Mountable device for inspecting driving system of aerial vehicle

Abstract

The present invention relates to a mountable device for inspecting a driving system of an aerial vehicle, the device comprising: a mountable inspection unit detachably mounted on an aerial vehicle equipped with a driving system including a driving motor and a propeller; and an operation inspection unit provided in the mountable inspection unit and for inspecting whether the driving system is normally operated. The device can selectively be mounted on an aerial vehicle such as a drone to accurately diagnose whether the driving system of the aerial vehicle is normally operated during operation, thereby preventing an accident caused by a driving system failure during actual flight of the aerial vehicle and significantly improving flight stability of the aerial vehicle.

Description

Aircraft Mounted Drive System Inspection Device

[0001] The present invention relates to a drive system inspection device mounted on an aircraft, and more specifically, to a drive system inspection device mounted on an aircraft, such as a drone, for diagnosing whether the drive system of the aircraft is operating normally.

[0002] Generally, aircraft are primarily used to fly through the air and transport people or cargo.

[0003] Small aircraft capable of vertical take-off and landing using drive motors, such as drones, are being widely adopted in various fields, including photography and transportation, due to the advantage of being unmanned and not requiring a runway for take-off and landing.

[0004] In particular, interest in air mobility has been increasing recently due to urban environmental pollution and traffic problems. With the rapid advancement of technology for small aircraft capable of vertical take-off and landing using drive motors, such as drones, the development of air taxis and drone taxis is actively underway.

[0005] In addition, a vertical take-off and landing aircraft operates with a drive system that includes a propeller and a drive motor that rotates the propeller.

[0006] The aircraft takes off and lands at the landing strip, periodically checks drive systems such as motors and propellers upon landing, and then takes off again to begin flight.

[0007] Typically, inspectors visually check for abnormalities in an aircraft's drive system; however, since simple visual inspections cannot accurately determine the condition of the drone's motors and propellers, various serious accidents caused by drive system failures are frequently occurring during actual flight.

[0008] To solve these problems, the applicant has proposed Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft."

[0009] Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft," is equipped with a physical motion detection unit capable of checking the operating status of a drive unit in the station part where the aircraft takes off and lands, so that the operating status of the drive system can be checked during the takeoff and landing of the aircraft.

[0010] However, since Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft," checks the operating drive system while the aircraft is airborne after taking off from the station, there may be cases where it is difficult to accurately check the operating status of the drive system from the physical motion detection unit due to the distance between the physical motion detection unit equipped in the station and the aircraft's drive system.

[0011] In addition, Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft," had a problem in that it was difficult to check the operating status of the drive system in various flight environments of the aircraft.

[0012] A prior art patent related to the present invention is Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft" (registered May 24, 2023).

[0013] The objective of the present invention is to provide a drive system inspection device mounted on an aircraft, such as a drone, which can diagnose whether the drive system of the aircraft is operating normally during operation.

[0014] To achieve the above objective, one embodiment of a drive system inspection device mounted on an aircraft according to the present invention is characterized by comprising an inspection mounting part detachably mounted on an aircraft equipped with a drive system including a drive motor and a propeller, and an operation inspection part provided on the inspection mounting part for checking whether the drive system is operating normally.

[0015] In the present invention, the inspection mounting part can be detachably mounted to a plurality of arms on the aircraft where the drive system is mounted.

[0016] In the present invention, the inspection mounting portion may be mounted on the arm by including a first mounting jig portion that wraps around a part of the arm portion on one side of the arm portion and a second mounting jig portion that wraps around another part of the arm portion on the other side of the arm portion, in a manner that pressurizes and holds the arm portion between the first mounting jig portion and the second mounting jig portion.

[0017] In the present invention, the first mounting jig portion is provided with a first arm insertion portion into which a part of the arm portion is inserted, and the second mounting jig portion is provided with a second arm insertion portion into which another part of the arm portion is inserted, and the inner surface of the first arm insertion portion is provided with a first grip elastic pad portion, and the inner surface of the second arm insertion portion is provided with a second grip elastic pad portion.

[0018] In the present invention, the inspection mounting part may further include a jig driving part capable of moving at least one of the first mounting jig part and the second mounting jig part to press and hold or release the arm part between the first mounting jig part and the second mounting jig part.

[0019] In the present invention, the driving unit for the jig is screw-coupled to the first mounting jig and the second mounting jig by penetrating them, and includes a moving screw that is screw-coupled in opposite directions and a screw rotation motor that rotates the moving screw, so that the first mounting jig and the second mounting jig can be simultaneously moved in an inward direction facing each other or simultaneously moved outward in the opposite direction by the rotation of the moving screw.

[0020] In the present invention, the operation inspection unit may include a sensor housing unit connected to the first mounting jig unit or the second mounting jig unit, and a diagnostic sensor unit provided in the sensor housing unit that detects a physical quantity capable of verifying whether the driving system is operating normally.

[0021] In the present invention, the operation inspection unit may further include a housing connection unit, one end of which is mounted on the sensor housing unit and the other end of which is connected to the inspection mounting unit, and a sensor movement drive unit that moves the housing connection unit forward and backward in the length direction of the arm unit to position the sensor housing unit facing the drive system.

[0022] In the present invention, the operation inspection unit may include a first sensor housing unit positioned on one side of the driving system to be inspected, with a sensing surface equipped with a plurality of diagnostic sensor units positioned to face the driving system; a second sensor housing unit positioned on the other side of the driving system, with a sensing surface equipped with a plurality of diagnostic sensor units positioned to face the driving system; a first housing connection unit positioned to be movable through the first mounting jig unit and having the first sensor housing unit mounted on one side; a first sensor movement drive unit that moves the first housing connection unit in a straight line forward and backward; a second housing connection unit positioned to be movable through the second mounting jig unit and having the second sensor housing unit mounted on one side; and a second sensor movement drive unit that moves the second housing connection unit in a straight line forward and backward.

[0023] In the present invention, the operation inspection unit may further include a third sensor housing unit in which one end is mounted on the lower end of the first sensor housing unit and is positioned so as to be bent toward the second sensor housing unit, and the upper sensing surface equipped with a plurality of diagnostic sensor units is positioned to face the lower end of the driving system.

[0024] In the present invention, the operation inspection unit may further include a lifting / lowering drive unit located in the first sensor housing unit that moves the third sensor housing unit up and down.

[0025] In the present invention, the operation inspection unit may further include a fourth sensor housing unit that is mounted at one end of the second sensor housing unit and positioned so as to be bent toward the first sensor housing unit, with a sensing surface equipped with a plurality of diagnostic sensor units positioned to face the driving system.

[0026] In the present invention, the operation inspection unit may further include a housing rotation drive unit provided at one end of the second sensor housing unit to rotate the fourth sensor housing unit to open and close the space between the first sensor housing unit and the second sensor housing unit.

[0027] In the present invention, the diagnostic sensor unit may include a magnetic field sensing unit that detects a change in the magnetic field of the driving system, a vibration sensing unit for a driving unit that detects vibrations of the driving system, and a sound wave sensing unit that measures sound waves generated by the driving system.

[0028] In the present invention, the operation inspection unit further includes a position detection unit that confirms the position of the driving system to be inspected, and the position detection unit may be a thermal imaging camera unit.

[0029] The present invention is selectively mounted on an aircraft such as a drone to accurately diagnose whether the propulsion system of the aircraft is operating normally during operation, thereby preventing accidents caused by propulsion system failures during actual flight and significantly improving the flight stability of the aircraft.

[0030] The present invention can be selectively mounted on an aircraft such as a drone to simply and periodically check for normal operation during the operation of the aircraft's drive system, thereby ensuring both accuracy and convenience when inspecting the drive system.

[0031] FIGS. 1 and FIGS. 2 are perspective views illustrating an embodiment of a drive system inspection device mounted on an aircraft according to the present invention.

[0032] FIG. 3 is a plan view illustrating an embodiment of a drive system inspection device mounted on an aircraft according to the present invention.

[0033] FIG. 4 is a schematic diagram illustrating an embodiment of a drive system inspection device mounted on an aircraft according to the present invention.

[0034] Explanation of major symbols in the drawings

[0035] 10 : Aircraft 20 : Dark part

[0036] 30 : Drive system 31 : Drive motor

[0037] 32 : Propeller

[0038] 100: Inspection mounting part 110: First mounting jig part

[0039] 111: First arm insertion part 112: First grip elastic pad part

[0040] 120: Second mounting jig part 121: Second arm insertion part

[0041] 122: Elastic pad section for the second grip 130: Driving section for the jig

[0042] 200: Operation inspection unit 210: Sensor housing unit

[0043] 211: First sensor housing part 212: Second sensor housing part

[0044] 213: Third sensor housing part 214: Fourth sensor housing part

[0045] 220: Diagnostic sensor unit 221: Magnetic field detection unit

[0046] 222: Vibration detection unit for drive unit 223: Sound wave detection unit

[0047] 224: Thermal imaging camera unit 230: Housing connection unit

[0048] 231: 1st housing connection part 232: 2nd housing connection part

[0049] 240: Drive unit for sensor movement 241: Drive unit for first sensor movement

[0050] 242: Drive unit for moving the second sensor 250: Lifting / lowering drive unit

[0051] 260: Drive unit for housing rotation

[0052] Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. However, the technical concept of the present invention is not limited to the embodiments described herein and may be embodied in other forms. Rather, the embodiments introduced herein are provided to ensure that the disclosed content is thorough and complete and to sufficiently convey the concept of the present invention to those skilled in the art.

[0053] In this specification, when a component is described as being on another component, it means that it may be formed directly on the other component or that a third component may be interposed between them. Additionally, in the drawings, the thicknesses of shapes and regions are exaggerated for the effective description of the technical content.

[0054] Furthermore, although terms such as first, second, third, etc., have been used to describe various components in the various embodiments of this specification, these components should not be limited by such terms. These terms are used merely to distinguish one component from another. Accordingly, what is referred to as the first component in one embodiment may be referred to as the second component in another embodiment. Each embodiment described and illustrated herein also includes its complementary embodiment. Additionally, in this specification, "and / or" is used to mean including at least one of the components listed before and after it.

[0055] In the specification, singular expressions include plural expressions unless the context clearly indicates otherwise. Furthermore, terms such as "include" or "have" are intended to specify the existence of the features, numbers, steps, components, or combinations thereof described in the specification, and should not be understood as excluding the existence or addition of one or more other features, numbers, steps, components, or combinations thereof. Additionally, in this specification, "connection" is used to include both indirectly connecting multiple components and directly connecting them.

[0056] Furthermore, in describing the present invention below, if it is determined that a detailed description of related known functions or configurations could unnecessarily obscure the essence of the invention, such detailed description will be omitted.

[0057] FIGS. 1 and FIGS. 2 are perspective views illustrating an embodiment of a mounted drive system inspection device for an aircraft (10) according to the present invention, FIG. 3 is a plan view illustrating an embodiment of a mounted drive system inspection device for an aircraft (10) according to the present invention, and FIG. 4 is a schematic diagram illustrating an embodiment of a mounted drive system inspection device for an aircraft (10) according to the present invention.

[0058] An embodiment of a mounted drive system inspection device for an aircraft (10) according to the present invention will be described in detail below with reference to FIGS. 1 to 4.

[0059] One embodiment of the drive system inspection device mounted on an aircraft (10) according to the present invention is a drive system inspection device that is detachably mounted on an aircraft (10), such as a drone, that flies with a drive system (30) including a drive motor (31) and a propeller (32) rotated by the drive motor (31), and checks whether the drive system (30) is operating normally.

[0060] One embodiment of the drive system inspection device mounted on an aircraft (10) according to the present invention is an example in which the device is mounted on the aircraft (10) to check whether the drive motor (31) and propeller (32), etc. are operating normally while the aircraft (10) is flying, to check the degree of failure and aging of the drive system (30), and is separated from the aircraft (10) after the inspection of the drive system (30) is completed.

[0061]

[0062] One embodiment of the inspection device for a mounted drive system of an aircraft according to the present invention includes an inspection mounting part (100) that is detachably mounted to an aircraft (10) to be inspected, and the inspection mounting part (100) is detachably mounted to an arm (20) of the aircraft (10) on which the drive system (30) is mounted.

[0063] The aircraft (10) is provided with a plurality of arm sections (20) on which a drive system (30) is mounted, and the drive system (30) is located at the end side of the arm section (20).

[0064]

[0065] One embodiment of the mounted drive system inspection device for an aircraft according to the present invention is such that an inspection mounting part (100) is detachably mounted to each of a plurality of arm parts (20) to inspect a drive system (30) provided in each arm part (20), that is, a drive system (30) including a drive motor (31) and a propeller (32), etc.

[0066] An inspection mounting part (100) is exemplified by including a first mounting jig part (110) that covers at least a portion of the arm (20) on one side of the arm (20) and a second mounting jig part (120) that covers at least another portion of the arm (20) on the other side of the arm (20).

[0067] The inspection mounting part (100) is mounted on the arm (20) in a manner that presses and holds the arm (20) between the first mounting jig part (110) and the second mounting jig part (120).

[0068] The first mounting jig part (110) is provided with a first arm insertion part (111) into which a part of the arm part (20) is inserted, and the second mounting jig part (120) is provided with a second arm insertion part (121) into which another part of the arm part (20) is inserted.

[0069] An elastic pad portion (112) for a first grip is provided on the inner surface of the first arm insertion portion (111), and an elastic pad portion (122) for a second grip is provided on the inner surface of the second arm insertion portion (121).

[0070] The first grip elastic pad portion (112) and the second grip elastic pad portion (122) prevent the arm portion (20) from being damaged or deformed by pressure generated when the arm portion (20) is pressed between the first mounting jig portion (110) and the second mounting jig portion (120), and allow the arm portion (20) to be firmly gripped between the first mounting jig portion (110) and the second mounting jig portion (120).

[0071] Additionally, the inspection mounting part (100) further includes a jig driving part (130) that can move at least one of the first mounting jig part (110) and the second mounting jig part (120) to press and hold or release the arm part (20) between the first mounting jig part (110) and the second mounting jig part (120).

[0072] The jig drive unit (130) moves at least one of the first mounting jig unit (110) and the second mounting jig unit (120) in a direction that narrows or widens the gap between the first mounting jig unit (110) and the second mounting jig unit (120).

[0073] The drive unit (130) for the jig is exemplified as a linear actuator of the ball screw type, and although not illustrated as an example, it may include a moving screw (not illustrated) that is screw-coupled to the first mounting jig unit (110) and the second mounting jig unit (120) respectively by passing through them and screw-coupled in opposite directions, and a screw rotation motor (not illustrated) that rotates the moving screw.

[0074] The first mounting jig part (110) and the second mounting jig part (120) are each screw-coupled to a moving screw in opposite directions, so that by the rotation of the moving screw, they can move inwardly toward each other or move outwardly toward the opposite direction, thereby narrowing or widening the gap.

[0075] Although not illustrated, the first mounting jig part (110) and the second mounting jig part (120) may have a rotating opening and closing structure in which the other end part opens or closes around the hinge and surrounds and presses the arm part (20).

[0076] The rotational opening and closing structure of the first mounting jig part (110) and the second mounting jig part (120) includes a jig driving part (130) that rotates the first mounting jig part (110) and the second mounting jig part (120) using a jig motor.

[0077] The jig motor rotates the first mounting jig part (110) and the second mounting jig part (120) to open and close the space between the first mounting jig part (110) and the second mounting jig part (120), thereby allowing the arm part (20) to be gripped by the first mounting jig part (110) and the second mounting jig part (120), or the first mounting jig part (110) and the second mounting jig part (120) to be separated from the arm part (20).

[0078] Meanwhile, the first mounting jig part (110) and the second mounting jig part (120) move simultaneously inwardly facing each other by the rotation of the moving screw to grip the arm part (20), or move simultaneously outwardly to the opposite direction to place the arm part (20) while creating a gap.

[0079] The first mounting jig part (110) and the second mounting jig part (120) can move inward or outward simultaneously to grip or release the arm part (20), so that the arm part (20) can be accurately grasped at the center of the jig drive part (130), and the travel distance is minimized so that it can be mounted on the arm part (20) or detached from the arm part (20) quickly and rapidly.

[0080] The above inspection mounting part (100) is equipped with an operation inspection part (200) for checking whether the driving system (30) is operating normally.

[0081] The operation inspection unit (200) includes a sensor housing unit (210) connected to a first mounting jig unit (110) or a second mounting jig unit (120), and a diagnostic sensor unit (220) provided in the sensor housing unit (210) for detecting a physical quantity that can verify whether the driving system (30) of the aircraft (10) is operating normally.

[0082] The diagnostic sensor unit (220) is, as an example, a sensor capable of measuring physical quantities generated from the drive motor (31) and propeller (32) to check whether the drive motor (31) and propeller (32), etc., of the drive system (30) of the aircraft (10) are operating normally, that is, whether the drive motor (31) and propeller (32), etc. of the drive system (30) are malfunctioning or the condition of the drive motor (31) and propeller (32), etc. of the aging.

[0083] The diagnostic sensor unit (220) includes multiple sensors that detect different types of failure factors, that is, different types of physical quantities, and measures various types of physical quantities to check whether the drive motor (31) and propeller (32), etc. are operating normally, thereby more accurately detecting whether there is abnormal operation of the drive system (30) of the aircraft (10).

[0084] Additionally, the interior of the sensor housing (210) includes a wireless communication unit that transmits physical quantities measured by a plurality of diagnostic sensor units (220) to an aircraft management system (not shown).

[0085] The aircraft management system (not shown) can communicate via wireless communication with an application for diagnosing the drive system of the aircraft (10) installed on the aircraft manager's portable terminal or the aircraft pilot's portable terminal, and transmit the diagnosis result of the drive system (30) of the aircraft (10) detected by the diagnosis sensor unit (220) to the application for diagnosing the drive system.

[0086] The aircraft management system (not shown) receives physical quantities of the driving system (30) of the aircraft (10) detected by the diagnostic sensor unit (220), checks whether the driving system (30) is operating normally through data analysis, and transmits the confirmed diagnostic results to the driving system diagnostic application and the control unit via wireless communication.

[0087] The aircraft management system (not shown) diagnoses the driving system (30) as operating normally if the physical quantity measured by the diagnostic sensor unit (220) falls within a preset range, and diagnoses the driving system (30) as operating abnormally if the physical quantity measured by the diagnostic sensor unit (220) falls outside the preset range.

[0088] The aircraft manager or aircraft pilot can easily check the diagnostic results of the aircraft's (10) drive system (30) by running an application for diagnosing the aircraft's (10) drive system on a portable terminal and verifying the results through the physical quantity detected by the diagnostic sensor unit (220).

[0089] A portable terminal is exemplified by a smartphone, and may also include other known portable terminals such as tablet PCs.

[0090] Meanwhile, the diagnostic sensor unit (220) includes at least two of a magnetic field detection unit (221) that detects changes in the magnetic field of the driving system (30), a vibration detection unit (222) for the driving unit that detects vibrations of the driving system (30), and a sound wave detection unit (223) that measures sound waves, i.e., noise, generated from the driving system (30), to detect whether there is an abnormal operation of the driving system (30) of the aircraft (10).

[0091] The magnetic field detection unit (221) is for detecting changes in the magnetic field generated by the drive motor (31) and is positioned as close as possible to the drive motor (31) to detect changes in the magnetic field generated by the drive motor (31).

[0092] The drive system (30) includes a propeller (32), a drive motor (31) that rotates the propeller (32), and an electronic speed controller (ESC) that controls the speed of the drive motor (31). The drive unit inspection sensor unit (211) includes a magnetic field detection unit (221) that detects a magnetic field generated in the drive system (30).

[0093] The magnetic field detection unit (221) detects the magnetic field generated by the drive system (30), that is, the drive motor (31) and the electronic speed controller (ESC) that controls the speed of the drive motor (31).

[0094] An electronic speed controller (ESC) is installed to change the speed of a drive motor (31) in an aircraft (10) such as a drone, and further detailed description is omitted.

[0095] When the drive motor (31) is in operation, a permanent magnetic field and an induced magnetic field are generated around it, and the ESC, that is, the electronic speed controller, generates a motor control signal for speed control of the drive motor (31).

[0096] The magnetic field detection unit (221) detects the magnetic field generated by the drive motor (31), that is, the permanent magnetic field and the induced magnetic field generated during motor operation, and detects the magnetic field from the motor control signal of the ESC, that is, the electronic speed controller, and transmits it to the flight management system (not shown).

[0097] The magnetic field detection unit (221) detects the permanent magnetic field and induced magnetic field generated when the drive motor (31) operates, as well as the motor control signal of the electronic speed controller.

[0098] One example is that the vibration detection unit (222) for the drive unit is a radar sensor unit that measures the vibration physical quantity of the drive system (30), namely the vibration physical quantity of the propeller (32) and the drive motor (31), using radio waves.

[0099] The radar sensor unit emits radio waves to the propeller (32) of the drive system (30) to measure the physical vibration quantity of the propeller (32).

[0100] In the sensor housing (210), a radio wave emission opening (not shown) is located, which is blocked by a radio wave transmission cover member made of a material through which radio waves can pass, and through which radio waves are emitted from a radar sensor unit installed inside.

[0101] The radar sensor part is located within the sensor housing part (210) and is protected from external environments such as moisture.

[0102] The radio wave emission opening (not shown) is positioned so that the center of the emitted radio wave, that is, the center of the directional radio wave beam, is directed toward the motor, so as to accurately measure the vibrations generated from the drive motor (31) and the propeller (32).

[0103] The radar sensor unit can simultaneously measure physical quantities by the propeller (32) by the center of the radio wave, that is, the center of the directional radio wave beam, directed toward the motor, and the width of the radio wave, that is, the beam width.

[0104] That is, the radar sensor unit can individually detect and measure the vibration physical quantity of the drive motor (31) and the vibration physical quantity of the propeller (32) during the flight of the aircraft (10) and transmit them to a flight management system (not shown).

[0105] Additionally, the sound wave detection unit (223) is, for example, a microphone capable of receiving sound waves and converting them into voice current, and includes a plurality of microphones to receive sound, i.e., sound waves generated in the driving system (30), convert the sound waves into an electrical signal, i.e., voice current, and enable the magnitude of the sound waves to be checked.

[0106] The diagnostic sensor unit (220) further includes a thermal imaging camera unit (224) that photographs the drive motor (31) of the drive system (30).

[0107] The thermal imaging camera unit (224) can measure the heat distribution of the drive motor (31) to check whether the drive motor (31) is operating abnormally, and also allows the position of the sensor housing unit (210) relative to the drive system (30) to be checked based on the position mounted on the sensor housing unit (210).

[0108]

[0109] Meanwhile, the operation inspection unit (200) further includes a housing connection unit (230) in which one end is mounted on the sensor housing unit (210) and the other end is connected to the inspection mounting unit (100) to position the sensor housing unit (210) facing the driving system (30).

[0110] The sensor housing part (210) is connected to the inspection mounting part (100) via the housing connection part (230) so that its position is fixed.

[0111] That is, the sensor housing part (210) is connected to the first mounting jig part (110) or the second mounting jig part (120) to fix its position, and is positioned so that one side on which a plurality of diagnostic sensor parts (220) are located faces the driving system (30).

[0112] One side of the sensor housing (210) is a sensing surface on which a plurality of diagnostic sensor units (220) are located and which can detect a physical quantity generated by the driving system (30) while facing the driving system (30), and as an example, the sensor housing (210) is positioned so that the side on which the plurality of diagnostic sensor units (220) are located faces the driving system (30).

[0113] Additionally, the operation inspection unit (200) further includes a sensor movement drive unit (240) that moves the housing connection unit (230) forward and backward, that is, moves it forward and backward in the length direction of the arm (20), thereby positioning the sensor housing unit (210) so that it faces the drive motor (31) on the lower side of the propeller (32).

[0114] As an example, the housing connection part (230) is formed in a rod shape or a bar shape and is positioned to move forward and backward in the length direction of the arm part (20) by penetrating the inspection mounting part (100), and the sensor movement drive part (240) is provided in the inspection mounting part (100) to move the housing connection part (230) forward and backward.

[0115] The sensor moving drive unit (240) can move the sensor housing unit (210) to the inspection position of the drive system (30) regardless of the position where the inspection mounting unit (100) is mounted on the arm (20) or the model of the aircraft (10).

[0116] The operation inspection unit (200) is provided in the sensor housing unit (210) and further includes a position detection unit for confirming the position of the driving system (30) to be inspected.

[0117] The sensor moving drive unit (240) is exemplified as a rack-pinion structure including a rack gear formed in the longitudinal direction of the housing connecting unit (230), a pinion gear that rotates by meshing with the rack gear, and a motor that rotates the pinion gear.

[0118] The operation inspection unit (200) is provided in the sensor housing unit (210) and further includes a position detection unit for confirming the position of the driving system (30) to be inspected.

[0119] The position detection unit can confirm the position of the driving system (30) by photographing the driving system (30) with a thermal imaging camera unit (224) and can confirm the heat distribution state generated from the driving motor (31) during the operation of the driving motor (31).

[0120]

[0121] The position detection unit may be a known camera that captures the driving system (30) in addition to the thermal imaging camera unit (224) to confirm the position of the driving system (30), and may also be implemented in various modified ways using a known detection structure capable of confirming the position of the driving system (30), such as a laser distance sensor.

[0122] Since the driving system (30) is generally located at the end side of the arm (20), if the position detection part is a laser distance sensor, the laser distance sensor is located at the end side of the sensor housing part (210) based on the direction of movement of the sensor housing part (210).

[0123] The laser distance sensor is positioned at the end of the sensor housing (210) and detects when the sensor housing (210) is moved by the sensor moving drive unit (240) and the end of the sensor housing (210) is positioned so that the sensor housing (210) moves out of the arm (20).

[0124] The sensor moving drive unit (240) moves the sensor housing unit (210) so that when the laser distance sensor located at the end of the sensor housing unit (210) moves away from the end of the arm unit (20), the operation stops and the sensing surface of the sensor housing unit (210) can be positioned to face the driving system (30).

[0125] The sensor moving drive unit (240) is controlled by a control unit provided in the sensor mounting unit, and the control unit is equipped with a wireless communication unit and controls the operation of the sensor moving drive unit (240) as well as being connected to a plurality of diagnostic sensor units (220), namely a magnetic field detection unit (221), a vibration detection unit for the drive unit (222), a sound wave detection unit (223), and a thermal imaging camera unit (224).

[0126] The control unit receives signals or images detected by a plurality of diagnostic sensor units (220), namely a magnetic field detection unit (221), a vibration detection unit for a driving unit (222), a sound wave detection unit (223), and a thermal imaging camera unit (224), and transmits them to an aircraft management system (not shown) via a wireless communication unit.

[0127] The control unit receives an image captured by the thermal imaging camera unit (224), checks the position of the driving system (30), and controls the operation of the sensor moving drive unit (240) to accurately position the sensor housing unit (210) at the inspection position of the driving system (30).

[0128] With the sensor housing (210) positioned facing the driving system (30), a plurality of diagnostic sensor units (220) are positioned facing the driving system (30).

[0129] That is, the magnetic field detection unit (221), the vibration detection unit for the driving unit (222), the sound wave detection unit (223), and the thermal imaging camera unit (224) are positioned facing the driving system (30) to detect the magnetic field, vibration, and sound waves generated by the driving system (30), respectively, and transmit them to the control unit. The control unit transmits the signals and images detected by the magnetic field detection unit (221), the vibration detection unit for the driving unit (222), the sound wave detection unit (223), and the thermal imaging camera unit (224) to a flight management system (not shown) via a wireless communication unit.

[0130] The flight management system (not shown) includes an abnormality determination unit (not shown) that checks whether the drive system (30) is operating normally and the degree of aging using information detected from a magnetic field detection unit (221), a vibration detection unit (222) for the drive unit, a sound wave detection unit (223), and a thermal imaging camera unit (224).

[0131] An abnormality determination unit (not shown) can identify an abnormal state by deriving frequency components related to rotation through FFT analysis of the received signal processing and deriving a waveform pattern.

[0132] For example, an abnormality determination unit (not shown) determines that the condition of the drive motor (31) or propeller (32) is normal when the pattern of the signal received from the radar sensor unit shows a repeating pattern of a relatively smooth waveform.

[0133] And, the abnormality determination unit (not shown) determines that if the vibration value received from the radar sensor unit exceeds a preset vibration value, an abnormality has occurred in the operation of the drive motor (31) or propeller (32).

[0134] When the blades of the propeller (32) are broken and rotate unevenly and exceed the preset vibration value, noise is interspersed in the pattern of the received signal, and large and small irregular patterns occur.

[0135] An abnormality determination unit (not shown) determines that an abnormality has occurred in the operation of the drive motor (31) or propeller (32) if there is noise interspersed in the pattern of the signal received from the radar sensor unit and large and small irregular patterns occur.

[0136] In the abnormality determination unit (not shown), the normal vibration range and the aging vibration range of the drive motor (31) and the propeller (32) are pre-set, and for the signal pattern received through the radar sensor unit, multiple forms of normal signal patterns, aging signal patterns, and fault signal patterns are pre-stored, and in the case of the aging signal pattern, they are pre-stored by classifying them according to the aging state.

[0137] An abnormality determination unit (not shown) determines normal operation if the vibration value received through the radar sensor unit is within the normal vibration range, and determines that it is malfunctioning if the vibration value received through the radar sensor unit deviates from the normal vibration range.

[0138] Additionally, an abnormality determination unit (not shown) determines the aging state by comparing it with a pre-established aging signal pattern for each aging state when it is located within the aging vibration range, and if the aging signal pattern is not a normal signal pattern, it determines that a failure has occurred in the drive system (30) including the drive motor (31) or propeller (32).

[0139] In addition, the abnormality determination unit (not shown) can determine whether the driving system (30) is aging or malfunctioning through the signal pattern of the magnetic field detected and received from the magnetic field detection unit (221).

[0140] When the drive motor (31) operates normally, it ideally generates rotational force, that is, because rotational force is generated regularly, the magnetic field signal pattern of the drive motor (31) detected by the magnetic field detection unit (221) is symmetrical and continues regularly.

[0141] On the other hand, if the winding of the drive motor (31) is broken or the shaft is tilted, the magnetic field signal pattern detected by the magnetic field detection unit (221) is not symmetrical, is irregular, and patterns such as large and small noise occur in the middle.

[0142] Accordingly, the abnormality determination unit (not shown) determines that the driving system (30) is operating normally if the magnetic field signal pattern of the driving motor (31) detected by the magnetic field detection unit (221) is symmetrical and follows regularly.

[0143] And, the abnormality determination unit (not shown) determines that the drive motor (31) is old or has malfunctioned if the magnetic field signal pattern detected by the magnetic field detection unit (221) is not symmetrical, is irregular, and has patterns such as large and small noise in the middle.

[0144] That is, the abnormality determination unit (not shown) has a first motor magnetic field signal pattern range stored in advance for checking the normal state of the drive motor (31), a second motor magnetic field signal pattern range stored in advance for checking the aging state of the drive motor (31) according to the aging state, and a third motor magnetic field signal pattern range stored in advance for checking the failure of the drive motor (31).

[0145] An abnormality determination unit (not shown) can determine whether the driving motor (31) is aging and whether it is malfunctioning by comparing the magnetic field signal pattern of the driving motor (31) detected by the magnetic field detection unit (221) with the previously stored first motor magnetic field signal pattern range, second motor magnetic field signal pattern range, and third motor magnetic field signal pattern range.

[0146] And, when the motor control signal of the electronic speed controller (ESC) detected by the magnetic field detection unit (221) is normal, the width and size of the PWM (pulse width modulation) waveform for motor control are within a preset range, and when a fault occurs, the PWM (pulse width modulation) waveform for motor control goes out of the preset range.

[0147] An abnormality determination unit (not shown) can determine that the electronic speed controller (ESC) is operating normally if the pulse width modulation (PWM) of the motor control signal detected by the magnetic field detection unit (221) has a waveform width and size within a preset range, and determine that the electronic speed controller (ESC) is malfunctioning if the pulse width modulation (PWM) of the motor control signal has a waveform width and size outside a preset range.

[0148] That is, the abnormality determination unit (not shown) has a first controller magnetic field signal pattern range stored in advance for verifying the normal state of the electronic speed controller (ESC), a second controller magnetic field signal pattern range stored in advance for verifying the aging state of the electronic speed controller (ESC) according to the aging state, and a third controller magnetic field signal pattern range stored in advance for verifying the failure of the electronic speed controller (ESC).

[0149] An abnormality determination unit (not shown) can determine the aging status and failure status of the electronic speed controller (ESC) by comparing the magnetic field signal pattern of the electronic speed controller (ESC) detected by the magnetic field detection unit (221) with the previously stored first controller magnetic field signal pattern range, second controller magnetic field signal pattern range, and third controller magnetic field signal pattern range.

[0150] In addition, the abnormality determination unit (not shown) can determine the degree of aging and abnormality of the part using the sound wave signal detected by the sound wave detection unit (223).

[0151] The sound wave detection unit (223) detects the sound, i.e., noise, generated by the aerodynamic phenomenon caused by the rotation of the propeller (32) and the bearing wear of the drive motor (31), and transmits this to the abnormality determination unit (not shown).

[0152] When the propeller (32) rotates normally, tonal noise is generated in a balanced manner due to the aerodynamic force of the propeller (32) rotation. On the other hand, when the propeller (32) is unbalanced or vibration, i.e., shaking, occurs in the propeller (32) due to aging of the bearing, noise is generated in the aerodynamic phenomenon and is buried in the received sound waves.

[0153] And, when the bearing of the drive motor (31) is worn out, a high-frequency sound is generated, and the sound wave detection unit (223) detects this high-frequency sound and transmits it along with the sound wave to the abnormality determination unit (not shown), so that the abnormality determination unit (not shown) determines whether there is an abnormality or the degree of aging of the drive motor (31) or propeller (32) through the waveform pattern of the sound wave and the high frequency received.

[0154] That is, the abnormality determination unit (not shown) has a first sound wave pattern range stored in advance for checking the normal state of the driving system (30), a second sound wave pattern range stored in advance for checking the aging state of the driving system (30) according to the aging state, and a third sound wave pattern range stored in advance for checking the failure of the driving system (30).

[0155] An abnormality determination unit (not shown) can determine the aging status and failure status of the electronic speed controller (ESC) by comparing the sound wave signal pattern detected by the sound wave detection unit (223) with the previously stored first sound wave pattern range, second controller magnetic field signal pattern range, and third controller magnetic field signal pattern range.

[0156] An abnormality determination unit (not shown) stores reference values ​​and signal patterns for vibration, magnetic field, and sound wave classified by the normal operating state and degree of aging of the corresponding drive motor (31), propeller (32), and electronic speed controller (ESC) obtained through multiple experiments.

[0157] An abnormality determination unit (not shown) can check in real time whether the driving system (30) is malfunctioning and aging by comparing the measured value or signal pattern measured or detected in real time by the vibration detection unit (222) for the driving unit, the magnetic field detection unit (221), and the sound wave detection unit (223) with the previously stored reference value and signal pattern.

[0158] The thermal imaging camera unit (224) can check the heat distribution state generated inside the aircraft (10) after it has completed flight and landed, or check the heat distribution state generated from the drive motor (31) during the operation of the drive motor (31).

[0159] The abnormality determination unit stores an internal heat distribution image in a normal state according to the model of the aircraft (10), and compares a heat distribution image captured by the thermal imaging camera unit (224) with the stored internal heat distribution image to check for a malfunction or aging condition of the interior of the aircraft (10) or the drive motor (31).

[0160]

[0161] Meanwhile, the operation inspection unit (200) comprises: a first sensor housing unit (211) positioned on one side of the driving system (30) to be inspected, with a sensing surface equipped with a plurality of diagnostic sensor units (220) facing the driving system (30); a second sensor housing unit (212) positioned on the other side of the driving system (30), with a sensing surface equipped with a plurality of diagnostic sensor units (220) facing the driving system (30); a first housing connection unit (231) positioned to be movable through the first mounting jig unit (110), with the first sensor housing unit (211) mounted on the end side; a first sensor movement drive unit (241) that moves the first housing connection unit (231) forward and backward, that is, in the length direction of the arm unit (20); and a second sensor housing unit (212) positioned to be movable through the second mounting jig unit (120), with the second sensor housing unit (212) mounted on the end side. It includes a second housing connection part (232) and a second sensor movement drive part (242) that moves the second housing connection part (232) in a straight line forward and backward, that is, in the length direction of the arm part (20).

[0162] The first sensor housing (211) and the second sensor housing (212) are positioned facing the driving system (30) on both sides of the driving system (30), respectively, and each of the multiple diagnostic sensor units (220) detects physical quantities generated in the driving system (30).

[0163] The first sensor housing part (211) and the second sensor housing part (212) are each equipped with a position detection part that detects the position of the driving system (30), and the control unit controls the operation of the first sensor moving driving part (241) and the second sensor moving driving part (242) using a signal detected by the position detection part, thereby positioning the first sensor housing part (211) and the second sensor housing part (212) so as to face the driving system (30) on both sides of the driving system (30).

[0164] It should be noted that an embodiment of the position detection unit can be implemented in the same manner as mentioned above, so a further detailed description is omitted.

[0165] Additionally, the operation inspection unit (200) further includes a third sensor housing unit (213) which is positioned such that one end is mounted on the lower end of the first sensor housing unit (211) and is bent toward the second sensor housing unit (212), with the upper sensing surface equipped with a plurality of diagnostic sensor units (220) facing the lower end of the driving system (30).

[0166] Additionally, the operation inspection unit (200) further includes a lifting / lowering drive unit (250) located in the first sensor housing unit (211) to move the third sensor housing unit (213) up and down.

[0167] It should be noted that the lifting / lowering drive unit (250) is exemplified as a ball screw type linear actuator, and can be implemented in various modified forms using known lifting / lowering devices such as a rack gear and a pinion gear that meshes with the rack gear and is rotated by a motor, a rack and pinion structure that converts the motor's rotational force into linear movement, and a hydraulic cylinder, so further detailed description is omitted.

[0168] The lifting / lowering drive unit (250) can adjust the height of the third sensor housing unit (213) to position the third sensor housing unit (213) on the lower side of the drive system (30) regardless of the model, and can measure physical quantities generated by the drive system (30) under various conditions using a plurality of diagnostic sensor units (220) while adjusting the distance from the drive system (30) during inspection.

[0169] Additionally, the operation inspection unit (200) further includes a fourth sensor housing unit (214) which is mounted on one end of the second sensor housing unit (212) and positioned so as to be bent toward the first sensor housing unit (211), with a sensing surface equipped with a plurality of diagnostic sensor units (220) facing the driving system (30).

[0170] The fourth sensor housing part (214) is positioned to cover the space between the first sensor housing part (211) and the second sensor housing part (212), so that a sensing surface equipped with a plurality of diagnostic sensor parts (220) is positioned to face the driving system (30).

[0171] Additionally, the operation inspection unit (200) further includes a housing rotation drive unit (260) provided at one end of the second sensor housing unit (212) to rotate the fourth sensor housing unit (214) to open and close the space between the first sensor housing unit (211) and the second sensor housing unit (212).

[0172] The housing rotation drive unit (260) rotates the fourth sensor housing unit (214) around a vertical axis to position it in a straight line with the second sensor housing unit (212), thereby opening the space between the first sensor housing unit (211) and the second sensor housing unit (212), so that when the inspection mounting unit (100) is mounted on the arm (20) of the aircraft (10), the fourth sensor housing unit (214) can be mounted stably and smoothly without getting caught on the arm (20).

[0173] And, the fourth sensor housing part (214) can be rotated by the housing rotation drive part (260) while the second sensor housing part (212) is positioned in an inspection position facing the drive system (30) on the other side of the drive system (30) by the operation of the second sensor movement drive part (242), thereby closing the gap between the first sensor housing part (211) and the second sensor housing part (212) so that the sensing surface is positioned in an inspection position facing the drive system (30).

[0174] The first sensor housing (211), the second sensor housing (212), the third sensor housing (213), and the fourth sensor housing (214) are each equipped with a plurality of diagnostic sensor units (220), namely a vibration detection unit (222) for a driving unit, a magnetic field detection unit (221), a sound wave detection unit (223), and a thermal imaging camera unit (224), on their respective sensing surfaces.

[0175] Accordingly, the first sensor housing part (211), the second sensor housing part (212), the third sensor housing part (213), and the fourth sensor housing part (214) can each individually check whether the driving system (30) is operating normally through the vibration detection part (222), the magnetic field detection part (221), the sound wave detection part (223), and the thermal imaging camera part (224).

[0176] One embodiment of the driving system inspection device mounted on an aircraft according to the present invention can more accurately diagnose whether the driving system (30) is operating normally by individually measuring physical quantities generated from the driving system (30) in four directions relative to the driving system (30) through a first sensor housing part (211) and a second sensor housing part (212) located on both sides of the driving system (30), a third sensor housing part (213) located at the bottom of the driving system (30), and a fourth sensor housing part (214) facing the driving system (30) between the first sensor housing part (211) and the second sensor housing part (212).

[0177]

[0178] The present invention is mounted on an aircraft (10), such as a drone, to accurately diagnose whether the driving system (30) of the aircraft (10) is operating normally during operation, thereby preventing accidents caused by failure of the driving system (30) during actual flight of the aircraft (10) and significantly improving the flight stability of the aircraft (10).

[0179] The present invention is selectively mounted on an aircraft such as a drone, and can periodically and simply check whether the driving system (30) of the aircraft (10) is operating normally, thereby having the effect of simultaneously ensuring accuracy and convenience when inspecting the driving system.

[0180]

[0181] Although the present invention has been described in detail using preferred embodiments, the scope of the invention is not limited to specific embodiments and should be interpreted by the appended claims. Furthermore, those skilled in the art will understand that many modifications and variations are possible without departing from the scope of the invention.

Claims

1. An inspection mounting part detachably mounted to an aircraft equipped with a drive system including a drive motor and a propeller; and A drive system inspection device mounted on an aircraft, characterized by including an operation inspection unit provided in the above-mentioned inspection mounting part and checking whether the drive system is operating normally.

2. In Claim 1, A drive system inspection device for an aircraft, characterized in that the above-mentioned inspection mounting part is detachably mounted to a plurality of arms on which the drive system is mounted in the aircraft.

3. In Claim 2, The above inspection mounting part is, An inspection device for a mounted drive system of an aircraft, characterized by being mounted on the arm in a manner that pressurizes and holds the arm between the first mounting jig and the second mounting jig, comprising a first mounting jig that surrounds a portion of the arm on one side of the arm and a second mounting jig that surrounds another portion of the arm on the other side of the arm.

4. In Claim 3, The above-mentioned first mounting jig portion is provided with a first arm insertion portion into which a part of the arm portion is inserted, and The above second mounting jig part is provided with a second arm insertion part into which another part of the arm part is inserted, and The inner surface of the first arm insertion part is provided with a first grip elastic pad part, and An inspection device for a drive system mounted on an aircraft, characterized in that the inner surface of the second arm insertion part is provided with a second grip elastic pad part.

5. In Claim 4 The above inspection mounting part is, An inspection device for a mounted drive system of an aircraft, characterized by further including a jig drive unit capable of moving at least one of the first mounting jig unit and the second mounting jig unit to press and hold or release the arm unit between the first mounting jig unit and the second mounting jig unit.

6. In Claim 5, The driving unit for the above jig is, An inspection device for a mounted drive system of an aircraft, characterized by including a moving screw that is screw-coupled to each other through the first mounting jig part and the second mounting jig part, and screw-coupled in opposite directions, and a screw rotation motor that rotates the moving screw, so that the first mounting jig part and the second mounting jig part are simultaneously moved inwardly facing each other or simultaneously moved outwardly oppositely by the rotation of the moving screw.

7. In Claim 3, The above operation inspection unit is, A sensor housing portion connected to the first mounting jig portion or the second mounting jig portion; and An aircraft-mounted drive system inspection device characterized by including a diagnostic sensor unit that is provided in the sensor housing and detects a physical quantity capable of verifying whether the drive system is operating normally.

8. In Claim 7, The above operation inspection unit is, A housing connection part in which one end is mounted on the sensor housing part and the other end is connected to the inspection mounting part; and An inspection device for a drive system mounted on an aircraft, characterized by further including a sensor movement drive unit that moves the housing connection part forward and backward in the longitudinal direction of the arm part to position the sensor housing part facing the drive system.

9. In Claim 7, The above operation inspection unit is, A first sensor housing unit positioned on one side of the driving system to be inspected, with a sensing surface equipped with a plurality of diagnostic sensor units positioned to face the driving system; A second sensor housing unit positioned on the other side of the above-mentioned driving system, wherein a sensing surface equipped with a plurality of the above-mentioned diagnostic sensor units is positioned to face the above-mentioned driving system; A first housing connection part positioned to be movable through the first mounting jig part and the first sensor housing part mounted on the end side; A first sensor movement drive unit that moves the first housing connection part in a straight line forward and backward; A second housing connection part positioned to be movable through the second mounting jig part and having the second sensor housing part mounted on the end side; and An inspection device for a drive system mounted on an aircraft, characterized by including a second sensor movement drive unit that moves the second housing connection part in a straight line forward and backward.

10. In Claim 9, The above operation inspection unit is, An aircraft-mounted drive system inspection device characterized by further including a third sensor housing, wherein one end is mounted on the lower end of the first sensor housing and positioned so as to be bent toward the second sensor housing, and the upper sensing surface equipped with a plurality of diagnostic sensor parts is positioned to face the lower end of the drive system.

11. In Claim 10, The above operation inspection unit is, An inspection device for a drive system mounted on an aircraft, characterized by further including a lifting / lowering drive unit located in the first sensor housing and moving the third sensor housing up and down.

12. In Claim 10, The above operation inspection unit is, An aircraft-mounted drive system inspection device characterized by further including a fourth sensor housing part mounted on one end of the second sensor housing part, positioned so as to be bent toward the first sensor housing part, and having a sensing surface equipped with a plurality of diagnostic sensor parts positioned to face the drive system.

13. In Claim 12, The above operation inspection unit is, An inspection device for a drive system mounted on an aircraft, characterized by further including a housing rotation drive unit provided at one end of the second sensor housing part to rotate the fourth sensor housing part to open and close the space between the first sensor housing part and the second sensor housing part.

14. In claim 8 or claim 9, The above diagnostic sensor unit is, An inspection device for a drive system mounted on an aircraft, characterized by including a magnetic field sensing unit for detecting a change in the magnetic field of the drive system, a vibration sensing unit for a drive unit for detecting vibrations of the drive system, and a sound wave sensing unit for measuring sound waves generated by the drive system.

15. In Claim 14, The above operation inspection unit is, It further includes a position detection unit for verifying the location of the above-mentioned drive system subject to inspection, and An inspection device for a drive system mounted on an aircraft, characterized in that the above-mentioned position detection unit is a thermal imaging camera unit.

Images