Unmanned aerial vehicle braking system onboard ground test device and method

Abstract

The invention discloses an unmanned aerial vehicle braking system onboard ground test device and method, and the device is constructed through a computer, an electronic circuit and a software system, and can achieve the detection of a common wheel speed sensor output signal, an undercarriage folding and unfolding state signal and a wheel load state signal. Accurate and reliable simulation of working environment states of the unmanned aerial vehicle brake system, such as brake instructions and data communication, is realized. The test device is simple in structure, simple and convenient in method operation, low in energy consumption and comprehensive in functional performance, can replace an existing system device constructed by complex equipment such as an aircraft wheel driver composed of a high-power motor and the like, an unmanned aerial vehicle ground station, a wheel load simulator (WOW) and the like, and realizes high working efficiency, high reliability and the like in an unmanned aerial vehicle brake system on-board ground test. The quality and the safety are good, the energy consumption is low, and the personnel guarantee requirement is low.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft brake system testing and detection, and in particular relates to an onboard ground test device and method for a brake system of an unmanned aerial vehicle (UAV). Background Art

[0002] The UAV braking system is a critical component during takeoff, taxiing, and landing, and its performance is directly related to the safety and efficiency of a drone's operation. Testing and inspection of UAV braking systems, including product development, factory inspection, pre-installation testing, and onboard ground testing, are crucial tasks for both the host company and the brake system manufacturer. These tests are crucial for ensuring the proper functioning and reliable performance of the UAV's braking system, thereby ensuring flight safety. Existing ground testing methods for UAV braking systems are relatively limited, making it difficult to fully simulate the performance and response of a drone under different braking conditions. These testing methods typically rely on the use of physical equipment, such as wheel speed sensors and mechanical actuators. Manually operating the wheel load signal switch in the landing gear system simulates either "air" or "ground" wheel load conditions. Manually operating a device composed of high-power motors and other components drives the wheels to simulate a certain wheel speed during taxiing. Signals are then sent to the flight control / flight management computer via a ground station, instructing the flight control / flight management computer to issue braking commands. At the same time, receiving the working status data of the brake system requires building a test system environment. As a result, there are disadvantages such as complex test equipment structure, high energy consumption, heavy structure, large resource consumption due to personnel support requirements, and insufficient test and detection effects and functional performance. Summary of the Invention

[0003] To address these shortcomings, the present invention provides an onboard ground test device and method for UAV brake systems. This device can fully simulate various operating states of a UAV brake system, replacing some physical equipment and improving detection efficiency and accuracy.

[0004] In order to achieve the above technical objectives, the following technical solutions are adopted: 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 state simulation unit, a right wheel speed signal simulation unit, a power supply unit, and a transfer cable unit; The host computer is connected to the simulation control unit and the adapter cable unit respectively, outputs a control instruction to the simulation control unit, and outputs a brake instruction analog signal to the adapter cable unit; The simulation control unit is connected to the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit respectively, and outputs host computer instructions to the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit respectively; After receiving the instruction, the left wheel speed signal simulation unit, the landing gear status simulation unit and the right wheel speed signal simulation unit output the left wheel speed simulation signal, the right wheel speed simulation signal and the landing gear status simulation signal required for the test to the adapter cable unit; The adapter cable unit is connected to the on-board test unit input and output, transmits the simulated status signal and brake command simulation signal required for the test to the on-board test unit for testing, and outputs the received status signal data fed back by the on-board test unit to the host computer; The power supply unit is respectively connected to the host computer, the simulation control unit, the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit to output power to them.

[0005] Furthermore, the on-board test unit includes a brake controller, brake system accessories and on-board cables; the adapter cable unit is connected to the brake controller and the on-board cable respectively, and the host computer, left wheel speed signal simulation unit, right wheel speed signal simulation unit and landing gear status simulation unit respectively output the brake command simulation signal, left wheel speed simulation signal, right wheel speed simulation signal and landing gear status simulation signal to the brake controller through the adapter cable unit; the brake controller then realizes the input and output connection with the brake system accessories through the adapter cable unit and the on-board cable; the brake controller outputs the brake pressure status signal, left / right wheel speed status signal and wheel load status signal collected from 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.

[0006] Furthermore, the brake system accessories include a brake pressure sensor and a servo valve.

[0007] Furthermore, the power supply unit outputs power to the brake controller via a switching cable unit.

[0008] 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 with different rotational speed frequencies, and the landing gear status simulation unit can simulate and output wheel load status signals of the aircraft's front, left and right landing gears in the "air" or "ground".

[0009] Furthermore, the host computer is composed of a portable industrial 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 the brake system self-test instructions and the brake instructions of different states such as normal braking, anti-skid braking, differential braking, and cross protection, receive the brake pressure, wheel speed, wheel load status and brake system working status self-test signals output by the brake controller, and compare and analyze the relevant instructions and status data to determine whether the working status of the brake system meets the requirements.

[0010] The onboard ground test method for the UAV brake system of the present invention comprises the following steps: Step 1: Set the output and working status of the analog control unit through the host computer; Step 2: After receiving the host computer command, 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; Step 3: The host computer sends different brake command signals to the brake controller according to the braking test and detection requirements of the UAV braking system in different states, such as normal braking, anti-skid braking, differential braking, and cross protection; Step 4: Receive brake pressure, left / right wheel speed, wheel load status and other status signals fed back by the brake controller; Step 5: Determine whether the feedback data meets expectations. If yes, return to step 1; if not, go to step 6. Step 6: Continuously adjust and monitor the wheel speed simulation signals output by the left wheel speed signal simulation unit and the right wheel speed signal simulation unit.

[0011] The beneficial effects achieved by the present invention are: Compared to existing technologies, the present invention simulates aircraft wheel speed signals, landing gear status signals, flight control system brake commands, and communications for UAV brake systems. This not only provides the signal and status environment required for UAV brake system testing and inspection, but also provides the testing and inspection functional environment required for independent onboard ground testing of the UAV brake system, such as sending brake control commands, receiving and displaying status data feedback, and analyzing and determining whether functional performance is normal. This meets the requirements for conducting onboard ground testing of UAV brake systems. The present invention offers the following advantages: comprehensive simulation of various braking conditions. Through host computer control, various state commands, such as normal braking, anti-skid braking, differential braking, and cross-protection, are sent to the brake controller. Testing efficiency and safety are improved. By continuously displaying and analyzing received feedback data, the simulated wheel speed signals can be adjusted and monitored in a timely manner, ensuring real-time and accurate testing, thereby improving testing efficiency and safety. Furthermore, the present invention simplifies the system structure and operational process. Unlike existing methods that rely on physical equipment (such as high-power motors and wheel speed sensors), the present invention combines host computer control with simulation units, simplifying the system structure, reducing equipment complexity, and lowering operational difficulty and cost. At the same time, it avoids the potential safety hazards caused by high-speed rotating equipment and improves the stability and reliability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The present invention will be described below with reference to the accompanying drawings.

[0013] Attachment Figure 1 This is a system diagram of an onboard ground test device for a UAV braking system according to the present invention. DETAILED DESCRIPTION

[0014] The following specific embodiments illustrate the embodiments of the present invention. Those skilled in the art can easily understand the other advantages and effects of the present invention from the contents disclosed in this specification. The described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0015] 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 state simulation unit, a right wheel speed signal simulation unit, a power supply unit, and a transfer cable unit; The host computer is composed of a portable industrial computer and a test software module; it is connected to the simulation control unit through 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 input and output of the adapter cable unit, and simulates the output of the brake system self-test instructions and brake instructions for normal braking, anti-skid braking, differential braking, and cross protection to the brake controller through the adapter cable unit, and at the same time 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 instructions and status data to determine whether the working status of the brake system meets the requirements.

[0016] 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, the right wheel speed signal simulation unit and the landing gear status simulation unit respectively. 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 aircraft commonly used wheel speed sensors with different speed frequencies; the landing gear status simulation unit can simulate and output wheel load status signals of the aircraft's front landing gear, left landing gear and right landing gear in the "air" or "ground"; the left wheel speed signal simulation unit outputs the left wheel speed simulation signal to the brake controller through the adapter cable unit, the right wheel speed signal simulation unit outputs the right wheel speed simulation signal to the brake controller through the adapter cable unit, and the landing gear status simulation unit outputs the landing gear status simulation signal to the brake controller through the adapter cable unit.

[0017] The adapter cable unit is an input-output intermediary unit connecting the ground test device and the onboard test unit. It is connected to the input and output of the onboard test unit, transmits the simulated status signal and brake command simulation signal required for the test to the brake controller in the onboard test unit for testing, and receives the status signal data fed back by the brake controller and outputs it to the host computer to complete the test.

[0018] The onboard test unit includes a brake controller, onboard cables and brake system accessories; the brake controller is connected to the input and output of the brake system accessories through the adapter cable unit and the onboard cable; the brake system accessories include a brake pressure sensor and a servo valve, which can be used to record the brake force data and wheel speed data output by the brake system, and transmit these data back to the ground test device through the brake controller to form a dynamic closed loop, so as to observe and adjust the brake force and wheel speed in real time and achieve precise and timely control.

[0019] The power supply unit is a power supply module, which supplies power to the host computer, simulation control unit, left wheel speed signal simulation unit, landing gear status simulation unit, right wheel speed signal simulation unit and brake controller output.

[0020] The onboard ground test method for the UAV brake system proposed in the present invention has the following operating steps: Step 1: Use the host computer to set the output and working status of the simulation control unit. The user enters 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, and the wheel load status parameters of the landing gear status simulation unit. Then, the host computer sets the working status of the simulation control unit. After ensuring that the output parameters and working status are correct, confirm the setting is complete and save the parameters; 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 to respectively output the left and right wheel speed simulation signals and wheel load status simulation signals required for the test; 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 aircraft commonly used wheel speed sensors of different rotational speed frequencies; and the landing gear status simulation unit simulates and outputs wheel load status signals indicating whether the aircraft's front, left, and right landing gears are in the air or on the ground. Step 3: The host computer selects the corresponding brake command signal according to the set brake state and transmits it to the brake controller through the interface harness, including normal braking, anti-skid braking, differential braking and cross protection braking states; Step 4: The host computer receives brake pressure, left / right wheel speed, wheel load status and other status signals fed back by the brake controller, and stores and displays the brake pressure signal, left / right wheel speed signal and wheel load status signal; 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, it returns to step 1 for the next round of testing; if the data does not meet expectations, it proceeds to step 6 for adjustment.

[0021] Step 6: Continuously adjust and monitor the wheel speed simulation 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 wheel speed simulation signals, and displays and analyzes the adjusted signals in real time on the host computer to ensure that they meet the test requirements.

[0022] Other aspects of the present invention that are not described in detail are all conventional techniques known to those skilled in the art.

[0023] It should be noted that the terms "comprises," "includes," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or elements that are inherent to such process, method, article, or apparatus.

[0024] The protection scope of the present invention is not limited to the technical solutions disclosed in the specific implementation methods. Any modifications, equivalent replacements, improvements, etc. made to the above embodiments based on the technical essence of the present invention fall within the protection scope of the present invention.

Claims

1. An onboard ground test device for a UAV braking system, characterized in that: It includes a host computer, a simulation control unit, a left wheel speed signal simulation unit, a landing gear state simulation unit, a right wheel speed signal simulation unit, a power supply unit and a transfer cable unit; The host computer is connected to the simulation control unit and the adapter cable unit respectively, outputs a control instruction to the simulation control unit, and outputs a brake instruction simulation signal to the adapter cable unit; The simulation control unit is connected to the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit respectively, and outputs host computer instructions to the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit respectively; After receiving the instruction, the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit output the left wheel speed simulation signal, the right wheel speed simulation signal and the landing gear state simulation signal required for the test to the transfer cable unit; The adapter cable unit is connected to the onboard test unit input and output, transmits the simulated state signal and brake command simulation signal required for the test to the onboard test unit for testing, and outputs the received state signal data fed back by the onboard test unit to the host computer; The power supply unit is respectively connected to the host computer, the simulation control unit, the left wheel speed signal simulation unit, the landing gear state simulation unit and the right wheel speed signal simulation unit to output power for them.

2. The onboard ground test device for the braking system of an unmanned aerial vehicle according to claim 1, characterized in that: The onboard test unit includes a brake controller, brake system accessories and onboard cables; the adapter cable unit is connected to the brake controller and the onboard cable respectively, and the host computer, the left wheel speed signal simulation unit, the right wheel speed signal simulation unit and the landing gear status simulation unit respectively output the brake command simulation signal, the left wheel speed simulation signal, the right wheel speed simulation signal and the landing gear status simulation signal to the brake controller through the adapter cable unit; the brake controller then realizes the connection with the brake system accessories input and output through the adapter cable unit and the onboard cable; 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 upper computer through the adapter cable unit; the upper computer then displays and compares and analyzes the status 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.

3. The onboard ground test device for the brake system of an unmanned aerial vehicle according to claim 2, characterized in that: The brake system accessories include a brake pressure sensor and a servo valve.

4. The onboard ground test device for the brake system of an unmanned aerial vehicle according to claim 3 is characterized in that: The power supply unit outputs power to the brake controller via the adapter cable unit.

5. The onboard ground test device for the brake system of an unmanned aerial vehicle according to claim 4, characterized in that: The left wheel speed signal simulation unit, the right wheel speed signal simulation unit, the landing gear state 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 aircraft commonly used wheel speed sensors with different rotation speed frequencies, and the landing gear state simulation unit can simulate and output the wheel load state signals of the front, left and right landing gears of the aircraft in the "air" or "ground".

6. An onboard ground test device for a UAV brake system according to any one of claims 2 to 4, characterized in that: The host computer is composed of a portable industrial 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 the output of the brake system self-test instructions and the brake instructions of normal braking, anti-skid braking, differential braking, and cross protection in different states, receive the brake pressure, wheel speed, wheel load status and brake system working status self-test signals output by the brake controller, and compare and analyze the relevant instructions and status data to determine whether the working status of the brake system meets the requirements.

7. A method for ground testing of a brake system of a UAV according to claim 1, characterized in that: The following steps are involved: Step 1: Set the output and working status of the analog control unit through the host computer; Step 2: After receiving the command 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; Step 3: The host computer sends different brake command signals to the brake controller according to the braking test and detection requirements of the UAV braking system in different states, such as normal braking, anti-skid braking, differential braking, and cross protection; Step 4, receiving brake pressure, left / right wheel speed, wheel load status and other status signals fed back by the brake controller; Step 5: Determine whether the feedback data meets expectations. If yes, return to step 1; if no, go to step 6. Step 6: Continuously adjust and monitor the wheel speed simulation signals simulated output by the left wheel speed signal simulation unit and the right wheel speed signal simulation unit.

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