Inspection and calibration device for aircraft

Abstract

The present invention relates to an inspection and calibration apparatus for an aircraft, the apparatus comprising: an inspection base unit, above which is positioned an aircraft provided with a driving system, including a driving motor and a propeller, and a navigation sensor; an operation inspection unit that is provided on the inspection base unit and inspects whether the driving system is operating normally; and an axial-direction correction unit for correcting the axial direction of the navigation sensor. The apparatus can not only accurately inspect whether the driving system of the aircraft is operating normally while in operation, but can also automatically calibrate the navigation sensor of the aircraft, and thus can significantly reduce the cost and time required in inspecting the driving system and calibrating the navigation sensor, and efficiently inspect the driving system and calibrate the navigation sensor.

Description

Inspection and calibration device for aircraft

[0001] The present invention relates to an inspection and calibration device for an aircraft, and more specifically, to an inspection and calibration device for an aircraft capable of inspecting the drive system of an aircraft and calibrating a navigation sensor equipped in the aircraft.

[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] In addition, the vertical take-off and landing aircraft operates with a drive system that includes a propeller and an electric motor to rotate the propeller, and is equipped with an electronic compass inside capable of detecting attitude, position, and direction.

[0009] The electronic compass detects the attitude position and direction of an aircraft during flight using the 3-axis Earth's magnetic field as a reference point, but as the Earth's magnetic field changes over time, the reference point shifts.

[0010] Accordingly, the aircraft performs calibration to periodically reset the reference point of the electronic compass, thereby resetting the reference point and enabling accurate detection of attitude, position, and direction by the electronic compass.

[0011] As a device for inspecting the drive system of an aircraft, the applicant has proposed the "Station Device for Take-off and Landing of an Aircraft" under Korean Patent Registration No. 10-2538053.

[0012] 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.

[0013] However, Korean Patent Registration No. 10-2538053, "Station device for takeoff and landing of an aircraft," only allows for the inspection of the aircraft's drive system, which necessitated the inconvenience of having to separately calibrate the aircraft's navigation sensors after the drive system was inspected.

[0014] In addition, since the calibration of the navigation sensor of a conventional aircraft is performed manually by multiple workers lifting the aircraft, there was a problem in that the accuracy was low and a lot of time and cost were required to manage the aircraft (101).

[0015] In particular, as aircraft became larger, there were cases where it became impossible for multiple workers to manually lift the aircraft to calibrate the navigation sensors, leading to a problem where costs increased significantly due to the resulting increase in required personnel.

[0016] The objective of the present invention is to provide an inspection and calibration device for an aircraft that can not only accurately check whether the propulsion system of the aircraft is operating normally during operation, but also automatically calibrate the navigation sensor of the aircraft.

[0017] To achieve the above objectives, one embodiment of an inspection and calibration device for an aircraft according to the present invention is characterized by comprising: an inspection base portion on which an aircraft equipped with a driving system including a driving motor and a propeller and a navigation sensor is positioned on the upper side; an operation inspection portion provided on the inspection base portion for checking whether the driving system is operating normally; and an axial calibration portion for correcting the axial direction of the navigation sensor.

[0018] In the present invention, the navigation sensor includes a geomagnetic sensor, and the axial correction unit may include a first axis correction coil unit and a second axis correction coil unit that apply a magnetic field in at least two axis directions from the three axis directions of the geomagnetic sensor.

[0019] In the present invention, the operation inspection unit is provided in the inspection base unit and includes a diagnostic sensor unit that detects a physical quantity capable of verifying whether the drive system is operating normally. The operation inspection unit and the axial correction unit may further include an inspection control unit that determines whether the drive system is operating normally based on the physical quantity information of the drive system measured by the diagnostic sensor unit, applies voltage to the first axis correction coil unit and the second axis correction coil unit, and corrects the axial error value of the geomagnetic sensor based on the difference between the voltage value measured by the geomagnetic sensor and the applied voltage value.

[0020] In the present invention, the first axis correction coil section includes a first axis correction coil section and a second axis correction coil section located respectively on the lower and upper sides of the aircraft, and the second axis correction coil section may include a third axis correction coil section and a fourth axis correction coil section located respectively on both sides of the aircraft.

[0021] In the present invention, the first coil part for axis correction, the second coil part for axis correction, the third coil part for axis correction, and the fourth coil part for axis correction may each have a ring or frame shape that surrounds the magnetic field forming space.

[0022] In the present invention, the first coil portion for axis correction is mounted on the inspection base portion, and one embodiment of the inspection and calibration device for an aircraft according to the present invention may further include an upper support portion located on the upper side of the inspection base portion and on which the second coil portion for axis correction is mounted, and a first side support portion and a second side support portion located on both sides of the inspection base portion and on which the third coil portion for axis correction and the fourth coil portion for axis correction are respectively mounted.

[0023] One embodiment of the inspection and calibration device for an aircraft according to the present invention may further include an aircraft position support member connected to the aircraft and fixing the position of the aircraft between the first coil part for axis correction and the second coil part for axis correction and between the third coil part for axis correction and the fourth coil part for axis correction.

[0024] In the present invention, the aircraft position support member may include a fixed support member to which the position is fixed and an aircraft coupling member provided on the fixed support member and detachably coupled to the aircraft.

[0025] In the present invention, the aircraft coupling part may include a power supply battery part that is coupled to the battery coupling part of the aircraft and supplies power to the aircraft.

[0026] In the present invention, the aircraft position support may further include a height-adjusting lifting and lowering device capable of adjusting the height of the aircraft by raising and lowering the aircraft coupling part.

[0027] In the present invention, the aircraft position support further includes a rotating part that rotates the aircraft coupling part at a 90-degree angle, and by applying voltage to the third coil part for axis correction and the fourth coil part for axis correction, correction of the X-axis and Y-axis of the geomagnetic sensor can be performed respectively.

[0028] The present invention not only allows for accurate checking of normal operation during the operation of an aircraft's drive system but also enables automatic calibration of the aircraft's navigation sensors, thereby significantly reducing the cost and time required for drive system inspection and navigation sensor calibration, and has the effect of efficiently carrying out drive system inspection and navigation sensor calibration.

[0029] FIG. 1 is a perspective view illustrating one embodiment of an inspection and calibration device for an aircraft according to the present invention.

[0030] FIG. 2 is a perspective view illustrating an axial correction section in one embodiment of an inspection and calibration device for an aircraft according to the present invention.

[0031] FIG. 3 is a side cross-sectional view illustrating one embodiment of an inspection and calibration device for an aircraft according to the present invention.

[0032] FIG. 4 is a side cross-sectional view illustrating another embodiment of an inspection and calibration device for an aircraft according to the present invention.

[0033] FIGS. 5 and 6 are plan views illustrating other embodiments of an inspection and calibration device for an aircraft according to the present invention.

[0034] * Explanation of the symbols *

[0035] 10: Aircraft 20: Drive System

[0036] 100: Inspection base part 200: Operation inspection part

[0037] 210: Sensor housing part 220: Diagnostic sensor part

[0038] 221: Magnetic field sensor 222: Vibration sensor for drive unit

[0039] 223: Sound wave detection unit 230: Camera unit for external imaging

[0040] 240: Thermal imaging camera unit 250: Camera mounting member

[0041] 300: Axial correction unit 310: First axis correction coil unit

[0042] 311: First coil section for shaft correction 312: Second coil section for shaft correction

[0043] 320: Second axis correction coil section 321: Third axis correction coil section

[0044] 322: 4th coil section for axis correction

[0045] 400 : Inspection control unit

[0046] 500: Inspection housing part 510: Upper support part

[0047] 520: First side support 530: Second side support

[0048] 540 : Rear support part 550 : Housing opening / closing part

[0049] 600: Aircraft position support 610: Fixing support

[0050] 620: Aircraft coupling part 621: Power supply battery part

[0051] 630: Height-adjustable lifting / lowering device 640: Rotating part

[0052] 650: 1st flying vehicle mobile device 660: 2nd flying vehicle mobile device

[0053] 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 ensure that the concept of the present invention is sufficiently conveyed to those skilled in the art.

[0054] 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.

[0055] Additionally, 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. Furthermore, in this specification, "and / or" is used to mean including at least one of the components listed before and after it.

[0056] 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.

[0057] In addition, 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.

[0058] FIG. 1 is a perspective view illustrating an embodiment of an inspection and calibration device for an aircraft according to the present invention, FIG. 2 is a perspective view illustrating an axial calibration part (300) in an embodiment of an inspection and calibration device for an aircraft according to the present invention, and FIG. 3 is a side cross-sectional view illustrating an embodiment of an inspection and calibration device for an aircraft according to the present invention.

[0059] An embodiment of an inspection and calibration device for an aircraft according to the present invention is described in detail below with reference to FIGS. 1 to 3.

[0060] One embodiment of the inspection and calibration device for an aircraft according to the present invention is an example of an inspection and calibration device for an aircraft (10), such as a drone, that flies with a driving system (20) including a driving motor and a propeller rotated by the driving motor, and is equipped with a navigation sensor including a geomagnetic sensor, that checks whether the driving system (20) is operating normally through the physical quantity of the driving system (20) and corrects the axial direction of the geomagnetic sensor part.

[0061] One embodiment of the inspection and calibration device for an aircraft according to the present invention is an example of an inspection and calibration device for an aircraft that checks whether the drive motor and propeller, etc., of the drive system (20) of the aircraft (10) are operating normally during operation, confirms the degree of failure and aging of the drive system (20), and calibrates the axial direction of the geomagnetic sensor to a preset standard.

[0062]

[0063] One embodiment of an inspection and calibration device for an aircraft according to the present invention includes an inspection base part (100) on which an aircraft (10) equipped with a driving system (20) including a driving motor and a propeller and a navigation sensor is positioned on the upper side.

[0064] The inspection base part (100) may be provided integrally with the ground, or may be manufactured as a separate panel mounted on the ground.

[0065] Additionally, the inspection base part (100) may be the lower surface of the inspection housing part (500) in which the aircraft (10) to be inspected and calibrated is located inside.

[0066]

[0067] The inspection base unit (100) is equipped with an operation inspection unit (200) for checking whether the drive system (20) is operating normally, and the operation inspection unit (200) includes a diagnostic sensor unit (220) that detects a physical quantity capable of confirming whether the drive system (20) of the aircraft (10) is operating normally.

[0068] The diagnostic sensor unit (220) is provided in a plurality on the inspection base unit (100), and is provided in a number at least equal to the number of driving systems (20) to be inspected, so that inspection of each driving system (20) can be performed individually.

[0069] In addition, one embodiment of the inspection and calibration device for an aircraft according to the present invention includes an axial calibration unit (300) for calibrating the axial direction of a navigation sensor, and the axial calibration unit (300) includes a first axis correction coil unit (310) and a second axis correction coil unit (320) for applying a magnetic field in at least two axis directions from three axis directions of a geomagnetic sensor.

[0070] The first axis correction coil section (310) includes a first axis correction coil section (311) and a second axis correction coil section (312) located respectively on the lower and upper sides of the aircraft (10), and the second axis correction coil section (320) includes a third axis correction coil section (321) and a fourth axis correction coil section (322) located respectively on both sides of the aircraft (10).

[0071] Additionally, the operation inspection unit (200) and the axial correction unit (300) further include an inspection control unit (400) that determines whether the drive system (20) is operating normally based on physical quantity information of the drive system (20) measured by the diagnostic sensor unit (220), applies voltage to the first axis correction coil unit (310) and the second axis correction coil unit (320), and corrects the axial error value of the geomagnetic sensor based on the difference between the voltage value measured by the geomagnetic sensor and the applied voltage.

[0072] The inspection control unit (400) includes a normal operation determination unit that receives physical quantity information of the driving system (20) measured by the diagnostic sensor unit (220) via wired or wireless communication with the diagnostic sensor unit (220) and determines whether the driving system (20) is operating normally, a coil operation control unit that applies voltage to the first axis correction coil unit (310) and the second axis correction coil unit (320), and an axial correction control unit that receives a voltage value measured by a geomagnetic sensor, compares it with the voltage value applied by the coil operation control unit to check for an error, and transmits it to the aircraft (10).

[0073] The axial correction control unit applies a first voltage to the first axis correction coil unit (310), that is, the first axis correction coil unit (311) and the second axis correction coil unit (312), and then compares the second voltage measured in the Z-axis direction of the geomagnetic sensor with the first voltage value. When a difference occurs between the first voltage value and the second voltage value, the difference between the first voltage value and the second voltage value is transmitted to the aircraft (10) to correct the error in the Z-axis direction of the geomagnetic sensor.

[0074] Additionally, the axial correction control unit applies a third voltage to the second axis correction coil unit (320), that is, the third axis correction coil unit (321) and the fourth axis correction coil unit (322), and then compares the first voltage value with the fourth voltage measured in the X-axis or Y-axis direction of the geomagnetic sensor, and when a difference occurs between the first voltage value and the second voltage value, transmits the difference between the first voltage value and the second voltage value to the aircraft (10) to correct the error in the Z-axis direction of the geomagnetic sensor.

[0075] The axial correction control unit may correct the Z-axis direction of the geomagnetic sensor by applying voltage to the first coil unit (311) for axis correction and the second coil unit (312) for axis correction, and then correct the X-axis direction or Y-axis direction of the geomagnetic sensor by applying voltage to the third coil unit (321) for axis correction and the fourth coil unit (322) for axis correction, or correct the X-axis direction or Y-axis direction of the geomagnetic sensor by applying voltage to the third coil unit (321) for axis correction and the fourth coil unit (322) for axis correction, and then correct the X-axis direction or Y-axis direction of the geomagnetic sensor by applying voltage to the first coil unit (311) for axis correction and the second coil unit (312) for axis correction.

[0076] That is, the axial correction control unit applies voltage to each of the two coils in which the aircraft (10) is located between at least two axial directions, including the Z-axis, among the three axial directions of the geomagnetic sensor, and performs correction for the two axial directions in the geomagnetic sensor based on the difference between the applied voltage and the voltage measured by the geomagnetic sensor, and performs correction for the axial directions so that the applied voltage and the voltage measured by the geomagnetic sensor match.

[0077] As an example, the first coil part (311) for axis correction, the second coil part (312) for axis correction, the third coil part (321) for axis correction, and the fourth coil part (322) for axis correction are each formed as coil bodies having a ring or frame shape that surrounds the magnetic field forming space.

[0078] In addition, the first coil section (311) for axis correction, the second coil section (312) for axis correction, the third coil section (321) for axis correction, and the fourth coil section (322) for axis correction each have a square frame shape having a square magnetic field forming space inside, and are coil bodies in which an aircraft (10) can be positioned inside the magnetic field forming space.

[0079] As an example, the magnetic field forming space of each coil section is formed to be larger than the size of the aircraft (10).

[0080] The first coil section (311) and the second coil section (312) for axis correction, which are in the shape of a square frame, are laid down so that a horizontal magnetic field forming space is positioned on the lower side and the upper side of the aircraft (10), respectively, spaced apart from the aircraft (10); the third coil section (321) and the fourth coil section (322) for axis correction, which are in the shape of a square frame, are erected so that a portion of them overlap the first coil section (311) and the second coil section (312) for axis correction, and a vertical magnetic field forming space is positioned on both sides of the aircraft (10), respectively, spaced apart from the aircraft (10).

[0081] A first coil section (311) for axis correction is mounted on an inspection base section (100), and an embodiment of an inspection and calibration device for an aircraft according to the present invention includes an upper support section (510) located on the upper side of the inspection base section (100) to which a second coil section (312) for axis correction is mounted, and a first side support section (520) and a second side support section (530) located on both sides of the inspection base section (100) to which a third coil section (321) for axis correction and a fourth coil section (322) for axis correction are respectively mounted.

[0082] In addition, one embodiment of the inspection and calibration device for an aircraft according to the present invention further includes an aircraft position support member (600) connected to the aircraft (10) to fix the position of the aircraft (10) between the first coil part (311) for axis correction and the second coil part (312) for axis correction, and between the third coil part (321) for axis correction and the fourth coil part (322) for axis correction.

[0083] The aircraft position support member (600) fixes the position of the aircraft (10) when the driving system (20) of the aircraft (10) is operated, thereby maintaining a constant distance between the driving system (20) and the diagnostic sensor member (220) during inspection, and enables stable detection of the physical quantity of the driving system (20) through the diagnostic sensor member (220).

[0084] The aircraft (10) is coupled to the aircraft position support member (600) so that a plurality of drive systems (20) are positioned facing a plurality of diagnostic sensor members (220), and the diagnostic sensor members (220) are maintained at a constant distance from the drive system (20) in operation so that the physical quantity of the drive system (20) can be detected stably and accurately.

[0085] The aircraft position support member (600) supports the position of the aircraft (10) during inspection of the drive system (20) and also serves to fix the aircraft in an optimal position during axial calibration of the geomagnetic sensor.

[0086] As an example, the aircraft position support member (600) includes a fixed support member (610) to which the position is fixed and an aircraft coupling member (620) provided on the fixed support member (610) and detachably coupled to the aircraft (10).

[0087] In addition, the fixed support (610) is mounted on the rear support (540) erected on the rear side of the inspection base (100) or on the inspection base (100) to fix its position as an example.

[0088] The aircraft coupling part (620) is exemplified by including a power supply battery part (621) that is coupled to the battery coupling part of the aircraft (10) to supply power to the aircraft (10), and can be implemented in various modified ways such as being attached to the aircraft (10) by magnetic force, being coupled to the aircraft (10) by gripping the aircraft (10) with a separate jig structure, or being a known coupling structure that is detachable.

[0089] As an example, the power supply battery unit (621) is manufactured to the same specifications as the battery of the aircraft (10) being inspected and calibrated, and is detachably coupled to the battery coupling part of the aircraft (10) to supply power to the aircraft (10).

[0090] Also, the power supply battery unit (621) is detachably connected to the fixed support (610) so that it can be replaced with a battery suitable for the model of the aircraft (10).

[0091] The power supply battery unit (621) is coupled to the aircraft (10) with the battery detached, thereby stably supplying power to the aircraft (10) for calibration of the drive system (20) and the navigation sensor, and also stably supporting the aircraft (10) in its correct position during inspection and calibration.

[0092] The aircraft position support member (600) fixes the position of the aircraft (10) so that the aircraft (10) is positioned vertically from the center of each magnetic field forming space between the first coil part (311) and the second coil part (312) for axis correction positioned facing each other, and between the third coil part (321) and the fourth coil part (322) for axis correction.

[0093] A correction space is formed between the first coil section (311) for axis correction and the second coil section (312) for axis correction, and between the third coil section (321) for axis correction and the fourth coil section (322) for axis correction, surrounded by the magnetic field forming space of each coil section, and the aircraft position support section (600) fixes the position of the aircraft (10) so that the geomagnetic sensor of the aircraft (10) is positioned at the center of the correction space or positioned as close as possible to the center of the correction space.

[0094] The first coil section (311) for axis correction and the second coil section (312) for axis correction, which have a ring frame shape or a polygonal frame shape, are positioned symmetrically, and the third coil section (321) for axis correction and the fourth coil section (322) for axis correction, which have a ring frame shape or a polygonal frame shape, are positioned symmetrically facing each other on both sides of the first coil section (311) for axis correction and the second coil section (312) for axis correction.

[0095] Accordingly, a correction space is formed that is wrapped by the magnetic field forming space of each coil part between the first coil part (311) for axis correction and the second coil part (312) for axis correction, and between the third coil part (321) for axis correction and the fourth coil part (322) for axis correction, and the aircraft position support part (600) is fixed so that the aircraft (10) is positioned at the center of the correction space, so that the geomagnetic sensor of the aircraft (10) can accurately measure the voltage value through the magnetic field generated as voltage is applied from each coil part.

[0096] Additionally, the aircraft position support member (600) may further include a height adjustment lifting / lowering device (630) capable of adjusting the height of the aircraft (10) by raising and lowering the aircraft coupling member (620).

[0097] The height-adjusting lifting / lowering device (630) can raise and lower the aircraft coupling part (620) to adjust the distance between the diagnostic sensor part (220) and the driving system (20) to a preset distance according to the physical quantity measured by the diagnostic sensor part (220), and can adjust the height of the aircraft (10) according to the model of the aircraft (10) to adjust the distance between the diagnostic sensor part (220) and the driving system (20) according to the model of the aircraft.

[0098] The height-adjusting lifting / lowering device (630) is exemplified as a ball screw type linear actuator, and it is noted that it can be implemented in various modified forms using known linear movement devices, such as a hydraulic cylinder, a rack gear and a pinion gear that is meshed with the rack gear and rotated by a motor, and a rack and pinion structure that converts the rotational force of the motor into linear movement, so further detailed description is omitted.

[0099] One embodiment of the inspection and calibration device for an aircraft according to the present invention further includes an inspection housing part (500) comprising an inspection base part (100) on the lower surface, an upper support part (510) on the upper surface, a rear support part (540) on the rear surface, and a first side support part (520) and a second side support part (530) on both sides.

[0100] The inspection housing part (500) has a structure including an inspection base part (100) on which a plurality of diagnostic sensor parts (220) and a first coil part (311) for axis correction are mounted, an upper surface on which the first coil part (311) for axis correction is mounted, and two sides on which the first coil part (311) for axis correction is mounted. By inserting the aircraft (10) inside through the open front and connecting it to the aircraft position support part (600) to fix its position, inspection of the drive system (20) and calibration of the navigation sensor can be performed.

[0101] As an example, the first coil section (311) for shaft correction, the second coil section (312) for shaft correction, the third coil section (321) for shaft correction, and the fourth coil section (322) for shaft correction are embedded and mounted within the inspection housing section (500) so as not to be exposed to the outside.

[0102] The inspection housing part (500) has a front that is open and further includes a housing opening / closing part (550) that opens and closes the open front.

[0103] The housing opening / closing part (550) can close the open front of the aircraft (10) when inspecting the driving system (20) of the aircraft (10) and calibrating the navigation sensor within the inspection housing part (500).

[0104] One embodiment of the inspection and calibration device for an aircraft according to the present invention is such that an aircraft (10) is placed inside an inspection housing part (500) that can be opened and closed by a housing opening / closing part (550), and the position of the aircraft (10) is fixed by an aircraft position fixing part, and the inspection of the driving system (20) and the calibration of the navigation sensor are performed inside the inspection housing part (500), thereby enabling stable inspection of the driving system (20) and calibration of the navigation sensor within the inspection housing part (500) without being affected by external environments such as wind.

[0105]

[0106] Meanwhile, the diagnostic sensor unit (220) is exemplified as a sensor capable of measuring physical quantities generated from the drive motor and propeller, etc., to check whether the drive motor and propeller, etc., of the drive system (20) of the aircraft (10) are operating normally, that is, whether the drive motor and propeller, etc. of the drive system (20) are malfunctioning or the condition of the drive motor and propeller, etc., is aging.

[0107] 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 and propeller are operating normally, thereby more accurately detecting whether the drive system (20) of the aircraft (10) is operating abnormally.

[0108] Additionally, the diagnostic sensor unit (220) transmits physical quantities measured by a plurality of diagnostic sensor units (220) via wired or wireless communication to the inspection control unit (400), i.e., the normal operation determination unit.

[0109] The normal operation determination unit receives the physical quantity of the driving system (20) of the aircraft (10) detected by the diagnostic sensor unit (220), checks whether the driving system (20) is operating normally through data analysis, and can transmit the confirmed diagnostic result to a driving system diagnostic application and an aircraft management system (not shown) via wired or wireless communication.

[0110] In addition, the axial correction control unit can transmit each axial error of the geomagnetic sensor and the corrected results to an application for diagnosing the drive system and an aircraft management system (not shown) via wired or wireless communication.

[0111] An application for diagnosing the drive system can be installed on a portable terminal of the aircraft manager or aircraft pilot to notify the aircraft manager or aircraft pilot of the inspection results of the drive system (20) and the calibration results of the navigation sensor.

[0112] The normal operation determination unit diagnoses the driving system (20) as operating normally if the physical quantity measured by the diagnostic sensor unit (220) falls within a preset range, and diagnoses the driving system (20) as operating abnormally if the physical quantity measured by the diagnostic sensor unit (220) falls outside the preset range.

[0113] The aircraft manager or aircraft pilot can easily check the diagnostic results of the aircraft's (10) drive system (20) 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).

[0114] A portable terminal is exemplified by a smartphone, and may also include other known portable terminals such as tablet PCs.

[0115] 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 (20), a vibration detection unit (222) for the driving unit that detects vibrations of the driving system (20), and a sound wave detection unit (223) that measures sound waves, i.e., noise, generated from the driving system (20), to detect whether there is an abnormal operation of the driving system (20) of the aircraft (10).

[0116] The magnetic field detection unit (221) is for detecting changes in the magnetic field generated by the drive motor and is positioned as close as possible to the drive motor to detect changes in the magnetic field generated by the drive motor.

[0117] The drive system (20) includes a propeller, a drive motor that rotates the propeller, and an electronic speed controller (ESC) that controls the speed of the drive motor, and the drive unit inspection sensor unit (211) includes a magnetic field detection unit (221) that detects a magnetic field generated in the drive system (20).

[0118] The magnetic field detection unit (221) detects the magnetic field generated by the drive system (20), that is, the drive motor and the electronic speed controller (ESC) that controls the speed of the drive motor.

[0119] An electronic speed controller (ESC) is installed to change the speed of a drive motor in an aircraft (10) such as a drone, and further details are omitted.

[0120] When the drive motor operates, permanent and induced magnetic fields are generated in the surroundings, and the ESC, or electronic speed controller, generates motor control signals for controlling the speed of the drive motor.

[0121] The magnetic field detection unit (221) detects the magnetic field generated by the drive motor, 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).

[0122] The magnetic field detection unit (221) detects the permanent magnetic field and induced magnetic field generated when the drive motor operates, as well as the motor control signal of the electronic speed controller.

[0123] 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 (20), that is, the vibration physical quantity of the propeller and the drive motor, using radio waves.

[0124] The radar sensor unit emits radio waves to the propeller of the driving system (20) to measure the physical quantity of the propeller's vibration.

[0125] In the operation inspection section (200), radio waves are emitted from the radar sensor section installed inside, and a radio wave emission opening (not shown) is located that is blocked by a radio wave transmission cover member made of a material through which radio waves can pass.

[0126] The radar sensor unit is located inside the inspection base unit (100) or within a separate sensor housing unit (210) and is protected from external environments such as moisture.

[0127] The open portion for radio wave emission (not shown) is positioned so that the center of the emitted radio waves, that is, the center of the directional radio wave beam, is directed toward the motor, in order to accurately measure vibrations generated from the drive motor and propeller.

[0128] The radar sensor unit directs the center of the radio wave, that is, the center of the directional radio beam, toward the motor, and can simultaneously measure physical quantities caused by the propeller through the width of the radio wave, that is, the beam width.

[0129] That is, the radar sensor unit can individually detect and measure the vibration physical quantity of the drive motor and the vibration physical quantity of the propeller during flight of the aircraft (10) and transmit them to a flight management system (not shown).

[0130] 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 (20), convert the sound waves into an electrical signal, i.e., voice current, and enable the magnitude of the sound waves to be checked.

[0131] The operation inspection unit (200) further includes an exterior camera unit (230) located on the upper side of the aircraft (10) for photographing the exterior of the aircraft (10).

[0132] The exterior camera unit (230) photographs the exterior of the aircraft (10) to check for any damage to the exterior of the aircraft (10).

[0133] The exterior camera unit (230) is provided in multiple units to partially photograph the aircraft (10), and by photographing parts of each other overlapping, it provides an image that can accurately and precisely check for damage to the entire exterior of the aircraft (10).

[0134] Additionally, the operation inspection unit (200) further includes a thermal imaging camera unit (240) located on the upper side of the aircraft (10) to photograph the drive motor of the drive system (20).

[0135] The thermal imaging camera unit (240) measures the heat distribution of the drive motor to check whether the drive motor is operating abnormally.

[0136] As an example, the external camera unit (230) and the thermal camera unit (240) are provided on the lower surface of the upper support unit (510), that is, on the upper surface of the inspection housing unit (500), and positioned spaced apart from the upper side of the aircraft (10).

[0137] As an example, the thermal imaging camera unit (240) is provided in multiple units facing the drive system (20) according to the number of drive systems (20) of the aircraft (10).

[0138] A plurality of thermal imaging camera units (240) are positioned facing each drive system (20) of the aircraft (10) and individually photograph each drive system (20) to measure the heat distribution of each drive motor, thereby providing images that can individually and accurately check whether the drive motor is operating abnormally.

[0139] Additionally, the operation inspection unit (200) is equipped with a plurality of external camera units (230) and a plurality of thermal imaging camera units (240), and further includes a camera mounting member (250) that is detachably mounted on an upper support unit (510).

[0140] The camera mounting member (250) is detachably coupled to the lower surface of the upper support member (510) using a known detachable coupling structure such as a plate structure, screw coupling, or a press fit structure, so that it can be replaced depending on the model of the aircraft (10).

[0141] The number of drive systems (20) and the size and shape of the aircraft body may vary depending on the model of the aircraft (10), and accordingly, the positions of the multiple external camera units (230) and multiple thermal camera units (240) are mounted on the camera mounting member (250) so as to be able to photograph the entire outer surface of the aircraft body and the drive systems (20) of the corresponding model according to the model of the aircraft (10).

[0142] Accordingly, a camera mounting member (250) equipped with a plurality of exterior camera units (230) and a plurality of thermal imaging camera units (240) can be replaced and used according to the model of the aircraft (10) to be inspected, so that the driving system (20) and the entire exterior of the aircraft (10) can be photographed. This improves accuracy when inspecting the aircraft (10).

[0143]

[0144] Meanwhile, FIG. 4 is a side cross-sectional view illustrating another embodiment of an inspection and calibration device for an aircraft according to the present invention, and FIG. 5 and FIG. 6 are plan views illustrating other embodiments of an inspection and calibration device for an aircraft according to the present invention.

[0145] Referring to FIGS. 4 to 6, another embodiment of an inspection and calibration device for an aircraft according to the present invention, which can perform calibration on the X-axis and Y-axis of a geomagnetic sensor, is described in detail below, in which the aircraft position support member (600) includes a rotating member (640) that rotates the aircraft (10) at a 90-degree angle.

[0146] The aircraft (10) is coupled to the aircraft position support (600) and positioned within the inspection housing (500) such that the Y-axis direction of the geomagnetic sensor, which is the front and rear direction, aligns with the front and rear direction of the inspection housing (500).

[0147] The aircraft position support member (600) includes a fixed support member (610) to which the position is fixed, an aircraft coupling member (620) provided on the fixed support member (610) and detachably coupled to the aircraft (10), and a rotating member (640) provided on the fixed support member (610) and connected to the aircraft coupling member (620) to rotate the aircraft coupling member (620) around a rotation axis in the Z-axis direction.

[0148] The fixed support (610) may further include a height-adjusting lifting / lowering device (630) that moves the aircraft coupling part (620) up and down, and the height-adjusting lifting / lowering device (630) can raise and lower the aircraft coupling part (620) to adjust the height of the aircraft (10) according to the model of the aircraft (10).

[0149] The rotating part (640) may rotate the aircraft coupling part (620) by electric power including a rotating motor, or it may be rotated manually by a worker using a hinge shaft coupling structure.

[0150] The rotating part (640) can rotate the aircraft coupling part (620) to rotate the axial direction of the aircraft (10) by 90 degrees in a plane.

[0151] Accordingly, the rotating part (640) can selectively rotate the aircraft (10) by 90 degrees on a plane to align the X-axis and Y-axis of the geomagnetic sensor with the axial direction of the second axis correction coil part (320), that is, the axial direction of the third axis correction coil part (321) and the fourth axis correction coil part (322).

[0152] The aircraft (10) is coupled to the aircraft position support member (600) within the inspection housing member (500) and its position is fixed between the first coil member (311) for axis correction and the second coil member (312) for axis correction, and between the third coil member (321) for axis correction and the fourth coil member (322) for axis correction.

[0153] With the aircraft (10) coupled to the aircraft position support member (600) and its position fixed, the axial support member axial correction control unit can correct the three-axis errors of the geomagnetic sensor of the aircraft (10) in sequence.

[0154] The axial correction control unit applies a first voltage to the first coil unit (311) for axis correction and the second coil unit (312) for axis correction, and transmits the error between the second voltage measured by the geomagnetic sensor and the first voltage value to the aircraft (10) to correct the Z-axis of the geomagnetic sensor.

[0155] Additionally, the axial correction control unit applies a third voltage to the third coil unit (321) for axis correction and the fourth coil unit (322) for axis correction, and transmits the error between the fourth voltage and the third voltage value measured by the geomagnetic sensor to the aircraft (10) to correct the X-axis of the geomagnetic sensor.

[0156] After correcting the X-axis of the geomagnetic sensor, the rotation unit (640) rotates the aircraft (10) by 90 degrees to align the Y-axis of the geomagnetic sensor with the X-axis where the third coil unit (321) for axis correction and the fourth coil unit (322) for axis correction are arranged, and the axial correction control unit applies a third voltage to the third coil unit (321) for axis correction and the fourth coil unit (322) for axis correction and transmits the error between the fourth voltage measured by the geomagnetic sensor and the third voltage value to the aircraft (10) to correct the Y-axis of the geomagnetic sensor.

[0157]

[0158] Additionally, another embodiment of the inspection and calibration device for an aircraft according to the present invention further includes a first aircraft moving device (650) that moves the aircraft position support member (600) back and forth and a second aircraft moving device (660) that moves the aircraft position support member (600) to both sides.

[0159] It should be noted that the first aircraft moving device (650) and the second aircraft moving device (660) are examples of ball screw type linear actuators, and further detailed descriptions are omitted as they can be implemented in various modified forms using known linear moving devices, such as a rack and pinion structure that converts the rotational force of a motor into linear movement by including a rack gear and a pinion gear that is rotated by a motor and meshes with the rack gear, and a driving structure that includes a driving wheel that moves along a rail and rotates by a motor.

[0160] The first aircraft moving device (650) moves the aircraft position support member (600) in the Y-axis direction, and the second aircraft moving device (660) moves the aircraft position support member (600) in the X-axis direction.

[0161] The first aircraft moving device (650) and the second aircraft moving device (660) can move the position of the aircraft, which has been rotated 90 degrees by the rotating part (640), to a preset correction position, that is, the position of the aircraft (10) that was initially fixed by the aircraft position support part (600).

[0162] The first aircraft moving device (650) and the second aircraft moving device (660) can move the aircraft (10), which has been rotated 90 degrees, in the X-axis direction and the Y-axis direction to adjust the position of the aircraft (10) so that the geomagnetic sensor is positioned at the center of the calibration space or as close as possible to the center of the calibration space according to the model of the aircraft (10), thereby increasing the calibration accuracy of the geomagnetic sensor.

[0163]

[0164] The inspection and calibration device for an aircraft according to the present invention operates a driving system (20) while the aircraft (10) is coupled to the aircraft position support member (600), and checks whether the driving system (20) is operating normally by measuring the physical quantity of the driving system (20) using a diagnostic sensor member (220).

[0165] Then, after the inspection of whether the drive system (20) is operating normally is completed, power is selectively applied to the first coil section (311) for axis correction, the second coil section (312) for axis correction, the third coil section (321) for axis correction, and the fourth coil section (322) for axis correction to correct the axial error of the geomagnetic sensor.

[0166] When correcting the axial error of a geomagnetic sensor, calibration is performed for either the Z-axis or the X-axis of the geomagnetic sensor, and then calibration is performed for the other direction.

[0167] Then, after the calibration work for the Z-axis and X-axis of the geomagnetic sensor is completed, the aircraft (10) can be rotated 90 degrees on a plane using the rotating part (640) to align the Y-axis of the geomagnetic sensor with the direction of magnetic field generation of the second axis correction coil part (320), that is, the axis direction of the third axis correction coil part (321) and the fourth axis correction coil part (322), and then the calibration work for the Y-axis of the geomagnetic sensor can be performed.

[0168] It is noted that the inspection and calibration device for an aircraft according to the present invention may operate the driving system (20) after correcting the axial error of the geomagnetic sensor while the aircraft (10) is coupled to the aircraft position support member (600), and may check whether the driving system (20) is operating normally by measuring the physical quantity of the driving system (20) using the diagnostic sensor member (220).

[0169]

[0170] The present invention can not only accurately check whether the driving system (20) of the aircraft (10) is operating normally during operation, but also automatically calibrate the navigation sensor of the aircraft (10), thereby significantly reducing the cost and time required for the inspection of the driving system (20) and the calibration of the navigation sensor, and thus has the effect of efficiently carrying out the inspection of the driving system and the calibration of the navigation sensor.

[0171]

[0172] 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 base section having an aircraft equipped with a drive system including a drive motor and a propeller and a navigation sensor located on the upper side; An operation inspection unit provided in the inspection base unit above and checking whether the drive system operates normally; and An inspection and calibration device for an aircraft characterized by including an axial correction unit for correcting the axial direction of the above-mentioned navigation sensor.

2. In Claim 1, The above navigation sensor includes a geomagnetic sensor, and An inspection and calibration device for an aircraft, characterized in that the above-described axial calibration unit includes a first axis correction coil unit and a second axis correction coil unit that apply a magnetic field in at least two axis directions from the three axis directions of the geomagnetic sensor.

3. In Claim 2, The above operation inspection unit is, It includes a diagnostic sensor unit equipped in the inspection base unit and capable of detecting a physical quantity to verify whether the driving system is operating normally, and The above-mentioned operation inspection unit and the above-mentioned axial correction unit are, An inspection and calibration device for an aircraft, characterized by further including an inspection control unit that determines whether the driving system is operating normally based on physical quantity information of the driving system measured by the diagnostic sensor unit, applies voltage to the first axis correction coil unit and the second axis correction coil unit, and corrects the axial error value of the geomagnetic sensor based on the difference between the voltage value measured by the geomagnetic sensor and the applied voltage value.

4. In Claim 2, The above-mentioned first axis correction coil part is, It includes a first coil part for axis correction and a second coil part for axis correction located respectively on the lower and upper sides of the above-mentioned aircraft, and An inspection and calibration device for an aircraft, characterized in that the second axis correction coil section comprises a third axis correction coil section and a fourth axis correction coil section located on each side of the aircraft.

5. In Claim 4, An inspection and calibration device for an aircraft, characterized in that the first coil part for axis correction, the second coil part for axis correction, the third coil part for axis correction, and the fourth coil part for axis correction each have a ring or frame shape that surrounds a magnetic field forming space.

6. In Claim 4, The first coil part for shaft correction is mounted on the inspection base part, and An upper support member located on the upper side of the inspection base member and on which the second coil member for shaft correction is mounted; An inspection and calibration device for an aircraft, characterized by further including a first side support and a second side support located on both sides of the inspection base and each having a third coil part for axis correction and a fourth coil part for axis correction mounted thereon.

7. In Claim 4, An inspection and calibration device for an aircraft, characterized by further including an aircraft position support member connected to the aircraft and fixing the position of the aircraft between the first coil part for axis correction and the second coil part for axis correction and between the third coil part for axis correction and the fourth coil part for axis correction.

8. In Claim 7, The above-mentioned aircraft position support is, A fixed support for fixing the position; and An inspection and calibration device for an aircraft, characterized by including an aircraft coupling part provided on the above-mentioned fixed support and detachably coupled to the aircraft.

9. In Claim 8, The above-mentioned aircraft coupling part is, An inspection and calibration device for an aircraft, characterized by including a power supply battery unit coupled to a battery coupling part of the aircraft and supplying power to the aircraft.

10. In Claim 8, The above-mentioned aircraft position support is, An inspection and calibration device for an aircraft, characterized by further including a height-adjusting lifting and lowering device capable of adjusting the height of the aircraft by raising and lowering the aircraft coupling part.

11. In Claim 8, The above-mentioned aircraft position support is, An inspection and calibration device for an aircraft, characterized by including a rotating part that rotates the aircraft coupling part at a 90-degree angle, and applying voltage to the third coil part for axis correction and the fourth coil part for axis correction to perform calibration for the X-axis and Y-axis of the geomagnetic sensor, respectively.

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