Airborne dual-redundancy triaxial angular acceleration measurement system

Abstract

The invention provides an airborne dual-redundancy triaxial angular acceleration measurement system. The measurement system mainly comprises a case assembly, an angular acceleration measurement unit, a signal processing circuit and a power conversion circuit. The case assembly provides an installation reference for the whole measurement system and plays a sealing role, the angular acceleration measurement unit mainly realizes measurement of an angular acceleration signal, and the signal processing circuit mainly realizes receiving, processing and sending of the angular acceleration signal. The power conversion circuit realizes power supply interaction between an internal circuit and an external power supply. The dual-redundancy triaxial angular acceleration measuring system provided by the invention is high in precision, strong in real-time performance, high in integration level, strong in reliability, high in stability and capable of directly measuring an angular acceleration signal of an airplane.

Description

Technical Field

[0001] This invention relates to the field of angular acceleration measurement, and more specifically to an airborne dual-redundant triaxial angular acceleration measurement system. Background Technology

[0002] Angular acceleration, as a crucial physical quantity describing changes in aircraft motion, provides faster dynamic response capabilities and improves control accuracy in areas such as maneuver control, attitude stabilization, and guidance precision. An angular acceleration measurement system is an inertial system that directly measures the angular acceleration of the carrier. It features high precision, good real-time performance, and strong reliability, making it suitable for aircraft control systems operating under large attitude angles, high maneuverability, and high steady-state motion.

[0003] Furthermore, with the ever-increasing demands for high reliability, high precision, and high integration in modern aircraft systems, higher standards are being placed on the fault tolerance, fault detection capabilities, and data reliability of angular acceleration measurement systems. Especially when facing harsh conditions such as complex electromagnetic environments, high overloads, and mechanical vibrations, system stability and data reliability are challenged. There is an urgent need for a three-axis angular acceleration measurement system with redundant acquisition and independent data processing capabilities to improve the system's reliability, stability, and fault tolerance in complex flight environments, and to meet the high requirements of modern aircraft for motion sensing and measurement. Summary of the Invention

[0004] The purpose of this invention is to propose an airborne dual-redundant triaxial angular acceleration measurement system that is highly accurate, has strong real-time performance, high integration, high reliability, and high stability, and can directly measure aircraft angular acceleration signals.

[0005] Technical solution: The present invention provides an airborne dual-redundant triaxial angular acceleration measurement system, comprising: a chassis assembly 1, two signal processing circuits 2, two power conversion circuits 3, and an angular acceleration measurement unit 4; The angular acceleration measurement unit 4, two signal processing circuits 2 and two power conversion circuits 3 are all encapsulated in the chassis assembly 1; The angular acceleration measurement unit 4 includes: a mounting platform 5, multiple vibration dampers 6, and six angular accelerometers 7; The angular accelerometer 7 is installed inside the mounting platform 5; The vibration damper 6 is installed on the outside of the mounting platform 5 and fixed to the side wall of the chassis assembly 1 with screws; The center of mass of the angular acceleration measuring unit 4 overlaps with the centroid of the multiple dampers 6; Each angular accelerometer 7 is used to sense angular acceleration in a single direction, so that the angular acceleration measurement unit 4 is dual-redundant in sensing the angular acceleration information of the aircraft motion, and the information is output after being acquired and processed by two signal processing circuits 2. The power conversion circuit 3 preprocesses the primary power supply and supplies power to the signal processing circuit 2 and the corresponding redundant angular accelerometer 7. The signal processing circuit 2 then converts the secondary power supply to power the processor chip.

[0006] Optionally, each angular accelerometer 7 is a flexible pendulum angular accelerometer.

[0007] Optionally, the number of vibration dampers 6 is 4, symmetrically distributed on both sides of the mounting platform 5.

[0008] Optionally, the chassis assembly 1 is machined and has external heat dissipation and weight reduction designs.

[0009] Optionally, the signal processing circuit 2 includes the following functions: data compensation processing, analog-to-digital conversion, signal conditioning, RS422 transceiver, secondary power supply conversion, parameter storage, clock management, and self-testing.

[0010] Optionally, the power conversion circuit 3 includes the following functions: lightning protection, reverse connection protection, primary power filtering, surge suppression, primary power conversion, and top power supply.

[0011] Optionally, the signal processing circuit 2 runs angular acceleration information processing software, which has four working modes: power-on / initialization, normal operation, pre-flight self-test, and online loading. When powered on, the angular acceleration information processing software automatically enters the power-on initialization mode and completes component initialization, processor reset, and minimum unit power-on self-test during the startup process. After completion, it immediately starts serial port transmission and initiates periodic self-test; after power-on / initialization is completed, it enters normal working mode. In normal operating mode, if the angular acceleration information processing software receives the PBIT command sent by the host computer, it enters the pre-flight self-test mode and returns to normal operating mode after the self-test is completed; if the angular acceleration information processing software receives the online loading command sent by the host computer, it enters the online loading mode and returns to normal operating mode when it receives the loading end command.

[0012] Optionally, the rigid body motion frequency of the angular acceleration measurement unit 4 is far from the operating resonant frequency of the angular accelerometer 7, while the high-order resonant frequency of the mounting platform 5 avoids the environmental vibration frequency band transmitted from the carrier aircraft to the chassis assembly 1.

[0013] The beneficial effects of this invention: This invention proposes an airborne dual-redundant triaxial angular acceleration measurement system, which features high precision, strong real-time performance, high integration, high reliability, and high stability. The main parameters are shown in Table 1. It has significant advantages over current domestic related products and can achieve high-precision, high-real-time, and high-reliability direct measurement and analysis of angular acceleration, and has broad application prospects.

[0014] Table 1. Main parameters of the angular acceleration measurement system Attached Figure Description

[0015] 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.

[0016] Figure 1 This is a schematic diagram of the overall shape of the present invention; Figure 2 This is a schematic diagram of the angular acceleration measurement unit of the present invention; Figure 3 This is a schematic diagram illustrating the working principle of the present invention; Among them, 1-chassis assembly, 2-signal processing circuit, 3-power conversion circuit, 4-angular acceleration measurement unit, 5-mounting platform, 6-vibration damper, and 7-angular accelerometer. Detailed Implementation

[0017] 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.

[0018] 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.

[0019] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0020] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0021] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0023] Specifically, such as Figure 1-3 As shown, this invention provides an airborne dual-redundant triaxial angular acceleration measurement system, comprising: a chassis assembly, an angular acceleration measurement unit, a signal processing circuit, and a power conversion circuit; the system uses the angular acceleration measurement unit to sense the angular acceleration information of the aircraft motion, and the signal processing circuit collects and processes the information to achieve high-precision, real-time output; the power conversion circuit preprocesses the primary power supply and transmits a safe and stable power supply to the signal processing circuit, and the signal processing circuit converts the secondary power supply to power the processor; the angular acceleration measurement unit, the signal processing circuit, and the power conversion circuit are respectively fixed inside the chassis assembly with screws.

[0024] The angular acceleration measurement unit is the core component of the angular acceleration measurement system, which includes six angular accelerometers, four vibration dampers, and a mounting platform. The angular accelerometers and vibration dampers are mounted on the mounting platform with screws. Furthermore, the angular accelerometer is a flexible pendulum angular accelerometer, which works based on Newton's laws of motion. It directly measures the angular acceleration signal of the carrier by sensing the inertial force acting on the carrier, and can be sensitive to angular acceleration in one direction. Furthermore, the shock absorber is made of nitrile rubber material, which has good vibration reduction and buffering performance, while also taking into account wear resistance and aging resistance. The shock absorber can effectively filter out high-frequency, high-energy vibrations on the aircraft, enabling the angular acceleration measurement unit to accurately measure the low-frequency signals (<20Hz) of aircraft motion. Furthermore, the rigid body motion frequency of the angular acceleration measurement unit is far away from the working resonant frequency of the angular accelerometer, while the high-order resonant frequency of the mounting platform avoids the environmental vibration frequency band transmitted from the carrier aircraft to the chassis components, thereby avoiding signal distortion during the transmission of the angular acceleration signal and achieving high reliability output of the angular acceleration signal. Furthermore, the center of mass of the angular acceleration measurement unit should coincide with the centroid of the vibration damper in order to reduce the energy coupling of linear-angular motion during vibration and achieve precise sensitivity of the angular acceleration measurement unit to the body motion. Furthermore, the signal processing circuit is housed within the chassis assembly, connected to the angular acceleration measurement unit and the power conversion circuit via connectors or cables. The signal processing circuit includes data compensation processing, analog-to-digital conversion, signal conditioning, RS422 transceiver, secondary power conversion, parameter storage, clock management, and self-testing functions. The signal processing circuit acquires and receives analog signals from the angular accelerometer, performs high-speed computation to complete signal conditioning, digital conversion, and algorithm processing, and then transmits the processed digital signal through the RS422 interface. Simultaneously, it converts the secondary power generated by the power conversion circuit to provide power to the processor. To ensure high precision in signal conversion, processing, and transmission, appropriate components must be carefully selected. Furthermore, the chassis components are machined from a single piece of aluminum alloy, possessing good strength, rigidity, and excellent thermal and electrical conductivity, while maintaining a compact size. The outer surface is designed with ribbed heat dissipation, which also reduces unnecessary weight, achieving a lightweight design. The bottom and outer sides of the four front and rear mounting feet of the chassis can be used as positioning references. Electromagnetic shielding pads have been added to all openings in the chassis, effectively preventing external electromagnetic interference to the system and electromagnetic leakage within the chassis.

[0025] Furthermore, the power conversion circuit is equipped with functions such as lightning protection, reverse connection protection, primary power filtering, surge suppression, primary power conversion, and top power supply. It is mainly used to convert the primary power supplied by the aircraft into the secondary power required by the system, while also playing a role in power protection, and can ensure the high reliability of the angular acceleration measurement system. Furthermore, the measurement system adopts a dual-redundancy design. Each redundancy is equipped with a signal processing circuit, a power conversion circuit, and three angular accelerometers. The power supply circuits and data processing channels of each redundancy are independent of each other. If the angular accelerometer of one redundancy is damaged or there is a hardware malfunction, it will not affect the angular acceleration signal output of the other redundancy. Each redundancy contains three angular accelerometers, which are sensitive to the angular acceleration motion of the aircraft in the pitch, roll, and yaw directions, respectively. Furthermore, the angular acceleration information processing software has four operating modes: power-on / initialization, normal operation, pre-flight self-test, and online loading. Under normal power supply, the software automatically enters the power-on initialization mode, completing component initialization, processor reset, and minimum unit power-on self-test during startup. Upon completion, it immediately initiates serial port transmission and periodic self-tests. After power-on / initialization, it enters normal mode. The angular acceleration measurement system enters the pre-flight self-test mode upon receiving the PBIT command from the host computer. These self-test designs automatically detect and diagnose the status of the angular acceleration measurement system, ensuring high-reliability operation. The angular acceleration measurement system enters the online loading mode upon receiving the online loading command from the host computer, enabling portable software upgrades. The airborne dual-redundant triaxial angular acceleration measurement system of the present invention employs a multi-stage filtering and processing method to remove noise signals. After the original angular acceleration signal is sent to the angular acceleration measurement unit through a mechanical structure, the vibration damper first filters out high-frequency useless signals. The angular accelerometer detects the filtered signal and transmits it to the signal processing circuit. In the signal processing circuit, the signal undergoes low-pass filtering through an RC filter module. The signal is then further filtered by a low-pass digital filter provided by software, ultimately outputting the low-frequency useful signal required by the upper-level system with high accuracy. Each filtering stage requires precise design to ensure data accuracy and real-time performance (typically with a delay of no more than 30ms).

[0026] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. An airborne dual-redundant triaxial angular acceleration measurement system, characterized in that, include: The chassis assembly (1), two signal processing circuits (2), two power conversion circuits (3), and angular acceleration measurement unit (4); The angular acceleration measurement unit (4), two signal processing circuits (2) and two power conversion circuits (3) are encapsulated in the chassis assembly (1); The angular acceleration measurement unit (4) includes: a mounting platform (5), multiple vibration dampers (6), and 6 angular accelerometers (7); An angular accelerometer (7) is installed inside the mounting platform (5); The vibration damper (6) is installed on the outside of the mounting platform (5) and fixed to the side wall of the chassis assembly (1) with screws; The centroid of the angular acceleration measuring unit (4) overlaps with the centroid of the multiple dampers (6); Each angular accelerometer (7) is used to sense angular acceleration in a single direction, so that the angular acceleration measurement unit (4) is dual-redundant in sensing the angular acceleration information of the aircraft motion, and the output is realized through the acquisition and processing of two signal processing circuits (2); The power conversion circuit (3) performs preprocessing of the primary power supply and supplies power to the signal processing circuit (2) and the corresponding redundant angular accelerometer (7). The signal processing circuit (2) converts the secondary power supply to power the processor chip.

2. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, Each angular accelerometer (7) is a flexible pendulum angular accelerometer.

3. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The number of vibration dampers (6) is 4, which are symmetrically distributed on both sides of the mounting platform (5).

4. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The chassis assembly (1) is machined and has external heat dissipation and weight reduction design.

5. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The signal processing circuit (2) includes the following functions: data compensation processing, analog-to-digital conversion, signal conditioning, RS422 transceiver, secondary power supply conversion, parameter storage, clock management and self-testing.

6. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The power conversion circuit (3) includes the following functions: lightning protection, reverse connection protection, primary power filtering, surge suppression, primary power conversion and top power.

7. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The signal processing circuit (2) runs angular acceleration information processing software and has four working modes: power-on / initialization, normal operation, pre-flight self-test, and online loading. When powered on, the angular acceleration information processing software automatically enters the power-on initialization mode and completes component initialization, processor reset, and minimum unit power-on self-test during the startup process. After completion, it immediately starts serial port transmission and initiates periodic self-test; after power-on / initialization is completed, it enters normal working mode. In normal operating mode, if the angular acceleration information processing software receives the PBIT command sent by the host computer, it enters the pre-flight self-test mode and returns to normal operating mode after the self-test is completed; if the angular acceleration information processing software receives the online loading command sent by the host computer, it enters the online loading mode and returns to normal operating mode when it receives the loading end command.

8. The airborne dual-redundant triaxial angular acceleration measurement system according to claim 1, characterized in that, The rigid body motion frequency of the angular acceleration measurement unit (4) is far away from the working resonant frequency of the angular accelerometer (7), while the high-order resonant frequency of the mounting platform (5) avoids the environmental vibration frequency band transmitted from the carrier to the chassis assembly (1).

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