JP5491164B2 - Landing gear and aircraft - Google Patents

Description

Technology disclosed herein relates to the landing gear and the aircraft equipped with it.

For example, as disclosed in Patent Document 1, an aircraft landing gear has a WOW (Weight On Wheel) sensor for detecting whether the aircraft is on the ground or in the air. Attached to the legs. Such a WOW sensor is generally constituted by a non-contact type sensor such as a proximity sensor, for example, in order to avoid aged deterioration and maintenance requirements.

  Since each system of an aircraft performs various processes based on the status signal output from the WOW sensor, a high reliability is required for the sensing system including the WOW sensor. For example, Patent Document 2 discloses a sensing system that has a plurality of sensors and is made redundant by providing a plurality of sensors as a system mounted on an aircraft, and a landing system sensing system also includes a plurality of WOWs. Redundancy is provided with sensors.

JP 2004-345368 A JP 2003-76402 A

By the way, especially when landing, the WOW sensor of the leg pulled out from the fuselage is exposed to radio waves induced by an instrument landing system (ILS: Instrument Landing System), radio waves by airport weather Doppler radar, radio waves by airport surface detection radar, etc. Will be. Such strong radio waves can generate a noise environment that can cause malfunction or detection of the WOW sensor.

  In contrast, a plurality of WOW sensors constituting a redundant system are often arranged close to each other. For this reason, at the time of landing, a plurality of WOW sensors are placed under the same noise environment, and all of the plurality of WOW sensors may malfunction or be erroneously detected. In this case, since all the WOW sensors perform the same output, even if the sensing system is made redundant, it is impossible to determine the malfunction or detection of the WOW sensor. There is a risk that processing based on erroneous detection will be executed.

The disclosed technique has been made in view of the foregoing, and an object thereof to provide a malfunction or erroneous based on the detection processing later deposition apparatus that obtained avoids in advance the sensors is there.

  The technology disclosed herein is arranged in the same usage environment as the sensing unit in the vicinity of the sensing unit separately from the sensing unit that detects the state of the detection target and outputs a state signal corresponding to the state. A dummy sensing unit that always outputs a signal corresponding to a predetermined state regardless of the state change of the detection target is provided. Then, when the dummy sensing unit that outputs a state signal corresponding to a predetermined state outputs a state signal different from the predetermined state, the dummy sensing unit is malfunctioning or erroneously detected. The sensing unit under the same usage environment is presumed to be malfunctioning or erroneously detected, so that processing based on the output signal of the sensing unit is not performed. The processing based on the detection is prevented from being executed in advance.

  Specifically, the landing gear disclosed herein includes a leg that supports the aircraft when the aircraft is on the ground, a state where the aircraft is on the ground and is supported by the legs, and the aircraft is in the air. An output means for outputting a status signal for distinguishing from a status not supported by the legs, and a status signal from the output means, and when the aircraft is on the ground and in the air Processing means for executing a corresponding process, wherein the output means detects the leg state to change between a support state of the aircraft and a non-support state of the aircraft. A plurality of sensing units that are attached to the unit and output either one of the first and second state signals corresponding to the state change to the processing unit, and the output unit includes the legs. Regardless of the state of the department In addition, at least one dummy sensing unit is further provided in the vicinity of each sensing unit so that a normal signal that is one of the first and second status signals is always output to the processing means. When the signal from the dummy sensing unit is a normal signal, the processing means performs processing according to the state signal from the sensing unit, whereas when the signal from the dummy sensing unit is not a normal signal, It is comprised so that the process according to the state signal from the said sensing part may not be performed.

  According to this configuration, the output means outputs whether the aircraft is on the ground or in the air by outputting the support state and non-support state of the legs in the landing gear. The processing means executes processing according to the state signal (first or second state signal) from the output means. The output means has a plurality of sensing units for detecting the state of the legs and is made redundant, thereby enhancing the reliability of sensing.

  In addition to the plurality of sensing units, the output unit further includes a dummy sensing unit disposed in the vicinity of the sensing unit, and the dummy sensing unit is configured to be in the first or second state regardless of the state of the legs. The state signal is always output. For example, the dummy sensing unit may be attached to the leg so as to detect that the airframe is supported, or the dummy sensing unit may be attached to the leg so as to detect that the airframe is not supported. Good. By doing so, when the dummy sensing unit outputs the first or second state signal, that is, a normal signal, the dummy sensing unit is not malfunctioning or erroneously detected. When the normal signal is not output, for example, the place where the first state signal should be output, the second state signal is output, or conversely, the place where the second state signal should be output is When the 1-state signal is output, it is possible to estimate that the dummy sensing unit is malfunctioning or erroneously detected.

  The processing means is based on the signal from the dummy sensing unit, and when the signal is a normal signal, the dummy sensing unit has not malfunctioned or erroneously detected, and thus the sensing unit has malfunctioned or erroneously detected. If not, processing corresponding to the state signal from the sensing unit is executed. On the other hand, when the signal from the dummy sensing unit is not a normal signal, the dummy sensing unit is malfunctioning or erroneously detected. Therefore, the sensing unit is also assumed to be malfunctioning or erroneously detected. The processing according to the state signal is not executed. In this way, even if all of the multiple sensing units placed under the same usage environment malfunction or misdetect due to the usage environment, the sensing unit malfunctions or malfunctions. The processing based on detection is prevented from being executed in advance.

  Since this system is configured only by adding a dummy sensing unit, and only switching execution / non-execution of processing based on an output signal from the dummy sensing unit, the control logic can be extremely simple. . Therefore, there is an advantage that the system configuration is simplified.

  Here, although there may be one dummy sensing unit, for example, two dummy sensing units may be provided. In this case, it is preferable that one dummy sensing unit always outputs the first state signal while the other dummy sensing unit always outputs the second state signal. By doing this, when both of the two dummy sensing units output normal signals (when the two dummy sensing units output the first state signal and the second state signal, respectively), dummy sensing is performed. It is possible to estimate that the sensing unit and each sensing unit are not malfunctioning or erroneously detected, while at least one of the two dummy sensing units does not output a normal signal (for example, two dummy sensing units are In both cases, when the first state signal or the second state signal is output), it is possible to estimate that the sensing unit is malfunctioning or erroneously detected. In this case, it can be estimated more accurately that each sensing unit is malfunctioning or erroneously detected.

  The leg portion includes a buffer strut that expands and contracts between a support state of the airframe and an unsupported state of the airframe, and each sensing portion includes the proximity sensor and the proximity according to expansion and contraction of the buffer strut And the proximity sensor outputs the first and second state signals in accordance with the detection and non-detection of the target according to the expansion and contraction of the buffer strut. The dummy sensing unit includes a proximity sensor having the same configuration as the proximity sensor of the sensing unit, and the proximity sensor outputs one of the first and second state signals regardless of expansion and contraction of the buffer support column. It is good also as being attached and comprised so.

  Each sensing unit switches between the state where the proximity sensor detects the target and the state where it does not detect as the buffer struts expand and contract, so that the support state of the aircraft (the aircraft is on the ground) and the An unsupported state (a state in which the aircraft is in the air) can be detected.

  In contrast, the dummy sensing unit includes a proximity sensor having the same configuration as the proximity sensor of the sensing unit. Thereby, when the proximity sensor of the sensing unit malfunctions or malfunctions due to the use environment, the proximity sensor of the dummy sensing unit also malfunctions or malfunctions. The dummy sensing unit also does not include a target that is in contact with the proximity sensor in accordance with the expansion and contraction of the buffer column. In order to provide the proximity sensor of the dummy sensing unit so that it is always in a detection state regardless of expansion and contraction of the buffer support column, for example, a target or a similar member is provided so that the proximity sensor detects it and It may be provided so that the relative position with respect to the proximity sensor does not change even if the column expands or contracts (that is, the detection state is maintained). For example, the target itself may be eliminated, or the target or a similar member may be provided so that the proximity sensor does not detect the target, and relative to the proximity sensor even if the buffer column is expanded or contracted. You may provide so that a position may not change (that is, a non-detection state is maintained). By doing so, each sensing unit outputs a state signal corresponding to the state of the leg, while the dummy sensing unit always outputs one of the first and second state signals regardless of the state of the leg. Outputting can be realized.

  When the signal from the dummy sensing unit is not the normal signal, the processing means is a state signal when the signal from the dummy sensing unit is the normal signal and the sensing unit previously detected It may be configured to execute a corresponding process.

  That is, in a state where sensing malfunction or detection is expected, processing based on the state signal output from the sensing unit is not performed, and the state signal at the previous detection (however, the signal from the dummy sensing unit is a normal signal). Then, the processing is executed based on the state signal when the sensing unit does not malfunction or detect. As a result, it is possible to avoid in advance processing based on sensing malfunction or detection.

  The processing means is configured to output a processing signal to a predetermined system in an aircraft, and the processing means also responds to a status signal from the sensing section when the signal from the dummy sensing section is a normal signal. While the processed signal is output to the system, when the signal from the dummy sensing unit is not the normal signal, a preset processing signal is output to the system regardless of the state signal from the sensing unit. It may be configured.

  That is, when the signal from the dummy sensing unit is different from the normal signal, and the malfunction or detection of the sensing unit is expected, the processing means outputs a preset processing signal regardless of the status signal from the sensing unit. Output to the specified system. For example, when it is safe for the system to be in the support state, the processing signal may be a processing signal that the aircraft is in the support state. If there is something on the safe side, the processing signal may be “the aircraft is in an unsupported state”. As a result, it is possible to avoid the processing based on erroneous detection from being executed, and high safety is ensured.

  The aircraft disclosed herein includes a fuselage, legs that support the aircraft when the aircraft is on the ground, a state where the aircraft is on the ground and supported by the legs, and the aircraft is in the air An output means for outputting a state signal for distinguishing the state not supported by the leg, and a process corresponding to each of the state signal from the output means and when the aircraft is on the ground and in the air The output means is attached to the leg so as to detect a change in the state of the leg between a support state of the airframe and an unsupported state of the airframe. And a plurality of sensing units that output either one of the first and second state signals corresponding to the state change to the processing means, and the redundant means, and the output means is a state of the leg portion. Regardless of whether And further including at least one dummy sensing unit attached in the vicinity of each sensing unit so as to always output a normal signal, which is one of the second status signals, to the processing means. When the signal from the dummy sensing unit is a normal signal, the means performs processing according to the state signal from the sensing unit, while when the signal from the dummy sensing unit is not a normal signal, The processing according to the state signal is not executed.

As described above, landing gear and aircraft are equipped with separate dummy sensing unit and the sensing unit, based on a signal from the dummy sensing unit, by performing the determination of malfunction or erroneous detection of the sensing portion, It is possible to prevent the processing based on the malfunction or detection of the sensing unit due to the use environment from being executed. In other words, it is possible to avoid the execution of processing based on malfunctions or false detections only by making the sensing system redundant so that all of the multiple sensing units placed under the same usage environment malfunction or falsely detect. It can be avoided in no circumstances.

It is a perspective view which shows the principal part of an landing gear. It is a perspective view which expands and shows the attachment location of the WOW sensor in an landing gear. It is a side view which expands and shows the attachment location of the WOW sensor in an landing gear. It is a block diagram concerning the control system of the landing gear. It is a flowchart which concerns on control of a leg lifting control system. It is a flowchart which concerns on control of the leg lifting / lowering control system different from FIG. It is a side view which shows the attachment structure of the sensor for WOW in the landing gear different from FIG.

  Hereinafter, embodiments of an landing gear and the like will be described based on the drawings. The following description of the preferred embodiment is merely exemplary in nature.

  FIG. 1 shows a part of an aircraft landing gear 1, and this landing gear 1 includes leg portions 11 that support an airframe (not shown) on the ground. Here, the aircraft has a total of three leg portions including a front leg and left and right main legs, although illustration is omitted. The leg portion 11 shown in FIG. 1 corresponds to a main leg, but the basic structure is the same as that of the main leg except that the front leg also includes a steering mechanism, and illustration and description thereof are omitted here.

  The leg portion 11 includes a shock strut (shock strut) 2 disposed between the airframe and a wheel (not shown). The buffer strut 2 includes a strut cylinder 21 and a strut piston 22 that extend in the direction of the axis X, which is a substantially vertical direction, and the strut piston 22 is inserted coaxially with the strut cylinder 21 into the lower end portion of the strut cylinder 21. Is made up of. The strut cylinder 21 side of the buffer strut 2 is attached to the airframe via a storage mechanism (not shown). As a result, the buffer strut 2 is retracted from the airframe and pulled out of the airframe. Switch to a state that can be supported. On the other hand, on the strut piston 22 side of the buffer strut 2, an axle 23 that supports a wheel (not shown) is disposed extending in the horizontal direction.

  A torque link 3 is disposed between the strut cylinder 21 and the strut piston 22 in the buffer strut 2. The torque link 3 is composed of an upper link 31 disposed on the relatively upper side and a lower link 32 disposed on the relatively lower side. As shown in FIGS. 1 and 2, the base end portion of the upper link 31 is formed in a bifurcated shape so as to constitute pivot portions 311 and 311 on both the left and right sides of the axis X, respectively. The support portion 311 is pivotally coupled around an axis extending in the horizontal direction with respect to the lower end portion of the strut cylinder 21. The lower link 32 also has a base end portion formed in a bifurcated shape, and the bifurcated base end portion is pivotally connected to a lower end portion of the strut piston 22 around an axis extending in the horizontal direction. Yes. Thus, the upper link 31 extends obliquely downward from the base end portion pivotally supported by the strut cylinder 21, while the lower link 32 extends obliquely upward from the lower end portion of the strut piston 22. The tip of the upper link 31 and the tip of the lower link 32 are pivotally coupled to each other so as to be rotatable about an axis extending in the horizontal direction. With this configuration, the torque link 3 allows the strut cylinder 21 and the strut piston 22 to move relative to each other in the direction of the axis X to allow the buffer strut 2 to expand and contract as the upper link 31 and the lower link 32 rotate. However, the relative rotation of the strut cylinder 21 and the strut piston 22 around the axis line X is configured to be restricted by the rigidity of the upper link 31 and the lower link 32. Thus, as shown in FIG. 1, when the airframe is in the air and is not supported by the legs 11, the buffer strut 2 is in an extended state, while in the state where the airframe is on the ground and supported by the legs 11. The buffer strut 2 is in a contracted state.

  Whether the aircraft is in the air or on the ground is information used in various aircraft systems, and the landing gear 1 has a sensing system in order to detect this. . This sensing system is configured to include a WOW sensor 4 that is attached to the leg 11 and detects the expansion and contraction of the buffer support 2. In this embodiment, the WOW sensor 4 is constituted by a proximity sensor. Here, the type of the proximity sensor is not particularly limited, but may be, for example, an eddy current proximity sensor. This sensing system includes first and second WOW sensors 41 and 42 (see FIGS. 2 and 4) in order to form a redundant system. The first and second WOW sensors 41 and 42 are Respectively located on both the left and right sides with the axis X in between, they are disposed in the vicinity of the pivot portion 311 of the upper link 31 and are attached to the strut cylinder 21 via the attachment bracket 43. In addition, in FIG. 1, illustration of the attachment structure of each WOW sensor 41 and 42 is abbreviate | omitted. The detection targets 44 of the first and second WOW sensors 41 and 42 are respectively attached to the pivot portions 311 and 311 of the upper link 31. 2 and 3, each detection target 44 is a metal member to which the WOW sensor 4 (proximity sensor) can react, and includes a detection unit 442 having an arc-shaped sensing surface 441; The detector 442 is provided adjacent to the detector 442 in the circumferential direction, and includes a non-detector 443 that is recessed inward in the radial direction.

  In a state where the body is not supported by the leg portion 11 and the buffer support column 2 is extended, the upper link 31 is disposed so as to extend obliquely downward as shown by a solid line in FIG. In this state, the non-detection portion 443 of the detection target 44 attached to the pivot portion 311 of the upper link comes to face the WOW sensor 4, and in this state, the WOW sensor 4 outputs an off signal. As the airframe is supported by the legs by landing and the buffer strut 2 contracts from the unsupported state of the airframe, the upper link 31 rotates, and the upper link 31 as shown by the one-dot chain line in FIG. Are arranged so as to extend in a substantially horizontal direction. As the upper link 31 is rotated, the detection target 44 is rotated so that the sensing surface 441 of the detection unit 442 is opposed to the WOW sensor 4. In this state, the WOW sensor 4 outputs an ON signal. As shown in FIG. 4, the first and second WOW sensors 41 and 42 are connected to a leg lifting / lowering control system 51, and an off signal or an on signal from the first and second WOW sensors 41 and 42 is Input to the leg lift control system 51.

  The sensing system of the landing gear 1 also includes a third proximity sensor 45. This proximity sensor 45 is the same type and proximity sensor as the proximity sensor that constitutes the WOW sensor 4, and is not shown in FIG. 1 in the recessed portion 312 formed in the upper link 31. 46 is fixed. More specifically, as shown in FIGS. 2 and 3, a pseudo target portion similar to the detection target 44 is integrally formed on the bracket 46, and is arranged near the tip of the proximity sensor 45. The pseudo target unit includes a pseudo detection unit 463 corresponding to a part of the detection unit 442 of the detection target 44, and a pseudo non-detection unit corresponding to the non-detection unit 443 provided adjacent to the pseudo detection unit 463. 462. The third proximity sensor 45 is opposed to the pseudo non-detection unit 462. With this configuration, the third proximity sensor 45 is arranged in the vicinity of the WOW sensor 4 with a pseudo detection unit 463 and a pseudo non-detection unit 462, similarly to the WOW sensor 4 including the detection target 44. In addition, the third proximity sensor 45 always outputs an off signal regardless of the expansion and contraction of the buffer support 2. Hereinafter, the third proximity sensor 45 is referred to as a dummy sensor 45. As will be described later, the dummy sensor 45 is exposed to the WOW sensor 4 at the time of landing of an aircraft or the like by a guided radio wave by an instrument landing device, a radio wave by an airport weather Doppler radar, a radio wave by an airport surface detection radar, or the like. This is used to determine whether the WOW sensor 4 has malfunctioned or detected. Arranging the WOW sensor 4 and the dummy sensor 45 close to each other means placing these sensors in the same use environment. Further, by providing the pseudo detection unit 463 and the pseudo non-detection unit 462, the usage environment (electromagnetic environment) of the dummy sensor 45 becomes substantially the same as the electromagnetic environment of the WOW sensor 4. The dummy sensor 45 is also connected to the leg lift control system 51 as shown in FIG.

  FIG. 4 is a block diagram according to the control system for the landing gear. As described above, this aircraft has a total of three leg portions 11 including a front leg and left and right main legs. Each leg portion 11 includes first and second WOW sensors 41 and 42, a dummy sensor. A total of three proximity sensors, 45, are attached. Here, all the dummy sensors 45 attached to the respective leg portions 11 are configured to always output an off signal. A state signal from the first and second WOW sensors 41 and 42 in each leg 11 and a signal from the dummy sensor 45 are input to the leg lifting / lowering control system 51. Therefore, a total of nine proximity sensor signals including the status signals from the six WOW sensors 4 and the signals from the three dummy sensors 45 are input to the leg lift control system 51.

  The leg lift control system 51 also includes avionics 52 as various aircraft systems, flight control system 53, fire prevention system 54, air conditioning control system 55, cabin air pressure control system 56, angle of attack sensor 57, engine thrust, A reverser 58 and an onboard fuel metering system 59 are connected to each other. The leg lifting / lowering control system 51 relates to each of the systems 52 to 59 with respect to a processing signal based on the state signal of the WOW sensor 4, that is, whether the aircraft is on the ground or in the air. Output information. Each of the systems 52 to 59 appropriately executes various types of processing using information regarding whether the aircraft is on the ground or in the air.

  Next, processing in the leg lifting / lowering control system 51 will be described with reference to the flowchart shown in FIG. As described above, although this landing gear is provided with two WOW sensors in each leg portion 11 to form a redundant system, control related to the redundant system is omitted in this flowchart. .

  First, in step S11 after the start, based on the signal from the dummy sensor 45, it is determined whether the signal is normal or abnormal. Specifically, since the dummy sensor 45 is attached so as to always output an OFF signal, it is determined that the signal from the dummy sensor 45 is normal when the signal from the dummy sensor 45 is an OFF signal, whereas the signal from the dummy sensor 45 is When it is an ON signal, it is determined as abnormal. When the determination in step S11 is normal, the process proceeds to step S12. When the determination is abnormal, the process proceeds to step S15.

  In step S12, the leg lifting / lowering control system 51 determines the state of the WOW sensor 4, and if it is an ON signal, the process proceeds to step S13 to indicate that the system is in the WOW ON signal, that is, on the ground. Output to 52-59. On the other hand, when the signal is an off signal, the process proceeds to step S14, and a WOW off signal, that is, a state of being in the air is output to each of the systems 52 to 59. Thus, when the state of the dummy sensor 45 is normal, the leg lifting / lowering control system 51 determines that no malfunction or erroneous detection of the WOW sensor 4 has occurred, and detects and detects the WOW sensor 4. A processing signal corresponding to the output is output to each of the systems 52 to 59.

  On the other hand, when the signal from the dummy sensor 45 is abnormal, the dummy sensor 45 has malfunctioned or misdetected, and therefore is disposed in the vicinity of the dummy sensor 45 under the same usage environment (for example, The WOW sensors 41 and 42 that are placed in a noise environment such as a guided wave by an instrument landing device, a radio wave by an airport meteorological Doppler radar, or a radio wave by an airport surface detection radar also cause malfunction or detection. Probability is high. Therefore, in step S15, the leg lifting / lowering control system 51 retains the state of the previous WOW signal without using the current state signal from the WOW sensor 4. That is, a WOW on signal is output to each of the systems 52 to 59 when the previous WOW signal is on, and a WOW off signal when the previous WOW signal is off. However, the previous WOW signal here is a WOW signal output by the WOW sensor 4 when the dummy sensor 45 is in a normal state. Further, this processing can be applied when it is determined that it is safe to keep the state of the WOW signal as it is. When the state of the dummy sensor 45 is abnormal in this way, the WOW sensor 4 is also likely to have malfunctioned or erroneously detected, so the detection or output result of the WOW sensor 4 is not used. As a result, in each of the systems 52 to 59, it is possible to prevent the processing based on the malfunction or detection of the WOW sensor 4 from occurring, and the safety is ensured.

  FIG. 6 is a flowchart of processing in the leg lift control system 51, which is different from FIG. First, in step S21 after the start, based on the signal from the dummy sensor 45, it is determined whether the signal is normal (that is, an off signal) or abnormal (that is, an on signal). When it is normal, the process proceeds to step S22, and when it is abnormal, the process proceeds to step S25. In step S22, the leg lifting / lowering control system 51 determines the state of the WOW sensor 4, and if it is an ON signal, it outputs a WOW ON signal to each of the systems 52 to 59. In S24, a WOW off signal is output to each system 52-59. Similarly to the flow of FIG. 5, when the state of the dummy sensor 45 is normal, the leg lifting / lowering control system 51 determines that the WOW sensor 4 has not malfunctioned or detected, and the WOW sensor 4 is output to each of the systems 52-59.

  On the other hand, when the signal from the dummy sensor 45 is abnormal, there is a high possibility that both the dummy sensor 45 and the WOW sensors 41 and 42 are malfunctioning or erroneously detected. The control system 51 determines the state of the WOW signal on the safe side in each of the systems 52 to 59. Then, for a system where the WOW on signal is safe, a WOW on signal is output in step S26, and for a system where the WOW off signal is safe, a WOW off signal is output in step S27. To do. Whether the WOW on signal is on the safe side or the WOW off signal is on the safe side is preset and stored for each system 52-59, and in step S25, each system 52-59 is based on that setting. What is necessary is just to determine the processing signal output to (1). In this way, when the state of the dummy sensor 45 is abnormal, a WOW on signal or a WOW off signal that is preset so as to be on the safe side is output for each system, so that each system 52 to 59 uses a WOW signal. It is possible to avoid the processing based on the malfunction or detection of the sensor 4 from occurring, and high safety is ensured.

  As described above, in this landing gear 1, by arranging the dummy sensor 45 in the vicinity of the WOW sensor 4, the same proximity sensor is arranged in the same use environment as the WOW sensor 4. Based on the output of the dummy sensor 45, the influence of noise or the like on the WOW sensor 4 can be grasped. That is, it becomes possible to accurately grasp whether or not the WOW sensor 4 is malfunctioning or erroneously detected due to radio waves generated by the instrument landing device, the airport weather Doppler radar, or the airport surface detection radar.

  Thus, when the signal of the dummy sensor 45 is abnormal, the process based on the state signal from the WOW sensor 4 is not performed. Thus, the configuration in which the dummy sensor 45 is added has an advantage that the system configuration is simplified because the control logic can be extremely simple.

  In aircraft system design, laws and regulations stipulate that similar failures due to the same event do not occur. Unlike the system disclosed here, in the system that does not have the dummy sensor 45, the malfunction or detection of the WOW sensor 4 (proximity sensor) due to the noise environment described above is caused by the same event and the redundant sensor. This regulation cannot be satisfied because it is a similar fault that can occur regardless of gender. On the other hand, the system to which the dummy sensor 45 is added can reliably avoid the processing based on the malfunction or detection of the WOW sensor 4 (proximity sensor) due to noise environment or the like as described above. Events related to malfunction of the sensor 4 are eliminated. Thus, the system to which the dummy sensor 45 is added can be a means for conforming to related laws and regulations.

  In the configuration shown in FIG. 3, the pseudo detection unit 463 and the pseudo non-detection unit 462 are provided in the bracket 46. However, in the configuration in which the dummy sensor 45 always outputs an off signal, the pseudo detection unit 463 and the pseudo detection unit 463 are provided. The pseudo non-detection unit 462 may be omitted. In the configuration shown in FIG. 3, the dummy sensor 45 is configured to always output an OFF signal. For example, as shown in FIG. 7, the sensing unit 461 detected by the dummy sensor 45 is connected to the bracket 46. You may make it provide integrally. The shape or the like of the sensing unit detected by the dummy sensor 45 is not limited to the example in the figure, and although not shown, the shape similar to the detection unit 442 of the detection target 44 and the non-adjacent to the detection unit 442 The shape may include the detection unit 443. In this configuration, the dummy sensor 45 always outputs an ON signal regardless of the expansion and contraction of the buffer support 2. In this configuration, for example, in the flow of FIG. 5 or FIG. 6, it is determined that the signal is normal when the signal from the dummy sensor 45 is an on signal, and is abnormal when the signal from the dummy sensor 45 is an off signal.

  The dummy sensor 45 is not provided with one for each leg portion 11, but is omitted from illustration, but is mounted so as to output a always-on signal and a dummy sensor mounted so as to always output an off-signal. You may make it equip each leg part 11 with two dummy sensors with a dummy sensor. In this configuration, it is possible to determine that the signal is normal when the signals from the two dummy sensors are different from each other, and to determine that the signal is abnormal when the signals from the two dummy sensors are the same.

  In contrast to the above, the WOW sensor 4 outputs an off signal when the airframe is supported by the leg portion 11 and outputs an on signal when the airframe is not supported by the leg portion 11. A good sensor (Weight Off Wheel) may be used.

  Further, the attachment position of the dummy sensor 45 is not particularly limited, and may be disposed in the vicinity of the WOW sensor so that the usage environment is substantially the same as that of the WOW sensor 4.

  In addition, the dummy sensor 45 is not provided only for determination of malfunction or detection of the WOW sensor 4 as in this embodiment, but a sensor used for other purposes is used as a dummy sensor (shared use) ) Is also possible. For example, a proximity sensor attached to detect the pulled-out state and retracted state of the leg portion 11 always outputs an on or off signal when the leg portion 11 is pulled out, so that the proximity sensor is used as a dummy sensor. You may make it utilize.

  Moreover, in this embodiment, although the sensing system of the landing gear 1 is made redundant, the redundant system is not an indispensable configuration and can be omitted. Even if the sensing system using the dummy sensor 45 constitutes a redundant system, a situation in which processing based on malfunction or detection of the WOW sensor 4 can be executed, in other words, a plurality of WOWs constituting the redundant system. In a situation where all the sensors for the malfunction or malfunction are detected, it is possible to avoid the execution of the process based on the malfunction or the like.

  Furthermore, the system including the dummy sensor is not limited to the sensing system related to the WOW sensor in the landing gear, and can be applied to various sensing systems in various devices and systems including an aircraft. In this case, the sensor (sensor corresponding to the WOW sensor in the above configuration) is not limited to a sensor that outputs an on / off signal as in the above configuration, but may be a sensor that also outputs an intermediate value. . On the other hand, the dummy sensor may be configured to always output a specific status signal.

  As described above, the technique disclosed herein can be applied to various sensing systems because it can avoid processing based on sensor malfunction or detection, and in particular, a WOW sensor in an aircraft landing gear. It is useful for sensing systems including

DESCRIPTION OF SYMBOLS 1 Landing device 11 Leg part 2 Buffer support | pillar 41 1st WOW sensor (output means, sensing part)
42 Second WOW sensor (output means, sensing unit)
44 Detection target (target)
45 Dummy sensor (dummy sensing part)
51 Leg lifting control system (processing means)
52 Avionics (System)
53 Flight Control System (System)
54 Fire prevention system
55 Air conditioning control system
56 Cabin air pressure control system
57 Angle of attack sensor (system)
58 Engine Thrust Reverser (System)
59 Onboard fuel metering system

Claims (5)

Legs that support the aircraft when it is on the ground,
An output means for outputting a state signal for distinguishing between a state where the aircraft is on the ground and supported by the legs and a state where the aircraft is in the air and is not supported by the legs;
Processing means for receiving a status signal from the output means, and executing processing corresponding to each of when the aircraft is on the ground and when in the air,
The output means is attached to the leg portion so as to detect a change in the state of the leg portion between the support state of the airframe and the unsupported state of the airframe, and is adapted to change the state according to the state change. A plurality of sensing units that output either one of the first and second state signals to the processing means and are made redundant;
In the vicinity of each sensing unit, the output means always outputs a normal signal, which is one of the first and second state signals, to the processing means regardless of the state of the legs. And at least one dummy sensing unit disposed in
When the signal from the dummy sensing unit is a normal signal, the processing means performs processing according to the state signal from the sensing unit, while when the signal from the dummy sensing unit is not a normal signal, A landing gear configured not to execute processing according to a state signal from a section. The landing gear according to claim 1,
The leg portion includes a buffer post that expands and contracts between a support state of the airframe and an unsupported state of the airframe,
Each of the sensing units includes a proximity sensor and a target that is separated from and in contact with the proximity sensor according to expansion and contraction of the buffer column, and the proximity sensor detects and detects the target according to expansion and contraction of the buffer column. Configured to output the first and second state signals in accordance with non-detection;
The dummy sensing unit includes a proximity sensor having the same configuration as the proximity sensor of the sensing unit, and the proximity sensor outputs one of the first and second state signals regardless of the expansion and contraction of the buffer column. A landing gear that is installed and configured. The landing gear according to claim 1 or 2,
When the signal from the dummy sensing unit is not the normal signal, the processing means is a state signal when the signal from the dummy sensing unit is the normal signal and the sensing unit previously detected A landing gear configured to perform a process according to the response. The landing gear according to claim 1 or 2,
The processing means is configured to output a processing signal to a predetermined system in an aircraft,
When the signal from the dummy sensing unit is a normal signal, the processing means outputs a processing signal corresponding to the status signal from the sensing unit to the system, while the signal from the dummy sensing unit is the normal signal. An landing gear configured to output a preset processing signal to the system regardless of a state signal from the sensing unit when the signal is not a signal. The aircraft,
Legs that support the aircraft when the aircraft is on the ground;
An output means for outputting a state signal for distinguishing between a state where the aircraft is on the ground and supported by the legs and a state where the aircraft is in the air and is not supported by the legs;
Processing means for receiving a status signal from the output means, and executing processing corresponding to each of when the aircraft is on the ground and in the air,
The output means is attached to the leg portion so as to detect a change in the state of the leg portion between the support state of the airframe and the unsupported state of the airframe, and is adapted to change the state according to the state change. A plurality of sensing units that output either one of the first and second state signals to the processing means and are made redundant;
In the vicinity of each sensing unit, the output means always outputs a normal signal, which is one of the first and second state signals, to the processing means regardless of the state of the legs. And at least one dummy sensing unit attached to the
When the signal from the dummy sensing unit is a normal signal, the processing means performs processing according to the state signal from the sensing unit, while when the signal from the dummy sensing unit is not a normal signal, An aircraft configured not to execute processing according to a state signal from a section.

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