A stabilizer trim control assembly test system

Abstract

The application discloses a stabilizer trim control assembly test system, which belongs to the technical field of avionics test equipment. The application comprises a test cabinet, which is internally fixed with a test interface unit, a power supply unit, a load simulation unit and a monitoring unit. The power supply unit comprises a three-phase alternating current power supply module and a direct current power supply module, which are used to receive external input power and provide power supply for the trim control assembly through the test interface unit. The load simulation unit is used to drive a load simulator to apply adjustable resistance to the trim control assembly, so as to simulate the air load suffered by the trim control assembly in the air. The test interface unit is used to provide power supply access and test configuration information for the trim control assembly. The monitoring unit is used to monitor the rotation speed and torque data of the trim control assembly in real time through a torque sensor.

Description

Technical Field

[0001] This application relates to the field of avionics testing equipment technology, and in particular to a test system for a stabilizer trim control component. Background Technology

[0002] In the field of avionics test equipment technology, the horizontal stabilizer trim system, as the core actuator of aircraft pitch trim, directly affects the flight safety of the aircraft. Among them, the trim control component, as the core component of the horizontal stabilizer trim system, needs to be verified through testing to ensure its proper functioning.

[0003] Currently, existing technologies for testing trim control components primarily rely on manual operation. This means that during testing, the aircraft's hydraulic / electrical systems must be manually activated, the cockpit trim switches manually operated, and the stability movement response observed visually and operational sounds listened to, in conjunction with background fault code checking functions.

[0004] However, in practical applications, this testing method is limited by manual operation and cannot simulate complex working conditions such as load changes under different flight states, resulting in incomplete coverage of test scenarios, which in turn leads to inaccurate fault location and difficulty in identifying hidden problems. Utility Model Content

[0005] To address the aforementioned technical issues, this application provides a test system for a stabilizer balancing control component, comprising: a test cabinet, wherein a test interface unit, a power supply unit, a load simulation unit, and a monitoring unit are fixed inside the test cabinet; The power supply unit includes a three-phase AC power module and a DC power module. The three-phase AC power module and the DC power module are used to receive external input power and provide power to the balance control component through the test interface unit. The load simulation unit is used to drive the load simulator to apply adjustable resistance to the trim control component, simulating the air load experienced by the trim control component in the air. The test interface unit is used to provide power access and test configuration information for the balance control component; The monitoring unit is used to monitor the speed and torque data of the trim control component in real time via a torque sensor.

[0006] Optionally, the load simulator includes a load regulator and a magnetic powder brake; The load regulator is electrically connected to the magnetic powder brake; The magnetic powder brake is connected to the balancing control assembly via the torque sensor.

[0007] Optionally, the DC power module is also used to provide power to the load regulator and the torque sensor.

[0008] Optionally, the DC power supply module is equipped with: a DC voltmeter, a DC ammeter, a voltage adjustment knob, and a DC output interface; The voltage adjustment knob is connected to the DC output interface; The DC voltmeter and the DC ammeter are electrically connected to the DC output interface; The DC output interface is electrically connected to the load regulator and the torque sensor; The DC output interface is electrically connected to the balance control component through the test interface unit.

[0009] Optionally, the DC output interface provides 28VDC power to the trim control component through the test interface unit.

[0010] Optionally, the three-phase AC power module is equipped with an AC power measuring instrument and an AC output interface; The AC measuring instrument is electrically connected to the AC output interface; The AC output interface is electrically connected to the balance control component through the test interface unit.

[0011] Optionally, the AC output interface provides 115VAC, 400Hz AC power to the balance control component through the test interface unit.

[0012] Optionally, the test interface unit is an auxiliary test panel equipped with a multi-core aviation connector; The multi-core aviation connector is connected to the trim control assembly.

[0013] Optionally, the auxiliary test panel is provided with a power interface terminal; The power interface terminal is electrically connected to the DC output interface and the AC output interface.

[0014] Optionally, the auxiliary test panel is equipped with a signal configuration interface and status indicator lights; The status indicator light is electrically connected to the power interface terminal; The signal configuration interface is connected to the balance control component.

[0015] As can be seen from the above technical solutions, this application has the following beneficial effects: This application utilizes a three-phase AC power module and a DC power module in the power supply unit to automatically receive external input power and stably power the trim control component via the test interface unit. This avoids the cumbersome manual operation of starting the aircraft's hydraulic / electrical systems, improving the automation and stability of the power supply process. Next, the load simulation unit drives a load simulator to apply adjustable resistance to the trim control component, simulating the air loads it experiences under different flight conditions. This overcomes the difficulty in simulating complex operating conditions, making the test scenarios more comprehensive. Furthermore, the test interface unit provides the trim control component with professional power access and accurate test configuration information, ensuring the standardization and accuracy of the testing process. Finally, the monitoring unit uses a torque sensor to monitor the speed and torque data of the trim control component in real time. Compared to manual observation and listening to operating sounds, this provides more accurate and comprehensive data, effectively improving the accuracy of fault location, timely identifying hidden problems, and enhancing test efficiency and quality. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the device structure of the test system for the stabilizer balancing control component of this application; Figure 2 The circuit diagram of the DC power supply module of the test system for the stabilizer balancing control component of this application is shown. Figure 3 The circuit diagram of the three-phase AC power supply module of the stabilizer balancing control component test system of this application is shown. Figure 4 The circuit diagram is for the auxiliary test panel of the test system for the stabilizer balance control component of this application. Detailed Implementation

[0017] To address the aforementioned technical problems, this application provides a test system for stabilizer balancing control components, which solves the problems of difficulty in simulating complex working conditions, inaccurate fault location, and difficulty in identifying hidden problems caused by manual operation.

[0018] In this application, the terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "middle", "vertical", "horizontal", "lateral", "longitudinal" and other terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only used to describe the relative positional relationship between the components or parts and do not specifically limit the specific installation orientation of each component or part.

[0019] Furthermore, in addition to indicating location or positional relationship, some of the aforementioned terms may also have other meanings. For example, the term "above" may also be used in some cases to indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0020] Furthermore, the terms "installation," "setup," "equipped with," "connection," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0021] Furthermore, the structures, proportions, sizes, etc., drawn in the accompanying drawings of this application are only used to complement the content disclosed in the specification for those skilled in the art to understand and read, and are not intended to limit the conditions under which this application can be implemented. Therefore, they have no substantial technical significance. Any modification to the structure, change in the proportional relationship, or adjustment of the size, without affecting the effects and purposes that this application can produce, should still fall within the scope of the technical content disclosed in this application.

[0022] The technical solutions of this application will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0023] Please see Figures 1 to 4 This application provides a test system for a stabilizer balancing control component, which includes: a test cabinet 1, and a test interface unit 2, a power supply unit 3, a load simulation unit 6 and a monitoring unit 7 fixed inside the test cabinet 1; Power supply unit 3 includes a three-phase AC power supply module 4 and a DC power supply module 5. The three-phase AC power supply module 4 and the DC power supply module 5 are used to receive external input power and provide power to the balance control component through the test interface unit 2. The load simulation unit 6 is used to drive the load simulator to apply adjustable resistance to the trim control component, simulating the air load on the trim control component in the air. Test interface unit 2 is used to provide power input and test configuration information for the balance control component; The monitoring unit 7 is used to monitor the speed and torque data of the trim control component in real time via a torque sensor.

[0024] The components of this embodiment will be described below: Test cabinet 1 is an integrated mechanical support and protective structure for the stabilizer balancing control component test system. It houses core components such as power supply unit 3, load simulation unit 6, and monitoring unit 7, and integrates test interface unit 2, providing physical protection and heat dissipation for the test system.

[0025] Test interface unit 2 is located in test cabinet 1 and mainly serves as a bridge connecting the object under test (DUT) and the stabilization control component. It connects to the stabilization control component and power supply unit 3. Its main functions are to connect to the operating power supply, transmit power, various test control commands, and configuration information to the stabilization control component, and receive feedback signals from the stabilization control component.

[0026] The power supply unit 3, located in the test cabinet 1, consists of a three-phase AC power module 4 and a DC power module 5, and serves as the energy supply center. It primarily receives external power input and converts and regulates it into a dedicated power supply conforming to aviation standards. This power is precisely delivered to the trim control components through the test interface unit 2, simulating the actual onboard power supply environment and ensuring the accuracy and reliability of the test conditions.

[0027] The load simulation unit 6 is set in the test cabinet 1. Its core is the load simulator. It mainly simulates the air load on the horizontal stabilizer in the air by controlling the load simulator to generate and adjust the resistance torque that hinders the rotation of the output shaft of the balancing control component.

[0028] The monitoring unit 7 is located in the test cabinet 1, and its core component is a torque sensor. It is mainly used to monitor the dynamic performance parameters of the output shaft of the balancing control component in real time, including output torque and speed.

[0029] Working principle: In this embodiment, during the testing of the stabilizer trim control component, the power supply unit 3 first starts up. Its internal three-phase AC power module 4 and DC power module 5 convert the external input power into standard DC and AC power, respectively, and supply power to the trim control component through the test interface unit 2, simulating the actual energy environment on an aircraft. Next, the operator sends test configuration information to the trim control component through the test interface unit 2 to initialize its operating state. Further, the load simulation unit 6 starts working, driving the load simulator to apply an adjustable drag torque to the output shaft of the trim control component to simulate the air load borne by the aircraft's horizontal stabilizer in the air. Simultaneously, the monitoring unit 7 starts up, using a torque sensor to collect and record in real-time the speed and torque dynamic response data of the output shaft of the trim control component under load.

[0030] In practical applications, the three-phase AC power module 4 and DC power module 5 in power supply unit 3 can automatically receive external power input and provide stable power to the trim control component through test interface unit 2. This avoids the cumbersome operation of manually starting the aircraft's hydraulic / electrical systems, improving the automation and stability of the power supply process. Next, the load simulation unit 6 can drive a load simulator to apply adjustable resistance to the trim control component, simulating the air load it experiences under different flight conditions. This overcomes the difficulty in simulating complex operating conditions, making the test scenarios more comprehensive. Furthermore, test interface unit 2 provides the trim control component with professional power access and accurate test configuration information, ensuring the standardization and accuracy of the testing process. Finally, monitoring unit 7 uses a torque sensor to monitor the speed and torque data of the trim control component in real time. Compared to manual observation and listening to operating sounds, this provides more accurate and comprehensive data, effectively improving the accuracy of fault location, timely identifying hidden problems, and enhancing test efficiency and quality.

[0031] In an optional embodiment, the load simulator includes a load regulator and a magnetic powder brake; The load regulator is electrically connected to the magnetic powder brake; The magnetic powder brake is connected to the balancing control assembly via a torque sensor.

[0032] This embodiment provides a specific implementation of a load simulator, which consists of a load regulator and a magnetic powder brake. When simulating the aerodynamic loads experienced by an aircraft's horizontal stabilizer during flight, the load regulator first outputs a corresponding controllable excitation current to the excitation coil of the magnetic powder brake. Then, under the action of the excitation current, the magnetic particles inside the magnetic powder brake are magnetized and generate a chain-like structure, thus generating a drag torque that impedes the rotation of its rotor. This drag torque is then applied to the transmission chain rigidly connected to the output shaft of the trim control component, simulating the mechanical effects of the aerodynamic load. During this process, the load regulator continuously and dynamically adjusts the output current, ensuring that the drag torque provided by the magnetic powder brake can match the preset load spectrum in real time and accurately, thereby completing the simulation of complex aerodynamic environments.

[0033] In practical applications, by precisely controlling the current of the magnetic powder brake through the load regulator, a smooth drag torque with rapid response and continuous adjustment can be generated, effectively simulating the real aerodynamic load of the aircraft horizontal stabilizer in the air. This achieves high-precision, dynamic, real-time reproduction of complex and variable load spectra, providing a realistic and effective working environment for performance evaluation and fault diagnosis of trim control components.

[0034] In an optional embodiment, the DC power module 5 is also used to provide power to the load regulator and torque sensor.

[0035] This embodiment provides a specific implementation of the DC power supply module 5. In this implementation, the DC power supply module 5 provides a stable and reliable power supply to the load regulator and torque sensor, ensuring their continuous and stable operation during testing. After receiving power, the load regulator outputs excitation current to the magnetic powder brake, achieving precise control of the simulated load. After receiving power, the torque sensor can acquire and display torque and speed signals in real time. Furthermore, by using a single power supply module for unified power supply, the structure of the stabilizer balancing control component test system is simplified, compatibility issues caused by multiple power supplies are avoided, and the integration, reliability, and anti-interference capability of the entire stabilizer balancing control component test system are significantly improved.

[0036] In an optional embodiment, the DC power module 5 is provided with: a DC voltmeter, a DC ammeter, a voltage adjustment knob, and a DC output interface; The voltage adjustment knob is connected to the DC output interface; The DC voltmeter and DC ammeter are electrically connected to the DC output interface; The DC output interface is electrically connected to the load regulator and torque sensor; The DC output interface is electrically connected to the balance control component through test interface unit 2.

[0037] This embodiment provides a specific implementation of a DC power supply module 5. In this implementation, the DC power supply module 5 is equipped with a DC voltmeter, a DC ammeter, a voltage adjustment knob, and a DC output interface. When supplying DC power, the target voltage value is set by rotating the voltage adjustment knob. This command directly adjusts the internal circuitry of the DC power supply module 5, causing the DC output interface to generate a corresponding stable DC voltage. Simultaneously, during power supply, the DC voltmeter and ammeter monitor and display the voltage and current parameters of the DC output interface in real time. Then, the DC output interface provides operating power to the balance control component through the test interface unit 2, and simultaneously provides the necessary operating power to the control circuit of the load regulator and the measurement circuit of the torque sensor, ensuring the synchronous and stable operation of the load simulation and data acquisition functions. This achieves integrated power supply and precise control of the stabilizer balance control component test system.

[0038] In an optional embodiment, the DC output interface provides 28VDC power to the trim control component via test interface unit 2.

[0039] This embodiment provides a specific implementation of a DC output interface. In this implementation, the DC output interface provides 28VDC power to the trim control component through the test interface unit 2. This 28VDC power supply meets aerospace-grade standards, with voltage fluctuations controlled within ±0.5%. This ensures precise matching of the trim control component's drive requirements, guaranteeing that the trim control component can stably output drive force to overcome airflow pressure reaction forces or turbulent impact loads when simulating aerodynamic loads during cruise and takeoff / landing conditions. Simultaneously, it provides reliable power for the torque sensor to collect real-time speed and torque data, avoiding component drive abnormalities or data deviations caused by unstable power supply, thus ensuring test accuracy and reliability.

[0040] In an optional embodiment, the three-phase AC power module 4 is provided with an AC power measuring instrument and an AC output interface; The AC measuring instrument is electrically connected to the AC output interface; The AC output interface is electrically connected to the balance control component through test interface unit 2.

[0041] This embodiment provides a specific implementation of a three-phase AC power supply module 4. In this implementation, the three-phase AC power supply module 4 is equipped with an AC power measuring instrument and an AC output interface. When the three-phase AC power supply module 4 is started, its internal circuitry converts the external input power into three-phase AC power conforming to aviation standards and transmits it externally through the AC output interface. The AC power measuring instrument is directly connected to the three-phase lines of the AC output interface, monitoring the voltage and current parameters of each phase in real time and displaying the measured values. The AC output interface is electrically connected to the test interface unit 2 via a test cable. Finally, the test interface unit 2 transmits the three-phase AC power to the balance control component, providing it with operating power, while the AC power measuring instrument continuously monitors and ensures that the power supply quality meets the test specifications.

[0042] In an optional embodiment, the AC output interface provides 115VAC, 400Hz AC power to the trim control component via test interface unit 2.

[0043] This embodiment provides a specific implementation of an AC output interface. In this implementation, the AC output interface supplies 115VAC, 400Hz aviation standard AC power to the trim control component via test interface unit 2, ensuring that the drive motor of the trim control component obtains power characteristics completely consistent with actual flight conditions. This power supply method not only guarantees the accuracy and stability of voltage and frequency parameters, but also effectively verifies the performance of the trim control component under rated power conditions. Furthermore, the integrated interface design significantly improves the standardization of the test system, providing a reliable energy guarantee foundation for the trim control function.

[0044] In an optional embodiment, the test interface unit 2 is an auxiliary test panel equipped with a multi-core aviation connector; The multi-core aviation connector connects to the trim control assembly via a test cable.

[0045] This embodiment provides a specific implementation of the test interface unit 2, which is an auxiliary test panel equipped with a multi-core aviation connector. Before simulation testing, the multi-core aviation connector on the auxiliary test panel is connected to the corresponding interface of the trim control component via a dedicated test cable to form a complete electrical path. The high-current-carrying core of the multi-core aviation connector is directly connected to the power distribution circuit built into the auxiliary test panel. After connection, a high-current transmission channel can be immediately established, simultaneously supplying the 115VAC, 400Hz AC power and 28VDC DC power provided by the power supply unit 3 to the trim control component, ensuring it receives continuous and stable operating power.

[0046] In an optional embodiment, the auxiliary test panel is provided with a power interface terminal; The power interface terminals are electrically connected to the DC output interface and the AC output interface.

[0047] This embodiment provides a specific implementation of an auxiliary test panel, in which the auxiliary test panel is provided with a power interface terminal. This power interface terminal can connect the 115VAC, 400Hz AC power output from the AC output interface of the three-phase AC power module 4 and the 28VDC DC power output from the DC output interface of the DC power module 5 to the auxiliary test panel via a test cable. This eliminates the need for separate access components for different power types, effectively simplifying the internal wiring layout of the panel, reducing component redundancy costs, and improving the auxiliary test panel's adaptability and input reliability to different power types.

[0048] In an optional embodiment, the auxiliary test panel is provided with a signal configuration interface and status indicator lights; The status indicator light is electrically connected to the power interface terminal; The signal configuration interface is connected to the balance control component.

[0049] This embodiment provides another specific implementation of the auxiliary test panel. In this implementation, the auxiliary test panel is equipped with a signal configuration interface and status indicator lights. The signal configuration interface serves as the signal interaction channel between the auxiliary test panel and the balancing control component, directly connecting to the signal terminals of the balancing control component. During testing, external test commands, such as balancing test mode selection, load resistance threshold setting, and control logic trigger signals, are transmitted to the balancing control component through this signal configuration interface, enabling precise configuration of the component's test parameters.

[0050] The status indicator light is electrically connected to the power interface terminal via a wire, forming a power on / off monitoring loop. When the power interface terminal is connected to a 115VAC AC power supply or a 28VDC DC power supply, current flows along the loop to the status indicator light, illuminating it. At this time, the tester can visually reflect the normal power supply status. If the power interface terminal is de-energized, has poor contact, or a line fault causes a current interruption, the status indicator light will turn off due to the lack of current. In this case, the tester can quickly determine if there is an abnormality in the power supply by observing the status indicator light's off state, thus providing a basic power supply status basis for subsequent testing, helping to promptly troubleshoot power problems, and ensuring the progress of testing.

[0051] It should be noted that the above description of the disclosed embodiments enables those skilled in the art to implement or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A stability augmentation control assembly test system, comprising: include: The test cabinet contains a test interface unit, a power supply unit, a load simulation unit, and a monitoring unit. The power supply unit includes a three-phase AC power module and a DC power module. The three-phase AC power module and the DC power module are used to receive external input power and provide power to the balance control component through the test interface unit. The load simulation unit is used to drive the load simulator to apply adjustable resistance to the trim control component, simulating the air load experienced by the trim control component in the air. The test interface unit is used to provide power access and test configuration information for the balance control component; The monitoring unit is used to monitor the speed and torque data of the trim control component in real time via a torque sensor.

2. The tailplane trim control assembly test system as claimed in claim 1, wherein, The load simulator includes a load regulator and a magnetic powder brake; The load regulator is electrically connected to the magnetic powder brake; The magnetic powder brake is connected to the balancing control assembly via the torque sensor.

3. The tailplane trim control assembly test system as claimed in claim 2, wherein, The DC power module is also used to provide power to the load regulator and the torque sensor.

4. The tailplane trim control assembly test system as claimed in claim 3, wherein, The DC power module is equipped with: a DC voltmeter, a DC ammeter, a voltage adjustment knob, and a DC output interface; The voltage adjustment knob is connected to the DC output interface; The DC voltmeter and the DC ammeter are electrically connected to the DC output interface; The DC output interface is electrically connected to the load regulator and the torque sensor; The DC output interface is electrically connected to the balance control component through the test interface unit.

5. The tailplane trim control assembly test system as claimed in claim 4, wherein, The DC output interface provides 28VDC power to the balance control component through the test interface unit.

6. The tailplane trim control assembly test system as claimed in claim 5, wherein, The three-phase AC power module is equipped with AC power measuring instruments and an AC output interface; The AC measuring instrument is electrically connected to the AC output interface; The AC output interface is electrically connected to the balance control component through the test interface unit.

7. The tailplane trim control assembly test system as claimed in claim 6, wherein, The AC output interface provides 115VAC, 400Hz AC power to the balance control component through the test interface unit.

8. The tailplane trim control assembly test system as claimed in claim 7, wherein, The test interface unit is an auxiliary test panel equipped with a multi-core aviation connector; The multi-core aviation connector is connected to the trim control assembly.

9. The tailplane trim control assembly test system as claimed in claim 8, wherein, The auxiliary test panel is equipped with a power interface terminal; The power interface terminal is electrically connected to the DC output interface and the AC output interface.

10. The tailplane trim control assembly test system as claimed in claim 9, wherein, The auxiliary test panel is equipped with a signal configuration interface and status indicator lights; The status indicator light is electrically connected to the power interface terminal; The signal configuration interface is connected to the balance control component.

Images