Avionics system detection platform and method

Abstract

The invention relates to an avionics system detection platform and method, the avionics system detection platform comprises a main control unit, a test unit and a test cable, the main control unit is in communication connection with the test unit, the test cable comprises a complete machine test cable and a part test cable, the complete machine test cable and the part test cable are connected with the test unit, and the test unit is connected with the test unit. The main control unit can be directly connected with the unmanned aerial vehicle through the complete machine test cable, the main control unit has test connection authority of various types of unmanned aerial vehicles, and the test unit can be connected with an independent avionics component of the unmanned aerial vehicle through the component test cable. The problem that multiple unmanned aerial vehicle detection devices are incompatible is solved, the unmanned aerial vehicle detection device has the advantages of being portable, reinforced, light, high in applicability and high in supportability, and the detection requirements of unmanned aerial vehicle equipment avionics systems of different manufacturers can be met.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle detection, and in particular to an avionics system detection platform and method. Background Art

[0002] The avionics system of a UAV generally adopts an integrated design, combining the flight control system, sensors, mission equipment, etc., with functions such as flight control and navigation, mission execution and load management, and system coordination. It can support UAVs to perform tasks such as target identification, image transmission, reconnaissance and surveillance, and ensure that UAVs can complete tasks safely and efficiently in complex environments. Therefore, the avionics system plays a vital role for UAVs.

[0003] In order to ensure the safe flight and efficient operation of drones, avionics system testing equipment is needed to perform regular maintenance on drone avionics systems. Due to the large number of drone manufacturers, there are differences in drone models and types, and the avionics systems of drones from different manufacturers and types are also different. Therefore, existing avionics system testing equipment generally only tests the avionics system of a certain type of drone from a single manufacturer, with poor compatibility and lack of interoperability. There is an urgent need for new equipment that can simultaneously meet the avionics system testing needs of drones from different manufacturers. Summary of the invention

[0004] The present invention proposes an avionics system detection platform and method, which conveniently solves the problem of incompatibility of various UAV detection equipment. The present application has the advantages of portability, reinforcement, lightness, strong applicability and strong security, and can meet the detection needs of avionics systems of UAV equipment of different manufacturers.

[0005] The technical solution of the present invention is as follows: An avionics system detection platform includes a main control unit, a test unit and a test cable. The main control unit is communicatively connected with the test unit. The test cable includes a whole machine test cable and a component test cable. The whole machine test cable and the component test cable are connected to the test unit. The test unit can be directly connected to an unmanned aerial vehicle through the whole machine test cable. The main control unit has test connection permissions for multiple models of unmanned aerial vehicles. The test unit can be connected to individual avionics components of the unmanned aerial vehicle through the component test cable.

[0006] As a further optimization of this solution, the individual avionics components of the drone connected to the component test cable include a flight control computer, a servo, a barometric altitude / airspeed sensor, a vertical gyroscope, a power supply and engine manager, an airborne satellite navigation receiver, a magnetic heading sensor and a MIMU combined navigation device.

[0007] As a further optimization of this solution, the test unit includes a ±13V power supply monitoring module, which can power the UAV avionics components.

[0008] As a further optimization of this solution, the serial ports of the system include RS485, RS422 and RS232.

[0009] An avionics system detection method includes a whole machine test and a component test. The whole machine test includes performing a functional performance check on each component of the UAV avionics system in a whole machine environment: The main control unit is connected to the aircraft's ADT interface or ground measurement port through the whole machine test cable. The software sends various remote control commands to the aircraft through the interface, and then receives the telemetry data message returned by the aircraft. By analyzing the received message information, it is determined whether the functions of various avionics equipment on the aircraft are normal. During the test, the drone is powered by the drone's ground power supply.

[0010] As a further optimization of this solution, the whole machine test includes functional performance inspection of some components of the UAV avionics system in an environment separated from the whole machine: The main control unit is connected to the airborne equipment through the test unit and component test cable. The software sends various remote control commands to the test unit through the interface, and then receives the telemetry data message returned by the test unit. By analyzing the received message information, it is determined whether the function of the component is normal. During the test, the test unit supplies power to the component.

[0011] As a further optimization of this solution, the first part of the test cable is the whole machine test cable, which is used as an RS422 serial communication cable to connect the main control unit with the aircraft ADT interface or the ground measurement port. The second part is the component test cable, which connects the test unit with the avionics equipment. The structure, signal definition, and connector model are generally the same as the airborne cable, which facilitates the connection of avionics equipment. Each connector is labeled with the corresponding avionics equipment name to prevent misplugging.

[0012] As a further optimization of this solution, the test unit has self-test function, night navigation light control and self-test function, AD and DA self-test function, and RS422 self-test function; it can power the UAV avionics components and has various serial ports for communicating with the avionics components and airborne transceiver combination.

[0013] The working principle and beneficial effects of the present invention are: The present invention relates to an avionics system detection platform, which is composed of a main control unit, a test unit and a test cable. The present invention is used for regular maintenance of unmanned aerial vehicle equipment, and can complete the function and performance detection of avionics equipment such as airborne avionics computers, servo equipment, and measuring equipment in the avionics system of the main unmanned aerial vehicle equipment, and locate the fault to a replaceable unit. The present invention is a field portable product, which has the advantages of portability, reinforcement, lightness, strong applicability and strong security, and can meet the detection needs of avionics systems of unmanned aerial vehicle equipment of different manufacturers. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0015] Figure 1 This is a principle block diagram of an avionics system detection platform in this application; Figure 2 This is the principle block diagram of the avionics system detection equipment. DETAILED DESCRIPTION

[0016] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0017] The present invention relates to an avionics system detection device, which is composed of a main control unit, a test unit and a test cable. The present invention is used for regular maintenance of unmanned aerial vehicle equipment, and can complete the function and performance detection of avionics equipment such as airborne avionics computers, servo equipment, and measuring equipment in the avionics system of the main unmanned aerial vehicle equipment, and locate the fault to a replaceable unit. The present invention is a field portable product, which has the advantages of portability, reinforcement, lightness, strong applicability and strong security, and can meet the detection needs of avionics systems of unmanned aerial vehicle equipment of different manufacturers.

[0018] Embodiment 1, an avionics system detection platform, includes a main control unit, a test unit and a test cable, the main control unit is communicatively connected with the test unit, the test cable includes a whole machine test cable and a component test cable, the whole machine test cable and the component test cable are connected to the test unit, the main control unit can be directly connected to a drone via the whole machine test cable, the main control unit has test connection permissions for multiple models of drones, and the test unit can be connected to individual avionics components of the drone via the component test cable.

[0019] Main control unit: (1) Input voltage: AC 220V 50Hz; (2) Input power: ≤180W; (3) Total weight: ≤35kg.

[0020] Test unit output voltage: +13V±0.5V, -13V±0.5V; The test unit has: (1) 37 analog input channels: attitude angle (2 channels), cylinder temperature (4 channels), angular rate (3 channels), onboard power grid voltage (6 channels), ±8 V power supply (2 channels, used for vertical gyro), ±15 V power supply (2 channels), servo control signal (7 channels), servo feedback signal (7 channels), oil level, airspeed, air pressure altitude, platform lifting control signal, etc., a total of 37 channels; (2) 8 analog output channels: control signals of 7 servos including damper, airway, left direction, left aileron, right direction, right aileron, and elevator, plus a platform elevator control signal; (3) 5-way RS-422 serial communication interface: communicate with the aircraft, laser altimeter, directional antenna control box, mission aircraft platform or camera, and aircraft parameter detection table; (4) 1 RS-232 serial communication interface: for communication with positioning signal receiving board, video recorder, magnetic heading sensor, etc.; (5) 19-channel switch input interface: relay / task selection, detection table status signal, platform lifting position, platform lowering position, hatch opening position, hatch closing position, platform / camera selection, priority, fault monitoring, parking test (2 channels), parachute opening test (2 channels), self-destruction test (2 channels), parachute cutting test (2 channels), Q parachute opening test (2 channels) signal; (6) 16-channel switch output interface: The first group of 10 channels is called switch output: 3 channels such as single and double ignition control signal, night navigation light switch control signal, radar control signal (sent to the video recorder, currently a backup signal), and the other 7 channels are standby. The second group of 6 channels is called analog power output (i.e. power switch output), which outputs 4 channels of signals such as parking, parachute opening, self-destruction, and horizontal repair, and the other 2 channels are standby. The parking, parachute opening, parachute cutting, and horizontal repair signals are sent to the recovery board, amplified and processed, and 6 analog power outputs such as parking, parachute opening, parachute cutting, self-destruction (used for cabin door opening and closing control), horizontal repair 1, and horizontal repair 2 are generated.

[0021] (7) RS-485 interface: communicates with the barometric altitude / airspeed sensor, magnetic heading sensor, power supply and engine manager; (8) PWM control signal output interface: control the servo; (9) 28V power output: to power avionics components; ±13V power output, to power servos and night navigation lights The individual avionics components of the drone connected to the component test cable include a flight control computer, a servo, a barometric altitude / airspeed sensor, a vertical gyroscope, a power supply and engine manager, an airborne satellite navigation receiver, a magnetic heading sensor, and a MIMU combined navigation device.

[0022] The test unit includes a ±13V power monitoring module that can power the UAV avionics components.

[0023] The serial ports of this system include RS485, RS422 and RS232.

[0024] Embodiment 2, an avionics system detection method, including whole machine testing and component testing, wherein the whole machine testing includes performing functional performance inspection on each component of the UAV avionics system in a whole machine environment: The main control unit is connected to the aircraft's ADT interface or ground measurement port through the whole machine test cable. The software sends various remote control commands to the aircraft through the interface, and then receives the telemetry data message returned by the aircraft. By analyzing the received message information, it is determined whether the functions of various avionics equipment on the aircraft are normal. During the test, the drone is powered by the drone's ground power supply.

[0025] The whole machine test includes functional performance inspection of some components of the UAV avionics system in an environment separated from the whole machine: The main control unit is connected to the airborne equipment through the test unit and component test cable. The software sends various remote control commands to the test unit through the interface, and then receives the telemetry data message returned by the test unit. By analyzing the received message information, it is determined whether the function of the component is normal. During the test, the test unit supplies power to the component.

[0026] The first part of the test cable is the whole machine test cable, which is used to connect the main control unit with the aircraft ADT interface or the RS422 serial communication cable of the ground measurement port. The second part is the component test cable, which connects the test unit with the avionics equipment. The structure, signal definition, and connector model are generally the same as the airborne cable, which facilitates the connection of avionics equipment. Each connector is marked with the corresponding avionics equipment name to prevent misplugging.

[0027] The test unit has self-test function, night navigation light control and self-test function, AD and DA self-test function, and RS422 self-test function; it can power the UAV avionics components and has various serial ports for communicating with the avionics components and airborne transceiver combination.

[0028] In various embodiments, the hardware implementation of the technology can directly adopt existing intelligent devices, including but not limited to industrial computers, PCs, smart phones, handheld stand-alone computers, floor-standing stand-alone computers, etc. Its input device preferably adopts a screen keyboard, its data storage and calculation module adopts existing memory, calculator, controller, its internal communication module adopts existing communication ports and protocols, and its remote communication adopts existing GPRS network, World Wide Internet, etc.

[0029] The technicians in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In practical applications, the above-mentioned function allocation can be completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated in a processing unit, or each unit can exist physically separately, or two or more units can be integrated in one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of this application. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, which will not be repeated here.

[0030] In the embodiments provided by the present invention, it should be understood that the disclosed devices / terminal equipment and methods can be implemented in other ways. For example, the device / terminal equipment embodiments described above are only schematic, for example, the division of modules or units is only a logical function division, and there may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms. The units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the scheme of this embodiment.

[0031] Each functional unit in each embodiment of the present invention may be integrated into a processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of a software functional unit. If the integrated module / unit is implemented in the form of a software functional unit and sold or used as an independent product, it may be stored in a computer-readable storage medium. Based on such an understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and may also instruct the relevant hardware to complete it through a computer program. The computer program may be stored in a computer-readable storage medium, and the computer program may be executed by the processor to implement the steps of the above-mentioned method embodiments. Among them, the computer program includes computer program code, and the computer program code may be in the form of source code, object code, executable file or some intermediate form, etc. The computer-readable medium may include: any entity or device capable of carrying computer program code, recording medium, U disk, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium, etc. It should be noted that the content contained in the computer-readable medium can be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media does not include electrical carrier signals and telecommunications signals.

[0032] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An avionics system testing platform, characterized in that: It includes a main control unit, a test unit and a test cable. The main control unit is communicatively connected with the test unit. The test cable includes a whole machine test cable and a component test cable. The whole machine test cable and the component test cable are connected to the test unit. The main control unit can be directly connected to a drone via the whole machine test cable. The main control unit has test connection permissions for multiple models of drones. The test unit can be connected to separate avionics components of the drone via the component test cable.

2. The avionics system detection platform according to claim 1, characterized in that: The individual avionics components of the drone connected to the component test cable include a flight control computer, a servo, a barometric altitude / airspeed sensor, a vertical gyroscope, a power supply and engine manager, an airborne satellite navigation receiver, a magnetic heading sensor, and a MIMU combined navigation device.

3. The avionics system detection platform according to claim 1, characterized in that: The test unit includes a ±13V power monitoring module that can power the UAV avionics components.

4. The avionics system detection platform according to claim 1, characterized in that: The serial ports of this system include RS485, RS422 and RS232.

5. An avionics system detection method, characterized in that: It includes whole machine test and component test. The whole machine test includes functional performance inspection of each component of the UAV avionics system in the whole machine environment: The main control unit is connected to the aircraft's ADT interface or ground measurement port through the whole machine test cable. The software sends various remote control commands to the aircraft through the interface, and then receives the telemetry data message returned by the aircraft. By analyzing the received message information, it is determined whether the functions of various avionics equipment on the aircraft are normal. During the test, the drone is powered by the drone's ground power supply.

6. The avionics system detection method according to claim 5, characterized in that: The whole machine test includes functional performance inspection of some components of the UAV avionics system in an environment away from the whole machine: The main control unit is connected to the airborne equipment through the test unit and component test cable. The software sends various remote control commands to the test unit through the interface, and then receives the telemetry data message returned by the test unit. By analyzing the received message information, it is determined whether the function of the component is normal. During the test, the test unit supplies power to the component.

7. The avionics system detection method according to claim 5, characterized in that: The first part of the test cable is the whole machine test cable, which is used to connect the main control unit with the aircraft ADT interface or the RS422 serial communication cable of the ground measurement port. The second part is the component test cable, which connects the test unit with the avionics equipment. The structure, signal definition, and connector model are generally the same as the airborne cable, which facilitates the connection of avionics equipment. Each connector is marked with the corresponding avionics equipment name to prevent misplugging.

8. The avionics system detection method according to claim 5, characterized in that: The test unit has self-test function, night navigation light control and self-test function, AD and DA self-test function, and RS422 self-test function; it can power the UAV avionics components and has various serial ports for communicating with the avionics components and airborne transceiver combination.

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