corresponding indicator light and corresponding receiving pins, and then connected to an external signal device through a cable to form eight signal closed loop paths.
[0009] In a second aspect, the present invention further provides a signal testing method, which is applied to the signal testing device as described above, and the signal testing method comprises: Get the action execution status of the aircraft landing gear and flaps; Lighting up and extinguishing corresponding indicator lights according to the execution status of the action; Based on the on or off status of the indicator light, the execution status of the normal retracting and lowering of the landing gear during landing is determined; and / or; the execution status of the emergency measure to retract the aircraft landing gear in an abnormal situation is determined; and / or; the execution status of the warning sound action under abnormal conditions is determined.
[0010] In a possible implementation, determining the execution state of the normal retracting and lowering landing gear action during landing specifically includes: The simulated aircraft executes a landing signal in a stable flight state, and determines whether the landing gear of the aircraft is normally lowered according to whether the first indicator light, the third indicator light and the sixth indicator light are lit; Execute the landing gear emergency retraction signal, and determine whether the aircraft landing gear is normally retracted and can be fully retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are extinguished, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished; Execute the aircraft landing gear lowering signal, and determine whether the aircraft landing gear is lowered normally and can be fully retracted based on whether the second indicator signal light, the fourth indicator signal light and the fifth indicator signal light are lit and then extinguished.
[0011] In a possible implementation method, determining the execution state of the action of retracting the aircraft landing gear by taking emergency measures in an abnormal situation specifically includes: Simulate the landing flight process of the aircraft, execute the landing gear retraction signal, and determine whether the aircraft landing gear is retracted according to whether the first indicator signal light, the third indicator signal light and the sixth indicator signal light are off; When the landing gear is not retracted, the landing gear emergency retraction signal is executed, and whether the aircraft landing gear is successfully retracted is determined based on whether the first indicator light, the third indicator light and the sixth indicator light are extinguished, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
[0012] In a possible implementation, detecting an abnormal situation and adopting emergency measures to retract the aircraft landing gear execution state also includes: Simulate the flight process of an aircraft. When the landing gear interlock end switch is disconnected, the aircraft landing gear cannot be retracted. Determine whether the landing gear is retracted based on whether the first indicator light, the third indicator light and the sixth indicator light are off. When the landing gear is not retracted, execute the emergency retraction command of the aircraft landing gear, and determine whether the aircraft landing gear is successfully retracted based on whether the first indicator light, the third indicator light and the sixth indicator light are extinguished, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
[0013] In one possible implementation, determining the action execution state of the warning sound under abnormal conditions includes: determining the action execution state of the warning sound when the flaps are abnormally retracted or lowered, and determining the action execution state of the warning sound when the landing gear is abnormally retracted or lowered.
[0014] In a possible implementation, determining the execution state of the warning sound when the flaps are abnormally retracted or lowered specifically includes: Simulating the flight process of aircraft takeoff and landing, during the flap retraction and extension process, when the aircraft engine power is higher than the first preset power and the flaps are not at the preset angle, whether the action execution state of the warning sound when the flaps are abnormally retracted and extended is determined to be normal according to whether the seventh indicator signal light is on; When the flaps are at the preset angle, whether the seventh indicator light is off can be used to determine whether the warning sound stops issuing warning signals when the flaps are normally retracted and lowered.
[0015] In a possible implementation, determining the execution state of the warning sound when the landing gear is not retracted normally specifically includes: When the landing gear is in the retracted state, simulate the landing flight process of the aircraft, and determine whether the warning sounder normally sends out a warning signal when the aircraft landing gear is abnormally retracted according to whether the eighth indicator light is on; Firstly, the output power of the engine is increased to be higher than the second preset power, and then the output power of the engine is reduced to be lower than the second preset power, and whether the action execution state of the warning sound is normal is determined according to whether the eighth indicator signal light turns off and then turns on; The landing gear lowering signal is executed, and it is determined whether the warning sound stops issuing the warning signal according to whether the first indicator signal light, the third indicator signal light and the sixth indicator signal light are on.
[0016] The beneficial effects of the present invention are: by connecting the two ends of a plurality of indicator signal lights to one end of an input adapter socket head and one end of a signal receiving adapter socket head respectively; when performing a signal test, the other end of the input adapter socket head is connected to the input end of a signal device that generates an aircraft take-off and landing signal through a cable, and the other end of the signal receiving adapter socket head is connected to the output end of the signal device that generates an aircraft take-off and landing signal through a cable, and the action execution state of at least one target part when the aircraft takes off and lands is detected according to the signal states of the plurality of indicator signal lights. The present invention can quickly and accurately determine and isolate faults by displaying the aircraft take-off and landing signals in the form of light signals and judging whether the take-off and landing working sequence is normal through the light signals. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.
[0018] Figure 1 A schematic diagram of the structure of a signal testing device provided by the present invention; Figure 2 A schematic flow chart of an embodiment of a signal testing method provided by the embodiment of the present invention; Figure 3 The present invention provides Figure 2 A schematic flow chart of a first embodiment of step S203; Figure 4 The present invention provides Figure 2 A schematic flow chart of a second embodiment of step S203; Figure 5 The present invention provides Figure 2 A flowchart of a third embodiment of step S203; Figure 6 The present invention provides Figure 2 A schematic flow chart of a fourth embodiment of step S203; Figure 7 The present invention provides Figure 2 FIG. 5 is a flow chart of a fifth embodiment of step S203 in FIG. DETAILED DESCRIPTION
[0019] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.
[0020] In the description of the embodiments of the present invention, unless otherwise specified, "multiple" means two or more than two. "And / or" describes the association relationship of associated objects, indicating that three relationships may exist. For example, "A and / or B" may mean: A exists alone, A and B exist at the same time, and B exists alone.
[0021] The descriptions of "first", "second", etc. involved in the embodiments of the present invention are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the technical features defined as "first" or "second" may explicitly or implicitly include at least one of the features.
[0022] Reference to an "embodiment" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiment may be included in at least one embodiment of the present invention. The appearance of the phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.
[0023] The present invention provides a signal testing device and a signal testing method, which are respectively described below.
[0024] In some embodiments of the present invention, Figure 1 As shown, Figure 1 The structure diagram of the signal testing device provided by the present invention comprises: an input adapter socket head 1, a signal receiving adapter socket head 2 and a plurality of indicator signal lights 3; Two ends of a plurality of indicator signal lights 3 are respectively connected to one end of the input adapter socket head 1 and one end of the signal receiving adapter socket head 2; When performing a signal test, the other end of the input adapter socket head 1 is connected to the input end of the signal device that generates the aircraft take-off and landing signal through the cable 4, and the other end of the signal receiving adapter socket head 2 is connected to the output end of the signal device that generates the aircraft take-off and landing signal through the cable 4; the action execution state of at least one target part when the aircraft takes off and lands is detected according to the signal states of a plurality of indicator signal lights.
[0025] It should be noted that the signaler that generates the aircraft takeoff and landing signal is generally the aircraft's takeoff and landing system signaler. When a signal test is required, the input adapter socket head 1 is connected to the input end of the aircraft's takeoff and landing system signaler via a cable 4, and the signal receiving adapter socket head 2 is connected to the output end of the takeoff and landing system signaler via a cable 4. When checking the takeoff and landing system, the takeoff and landing system signaler sends a signal to a signal testing device, and the signal testing device displays the signal status sent by the takeoff and landing system signaler through a number of indicator lights.
[0026] This embodiment connects two ends of several indicator signal lights to one end of the input adapter socket head and one end of the signal receiving adapter socket head respectively; when performing a signal test, the other end of the input adapter socket head is connected to the input end of the signal device that generates the aircraft take-off and landing signal through a cable, and the other end of the signal receiving adapter socket head is connected to the output end of the signal device that generates the aircraft take-off and landing signal through a cable, and detects the action execution state of at least one target part when the aircraft takes off and lands according to the signal state of several indicator signal lights. The present invention displays the aircraft take-off and landing signal in the form of a light signal, and determines whether the take-off and landing working sequence is normal through the light signal, so as to quickly and accurately determine and isolate the fault.
[0027] In some embodiments of the present invention, the target parts include a left landing gear, a front landing gear, a right landing gear, and a flap of an aircraft; The action execution status includes the retracted and extended status of the landing gear and the flap extension angle status; The plurality of indicator light signals 3 include eight indicator light signals; The first signal indicator light L1 is a left landing gear lowering signal light, the second signal indicator light L2 is a left landing gear retracting signal light, the third signal indicator light L3 is a front landing gear lowering signal light, the fourth signal indicator light L4 is a front landing gear retracting signal light, the fifth signal indicator light L5 is a right landing gear retracting signal light, the sixth signal indicator light L6 is a right landing gear lowering signal light, the seventh signal indicator light L7 is a flap lowering signal light, and the eighth signal indicator light L8 is a landing gear lowering signal light; The signal state of the indicator light includes a lit state and an off state.
[0028] Specifically, when the left landing gear of the aircraft is lowered, the first signal indicator light L1 is lit; when the left landing gear of the aircraft is in the process of being retracted, the first signal indicator light L1 is off and the second signal indicator light L2 is lit; when the left landing gear of the aircraft is fully retracted, both the first signal indicator light L1 and the second signal indicator light L2 are off; when the front landing gear of the aircraft is lowered, the third signal indicator light L3 is lit; when the front landing gear of the aircraft is in the process of being retracted, the third signal indicator light L3 is off and the fourth signal indicator light L4 is lit; when the front landing gear of the aircraft is fully retracted, the third signal indicator light L3 and The fourth signal indicator light L4 is off; when the right landing gear of the aircraft is lowered, the sixth signal indicator light L6 is on; when the right landing gear of the aircraft is retracted, the sixth signal indicator light L6 is off and the fifth signal indicator light L5 is on; when the right landing gear of the aircraft is fully retracted, the sixth signal indicator light L6 and the fifth signal indicator light L5 are both off; when the aircraft flap deployment angle is abnormal, the seventh signal indicator light L7 is on; when the aircraft flap deployment angle is normal, the seventh signal indicator light L7 is off; when the aircraft landing gear is retracted abnormally, the eighth signal indicator light L8 is on.
[0029] This embodiment displays the action execution status of different parts of the aircraft through different signal indicator lights, and can clearly and accurately identify whether the working status of the aircraft parts is normal.
[0030] In some embodiments of the present invention, the input adapter socket head 1 includes eight input pins, and the signal receiving adapter socket head includes eight receiving pins; Each pair of input pins is connected in sequence with its corresponding indicator light and corresponding receiving pins, and then connected to an external signal device through a cable to form eight signal closed loop paths.
[0031] like Figure 1 As shown, the input adapter socket head 1 is numbered P1, and the eight input pins are numbered 1, 2, 3, 4, 5, 6, 7, and 9 respectively. The signal receiving adapter socket head 2 is divided into two adapter socket heads P2 and P3, and each of P2 and P3 has 4 pins.
[0032] This embodiment receives the signals sent by the signal device of the aircraft take-off and landing signals through different signal paths, and clearly and accurately identifies whether the working status of the aircraft parts is normal according to different signal indicator lights.
[0033] In order to better apply the signal testing device in the embodiment of the present invention, based on the signal testing device, correspondingly, Figure 2 The embodiment of the present invention also provides a flow chart of an embodiment of a signal testing method, such as Figure 2 As shown, the signal testing method includes: S201, obtaining the action execution status of the aircraft landing gear and flaps; S202, turning on and off the corresponding indicator light according to the execution status of the action; S203, determining the execution status of the normal retracting and lowering of the landing gear during landing according to the on or off status of the indicator light; and / or; determining the execution status of the emergency measure to retract the aircraft landing gear in an abnormal situation; and / or; determining the execution status of the warning sound action under abnormal conditions.
[0034] It should be noted that before starting the test, it is necessary to use a jack to lift the aircraft so that the landing gear is off the ground, connect the input adapter socket of the test device to the input end of the aircraft's takeoff and landing system signal device, connect the signal receiving adapter socket to the output end of the takeoff and landing system signal device, and at the same time, turn on the AC and DC power supplies, perform various operations on the aircraft on the aircraft's control operating system, and simulate various scenarios during the aircraft's takeoff and landing process.
[0035] In some embodiments of the present invention, Figure 3 As shown, Figure 3 The present invention provides Figure 2 The flowchart of the first embodiment of step S203 in the above embodiment is to detect the execution state of the normal retracting and lowering of the landing gear during the landing process, specifically including: S301, simulating an aircraft in a stable flight state, executing a landing signal, and determining whether the aircraft landing gear is normally lowered according to whether the first indicator light, the third indicator light, and the sixth indicator light are on; S302, executing the landing gear emergency retraction signal, and determining whether the aircraft landing gear is normally retracted and can be completely retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are off, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished; S303, executing the aircraft landing gear lowering signal, and determining whether the aircraft landing gear is lowered normally and fully retracted according to whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
[0036] It should be noted that the simulation of various flight states of the aircraft and various execution signals is achieved by performing various operations on the aircraft through the aircraft's take-off and landing system signalizer. The take-off and landing system signalizer then sends the action execution status signal of the target part to the test device. The test device lights up and extinguishes the corresponding indicator signal lights according to the received signal information, thereby characterizing the action execution status of the aircraft's target parts in turn.
[0037] Specifically, the aircraft is simulated to be in a stable flight state, and the landing gear of the aircraft is in a retracted state. The landing signal is executed by connecting the "landing signal" circuit breaker on the left DC circuit breaker board on the aircraft. Under normal conditions, the landing gear of the aircraft should be lowered, and the signal of the aircraft take-off and landing signal sends a corresponding signal, and the first indicator signal light, the third indicator signal light and the sixth indicator signal light are lit; Furthermore, at this time, turn on the "landing gear" circuit breaker on the left DC circuit breaker board, turn on the emergency hydraulic pump; turn on the spiral switch of the "emergency hydraulic system" on the control panel, and supply pressure to the normal hydraulic system, push the dual engine power levers to more than 37° to achieve stable power output of the aircraft engine, and put the landing gear control switch on the central instrument panel in the "retract" position to execute the landing gear emergency retraction signal. Under normal conditions, the landing gear is retracted, the first indicator light, the third indicator light and the sixth indicator light are off, and the second indicator light, the fourth indicator light and the fifth indicator light are on. The first indicator light is on, and the aircraft landing gear retraction action is in normal execution. When the landing gear is fully retracted, the second indicator light, the fourth indicator light and the fifth indicator light go out. Finally, place the landing gear control switch on the central instrument panel in the "down" position, the landing gear is lowered, the second indicator light, the fourth indicator light and the fifth indicator light are on, and the aircraft landing gear retraction action is in normal execution. When the landing gear is fully lowered, the second indicator light, the fourth indicator light and the fifth indicator light go out, and the first indicator light, the third indicator light and the sixth indicator light are on.
[0038] This embodiment tests whether the retracted and lowered states of the aircraft landing gear are normal by testing the normal retraction and lowering of the aircraft landing gear during the aircraft landing process.
[0039] In some embodiments of the present invention, Figure 4 As shown, Figure 4 The present invention provides Figure 2 The flowchart of the second embodiment of step S203 in the embodiment of the present invention is as follows: detecting an abnormal situation and adopting emergency measures to retract the aircraft landing gear execution state, specifically including: S401, simulating the landing flight process of the aircraft, executing the landing gear retraction signal, and determining whether the aircraft landing gear is retracted according to whether the first indicator light, the third indicator light, and the sixth indicator light are off; S402, when the landing gear is not retracted, executing the landing gear emergency retraction signal, and determining whether the aircraft landing gear is successfully retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are off, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
[0040] Specifically, the angle of the twin-engine power rods is set to be less than 37° to achieve low-power output of the aircraft engine to simulate the aircraft landing flight process. The landing gear retraction and extension switch on the central instrument panel is placed in the "retracted" position. During the landing flight process, in this scenario, the landing gear cannot be retracted, and the first indicator light, the third indicator light and the sixth indicator light do not go out; then the "emergency retraction landing gear switch" on the central instrument panel is turned on, and the landing gear is retracted in an emergency. The first indicator light, the third indicator light and the sixth indicator light go out, and the second indicator light, the fourth indicator light and the fifth indicator light light light up and then go out.
[0041] This embodiment tests that when the aircraft engine has low power output (i.e., during the aircraft landing flight), a landing gear retraction signal is executed, and the landing gear cannot be retracted, and emergency retraction of the landing gear is executed, and the landing gear is retracted, thereby realizing a test of the emergency retraction of the landing gear.
[0042] In some embodiments of the present invention, Figure 5 As shown, Figure 5 The present invention provides Figure 2 The flowchart of the third embodiment of step S203 in the embodiment of the present invention is as follows: detecting an abnormal situation and adopting emergency measures to retract the aircraft landing gear, and further comprising: S501, simulating an aircraft flight process, when the landing gear interlock end switch is disconnected, the aircraft landing gear cannot be retracted, and determining whether the landing gear is retracted according to whether the first indicator light, the third indicator light, and the sixth indicator light are off; S502, when the landing gear is not retracted, execute an emergency retraction command for the aircraft landing gear, and determine whether the aircraft landing gear is successfully retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are off, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
[0043] Specifically, the landing gear interlock end point switch is removed, and the dual-engine power levers are pushed to greater than 37°, that is, the aircraft is in flight status, the landing gear retraction and extension conversion switch on the central instrument panel is placed in the "retracted" position, the landing gear interlock end point switch is disconnected, and the aircraft landing gear cannot be retracted. In this scenario, the first indicator light, the third indicator light and the sixth indicator light do not go out; at this time, the "emergency retraction landing gear switch" on the central instrument panel is turned on, and the emergency retraction aircraft landing gear command is executed. The aircraft landing gear is retracted, the first indicator light, the third indicator light and the sixth indicator light go out, and the second indicator light, the fourth indicator light and the fifth indicator light light light up and then go out; at this time, the "emergency retraction landing gear switch" on the central instrument panel is turned on, and the emergency retraction aircraft landing gear command is executed. The aircraft landing gear is retracted, the first indicator light, the third indicator light and the sixth indicator light go out, and the second indicator light, the fourth indicator light and the fifth indicator light light light up and then go out.
[0044] In some embodiments of the present invention, detecting the action execution state of the warning sound under abnormal conditions includes: detecting the action execution state of the warning sound when the flaps are abnormally retracted or lowered, and detecting the action execution state of the warning sound when the landing gear is abnormally retracted or lowered.
[0045] In some embodiments of the present invention, Figure 6 As shown, Figure 6 The present invention provides Figure 2 The flowchart of the fourth embodiment of step S203 in the embodiment of the present invention is to detect the action execution state of the warning sound when the flaps are not normally retracted or lowered, and specifically includes: S601, simulating the flight process of aircraft takeoff and landing, during the flap retraction and extension process, when the aircraft engine power is higher than the first preset power and the flap is not at the preset angle, determining whether the warning sound emits a warning signal when the flap is abnormally retracted or extended according to whether the seventh indicator light is on; S602. When the flaps are at a preset angle, determine whether the warning sound stops sending warning signals when the flaps are normally retracted or lowered, based on whether the seventh indicator light is off.
[0046] Specifically, the "landing signal", "landing sound" and "oxygen use signal" circuit breakers on the left and right DC circuit breaker boards of the aircraft are turned on; during the process of flap retraction and extension, when the flap is not at the preset angle (that is, the flap deployment angle is too small or too large), the output power of the engine is increased, and when the engine power is higher than the first preset power, that is, when the angle of the dual-engine power lever push is greater than 63°, the warning sound circuit is started, the alarm rings, and the seventh indicator signal light is lit, indicating that the working state of the flap is abnormal; when the flap is at the preset angle, the seventh indicator signal light is extinguished and the alarm does not ring, indicating that the working state of the flap is normal; in this embodiment, the preset angle range of the flap is 5°~15°.
[0047] In some embodiments of the present invention, Figure 7 As shown, Figure 7 The present invention provides Figure 2 The flowchart of the fifth embodiment of step S203 in the embodiment of the present invention is to detect the action execution state of the warning sound when the landing gear is not retracted normally, and specifically includes: S701, simulating the landing flight process of the aircraft when the landing gear is in the retracted state, and determining whether the warning sounder normally sends out a warning signal when the aircraft landing gear is abnormally retracted according to whether the eighth indication signal light is on; S702, first increase the output power of the engine to make it higher than the second preset power, then reduce the output power of the engine to make it lower than the second preset power, and determine whether the signal state of the warning sound is normal according to whether the eighth indicator signal light turns off and then turns on; S703, executing the landing gear lowering signal, and determining whether the warning sound stops issuing the warning signal according to whether the first indicator light, the third indicator light, and the sixth indicator light are on.
[0048] Specifically, when the landing gear is retracted, the angles of the dual-engine power levers are set to be less than 37°, that is, the aircraft engine has a low power output. At this time, it should be in the landing state and the landing gear cannot be retracted. In this scenario, the eighth indicator light is on, the warning sound circuit is started, and the alarm rings; at this time, the alarm disconnect button on the pressure adjustment plate of the central control panel is pressed, the alarm stops ringing, the eighth indicator light is still on, and the output power of the engine is increased. When the engine power is higher than the second preset power, that is, when the angle of the power lever is greater than 37°, the aircraft engine outputs stable power, and the aircraft is in a normal flight state. At this time, the landing gear should be in the retracted state, the landing gear retraction signal is normal, and the eighth indicator light is still off. When the output power of the engine is reduced again, that is, the angle of the power lever is set to less than 37° again, the alarm rings again and the eighth indicator light is on again; at this time, the aircraft landing gear is lowered, and when the first indicator light, the third indicator light and the sixth indicator light are on, the alarm stops ringing, the eighth indicator light is off, and the state of the aircraft landing gear returns to normal.
[0049] This embodiment tests whether the aircraft warning sound circuit is normal by testing the working sequence of retracting the landing gear under abnormal conditions.
[0050] The signal testing device provided by the present invention is introduced in detail above. Specific examples are used in this article to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as a limitation on the present invention.
Claims
1. A signal testing device for testing aircraft take-off and landing signals, characterized in that: The device comprises: an input transfer socket head, a signal receiving transfer socket head and a plurality of indicator signal lights; The two ends of the plurality of indicator signal lights are respectively connected to one end of the input adapter socket head and one end of the signal receiving adapter socket head; When performing a signal test, the other end of the input adapter socket head is connected to the input end of the signal device that generates the aircraft take-off and landing signal through a cable, and the other end of the signal receiving adapter socket head is connected to the output end of the signal device that generates the aircraft take-off and landing signal through a cable; the action execution state of at least one target part when the aircraft takes off and lands is detected according to the signal states of the several indicator signal lights.
2. The signal testing device according to claim 1, characterized in that: The target parts include the left landing gear, the front landing gear, the right landing gear and the flaps of the aircraft; The action execution state includes the retracted and lowered state of the landing gear and the flap deployment angle state; The plurality of indicator light indicators include eight indicator light indicators; The first signal indicator light is a left landing gear lowering signal light, the second signal indicator light is a left landing gear retracting signal light, the third signal indicator light is a front landing gear lowering signal light, the fourth signal indicator light is a front landing gear retracting signal light, the fifth signal indicator light is a right landing gear retracting signal light, the sixth signal indicator light is a right landing gear lowering signal light, the seventh signal indicator light is a flap lowering signal light, and the eighth signal indicator light is a landing gear lowering signal light; The signal state of the indicator signal light includes a lit state and an extinguished state.
3. The signal testing device according to claim 2, characterized in that: The input adapter socket head includes eight input pins, and the signal receiving adapter socket head includes eight receiving pins; Each pair of the input pins is connected in sequence with its corresponding indicator light and the corresponding receiving pin, and then connected to the signal device through a cable to form eight closed-loop signal paths.
4. A signal testing method, applied to the testing device in claim 3, characterized in that: The signal testing method comprises: Get the action execution status of the aircraft landing gear and flaps; Lighting up and extinguishing corresponding indicator lights according to the execution status of the action; Based on the on or off status of the indicator light, the execution status of the normal retracting and lowering of the landing gear during the aircraft landing process is determined; and / or; the execution status of the emergency measure to retract the aircraft landing gear in an abnormal situation is determined; and / or; the execution status of the warning sound action under abnormal conditions is determined.
5. The signal testing method according to claim 4, characterized in that: Determine the execution status of the normal retracting and lowering landing gear action during landing, including: The simulated aircraft executes a landing signal in a stable flight state, and determines whether the landing gear of the aircraft is normally lowered according to whether the first indicator light, the third indicator light and the sixth indicator light are lit; Executing the landing gear emergency retraction signal, determining whether the aircraft landing gear is normally retracted and can be fully retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are off, and whether the second indicator light, the fourth indicator light and the fifth indicator light are on and then off; The aircraft landing gear lowering signal is executed, and whether the aircraft landing gear is lowered normally and can be fully retracted is determined according to whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
6. The signal testing method according to claim 4, characterized in that: Determine the execution status of the action to retract the aircraft landing gear using emergency measures in abnormal situations, including: Simulating an aircraft landing flight process, executing a landing gear retraction signal, and determining whether the aircraft landing gear is retracted according to whether the first indicator light, the third indicator light, and the sixth indicator light are off; When the landing gear is not retracted, the landing gear emergency retraction signal is executed, and whether the aircraft landing gear is successfully retracted is determined based on whether the first indicator light, the third indicator light and the sixth indicator light are extinguished, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
7. The signal testing method according to claim 6, characterized in that: Determine the execution status of the action of retracting the aircraft landing gear by taking emergency measures in abnormal situations, including: Simulating an aircraft flight process, when the landing gear interlock end switch is disconnected, the aircraft landing gear cannot be retracted, and determining whether the landing gear is retracted according to whether the first indicator light, the third indicator light and the sixth indicator light are off; When the landing gear is not retracted, an emergency retraction command for the aircraft landing gear is executed, and whether the aircraft landing gear is successfully retracted is determined based on whether the first indicator light, the third indicator light and the sixth indicator light are off, and whether the second indicator light, the fourth indicator light and the fifth indicator light are lit and then extinguished.
8. The signal testing method according to claim 4, characterized in that: Determining the action execution state of the warning sound under abnormal conditions includes: determining the action execution state of the warning sound when the flaps are abnormally retracted and lowered, and determining the action execution state of the warning sound when the landing gear is abnormally retracted and lowered.
9. The signal testing method according to claim 8, characterized in that: Determine the execution status of the warning sound when the flaps are not retracted or lowered normally, including: Simulating the flight process of aircraft takeoff and landing, during the flap retraction and extension process, when the aircraft engine power is higher than the first preset power and the flap is not at the preset angle, determining whether the action execution state of the warning sound when the flap is abnormally retracted and lowered is normal according to whether the seventh indicator signal light is on; When the flap is at a preset angle, it is determined whether the warning sound stops sending a warning signal when the flap is normally retracted and lowered, based on whether the seventh indicator signal light is off.
10. The signal testing method according to claim 9, characterized in that: Determine the execution status of the warning sound when the landing gear is not retracted normally, including: When the landing gear is in the retracted state, the aircraft landing flight process is simulated, and according to whether the eighth indication signal light is on, it is determined whether the warning sounder normally sends out a warning signal when the aircraft landing gear is abnormally retracted; Firstly, the output power of the engine is increased to be higher than the second preset power, and then the output power of the engine is reduced to be lower than the second preset power, and whether the action execution state of the warning sound is normal is determined according to whether the eighth indicator signal light is extinguished and then lit up; The landing gear lowering signal is executed, and it is determined whether the warning sound stops issuing the warning signal according to whether the first indicator light, the third indicator light and the sixth indicator light are on.