An unmanned aerial vehicle brake system on-ground test device and method

Abstract

The application discloses a kind of unmanned plane brake system on-machine ground test device and method, utilize computer, electronic circuit and software system constructed unmanned plane brake system on-machine ground test device, can to commonly used wheel speed sensor output signal, landing gear retraction and wheel load state signal, brake instruction and data communication etc. The environmental state of unmanned plane brake system work is accurately and reliably simulated.The test device described in the application is simple in structure, easy to operate in method, low in energy consumption, and comprehensive in functional performance, which can replace the existing system device constructed by complex equipment such as high-power motor, unmanned plane ground station and wheel load simulator (WOW). In the unmanned plane brake system on-machine ground test, high working efficiency, good quality and safety, low energy consumption and less personnel support are realized.

Description

Technical Field

[0001] This invention belongs to the field of aircraft braking system testing and inspection technology, specifically relating to an on-board ground testing device and method for unmanned aerial vehicle (UAV) braking systems. Background Technology

[0002] The UAV braking system is a critical component during UAV takeoff, taxiing, and landing, and its performance directly affects the operational safety and efficiency of the UAV. The development, factory inspection, pre-installation testing, and on-board ground testing of UAV braking systems are important tasks for both the main unit and the braking system manufacturer. These tests are essential for ensuring the normal operation and reliable performance of the UAV braking system, thus guaranteeing flight safety. Currently, ground testing methods for UAV braking systems are limited and cannot comprehensively simulate the performance and response of UAVs under different braking conditions. These testing methods typically rely on physical equipment, such as wheel speed sensors and mechanical drive devices. Manual mechanical operation of the landing gear system's wheel-mounted signal switches simulates the "air" or "ground" state of the landing gear wheels; manual operation of devices such as high-power motors drives the wheels to simulate a certain wheel speed during aircraft taxiing; and signals are sent from ground stations to the flight control / flight management computer to control the flight control / flight management computer to send braking commands. Simultaneously, receiving braking system operating status data requires constructing a test system environment. Consequently, the test equipment suffers from drawbacks such as complex structure, high energy consumption, large weight and structure, high personnel support requirements, insufficient test and detection effects and functional performance. Summary of the Invention

[0003] To address the aforementioned shortcomings, this invention aims to provide an onboard ground testing device and method for unmanned aerial vehicle (UAV) braking systems. This invention can comprehensively simulate various operating states of UAV braking systems, replacing the use of some physical equipment and improving testing efficiency and accuracy.

[0004] To achieve the above technical objectives, the following technical solutions were adopted:

[0005] A ground-based test device for an unmanned aerial vehicle (UAV) braking system includes a host computer, a simulation control unit, a left wheel speed signal simulation unit, a landing gear status simulation unit, a right wheel speed signal simulation unit, a power supply unit, and a transfer cable unit.

[0006] The host computer is connected to the analog control unit and the adapter cable unit respectively, outputting control commands to the analog control unit and outputting brake command analog signals to the adapter cable unit.

[0007] The simulation control unit is connected to the left wheel speed signal simulation unit, the landing gear status simulation unit and the right wheel speed signal simulation unit respectively, and outputs host computer commands to the left wheel speed signal simulation unit, the landing gear status simulation unit and the right wheel speed signal simulation unit respectively;

[0008] After receiving the command, the left wheel speed signal simulation unit, landing gear status simulation unit, and right wheel speed signal simulation unit output the left wheel speed simulation signal, right wheel speed simulation signal, and landing gear status simulation signal required for the test to the adapter cable unit.

[0009] The adapter cable unit is connected to the on-board test unit for input and output, transmitting the simulated status signals and brake command simulation signals required for the test to the on-board test unit for testing, and outputting the received status signal data from the on-board test unit to the host computer.

[0010] The power supply unit is connected to the host computer, the simulation control unit, the left wheel speed signal simulation unit, the landing gear status simulation unit, and the right wheel speed signal simulation unit, respectively, to supply power to them.

[0011] Furthermore, the onboard testing unit includes a brake controller, brake system accessories, and onboard cables. The adapter cable unit is connected to the brake controller and the onboard cables. The host computer, left wheel speed signal simulation unit, right wheel speed signal simulation unit, and landing gear status simulation unit output brake command simulation signals, left wheel speed simulation signals, right wheel speed simulation signals, and landing gear status simulation signals to the brake controller through the adapter cable unit. The brake controller then connects to the input / output of the brake system accessories through the adapter cable unit and the onboard cables. The brake controller outputs the brake pressure status signal, left / right wheel speed status signal, and wheel load status signal fed back by the brake system accessories to the host computer through the adapter cable unit. The host computer then displays and compares the status signal data fed back by the brake controller and adjusts and controls the left wheel speed simulation signal and the right wheel speed simulation signal.

[0012] Furthermore, the braking system accessories include a brake pressure sensor and a servo valve.

[0013] Furthermore, the power supply unit supplies power to the brake controller via an adapter cable unit.

[0014] Furthermore, the left wheel speed signal simulation unit, the right wheel speed signal simulation unit, the landing gear status simulation unit, and the simulation control unit are composed of electronic circuit modules. Under the control of the host computer and the simulation control unit, the left wheel speed signal simulation unit and the right wheel speed signal simulation unit can accurately simulate the sine wave and square wave signals output by multiple commonly used aircraft wheel speed sensors at different speed frequencies. The landing gear status simulation unit can simulate and output the wheel load status signals of the aircraft's front, left, and right landing gears when they are in the "air" or "ground".

[0015] Furthermore, the host computer consists of a portable industrial control computer and a test software module; it can control the output status of the left wheel speed signal simulation unit, the right wheel speed signal simulation unit, and the landing gear status simulation unit, simulate and output braking system self-test commands and braking commands for different states such as normal braking, anti-skid braking, differential braking, and cross protection, receive braking pressure, wheel speed, wheel load status, and braking system working status self-test signals output by the brake controller, and compare and analyze the relevant commands and status data to determine whether the braking system working status meets the requirements.

[0016] The on-board ground testing method for the UAV braking system of the present invention includes the following steps:

[0017] Step 1: Configure the output and operating status of the analog control unit via the host computer;

[0018] Step 2: After receiving the instructions from the host computer, the simulation control unit controls the left wheel speed signal simulation unit, the right wheel speed signal simulation unit, and the landing gear status simulation unit respectively, and outputs the left and right wheel speed simulation signals and wheel load status simulation signals required for the test respectively.

[0019] Step 3: The host computer sends different braking command signals to the brake controller according to the braking test and detection requirements of the UAV braking system under different states such as normal braking, anti-skid braking, differential braking, and cross protection.

[0020] Step 4: Receive status signals from the brake controller, such as brake pressure, left / right wheel speed, and wheel load status;

[0021] Step 5: Determine if the feedback data meets expectations. If yes, return to step 1; otherwise, proceed to step 6.

[0022] Step 6: Continuously adjust and monitor the simulated wheel speed signals output by the left wheel speed signal simulation unit and the right wheel speed signal simulation unit.

[0023] The beneficial effects achieved by this invention are:

[0024] Compared with existing technologies, this invention simulates the aircraft wheel speed signals, landing gear status signals, flight control system braking commands, and communication during the operation of the UAV braking system. It not only provides the signal and status environment required for UAV braking system operation testing and inspection, but also provides the necessary testing and inspection environment for independent on-airborne ground testing of the UAV braking system, including sending braking control commands, receiving and displaying status data feedback, and analyzing and judging whether functional performance is normal. This meets the requirements for conducting on-airborne ground testing of UAV braking systems. It has the following advantages: Comprehensive simulation of various braking states: Through upper-computer operation, it sends various state commands to the brake controller simulating normal braking, anti-skid braking, differential braking, and cross-protection of the UAV braking system; Improved testing efficiency and safety: By continuously displaying and analyzing the received feedback data, it can promptly adjust and monitor the simulated wheel speed signals, ensuring the real-time performance and accuracy of the test, thereby improving testing efficiency and safety; Simplified system structure and operation process: Unlike existing methods that rely on physical equipment (such as high-power motors and wheel speed sensors), this invention simplifies the system structure, reduces equipment complexity, and lowers operational difficulty and cost through the combination of upper-computer control and simulation units. At the same time, it avoids the safety hazards caused by high-speed rotating equipment and improves the stability and reliability of the system. Attached Figure Description

[0025] The present invention will now be described with reference to the accompanying drawings.

[0026] Appendix Figure 1 This is a system diagram of an onboard ground test device for a UAV braking system according to the present invention. Detailed Implementation

[0027] The following specific embodiments illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The described embodiments are merely some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] like Figure 1 As shown, an onboard ground test device for a UAV braking system includes a host computer, a simulation control unit, a left wheel speed signal simulation unit, a landing gear status simulation unit, a right wheel speed signal simulation unit, a power supply unit, and a transfer cable unit.

[0029] The host computer consists of a portable industrial computer and a test software module. It is connected to the simulation control unit via an interface harness and can control the output status of the left wheel speed signal simulation unit, the right wheel speed signal simulation unit, and the landing gear status simulation unit. The host computer is also connected to the adapter cable unit for input and output. Through the adapter cable unit, it simulates and outputs braking system self-test commands and braking commands for different states such as normal braking, anti-skid braking, differential braking, and cross protection to the brake controller. At the same time, it receives the brake pressure, wheel speed, wheel load status, and brake system working status self-test signals fed back by the brake controller, and compares and analyzes the relevant commands and status data to determine whether the working status of the brake system meets the requirements.

[0030] The simulation control unit, left wheel speed signal simulation unit, right wheel speed signal simulation unit, and landing gear status simulation unit are composed of electronic circuit modules. The simulation control unit receives instructions from the host computer and controls the left wheel speed signal simulation unit, right wheel speed signal simulation unit, and landing gear status simulation unit respectively. The left wheel speed signal simulation unit and right wheel speed signal simulation unit can accurately simulate sine wave and square wave signals output by multiple commonly used aircraft wheel speed sensors at different speed frequencies. The landing gear status simulation unit can simulate and output wheel load status signals of the aircraft's nose landing gear, left landing gear, and right landing gear in "air" or "ground". The left wheel speed signal simulation unit outputs a left wheel speed simulation signal to the brake controller through a converter cable unit. The right wheel speed signal simulation unit outputs a right wheel speed simulation signal to the brake controller through a converter cable unit. The landing gear status simulation unit outputs a landing gear status simulation signal to the brake controller through a converter cable unit.

[0031] The adapter cable unit is an input / output intermediary unit connecting the ground test device and the on-board test unit. It is connected to the input / output of the on-board test unit, transmits the simulated state signals and brake command simulated signals required for the test to the brake controller in the on-board test unit for testing, and receives the state signal data fed back by the brake controller and outputs it to the host computer to complete the test.

[0032] The onboard testing unit includes a brake controller, onboard cables, and brake system accessories. The brake controller connects to the input and output of the brake system accessories via an adapter cable unit and onboard cables. The brake system accessories include a brake pressure sensor and a servo valve, which can be used to record the braking force and wheel speed data output by the brake system. These data are then transmitted back to the ground testing device via the brake controller, forming a dynamic closed loop. This allows for real-time observation and adjustment of braking force and wheel speed, enabling precise and timely control.

[0033] The power supply unit is a power supply module that outputs power to the host computer, the analog control unit, the left wheel speed signal simulation unit, the landing gear status simulation unit, the right wheel speed signal simulation unit, and the brake controller.

[0034] The on-board ground testing method for the UAV braking system proposed in this invention comprises the following steps:

[0035] Step 1: Operate via the host computer to set the output and operating status of the simulation control unit. The user inputs the output parameters of the simulation control unit through the host computer, including the signal output amplitude parameters of the left wheel speed signal simulation unit and the right wheel speed signal simulation unit, as well as the wheel load status parameters of the landing gear status simulation unit. Then, the host computer sets the operating status of the simulation control unit. After ensuring that the output parameters and operating status are correct, confirm the settings are complete and save the parameters.

[0036] Step 2: The simulation control unit controls the left wheel speed signal simulation unit, the right wheel speed signal simulation unit, and the landing gear status simulation unit respectively, and outputs the left and right wheel speed simulation signals and wheel load status simulation signals required for the test respectively; the left wheel speed signal simulation unit and the right wheel speed signal simulation unit simulate and output sine wave and square wave signals generated by multiple commonly used aircraft wheel speed sensors at different speed frequencies; the landing gear status simulation unit simulates and outputs the wheel load status signals of the aircraft's front, left, and right landing gear when they are in the "air" or "ground";

[0037] Step 3: The host computer selects the corresponding braking command signal according to the set braking status and transmits it to the brake controller through the interface harness, including normal braking, anti-skid braking, differential braking and cross protection braking status.

[0038] Step 4: The host computer receives status signals such as brake pressure, left / right wheel speed, and wheel load status from the brake controller, and stores and displays the brake pressure signal, left / right wheel speed signal, and wheel load status signal.

[0039] Step 5: The host computer analyzes the received feedback data to determine whether it meets the expected braking effect and working status. If the data meets expectations, return to Step 1 for the next round of testing; if the data does not meet expectations, proceed to Step 6 for adjustment.

[0040] Step 6: Continuously adjust and monitor the simulated wheel speed signals output by the left wheel speed signal simulation unit and the right wheel speed signal simulation unit. The host computer adjusts the output signal parameters of the left wheel speed signal simulation unit and the right wheel speed signal simulation unit through the control unit, monitors the adjusted simulated wheel speed signals, and displays and analyzes the adjusted signals in real time to ensure that they meet the test requirements.

[0041] Other aspects of this invention that are not detailed herein are all conventional techniques known to those skilled in the art.

[0042] It should be noted that the terms “comprising,” “including,” or any other variations are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0043] The scope of protection of this invention is not limited to the technical solutions disclosed in the specific embodiments. Any modifications, equivalent substitutions, improvements, etc., made to the above embodiments based on the technical essence of this invention shall fall within the scope of protection of this invention.

Claims

1. An unmanned aerial vehicle brake system on-ground test device, characterized in that: The device comprises a host computer, an analog control unit, a left wheel speed signal analog unit, a landing gear state analog unit, a right wheel speed signal analog unit, a power supply unit, a switching cable unit and an on-board test unit. The host computer is connected with the analog control unit and the switching cable unit respectively, outputs control instructions to the analog control unit and outputs brake instruction analog signals to the switching cable unit. The analog control unit is connected with the left wheel speed signal analog unit, the landing gear state analog unit and the right wheel speed signal analog unit respectively, and outputs host computer instructions to the left wheel speed signal analog unit, the landing gear state analog unit and the right wheel speed signal analog unit respectively. The left wheel speed signal analog unit, the landing gear state analog unit and the right wheel speed signal analog unit output the required left wheel speed analog signals, right wheel speed analog signals and landing gear state analog signals to the switching cable unit after receiving the instructions; the left wheel speed signal and the right wheel speed signal can be output as sine wave signals and square wave signals of different rotating speed frequencies output by a plurality of airplane wheel speed sensors; the landing gear state analog signal can be output as wheel load state signals of the airplane front, left and right landing gears in the "air" or "ground" state. The switching cable unit is connected with the on-board test unit for input and output, transmits the required analog state signals and brake instruction analog signals to the on-board test unit for testing, and outputs the received state signal data fed back by the on-board test unit to the host computer. The on-board test unit comprises a brake controller, brake system accessories and an on-board cable; the brake system accessories comprise a brake pressure sensor and a servo valve; the switching cable unit is connected with the brake controller and the on-board cable respectively; the host computer, the left wheel speed signal analog unit, the right wheel speed signal analog unit and the landing gear state analog unit output brake instruction analog signals, left wheel speed analog signals, right wheel speed analog signals and landing gear state analog signals to the brake controller respectively through the switching cable unit; the brake controller realizes input and output connection with the brake system accessories through the switching cable unit and the on-board cable. The brake controller outputs brake pressure state signals, left / right airplane wheel rotating speed state signals and wheel load state signals fed back by the brake system accessories to the host computer through the switching cable unit; the host computer displays and compares and analyzes the state signal data fed back by the brake controller, and adjusts and controls the left wheel speed analog signal and the right wheel speed analog signal. The power supply unit is connected with the host computer, the analog control unit, the left wheel speed signal analog unit, the landing gear state analog unit and the right wheel speed signal analog unit respectively, and outputs power supply for them; the power supply unit outputs power supply to the brake controller through the connection with the switching cable unit.

2. The on-ground test device for unmanned aerial vehicle brake system on board, according to claim 1, characterized in that: The host computer is composed of a portable industrial computer and a test software module; it can control the output state of the left wheel speed signal simulation unit, the right wheel speed signal simulation unit and the landing gear state simulation unit, simulate the output brake system self-checking instruction and the brake instructions in different states of normal brake, anti-skid brake, differential brake and cross protection, receive the brake pressure, wheel speed, wheel load state and brake system working state self-checking signals output by the brake controller, and compare and analyze the related instructions and state data to determine whether the brake system working state meets the requirements.

3. A method of conducting an on-ground test of an unmanned aerial vehicle brake system as claimed in claim 1, wherein: The method comprises the following steps: Step 1: setting the output and working state of the simulation control unit through the host computer; Step 2: after receiving the host computer instruction, the simulation control unit controls the left wheel speed signal simulation unit, the right wheel speed signal simulation unit and the landing gear state simulation unit respectively, and outputs the required left and right wheel speed simulation signals and wheel load state simulation signals; Step 3: the host computer sends different brake instruction signals to the brake controller according to the different state brake test and detection requirements of the normal brake, anti-skid brake, differential brake and cross protection of the unmanned aerial vehicle brake system; Step 4: receiving the brake pressure state signal, left / right wheel speed state signal and wheel load state signal feedback by the brake controller; Step 5: determining whether the feedback data meets the expectation, if yes, returning to step 1, if not, executing step 6; Step 6: continuously adjusting and monitoring the wheel speed simulation signals simulated and output by the left wheel speed signal simulation unit and the right wheel speed signal simulation unit.

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