A high-synchronization pressure measuring device for flight test

Abstract

The application provides a high-synchronization pressure measurement device for flight test, comprising: a plurality of pressure sensing units, a fairing, and an acquisition control module; the fairing is attached to the outer surface of an airplane, and the plurality of pressure sensing units are embedded into the fairing with connecting cables; the fairing and the plurality of pressure sensing units form an integral whole, the surface of the pressure sensing units is smooth and adheres to the outer surface of the airplane; the pressure sensing units perceive the pressure at the location in real time and convert it into an analog electric signal to be transmitted to the acquisition control module; the acquisition control module stores the analog electric signal in the built-in memory after conditioning and digitizing the analog electric signal together with time stamp information; the device can be closely attached to various complex curved surfaces, has the characteristics of small volume, thin thickness, and synchronous acquisition, realizes high-resolution pressure synchronous measurement under the premise of not disturbing the flow field, and can be customized for measurement and reused.

Description

Technical Field

[0001] This invention belongs to the field of pressure distribution measurement technology in flight testing, and relates to a high-synchronous pressure measurement device for flight testing. Background Technology

[0002] Flight testing is an indispensable part of verifying aircraft aerodynamic characteristics and conducting load strength tests. Among these tests, the distribution data of pressure on the aircraft surface is a key parameter for evaluating aerodynamic performance and determining load distribution. To obtain this data, pressure measuring devices are typically installed on the aircraft surface.

[0003] Traditional flight test pressure distribution measurements often involve developing specialized test pieces and creating pressure measurement holes on their surfaces to connect long pressure-sensing pipelines. To shorten flight test cycles, integrated pressure measurement strips were subsequently developed, which integrate multiple pressure sensors onto a long strip base and are directly attached to the aircraft's outer surface for measurement. However, these pressure measurement strips still have the problem of not being able to completely conform to areas with drastic curvature changes (such as the wing leading edge). Summary of the Invention

[0004] To address the problem in existing technologies where pressure measuring tapes are difficult to fully adhere to areas with drastic curvature changes, this invention provides a high-synchronization pressure measurement device for flight testing. This device can adhere tightly to various complex curved surfaces like a film, while also possessing the characteristics of small size, thinness, and synchronous data acquisition. It achieves high-resolution synchronous pressure measurement without disturbing the flow field, and can be customized and reused. The technical solution is as follows: A high-synchronous pressure measurement device for flight testing includes: multiple pressure sensing units, a fairing, and a data acquisition and control module; The fairing is attached to the outer surface of the aircraft, and multiple pressure sensing units and connecting cables are embedded in the fairing. The fairing and multiple pressure sensing units form a whole. The surface of the pressure sensing units is flat and fits the outer surface of the aircraft, which can reduce the impact on the original aerodynamic shape of the aircraft components. The pressure sensing unit detects the pressure at its location in real time and converts it into an analog electrical signal, which is then transmitted to the acquisition and control module. After the acquisition and control module conditions and digitizes the analog electrical signal, it stores it together with the timestamp information in the built-in memory.

[0005] The fairing is made of a composite encapsulation material in an initial semi-flow state. This material fully fills and wraps multiple pressure sensing units and connecting cables on the same measurement profile, and after shaping, forms a single pressure measurement strip that can be directly attached to the outer surface of the aircraft. The use of this composite encapsulation material in the fairing ensures that it can conform to the curvature changes of complex three-dimensional surfaces such as the wing leading edge and wing root.

[0006] Each pressure sensing unit is no larger than 40*40mm in size and includes a power supply step-down and voltage regulation circuit, a pressure-sensitive chip, an FPGA core circuit, an RS485 interface circuit, an ADC analog-to-digital conversion circuit, and a temperature sensing circuit. Among them, the power supply buck regulator circuit converts the high input voltage into a stable low output voltage; The pressure-sensitive chip senses the pressure information at the location of the measuring point in real time. The FPGA core circuit is used for timing control, data packaging, timestamp insertion, and interface communication. It enables synchronous sampling of the ADC analog-to-digital conversion in multiple pressure sensing units; enables the ADC peripheral clock; sets the frequency division coefficient to determine the ADC operating frequency; sets the resolution; sets the sampling time; sets the data storage alignment; sets the operating voltage range; calibrates the local oscillator; starts the ADC self-calibration program to eliminate offset errors; configures the TIM trigger output (TRGO) as a synchronization signal for other peripherals; and enables the MAC / PTP hardware timestamp to record the precise time of key events. The RS485 interface circuit adopts a differential signal transmission mechanism, which can effectively suppress common-mode noise. It uses half-duplex communication to perform time-series scheduling and high-speed data polling of pressure information from all measuring points along an entire pressure measurement zone. While ensuring the determinism of command issuance and data upload, it meets the real-time requirements of the system for high-speed, periodic acquisition of hundreds of channels of data.

[0007] An ADC (Analog-to-Digital Converter) circuit is used for the digital processing of electrical signals; The temperature sensing circuit monitors the ambient temperature of the pressure-sensitive chip, providing input for the temperature drift compensation algorithm.

[0008] The pressure-sensitive chip has a waterproof barrier on its outer surface, which is a nanoscale organic molecular film obtained by vacuum deposition technology.

[0009] A nanoscale organic molecular film was used to construct a "nanoscale, ultrathin, and high-density" barrier on the surface of the pressure-sensitive chip of the pressure-sensing unit, which can block water molecules and ensure that the pressure signal is not attenuated.

[0010] The overall thickness of the device does not exceed 2mm. Existing pressure measuring band technology suffers from excessive thickness; this invention addresses this issue by providing a measuring device with the advantage of minimal thickness.

[0011] In the fairing fabrication process, composite encapsulation material is first poured into the mold containing the pressure sensing units, ensuring the material fully fills and encapsulates all pressure sensing units and cables. A curing reaction then forms a solid composite material shell, after which the mold is removed. The composite encapsulation material pouring achieves a seamless fit, and the subsequent curing reaction creates a robust, lightweight, and smooth solid composite material shell. This provides a comprehensive protective shield with excellent environmental resistance while meeting ultra-thin constraints.

[0012] The fairing surface is coated with a protective coating that is wear-resistant, waterproof, and oil-resistant; the internal pressure sensing unit and connecting cables are protected by the protective coating to jointly resist particle erosion, liquid splashing, and accidental impacts during flight testing.

[0013] The fairing shell is coated with conductive paint to form a conductive shell, which is connected to the ground wire of the pressure sensing unit to form a shielding layer. The conductive shell of the fairing is connected to the ground wire of the cabin through a low impedance path to form a continuous shield, which effectively suppresses external radio frequency interference and prevents its own signal radiation, ensuring full compatibility with the electromagnetic environment on the aircraft.

[0014] The acquisition and control module includes an FPGA processor submodule, a signal conditioning submodule, an ADC analog-to-digital converter submodule, a power supply management submodule, a data storage submodule, a clock synchronization submodule, a status indication submodule, and a data interface. The FPGA processor submodule is used for device control, timing management, and communication coordination. The FPGA processor submodule sends configuration instructions for sampling rate, working mode, and filter parameters to the pressure sensing units in the pressure measurement zone, and sends a high-precision global synchronization clock signal to ensure that the sampling time of all pressure sensing units is aligned. The signal conditioning submodule provides each pressure sensing unit with independent precision amplification and filtering circuitry to adapt to its output signal range and improve the signal-to-noise ratio. The ADC analog-to-digital conversion submodule is used for the synchronous acquisition of pressure data from all measuring points. The sampling frequency is configurable to meet the requirements of dynamic pressure measurement. The power management submodule provides a stable and clean power supply to the pressure sensing unit and the circuitry within the acquisition and control module. It supports external DC power input and features a wide voltage input range, reverse connection protection, and overcurrent and overvoltage protection. The data storage submodule is a solid-state storage unit used for uninterrupted recording of flight data throughout the entire flight; The clock synchronization submodule uses a high-precision temperature-compensated clock and supports the input of external time synchronization signals such as IRIG-B and PPS to achieve time synchronization between multiple systems. The status indicator submodule uses LED indicators to display the system's working status in real time, such as power supply, data acquisition, storage, and fault. The data interface is a high-speed data download interface (such as USB 3.0, Gigabit Ethernet), and RS422, UDP and other online transmission interfaces are reserved.

[0015] The time synchronization accuracy of data collected by all pressure sensing units distributed at different locations on the aircraft components is no greater than 10 microseconds. The FPGA processor submodule of the acquisition control module generates a high-precision, high-stability synchronization clock signal and periodic hardware trigger pulses, which are then distributed to each pressure sensing unit. The FPGA core circuit of the pressure sensing unit is equipped with a highly stable, phase-lockable clock source. When the edge of the hardware trigger pulse is detected, it triggers the ADC analog-to-digital converter circuit to start sampling. After sampling, the data is transmitted back via a high-speed data link. The pressure sensing units communicate with the FPGA processor submodule and the ADC analog-to-digital converter submodule within the acquisition control module to construct a reliable and deterministic hardware parsing and synchronization trigger pipeline to achieve time synchronization.

[0016] The pressure sensing unit has a test range of 0 to 15 PSI, where PSI is the pressure unit and A represents absolute pressure measurement; the test temperature range is -40℃ to 85℃.

[0017] The beneficial effects of this invention are at least as follows: Miniaturization and flexibility: The pressure measuring strip is thin and flexible, adaptable to complex curved surfaces, and has minimal installation interference; the data acquisition module is compact and lightweight; High precision and high reliability: High-grade sensors and components are selected, and the data is accurate and reliable through precise calibration and rigorous environmental testing. Synchronous multi-channel acquisition: A single pressure gauge can achieve high-speed synchronous sampling of multiple measuring points, accurately capturing dynamic pressure distribution; Strong environmental adaptability: The design meets the temperature, vibration, shock, and electromagnetic compatibility requirements of airborne environments; Ease of use and scalability: Modular design, flexible configuration, convenient installation, and support for customization of measurement point scale and arrangement. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the pressure measurement device installed and in flight.

[0020] Figure 2 This is a schematic diagram of the hardware architecture of the pressure measuring device. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, 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 those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0023] See Figure 1 and Figure 2 A high-synchronous pressure measurement device for flight testing includes: a pressure sensing unit, a fairing, and a data acquisition and control module; The fairing is made of a composite encapsulation material in an initial semi-fluid state. This material can fully fill and wrap multiple pressure sensing units and connecting cables on the same measurement profile like a liquid. After shaping, it forms a pressure measurement strip that can be directly pasted onto the outer surface of the aircraft. The fairing uses this composite encapsulation material to ensure that it can conform to the curvature changes of complex three-dimensional curved surfaces such as the leading edge and root of the wing. The fairing and multiple pressure sensing units form a single unit. The pressure sensing units have a flat surface that conforms to the outer surface of the aircraft component, minimizing the impact on the original aerodynamic shape of the aircraft component. The fairing is attached to the outer surface of the aircraft, and the multiple pressure sensing units and connecting cables are embedded within the fairing. In one embodiment, the overall thickness of the device after adding the fairing does not exceed 2mm. Existing pressure measurement band technology suffers from excessive thickness; this invention addresses this by providing a thinner measuring device. This invention achieves conformal fitting of the pressure measuring device to the outer surface of the aircraft component, reducing the overall thickness while further increasing the density of measuring points to meet the requirements of advanced aircraft flight testing for precise multi-point synchronous pressure measurement.

[0024] Multiple pressure sensing units detect the pressure at their location in real time, convert it into analog electrical signals, and then transmit it to the acquisition and control module; After the acquisition and control module conditions and digitizes the analog electrical signal, it stores it together with the timestamp information in the built-in memory.

[0025] The embodiments of the present invention adopt an architecture design of "distributed sensing and centralized acquisition and control". The pressure sensing unit collects the aerodynamic pressure at various points on the wing surface during flight and transmits the collection results to the acquisition and control module in the cabin in real time.

[0026] In one embodiment, pressure sensing units are deployed in a high-density array on the upper and lower surfaces of the wing and form a pressure measurement zone through a fairing. The spacing between the measurement points can be flexibly customized according to the aerodynamic measurement requirements. For close distribution requirements, the minimum center distance can reach 40 mm; for distributed measurement, the spacing can be arranged in the range of tens to hundreds of millimeters by extending the wires.

[0027] The fairing protects the delicate electronic components inside the pressure sensing unit from environmental damage while minimizing their disturbance to the original airfoil flow field. The pressure measurement strip, composed of multiple pressure sensing units and the fairing, has a substrate made of a special flexible composite material. This ensures that it can conform to the curvature changes of complex three-dimensional surfaces such as the leading edge and root of the wing, allowing it to be adhered to the outer surface of aircraft components and ensuring complete adhesion without affecting the original aerodynamic shape of the component.

[0028] The fairing utilizes flexible packaging technology to encapsulate and integrate multiple pressure sensing units into a single pressure measurement strip via connecting cables, enabling multi-point measurement and reserving interfaces for connecting the acquisition and control module. The pressure measurement strip, composed of the fairing and pressure sensing units, achieves a balance of high resolution, high stability, low power consumption, and scalability within a bending range of less than 25mm.

[0029] like Figure 2 As shown, the overall width of a single pressure testing strip is no greater than 40mm, the thickness is no greater than 2mm, the length of a single testing point is no greater than 40mm, and the spacing between testing points can be customized, with a minimum spacing of 40mm. One end of each pressure testing strip has a conversion / connection interface to allow for the connection of adapter cables or the series connection of multiple pressure testing strips, ensuring normal data transmission.

[0030] In one embodiment, the size of each pressure sensing unit in the device is no greater than 40*40mm. In this invention, the pressure sensing unit implements functions such as sensor front-end, analog conditioning, analog-to-digital conversion, data bus, and power management.

[0031] Specifically, the pressure sensing unit may include a power supply step-down and voltage regulation circuit, a pressure-sensitive chip, an FPGA core circuit, an RS485 interface circuit, an ADC analog-to-digital conversion circuit, and a temperature sensing circuit. Among them, the power supply buck regulator circuit converts the higher input voltage into a lower and more stable output voltage; The pressure-sensitive chip senses the pressure information at the location of the measuring point in real time. The FPGA core circuit is used for timing control, data packaging, timestamp insertion, and interface communication. It enables synchronous sampling of the ADC analog-to-digital converters in multiple pressure sensing units; enables the ADC peripheral clock, sets the frequency division coefficient to determine the ADC operating frequency, sets the resolution, sets the sampling time, sets the data storage alignment, sets the operating voltage range, calibrates the local oscillator, starts the ADC self-calibration program to eliminate offset errors, configures the TIM trigger output (TRGO) as a synchronization signal for other peripherals, and enables the MAC / PTP hardware timestamp to record the precise time of key events. The FPGA core circuit is responsible for precise timing control, data packaging, timestamp insertion, and interface communication, ensuring synchronous sampling of the ADCs (analog-to-digital converters) of all sensor channels in the pressure measurement matrix, with synchronization errors controllable at the nanosecond level.

[0032] The RS485 interface circuit employs a differential signal transmission mechanism, effectively suppressing common-mode noise. It uses half-duplex communication to perform timing scheduling and high-speed data polling of pressure information from all measuring points along an entire pressure measurement zone. This ensures determinism in command issuance and data upload while meeting the system's real-time requirements for high-speed, periodic acquisition of hundreds of channels of data. The high-speed RS485 bus enables highly reliable, long-distance, multi-node data acquisition and real-time response.

[0033] An ADC (Analog-to-Digital Converter) circuit is used for the digital processing of electrical signals; The temperature sensing circuit monitors the ambient temperature of the pressure-sensitive chip, providing input for the temperature drift compensation algorithm.

[0034] In one embodiment, a waterproof barrier is provided on the outer surface of the pressure-sensitive chip. The waterproof barrier is a nanoscale organic molecular film obtained by vacuum deposition technology. The nanoscale organic molecular film constructs a "nanoscale, ultrathin, and high-density" barrier on the surface of the pressure-sensitive chip of the pressure sensing unit, which can achieve water molecule blocking and ensure no attenuation of the pressure signal.

[0035] In one embodiment, during the fabrication of the fairing, composite encapsulation material is first poured into the mold containing the pressure sensing units, ensuring the material fully fills and encapsulates all pressure sensing units and cables. A solid composite material shell is then formed through a curing reaction, and finally, the mold is removed. The composite encapsulation material pouring achieves a seamless fit, and the subsequent curing reaction forms a robust, lightweight, and smooth-surfaced solid composite material shell, thus providing an integral protective shield with excellent environmental resistance while meeting ultra-thin constraints.

[0036] Furthermore, the fairing surface is coated with a protective coating that is wear-resistant, waterproof, and oil-resistant; the internal pressure sensing unit and connecting cables are protected by the protective coating, together resisting particle erosion, liquid splashing, and accidental impacts during flight testing.

[0037] The fairing shell is coated with conductive paint to form a conductive shell, which is connected to the ground wire of the pressure sensing unit to form a shielding layer. The conductive shell of the fairing is connected to the ground wire of the cabin through a low impedance path to form a continuous shield, which effectively suppresses external radio frequency interference and prevents its own signal radiation, ensuring full compatibility with the electromagnetic environment on the aircraft.

[0038] In one embodiment, the acquisition and control module is connected to the pressure measuring belt via a data line and a power line, performs command control on the pressure measuring belt and receives and stores data, and simultaneously receives RS232 timing signals for synchronization between the pressure sensing unit and the airborne time.

[0039] Specifically, the acquisition and control module includes an FPGA processor submodule, a signal conditioning submodule, an ADC analog-to-digital conversion submodule, a power supply management submodule, a data storage submodule, a clock synchronization submodule, a status indication submodule, and a data interface. The FPGA processor submodule is used for the control, timing management, and communication coordination of the measuring device. The FPGA processor submodule sends configuration instructions for sampling rate, working mode, and filter parameters to the pressure sensing units in the pressure measurement zone, and sends a high-precision global synchronization clock signal to ensure that the sampling time of all pressure sensing units is aligned. The signal conditioning submodule provides each pressure sensing unit with independent precision amplification and filtering circuitry to adapt to its output signal range and improve the signal-to-noise ratio. The ADC analog-to-digital conversion submodule is used for the synchronous acquisition of pressure data from all measuring points. The sampling frequency is configurable to meet the requirements of dynamic pressure measurement. The power management submodule provides a stable and clean power supply to the pressure sensing unit and the circuits within the acquisition and control module. It supports external DC power input (such as onboard 28V) and features a wide voltage input range, reverse connection protection, and overcurrent and overvoltage protection. The data storage submodule uses high-capacity, high-speed read / write, and vibration-resistant solid-state storage units to ensure uninterrupted recording of flight data throughout the entire flight. The clock synchronization submodule uses a high-precision temperature-compensated clock and supports the input of external time synchronization signals such as IRIG-B and PPS to achieve time synchronization between multiple systems. The status indicator submodule uses LED indicators to display the system's working status in real time (such as power supply, data acquisition, storage, and fault). The data interface is a high-speed data download interface (such as USB 3.0, Gigabit Ethernet), and RS422, UDP and other online transmission interfaces can be reserved as needed.

[0040] In one embodiment, the time synchronization accuracy of the data collected by all pressure sensing units distributed at different locations on the aircraft component is no greater than 10 microseconds. The pressure sensing units communicate with the FPGA processor submodule and ADC analog-to-digital conversion submodule within the acquisition and control module to construct a reliable and deterministic hardware parsing and synchronization triggering pipeline to achieve time synchronization. The FPGA processor submodule of the acquisition and control module generates a high-precision, high-stability synchronous clock signal and periodic hardware trigger pulses, which are then distributed to each pressure sensing unit. The FPGA core circuit of the pressure sensing unit is equipped with a high-stability, phase-lockable clock source. When the edge of the hardware trigger pulse is detected, the ADC analog-to-digital converter circuit is triggered to start sampling. After sampling is completed, the data is transmitted back through a high-speed data link.

[0041] In one embodiment, the test range of the pressure sensing unit is 0 to 15 PSI; PSI is the pressure unit, and A represents absolute pressure measurement; the test temperature range is -40°C to 85°C.

Claims

1. A high-synchronous pressure measurement device for flight testing, characterized in that, include: Multiple pressure sensing units, fairing, and data acquisition and control module; The fairing is attached to the outer surface of the aircraft, and multiple pressure sensing units and connecting cables are embedded in the fairing. The fairing and multiple pressure sensing units form a whole, and the surface of the pressure sensing units is flat and fits the outer surface of the aircraft. The pressure sensing unit detects the pressure at its location in real time and converts it into an analog electrical signal, which is then transmitted to the acquisition and control module. After the acquisition and control module conditions and digitizes the analog electrical signal, it stores it together with the timestamp information in the built-in memory.

2. The apparatus according to claim 1, characterized in that, The fairing is made of a composite encapsulation material in an initial semi-flow state. This material fully fills and wraps multiple pressure sensing units and connecting cables on the same measurement profile. After shaping, it forms a single pressure measurement strip that can be directly attached to the outer surface of the aircraft.

3. The apparatus according to claim 1, characterized in that, Each pressure sensing unit is no larger than 40*40mm in size. The pressure sensing unit includes a power supply step-down and voltage regulation circuit, a pressure-sensitive chip, an FPGA core circuit, an RS485 interface circuit, an ADC analog-to-digital conversion circuit, and a temperature sensing circuit. Among them, the power supply buck regulator circuit converts the high input voltage into a stable low output voltage; The pressure-sensitive chip senses the pressure information at the location of the measuring point in real time. The FPGA core circuit is used for timing control, data packaging, timestamp insertion, and interface communication. It enables synchronous sampling of the ADC analog-to-digital conversion in multiple pressure sensing units; enables the ADC peripheral clock; sets the frequency division coefficient to determine the ADC operating frequency; sets the resolution; sets the sampling time; sets the data storage alignment; sets the operating voltage range; calibrates the local oscillator; starts the ADC self-calibration program to eliminate offset errors; configures the TIM trigger output as a synchronization signal for other peripherals; and enables the MAC / PTP hardware timestamp to record the precise time of key events. The RS485 interface circuit adopts a differential signal transmission mechanism and uses half-duplex communication to perform timing scheduling and high-speed data polling of pressure information from all measuring points along an entire pressure measuring band. An ADC (Analog-to-Digital Converter) circuit is used for the digital processing of electrical signals; The temperature sensing circuit monitors the ambient temperature of the pressure-sensitive chip, providing input for the temperature drift compensation algorithm.

4. The apparatus according to claim 3, characterized in that, The outer surface of the pressure-sensitive chip is provided with a waterproof barrier, which is a nanoscale organic molecular film obtained by vacuum deposition technology.

5. The apparatus according to claim 1, characterized in that, The overall thickness of the device does not exceed 2mm.

6. The apparatus according to claim 2, characterized in that, When preparing the fairing, the composite encapsulation material is first poured into the mold containing the pressure sensing unit, so that the composite encapsulation material fully fills and wraps all the pressure sensing units and cables. Then, a solid composite material shell is formed through a curing reaction. Finally, the mold is removed.

7. The high-synchronization pressure measuring device according to claim 1, characterized in that, The fairing surface is coated with a protective coating that is wear-resistant, waterproof, and oil-resistant; The fairing outer shell is coated with conductive paint to form a conductive shell, which is connected to the ground wire of the pressure sensing unit to form a shielding layer; the conductive shell of the fairing is connected to the ground wire of the cabin through a low impedance path to form a continuous shield.

8. The apparatus according to claim 1, characterized in that, The acquisition and control module includes an FPGA processor submodule, a signal conditioning submodule, an ADC analog-to-digital conversion submodule, a power supply management submodule, a data storage submodule, a clock synchronization submodule, a status indication submodule, and a data interface. The FPGA processor submodule is used for device control, timing management, and communication coordination. The FPGA processor submodule sends configuration instructions for sampling rate, working mode, and filter parameters to the pressure sensing units in the pressure measurement zone, and sends a high-precision global synchronization clock signal to ensure that the sampling time of all pressure sensing units is aligned. The signal conditioning submodule provides each pressure sensing unit with independent precision amplification and filtering circuitry to adapt to its output signal range; The ADC analog-to-digital converter submodule is used for the synchronous acquisition of pressure data from all measuring points; The power management submodule provides a stable and clean power supply to the pressure sensing unit and the circuitry within the acquisition and control module. It supports external DC power input and features a wide voltage input range, reverse connection protection, and overcurrent and overvoltage protection. The data storage submodule is a solid-state storage unit used for uninterrupted recording of flight data throughout the entire flight; The clock synchronization submodule uses a high-precision temperature-compensated clock and supports external time synchronization signal input to achieve time synchronization between multiple systems. The status indicator submodule uses LED indicators to display the system's working status in real time; The data interface is a high-speed data download interface, and an online transmission interface is reserved.

9. The apparatus according to claim 8, characterized in that, The time synchronization accuracy of the data collected by all pressure sensing units distributed at different locations on the aircraft components is no greater than 10 microseconds; the FPGA processor submodule of the acquisition control module generates a high-precision, high-stability synchronization clock signal and periodic hardware trigger pulses, and distributes them to each pressure sensing unit; the FPGA core circuit of the pressure sensing unit is equipped with a highly stable, phase-lockable clock source, which triggers the ADC analog-to-digital conversion circuit to start sampling when the edge of the hardware trigger pulse is detected; after sampling is completed, the data is transmitted back through a high-speed data link.

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