Portable unmanned aerial vehicle undercarriage testing device

Abstract

The utility model discloses a portable unmanned aerial vehicle undercarriage testing device. The testing device comprises a power supply module, a charging module, a storage battery, a power supply conversion module, a man-machine interaction module, a control module and a driving module. According to the utility model, through the power supply module, the charging module and the storage battery, the undercarriage device can be tested in the presence or absence of an external power supply, and through the driving module, the undercarriage can be retracted and released when an airborne undercarriage control device fails or is lost; the testing device is portable, small and exquisite, can be carried by a single person, does not need external power supply, overcomes the defects that a traditional testing trolley is large in size and heavy in weight, needs an external power supply for power supply, depends on an airborne undercarriage controller for undercarriage folding and unfolding and the like, greatly expands the application range of the testing device, and improves the flexibility of the testing device.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle testing, and more specifically, to a portable unmanned aerial vehicle landing gear testing device. Background Art

[0002] At present, during the testing and maintenance of the landing gear of medium and large UAVs, a ground test vehicle needs to be connected to the aircraft through a panel cover to achieve communication with the aircraft's onboard landing gear control device and complete the control information transmission and feedback data display of the aircraft's onboard landing gear device. However, conventional ground test vehicles generally have the disadvantages of being large in size, heavy in weight, and requiring external AC power supply, which restricts the field use of UAVs. At the same time, conventional ground test vehicles require the help of an onboard landing gear control device to complete the retraction and extension of the landing gear. When the onboard landing gear control device fails or is missing, the retraction and extension of the landing gear device cannot be completed.

[0003] Therefore, there is an urgent need for a simple and portable test device that does not require external power supply and can control the onboard landing gear control device or directly drive the landing gear movement to complete the testing and routine maintenance of the landing gear system of medium and large UAVs.

[0004] The information disclosed in the background technology section of the present invention is only intended to deepen the understanding of the general background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Utility Model Content

[0005] The purpose of the utility model is to propose a portable UAV landing gear test device, which overcomes the shortcomings of the traditional test vehicle, such as large size, heavy weight, need for external power supply and reliance on an airborne landing gear controller for landing gear retraction and extension. It can be carried by one person and does not require external power supply. It can complete the retraction and extension of the landing gear when the airborne landing gear control device fails or is missing, which greatly expands the scope of use of the test device and improves the flexibility of the test device.

[0006] To achieve the above purpose, the utility model proposes a portable UAV landing gear test device, comprising:

[0007] A power supply module, used for converting input AC mains power into a first DC voltage;

[0008] a charging module, electrically connected to the power module, and configured to charge the battery based on the first DC voltage;

[0009] a storage battery, electrically connected to the charging module, and configured to output a second DC voltage;

[0010] a power conversion module, electrically connected to the power module, the battery, the onboard landing gear control device, the drive module, the human-machine interaction module and the control module, respectively, the power conversion module being used to convert the first DC voltage / the second DC voltage into a third DC voltage and a fourth DC voltage, and then provide the third DC voltage to the human-machine interaction module, provide the fourth DC voltage to the control module, and provide the first DC voltage / the second DC voltage to the drive module and the onboard landing gear control device;

[0011] A human-computer interaction module, which is in communication with the control module, and is used to receive instructions from a user and display the working status of the test device;

[0012] a control module, respectively connected to the driving module and the onboard landing gear control device for communication, the control module being used to control the driving module or the onboard landing gear control device to drive the landing gear to move to a corresponding position according to the instruction;

[0013] A driving module, wherein the driving module is used to drive a motor under the control of the control module, and drive the landing gear to move to a corresponding position through the motor.

[0014] Optionally, it also includes:

[0015] A first temperature acquisition module, used to acquire the temperature of the test device;

[0016] A heat dissipation module is electrically connected to the power conversion module, the power conversion module provides the first DC voltage / second DC voltage to the heat dissipation module, and the heat dissipation module is used to cool the test device based on the temperature of the test device.

[0017] Optionally, the human-computer interaction module includes:

[0018] Touch screen and control buttons.

[0019] Optionally, the battery further comprises:

[0020] A second temperature collection module, used to collect the temperature of the battery;

[0021] A heating module is used to increase the temperature of the battery based on the temperatures of the charging module and the battery.

[0022] Optionally, the charging mode of the charging module is constant current-constant voltage charging, and the charging current is 6A.

[0023] Optionally, the power conversion module includes:

[0024] Overcurrent protection module, reverse connection protection module, voltage acquisition module, current acquisition module and power switching module.

[0025] Optionally, the driving module includes:

[0026] Signal isolation module, motor drive module and current acquisition module.

[0027] Optionally, the control module further includes:

[0028] Storage module, used to store test data.

[0029] Optionally, the first DC voltage is 28V.

[0030] Optionally, the second DC voltage is 18-25.2V.

[0031] Optionally, the third DC voltage is 12V, and the fourth DC voltage is 5V.

[0032] The beneficial effects of the utility model are as follows: by arranging a power module, a charging module and a battery, it is possible to test the landing gear device with or without an external power supply, and by means of a driving module, it is possible to complete the retraction and extension of the landing gear when the onboard landing gear control device fails or is missing; the test device of the utility model is portable and compact, can be carried by one person and does not require an external power supply, thus overcoming the shortcomings of the traditional test trolley, such as being large in size, heavy in weight, requiring an external power supply and relying on an onboard landing gear controller for retraction and extension of the landing gear, thereby greatly expanding the scope of use of the test device and improving the flexibility of the test device.

[0033] The device of the present invention has other characteristics and advantages, which will be obvious from the drawings and subsequent specific embodiments incorporated in this document, or will be described in detail in the drawings and subsequent specific embodiments incorporated in this document, which are used together to explain the specific principles of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, in which the same reference numerals generally represent the same components.

[0035] Figure 1 A schematic diagram of a portable UAV landing gear testing device according to the utility model is shown.

[0036] Figure 2 A schematic diagram of a portable UAV landing gear testing device according to an embodiment of the utility model is shown.

[0037] Figure 3 A schematic diagram of a portable UAV landing gear testing device according to an embodiment of the utility model is shown.

[0038] Description of reference numerals:

[0039] 1. Battery, 2. Charging module, 3. AC / DC power module 3, 4. Heat dissipation module, 5. Power conversion module, 6. Drive module, 7. Core control module, 8. Human-computer interaction module. DETAILED DESCRIPTION

[0040] The present invention will be described in more detail below with reference to the accompanying drawings. Although preferred embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0041] like Figure 1 As shown, a portable UAV landing gear test device according to the utility model includes:

[0042] A power supply module, used for converting input AC mains power into a first DC voltage;

[0043] A charging module, electrically connected to the power module, and configured to charge the battery based on a first DC voltage;

[0044] A battery, electrically connected to the charging module, and the battery is used to output a second DC voltage;

[0045] a power conversion module, electrically connected to the power module, the battery, the onboard landing gear control device, the drive module, the human-machine interaction module and the control module, respectively, the power conversion module being used to convert the first DC voltage / the second DC voltage into a third DC voltage and a fourth DC voltage, and then provide the third DC voltage to the human-machine interaction module, provide the fourth DC voltage to the control module, and provide the first DC voltage / the second DC voltage to the drive module and the onboard landing gear control device;

[0046] A human-computer interaction module is connected to the control module for communication, and is used to receive user instructions and display the working status of the test device;

[0047] A control module, which is respectively in communication with the drive module and the onboard landing gear control device, and is used to control the drive module or the onboard landing gear control device to drive the landing gear to move to a corresponding position according to instructions;

[0048] The drive module is used to drive the motor under the control of the control module, and drive the landing gear to move to the corresponding position through the motor.

[0049] Specifically, the portable unmanned aerial vehicle landing gear test device of the utility model includes: a power module, a charging module, a battery, a power conversion module, a human-computer interaction module, a control module and a driving module. The power module is electrically connected to the charging module and the power conversion module. The AC power is converted into DC power, that is, a first DC voltage, through the power module, and then transmitted to the charging module and the power conversion module. The charging module is electrically connected to the battery. The first DC voltage is transmitted to the battery for charging through the charging module. The battery is electrically connected to the power conversion module. In the absence of AC power, a second DC voltage is provided to the power conversion module through the battery. The power conversion module is electrically connected to the driving module, the control module and the human-computer interaction module respectively. The power conversion module is used to convert the first DC voltage or the second DC voltage into a third DC voltage and a fourth DC voltage, and provide the third DC voltage to the human-computer interaction module and the fourth DC voltage to the control module. When the onboard landing gear control device of the unmanned aerial vehicle is damaged or missing, the power conversion module is used to The conversion module provides the first DC voltage or the second DC voltage to the driving module, and the driving module drives the motor to drive the landing gear to the corresponding position; when the unmanned aerial vehicle has an onboard landing gear control device, the onboard landing gear control device is electrically connected to the power conversion module, and the first DC voltage or the second DC voltage is provided to the onboard landing gear control device through the power conversion module, and an instruction is sent to the landing gear control device through the control module, and then the landing gear is driven to the corresponding position through the landing gear control device; the human-computer interaction module is communicatively connected with the control module, receives the user's instructions through the human-computer interaction module, and then sends them to the control module, and displays the working status of the test device through the human-computer interaction module; the test device of the utility model is portable and compact, can be carried by one person and does not require external power supply, overcomes the shortcomings of the traditional test vehicle such as large size, heavy weight, external power supply and reliance on the onboard landing gear controller for landing gear retraction and extension, greatly expands the scope of use of the test device and improves the flexibility of the test device.

[0050] In one example, it also includes:

[0051] A first temperature acquisition module, used to acquire the temperature of the test device;

[0052] The heat dissipation module is electrically connected to the power conversion module. The power conversion module provides the first DC voltage / the second DC voltage to the heat dissipation module. The heat dissipation module is used to cool the test device based on the temperature of the test device.

[0053] Specifically, the test device of the utility model further includes a first temperature acquisition module and a heat dissipation module, the heat dissipation module is electrically connected to the power conversion module, and the first DC voltage / second DC voltage is provided to the heat dissipation module through the power conversion module, the first temperature acquisition module is electrically connected to the control module, and the internal temperature of the test device is acquired through the first temperature acquisition module, and the acquired internal temperature of the test device is sent to the control module, and the control module controls the start and stop of the heat dissipation module according to the internal temperature of the test device. For example, when the internal temperature of the test device is greater than 35 degrees Celsius, the heat dissipation module is turned on, and when the internal temperature of the test device is lower than 30 degrees Celsius, the heat dissipation module is turned off.

[0054] In one example, the human-computer interaction module includes:

[0055] Touch screen and control buttons.

[0056] Specifically, the human-computer interaction module includes a touch screen and control buttons. The touch screen is used to send retraction and lowering instructions, display the retraction and lowering status of each landing gear, and display system time, voltage and current and other parameters; the control buttons are used to realize manual control of the retraction and lowering of each landing gear.

[0057] In one example, the battery further comprises:

[0058] A second temperature acquisition module is used to acquire the temperature of the battery;

[0059] The heating module is used to increase the temperature of the battery based on the temperature of the charging module and the battery.

[0060] Specifically, the battery further includes a second temperature acquisition module and a heating module. The second temperature acquisition module is used to acquire the temperature of the battery, and the heating module is used to increase the temperature of the battery. The heating module can be powered by the charging module.

[0061] For example, the charging module is equipped with a battery heating detection and control circuit. When the battery temperature is lower than 15°C, the battery heating circuit is turned on. When the battery temperature is higher than 25°C, the battery heating circuit is turned off, thereby ensuring that the low-temperature characteristics of the battery meet the use requirements.

[0062] In one example, the charging mode of the charging module is constant current-constant voltage charging, and the charging current is 6A.

[0063] In one example, the power conversion module includes:

[0064] Overcurrent protection module, reverse connection protection module, voltage acquisition module, current acquisition module and power switching module.

[0065] In one example, the driver module includes:

[0066] Signal isolation module, motor drive module and current acquisition module.

[0067] In one example, the first DC voltage is 28V.

[0068] In one example, the second DC voltage is 18-25.2V.

[0069] In one example, the third DC voltage is 12V, and the fourth DC voltage is 5V.

[0070] Example:

[0071] like Figure 2 and Figure 3 As shown, this embodiment provides a portable UAV landing gear testing device, comprising:

[0072] AC / DC power supply module 3, charging module 2, battery 1, heat dissipation module 4, power conversion module 5, drive module 6, core control module 7 and human-computer interaction module 8.

[0073] The AC / DC power module 3 inputs 220V AC power and outputs 28V DC power. The rated power of the AC / DC power module 3 is 300W, which supplies power to the entire test device.

[0074] The charging module 2 is responsible for charging the battery 1. The input voltage is DC28V, the charging mode is constant current-constant voltage charging, and the constant current charging current is 6A. At the same time, the charging module 2 is equipped with a battery heating detection and control circuit. When the temperature of the battery 1 is lower than 15°C, the battery heating circuit is turned on. When the temperature of the battery 1 is greater than 25°C, the battery heating circuit is turned off, thereby ensuring that the low temperature characteristics of the battery 1 meet the use requirements.

[0075] The battery 1 is a 6S lithium-ion battery, the monomer is a 18650 type battery, the output voltage is 18-25.2V, the capacity is 24Ah, and at the same time, the battery 1 is equipped with a set of Pt1000 temperature sensors and a set of heating belt devices, which cooperate with the charging module 2 to complete the temperature detection and temperature control of the battery 1, and the heating power is not more than 100W;

[0076] The power conversion module 5 includes a group of 2 diodes and an anti-reverse connection circuit to realize the dual-way power supply and anti-reverse connection function of the battery 1 and the AC / DC power module 3; a 20A fuse to realize the circuit overload protection function; a DCDC circuit composed of a WRB2412-15W to provide 12V DC power for the human-computer interaction module 8; a DCDC circuit composed of a WRB2405-15W to provide 5V DC power for the core control module 7.

[0077] The drive module 6 is composed of a signal isolation circuit, a motor drive circuit, and a current acquisition circuit. The signal isolation circuit isolates the PWM signal output by the core control module 7 from the motion direction signal through an optical coupler, thereby realizing electrical isolation between the control signal and the drive signal, and ensuring system safety; the isolated control signal is input to the motor drive circuit, which converts and amplifies the signal and drives the three-phase winding signal to control the motor movement. At the same time, the motor drive circuit completes the motor position feedback through the Hall signal to realize closed-loop control; in addition, the motor drive circuit is designed with a current acquisition circuit, which collects the current of the motor winding through a Hall current sensor, and inputs it to the core control module 7 after the conditioning circuit for the current loop control of the motor.

[0078] The core control module 7, the control core of the test system, is composed of the processor STM32F407ZET6 and its peripheral circuits, responsible for the system voltage, current, temperature and other parameter acquisition, external control signal acquisition, human-computer interaction module 8 control, motor control signal generation and other functions. The core control module 7 includes a power supply circuit, a core processor circuit, an IO isolation circuit, an RTC real-time clock circuit, an E 2 The PROM parameter storage circuit, TF card storage circuit, AD acquisition and conditioning circuit, and serial port circuit are composed of the power supply circuit. Among them, the power supply circuit is composed of AMS1117-3.3 and its peripheral circuits, which convert the 5V power output by the power conversion module 5 into 3.3V to power the processor and other chips of the core control module 7. At the same time, the power supply circuit contains a REF3330 power reference chip and its peripheral circuits to provide a reference power supply for the analog acquisition circuit of the core control module 7. The core processor circuit is composed of the processor STM32F407ZET6 chip, the external watchdog circuit and other peripheral circuits, which constitute the minimum system for the processor to run. The IO isolation circuit is composed of the bus interface chip SN74LVC4245, the optical coupler 6N137, and its peripheral circuits. The bus interface chip realizes the mutual conversion of 3.3V and 5V levels between the processor and the peripheral circuit. The optical coupler circuit realizes the photoelectric isolation of the external input key command and the output drive module 6 control signal to ensure the safety of the core control module 7. The processor RTC real-time circuit is composed of the clock chip DS1302, the crystal oscillator, and its peripheral circuits. Through I 2 The C interface is connected to the processor to provide clock information for the core control module 7. The storage circuit is divided into parameter storage and data storage. The parameter storage is composed of the AT24C02 chip and its peripheral circuits. 2 C interface is connected to the processor and stored in E 2PROM; data storage consists of a TF card slot and its peripheral circuits, which communicate with the processor through the SDIO interface and are used to store the test system's instructions, status, detection parameters and other data. The AD acquisition circuit includes a current sampling circuit, a voltage sampling circuit, and a temperature acquisition circuit. Among them, the current and voltage sampling circuits are composed of a Butterworth second-order filter composed of an MCP6002 op amp, with a cutoff frequency of 100kHz, which is used to collect voltage and current parameters; the temperature sampling circuit is composed of a differential amplifier circuit composed of an MCP6002 op amp, which converts the resistance signal of the PT1000 sensor into a voltage signal, thereby converting the collected temperature value. The serial port circuit consists of 2 MAX3160 chips and their peripheral circuits, 1 of which is configured in RS422 mode for communication with the onboard controller; 1 is configured in RS232 mode for communication and control of the test device GUI (graphical user interface). The core control module 7 is the information interaction center of the system. The core control module 7 receives the instructions (touch screen or hardware button instructions) from the human-computer interaction module 8, and selects the corresponding control mode according to the control mode. The control system is divided into two modes: direct drive and serial port control: in the direct drive mode, the landing gear control device does not need to be equipped on the aircraft. The core control module 7 sends a motion instruction to the drive module 6 to directly drive the landing gear to move to the corresponding position; in the serial port control mode, the landing gear control device needs to be equipped on the aircraft. The output signal of the core control module 7 does not pass through the drive module 6, but is directly sent to the onboard landing gear control device through the RS422 interface, and the landing gear is controlled to move to the corresponding position through the onboard landing gear control device. During the operation of the test device, the core control module 7 receives the status information sent back by the onboard landing gear control device, and at the same time collects the working voltage, current, temperature and other parameters of the test system in real time, and sends the parameters to the display screen interface of the human-computer interaction module 8 through the RS232 interface for display, so that the ground operator can observe the working status of the system in real time. At the same time, the core control module 7 runs the FatFs embedded file operating system, reads the onboard RTC clock information in real time, packages the instructions, status information, acquisition parameters and other data, and timestamps them, and stores them in the onboard TF storage card in text format to facilitate subsequent data analysis and troubleshooting.

[0079] The human-computer interaction module 8 is composed of a 10-inch touch screen and 4 sets of hardware control buttons. The 10-inch touch screen is used to send the retraction and lowering instructions, display the retraction and lowering status of each landing gear, and display time, voltage, current and other parameters; 3 of the 4 sets of hardware buttons are used to control the retraction and lowering instructions of the front, left and right landing gears, and 1 set is used to switch the state to achieve the switch between normal state and emergency state. The touch screen adopts an industrial serial port module, comes with a GUI system, and completes data communication through the RS232 interface; the hardware control button is connected to the core control module 7 through an optical coupler to complete the button state acquisition.

[0080] The various embodiments of the utility model have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes are obvious to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A portable UAV landing gear test device, characterized in that: include: A power supply module, used for converting input AC mains power into a first DC voltage; a charging module, electrically connected to the power module, and configured to charge the battery based on the first DC voltage; a storage battery, electrically connected to the charging module, and configured to output a second DC voltage; a power conversion module, electrically connected to the power module, the battery, the onboard landing gear control device, the drive module, the human-machine interaction module and the control module, respectively, the power conversion module being used to convert the first DC voltage / the second DC voltage into a third DC voltage and a fourth DC voltage, and then provide the third DC voltage to the human-machine interaction module, provide the fourth DC voltage to the control module, and provide the first DC voltage / the second DC voltage to the drive module and the onboard landing gear control device; A human-computer interaction module, which is in communication with the control module, and is used to receive instructions from a user and display the working status of the test device; a control module, respectively connected to the driving module and the onboard landing gear control device for communication, the control module being used to control the driving module or the onboard landing gear control device to drive the landing gear to move to a corresponding position according to the instruction; A driving module, wherein the driving module is used to drive a motor under the control of the control module, and drive the landing gear to move to a corresponding position through the motor.

2. The portable UAV landing gear test device according to claim 1, characterized in that: Also includes: A first temperature acquisition module, used to acquire the temperature of the test device; A heat dissipation module is electrically connected to the power conversion module, the power conversion module provides the first DC voltage / second DC voltage to the heat dissipation module, and the heat dissipation module is used to cool the test device based on the temperature of the test device.

3. The portable UAV landing gear test device according to claim 1, characterized in that: The human-computer interaction module comprises: Touch screen and control buttons.

4. The portable UAV landing gear test device according to claim 1, characterized in that: The battery also includes: A second temperature collection module, used to collect the temperature of the battery; A heating module is used to increase the temperature of the battery based on the temperatures of the charging module and the battery.

5. The portable UAV landing gear test device according to claim 1, characterized in that: The charging mode of the charging module is constant current-constant voltage charging, and the charging current is 6A.

6. The portable UAV landing gear testing device according to claim 1, characterized in that: The power conversion module comprises: Overcurrent protection module, reverse connection protection module, voltage acquisition module, current acquisition module and power switching module.

7. The portable UAV landing gear test device according to claim 1, characterized in that: The driving module comprises: Signal isolation module, motor drive module and current acquisition module.

8. The portable UAV landing gear test device according to claim 1, characterized in that: The first DC voltage is 28V.

9. The portable UAV landing gear testing device according to claim 1, characterized in that: The second DC voltage is 18-25.2V.

10. The portable UAV landing gear testing device according to claim 1, characterized in that: The third DC voltage is 12V, and the fourth DC voltage is 5V.

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