Aircraft heading attitude detection system and detection method

Abstract

The invention relates to the technical field of aircraft attitude and heading detection, and discloses an aircraft attitude and heading detection system which comprises an analog signal generation module, an analog signal processing module, a signal A / D module, an embedded computer and a touch display module. When the heading attitude is detected, firstly, the heading attitude of the airplane is sensed through the analog signal generation module, and then two paths of heading attitude signals (rotary transformer signals, referred to as rotary transformer signals for short) of pitching and inclination are output. And then hardware conditioning (filtering and amplitude conditioning) is carried out through an analog signal processing module, and then acquisition is carried out through a rotary transformer signal A / D module with the precision of 14 bits (the resolution can reach 0.022 degrees). Collected resolver signals are firstly subjected to preprocessing (digital filtering and denoising) through the embedded computer and finally sent to a program interface to be displayed by the touch display module. A software and hardware integrated design is adopted, direct AD sampling is carried out on a rotary transformer signal, and data is completely electronized. The method has the advantages of high precision, accurate numerical value and sensitive response.

Description

Technical Field

[0001] This application relates to the field of aircraft attitude detection technology, and in particular to an aircraft attitude detection system and detection method. Background Technology

[0002] During flight, aircraft require precise information about their attitude, including pitch, roll, and yaw angles, to enable pilots to accurately assess the aircraft's flight status, make correct flight decisions, and ensure flight safety. This attitude information is also a crucial input to the automatic flight control system, used for attitude control and navigation positioning. Aircraft attitude and its indications are as follows: Figure 1 As shown.

[0003] Early attitude control systems consisted of two separate parts: a mechanical sensing component (gyroscope) and a mechanical indicating component (indicator). Later, these evolved into integrated attitude control systems (altitude instruments), combining the gyroscope and indicator within a single housing. In these separate systems, the sensing and indicating components were directly connected, and attitude signals were transmitted via a synchro. The principle of early attitude control systems was as follows: Figure 2 As shown.

[0004] Mechanical gyroscopes and accelerometers have low accuracy and are susceptible to interference. With the development of electronic technology, micromechanical technology and optical technology, new types of sensors with higher accuracy and better stability have emerged, such as fiber optic gyroscopes, laser gyroscopes and microelectromechanical systems (MEMS) sensors, which can be applied to the field of aircraft attitude detection technology to replace traditional mechanical pointer-type attitude systems.

[0005] The information disclosed in the technical section is only intended to enhance the understanding of the background of this application and may therefore include information that does not constitute prior art known to a person skilled in the art. Summary of the Invention

[0006] To provide a basic understanding of some aspects of the disclosed technical solutions, a brief summary is given below. This summary is not a general commentary, nor is it intended to identify key / important components or describe the scope of protection of these technical solutions, but rather serves as an introduction to the detailed explanations that follow.

[0007] This disclosure provides an aircraft attitude detection system and method to solve the problems mentioned in the background section.

[0008] In some technical solutions, the aircraft attitude detection system includes: an analog signal generation module configured to sense the aircraft's attitude and output the aircraft's attitude signal; an analog signal processing module configured to filter and amplitude-condition the attitude signal; a signal A / D module configured to perform A / D conversion on the conditioned attitude signal to convert it into a digital signal; an embedded computer configured to filter and denoise the converted digital signal; and a touch display module configured to display the processed digital signal, used for human-computer interaction, displaying the program interface, and displaying simulated animations.

[0009] Optionally, the analog signal generation module includes: a first rotary transformer, installed on the aircraft; a second rotary transformer, installed at the detection end of the first rotary transformer, the axis of the detection end of the second rotary transformer being perpendicular to the axis of the detection end of the first rotary transformer; a third rotary transformer, installed at the detection end of the second rotary transformer, the axis of the detection end of the third rotary transformer being perpendicular to the axes of the detection ends of the first and second rotary transformers; and a pendulum, installed at the detection end of the third rotary transformer; wherein the attitude signal includes the resolver signal generated by the first rotary transformer, the second rotary transformer, and the third rotary transformer.

[0010] Optionally, the signal A / D module includes: a reference transformer connected to the output of the analog signal processing module; a sine multiplier connected to the output of the reference transformer; a cosine multiplier connected to the output of the reference transformer; a quadrant selection switch connected to the outputs of the sine multiplier and the cosine multiplier; a power amplifier connected to the output of the quadrant selection switch; and an output transformer connected to the output of the power amplifier; wherein the embedded computer is connected to the output of the output transformer.

[0011] Optionally, the signal A / D module is a 14-bit digital converter, and further includes: a level conversion chip connected to the 14-bit digital input terminal of the signal A / D module; and a timer connected to the 14 channels of the level conversion chip.

[0012] Optionally, the embedded computer includes: a GUI module configured to handle human-computer interaction, display a program interface, and receive user operations; a detection module bidirectionally connected to the GUI module, configured to send control commands and data, and receive measured data; a display module bidirectionally connected to the GUI module, configured to display the processed measured data; an I / O module connected to the detection module, configured to input measured data and output control commands; a data buffer and processing module connected between the I / O module, the detection module, and the display module, configured to read, buffer, and process measured data; a metrology and calibration module bidirectionally connected to the GUI module, configured to read and write calibration parameters to achieve whole-machine metrology and calibration; and a system setting module bidirectionally connected to the GUI module, configured to read and write configuration files to set system parameters. The I / O module is connected to the signal A / D module, and the display module is connected to the touch display module.

[0013] Optionally, the reception and processing of the measured data adopts a "producer-consumer" model, with separate lines for inbound and outbound data transmission.

[0014] Optionally, the human-computer interaction functions and control logic are implemented using the C++ language.

[0015] Optionally, the program interface adopts the QML+Widget approach.

[0016] Optionally, the simulated animation interface image is in SVG vector graphic format.

[0017] In some technical solutions, the aircraft attitude detection method includes: acquiring the aircraft's attitude signal based on the aircraft's flight attitude; filtering and amplitude conditioning the acquired attitude signal; determining whether the A / D acquisition is idle, and if not, re-determining; if so, performing A / D conversion on the conditioned attitude signal to convert it into a digital signal; determining whether the conversion is complete, and if not, re-determining; if so, reading and calculating; and displaying the calculated data.

[0018] The aircraft attitude detection system provided in this disclosure can achieve the following technical effects: This disclosure provides an aircraft attitude detection system, comprising an analog signal generation module, an analog signal processing module, a signal A / D module, an embedded computer, and a touch display module. The analog signal generation module is configured to sense the aircraft's attitude and output the aircraft's attitude signal. The analog signal processing module, connected to the analog signal generation module, is configured to filter and amplitude-condition the attitude signal. The signal A / D module, connected to the analog signal processing module, is configured to perform A / D conversion on the conditioned attitude signal to convert it into a digital signal. The embedded computer, connected to the signal A / D module, is configured to filter and denoise the converted digital signal. The touch display module, connected to the embedded computer, is configured to display the processed digital signal, and is used for human-computer interaction, displaying the program interface, and displaying simulated animations.

[0019] During attitude detection, the aircraft's attitude is first sensed by an analog signal generation module, which then outputs pitch and roll signals (resolver signals). These signals are then hardware-conditioned (filtered, amplitude-regulated) by an analog signal processing module, and acquired by a 14-bit (0.022-degree resolution) resolver signal A / D module. The acquired resolver signals are preprocessed (digital filtering, noise reduction) by an embedded computer before being sent to the program interface for display by a touchscreen module. The system employs an integrated hardware and software design, directly sampling the resolver signals using an analog-to-digital converter, resulting in fully electronic data processing. It fully utilizes computer, sensor, and virtual instrument technologies to display attitude information in both digital and analog animation formats. This digital detection, processing, and display of attitude information offers advantages such as high precision, accurate values, and rapid response.

[0020] The above general description and the description below are exemplary and illustrative only and are not intended to limit this application. Attached Figure Description

[0021] One or more embodiments are illustrated by way of example with reference to the accompanying drawings. These illustrations and drawings do not constitute a limitation on the embodiments. Elements having the same reference numerals in the drawings are shown as similar elements. The drawings are not to be scaled. And wherein: Figure 1 This is a schematic diagram of the aircraft's attitude and its indications; Figure 2 It is a schematic diagram of the early attitude control system principle; Figure 3 This is a schematic diagram of an aircraft attitude detection system provided in an embodiment of this disclosure; Figure 4 This is a schematic diagram of a signal A / D module of an aircraft attitude detection system provided in an embodiment of this disclosure; Figure 5This is a connection diagram of the signal A / D module, level conversion chip, and timer of an aircraft attitude detection system provided in this embodiment of the disclosure; Figure 6 This is a schematic diagram of an embedded computer for an aircraft attitude detection system provided in an embodiment of this disclosure; Figure 7 This is a schematic diagram of an aircraft attitude detection method provided in an embodiment of this disclosure; Figure 8 This is a schematic diagram of a controller provided in an embodiment of this disclosure. Detailed Implementation

[0022] To provide a more detailed understanding of the features and technical content of the embodiments of this disclosure, the implementation of the embodiments of this disclosure will be described in detail below with reference to the accompanying drawings. The accompanying drawings are for illustrative purposes only and are not intended to limit the embodiments of this disclosure. In the following technical description, for ease of explanation, several details are used to provide a full understanding of the disclosed embodiments. However, one or more embodiments may still be implemented without these details. In other cases, well-known structures and devices may be simplified in their depiction to simplify the drawings.

[0023] The terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this disclosure are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate for the embodiments of this disclosure described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion.

[0024] In this disclosure, the terms "upper," "lower," "inner," "middle," "outer," "front," and "rear," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for better describing the embodiments of this disclosure and their implementations, and are not intended to limit the indicated devices, elements, or components to having a specific orientation, or to require them to be constructed and operated in a specific orientation. Furthermore, some of the aforementioned terms may be used to indicate other meanings besides orientation or positional relationship; for example, the term "upper" may in some cases indicate a dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this disclosure according to the specific circumstances.

[0025] Furthermore, the terms "set up," "connect," and "fix" should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this disclosure according to the specific circumstances.

[0026] Unless otherwise stated, the term "multiple" means two or more.

[0027] In this embodiment of the disclosure, the character " / " indicates that the objects before and after it are in an "or" relationship. For example, A / B means: A or B.

[0028] The term "and / or" describes an association between objects, indicating that three relationships can exist. For example, A and / or B means: A or B, or A and B.

[0029] It should be noted that, unless otherwise specified, the embodiments and features described in the present disclosure can be combined with each other.

[0030] Combination Figure 3 As shown in the figure, this disclosure provides an aircraft attitude detection system, including an analog signal generation module, an analog signal processing module, a signal A / D module, an embedded computer, and a touch display module. The analog signal generation module is configured to sense the aircraft's attitude and output the aircraft's attitude signal. The analog signal processing module is connected to the analog signal generation module and is configured to filter and amplitude-condition the attitude signal. The signal A / D module is connected to the analog signal processing module and is configured to perform A / D conversion on the conditioned attitude signal to convert it into a digital signal. The embedded computer is connected to the signal A / D module and is configured to filter and denoise the converted digital signal. The touch display module is connected to the embedded computer and is configured to display the processed digital signal, used for human-computer interaction, displaying the program interface, and displaying simulated animations.

[0031] This disclosure provides an aircraft attitude detection system. The signal interface, implemented via an aviation socket, handles the flow of signals within and outside the system. During attitude detection, an analog signal generation module first senses the aircraft's attitude, outputting pitch and roll signals (resolver signals). These signals are then hardware-conditioned (filtered, amplitude-regulated) by an analog signal processing module, and acquired by a 14-bit (0.022-degree resolution) resolver signal A / D module. The acquired resolver signals are preprocessed (digitally filtered, noise-reduced) by an embedded computer before being sent to the program interface for display by a touch display module. The system employs an integrated hardware and software design, directly sampling the resolver signals using an analog-to-digital converter, resulting in fully electronic data processing. It fully utilizes computer, sensor, and virtual instrument technologies to display attitude information using both digital display and analog animation. This digital detection, processing, and display of attitude information offers advantages such as high precision, accurate values, and rapid response.

[0032] Optionally, the analog signal generation module includes a first rotary transformer, a second rotary transformer, a third rotary transformer, and a pendant. The first rotary transformer is mounted on the aircraft. The second rotary transformer is mounted on the detection end of the first rotary transformer, and the axis of the detection end of the second rotary transformer is perpendicular to the axis of the detection end of the first rotary transformer. The third rotary transformer is mounted on the detection end of the second rotary transformer, and the axis of the detection end of the third rotary transformer is perpendicular to the axes of the detection ends of the first and second rotary transformers. The pendant is mounted on the detection end of the third rotary transformer. The attitude signal includes the resolver signal generated by the first, second, and third rotary transformers.

[0033] In this embodiment, a first, second, and third rotary transformer are used as sensors to detect attitude data. A rotary transformer is a rotatable transformer. When an AC voltage is applied to each stator winding, an induced voltage is generated in the rotor winding due to changes in the linkage flux. The coupling coefficient between the induced voltage and the excitation voltage changes with the rotor angle. Its output signal has a certain functional relationship with the rotor angle; it can operate as a single unit, or in pairs or multiple units in combination. Because the relative position of the rotor winding and the stator excitation winding changes during rotor rotation, causing changes in mutual inductance, the output voltage has a sine and cosine relationship with the rotation angle. Therefore, the rotary transformer is also called a sine-cosine transformer. Thus, by measuring the output voltage, the magnitude of the rotor angle can be determined. A counterweight is used to increase the counterweight and change the center position, so that under the action of gravity, one, two, or three of the detection terminals of the first, second, and third rotary transformers deflect.

[0034] During attitude detection, the pendulum can swing freely in three-dimensional space because the axes of the detection terminals of the first, second, and third rotary transformers are perpendicular to each other. During flight, driven by the aircraft and under the influence of gravity, the pendulum swings with the aircraft, reaching different positions depending on its attitude. This causes the detection terminals of the first, second, and third rotary transformers to rotate to different angles, generating different induced voltages. These different induced voltages map various aircraft attitudes, enabling the output of pitch and roll resolver signals. These signals are then hardware-conditioned (filtered, amplitude-regulated) by an analog signal processing module and acquired using a 14-bit (0.022-degree resolution) resolver signal A / D module. The acquired resolver signals are first pre-processed (digitally filtered, denoised) by an embedded computer before being sent to the program interface for display by a touch display module. The integrated hardware and software design allows for direct AD sampling of the resolver signals, with fully electronic data processing. It fully utilizes computer, sensor, and virtual instrument technologies to display attitude and bearing information in both digital and simulated animation formats. The digital detection, processing, and display of attitude and bearing information offers advantages such as high precision, accurate values, and rapid response.

[0035] Optionally, combined Figure 4 As shown, the signal A / D module includes a reference transformer, a sine multiplier, a cosine multiplier, a quadrant selector switch, a power amplifier, and an output transformer. The input terminal of the reference transformer is connected to the output terminal of the analog signal processing module. The input terminal of the sine multiplier is connected to the output terminal of the reference transformer. The input terminal of the cosine multiplier is connected to the output terminal of the reference transformer. The input terminal of the quadrant selector switch is connected to the output terminals of the sine and cosine multipliers. The input terminal of the power amplifier is connected to the output terminal of the quadrant selector switch. The input terminal of the output transformer is connected to the output terminal of the power amplifier. The embedded computer is connected to the output terminal of the output transformer.

[0036] In this embodiment, the digital full-angle quantity and reference signal input are converted into sine and cosine signals representing the angle after being multiplied by a sine and cosine multiplier. After being amplified by a power amplifier, they have a load capacity of 1.3VA. Then, after isolation and voltage boosting by an output transformer, they become three-wire or four-wire analog signal outputs in the form of a synchro / rotary transformer. The expression for the analog output is: = = The left side of the equation represents the output voltage. To input the numerical angle, This is the proportionality coefficient. That is the reference voltage.

[0037] Optionally, combined Figure 5 As shown, the signal A / D module is a 14-bit digital converter, and also includes a level conversion chip and a timer. The level conversion chip is connected to the 14-bit digital input terminals of the signal A / D module. The timer's data ports D0-D11 are connected to the 14 channels of the level conversion chip.

[0038] In this embodiment, the timer uses two voltages: 3.3V for the I / O port and 5V for the signal A / D module (TTL level). Considering the driving capability of the timer's signal, level conversion is necessary to convert the 3.3V output from the timer port to 5V. The level conversion chip used is the SN74ALVC164245, a 16-channel bidirectional level conversion chip whose conversion direction is controlled by the DIR pin. The signal A / D module is a 14-bit converter, connected to the 14 channels of the level conversion chip via the timer's data ports D0-D13. The converted 14-bit level is then connected to the 14-bit digital input terminal of SXZ.

[0039] Optionally, combined Figure 6 As shown, the embedded computer includes a GUI module, a detection module, a display module, an I / O module, a data buffer and processing module, a metrology and calibration module, and a system setting module. The GUI module is configured to handle human-computer interaction, display the program interface, and receive user input. The detection module is bidirectionally connected to the GUI module and is configured to send control commands and data, and receive measured data. The display module is bidirectionally connected to the GUI module and is configured to display the processed measured data. The I / O module is connected to the detection module and is configured to input measured data and output control commands. The data buffer and processing module is connected between the I / O module, the detection module, and the display module and is configured to read, buffer, and process measured data. The metrology and calibration module is bidirectionally connected to the GUI module and is configured to read and write calibration parameters to achieve overall metrology and calibration. The system setting module is bidirectionally connected to the GUI module and is configured to read and write configuration files to set system parameters. The I / O module is connected to the signal A / D module, and the display module is connected to the touch display module.

[0040] In this embodiment, the embedded computer integrates hardware and software through a GUI module, a detection module, a display module, an I / O module, a data buffering and processing module, a metrology and calibration module, and a system setting module. This hardware-software integration sends control commands and data, receives the measured data, sequentially reads, buffers, and processes the measured data, displays the processed data, and receives user operations to complete the detection work. It fully utilizes computer, sensor, and virtual instrument technologies to display attitude and bearing information in both digital and simulated animation formats. This digital detection, processing, and display of attitude and bearing information offers advantages such as high precision, accurate values, and rapid response.

[0041] Optionally, the reception and processing of the measured data adopts a "producer-consumer" model, with separate lines for inbound and outbound data transmission.

[0042] In this embodiment, the reception and processing of the test data adopts a "producer-consumer" model to avoid conflicts and confusion. After receiving the test data, the data buffering and processing module first stores it in a buffer (the buffer uses a circular queue to avoid memory overflow). Simultaneously, it triggers data processing logic to preprocess the raw data. Upon completion, it notifies the display module via an event. Data reception (backend) and display (frontend) are implemented using an MVVM approach, employing QT's signal-slot mechanism for bidirectional data binding. When backend data changes, the frontend display is automatically triggered; conversely, frontend operations are automatically synchronized to the backend.

[0043] Optionally, the human-computer interaction functions and control logic are implemented using the C++ language.

[0044] In this embodiment of the disclosure, a graphical user interface (GUI) is created using C++, which can be achieved using libraries such as Qt, FLTK, or wxWidgets. These libraries provide rich controls and layout managers, enabling developers to easily build beautiful and powerful user interfaces.

[0045] Optionally, the program interface can use QML+Widget.

[0046] In this embodiment, a QML file is loaded using QQuickWidget and added to the QWidget. The QML file can be loaded by calling the setSource function of QQuickWidget. If interaction between the QML and QWidget is required, a signal and slot mechanism can be used. For example, a signal can be defined in the QML, then this signal can be connected to the QWidget, and the corresponding slot function can be implemented to handle the operation when the signal is triggered.

[0047] Optionally, the simulated animated interface images are in SVG vector graphics format.

[0048] In this embodiment of the disclosure, SVG (Scalable Vector Graphics) is an XML-based vector graphics format that uses code to describe images instead of pixels. This means that SVG images can be displayed clearly at any resolution without distortion. SVG images are typically smaller than bitmap images, which helps reduce page load time.

[0049] Combination Figure 1 As shown, in some embodiments, such as Figure 7 As shown, an aircraft attitude detection method is provided, including: Step 1: Obtain the aircraft's attitude signal based on the aircraft's flight attitude.

[0050] Step two: Filter and amplitude adjust the acquired attitude signal.

[0051] Step 3: Determine if the A / D acquisition is idle. If not, re-determine. If so, perform A / D conversion on the conditioned attitude signal to convert it into a digital signal.

[0052] Step 4: Determine if the conversion is complete. If not, determine again. If yes, read the value and calculate. Step 5: Display the calculated data.

[0053] This disclosure provides an aircraft attitude detection method. First, it acquires the aircraft's attitude signal based on its flight attitude. Then, it filters and adjusts the amplitude of the acquired attitude signal. Next, when the A / D acquisition is idle, it performs an A / D conversion on the adjusted attitude signal to convert it into a digital signal. After the digital signal conversion is complete, the value is read and calculated, and the calculated data is displayed. This completes the processing of the aircraft attitude signal and detects the aircraft's attitude. The entire detection method directly samples the aircraft's attitude signal using A / D, and the data is processed entirely electronically. It employs computer, sensor, and virtual instrument technology to display the attitude information in both digital and simulated animation formats. This digital detection, processing, and display of attitude information offers advantages such as high precision, accurate values, and rapid response.

[0054] This disclosure provides a controller, the structure of which is as follows: Figure 8 As shown, it includes a processor and memory, and may also include a communication interface and a bus. The processor, communication interface, and memory can communicate with each other via the bus. The communication interface can be used for information transmission. The processor can invoke logical instructions from the memory to execute the control method described in the above embodiments.

[0055] Memory, as a computer-readable storage medium, can be used to store software programs and computer-executable programs, such as program instructions / modules corresponding to the methods in the embodiments of this disclosure. The processor executes functional applications and data processing by running the program instructions / modules stored in the memory, thereby implementing the control methods in the above-described method embodiments.

[0056] This disclosure provides a computer-readable storage medium storing computer-executable instructions configured to perform the above-described control method.

[0057] This disclosure provides a computer program product, which includes a computer program stored on a computer-readable storage medium. The computer program includes program instructions that, when executed by a computer, cause the computer to perform the aforementioned control method.

[0058] The aforementioned computer-readable storage medium may be a transient computer-readable storage medium or a non-transitory computer-readable storage medium.

[0059] The foregoing description and accompanying drawings fully illustrate embodiments of the present disclosure to enable those skilled in the art to practice them. Other embodiments may include structural and other changes. The embodiments represent only possible variations. Individual components and functions are optional unless explicitly required, and the order of operation may vary. Parts and features of some embodiments may be included or substituted for parts and features of other embodiments. Embodiments of the present disclosure are not limited to the structures described above and shown in the accompanying drawings, and various modifications and changes may be made without departing from its scope. The scope of the present disclosure is limited only by the appended claims.

Claims

1. An aircraft attitude detection system, characterized in that, include: The analog signal generation module is configured to sense the aircraft's attitude and output the aircraft's attitude signal. The analog signal processing module is configured to filter and amplitude condition the attitude signal; The signal A / D module is configured to perform A / D conversion on the conditioned attitude signal to convert it into a digital signal; Embedded computers are configured to filter and denoise converted digital signals. The touch display module is configured to display the processed digital signal and is responsible for human-computer interaction, displaying program interfaces, and displaying simulated animations.

2. The aircraft attitude detection system according to claim 1, characterized in that, The analog signal generation module includes: The first rotary transformer was installed on the aircraft; A second rotary transformer is installed at the detection end of the first rotary transformer, and the axis of the detection end of the second rotary transformer is perpendicular to the axis of the detection end of the first rotary transformer. A third rotary transformer is installed at the detection end of the second rotary transformer, and the axis of the detection end of the third rotary transformer is perpendicular to the axis of the detection end of the first rotary transformer and the axis of the detection end of the second rotary transformer. An ornament is installed at the detection end of the third rotary transformer; The attitude signal includes the resolver signal generated by the first resolver, the second resolver, and the third resolver.

3. The aircraft attitude detection system according to claim 2, characterized in that, The signal A / D module includes: A reference transformer is connected to the output terminal of the analog signal processing module; A sinusoidal multiplier is connected to the output terminal of the reference transformer; A cosine multiplier is connected to the output terminal of the reference transformer; A quadrant selection switch is connected to the output terminals of the sine multiplier and the cosine multiplier; A power amplifier is connected to the output terminal of the quadrant selection switch; An output transformer is connected to the output terminal of the power amplifier. The embedded computer is connected to the output terminal of the output transformer.

4. The aircraft attitude detection system according to claim 1, characterized in that, The signal A / D module is a 14-bit converter, and also includes: The level conversion chip is connected to the 14-bit digital input terminal of the signal A / D module; The timer is connected to the 14 channels of the level conversion chip.

5. The aircraft attitude detection system according to claim 1, characterized in that, The embedded computer includes: The GUI module is configured to be responsible for human-computer interaction, displaying the program interface and receiving user operations; The detection module is bidirectionally connected to the GUI module and is configured to send control commands and data, and receive the data to be tested. The display module, which is bidirectionally connected to the GUI module, is configured to be responsible for displaying the processed test data; The I / O module, connected to the detection module, is configured to be responsible for inputting the measured data and outputting control commands. The data buffering and processing module, connected between the I / O module, the detection module, and the display module, is configured to be responsible for reading, buffering, and processing the data under test; The metrology and calibration module is bidirectionally connected to the GUI module and is configured to read and write calibration parameters to realize the metrology and calibration of the whole machine. The system settings module, which has a bidirectional connection with the GUI module, is configured to read and write configuration files to set system parameters. The I / O module is connected to the signal A / D module, and the display module is connected to the touch display module.

6. The aircraft attitude detection system according to claim 5, characterized in that: The reception and processing of the measured data adopts a "producer-consumer" model, with separate lines for inbound and outbound data transmission.

7. An aircraft attitude detection system according to any one of claims 1 to 6, characterized in that: The human-computer interaction functions and control logic are implemented in C++.

8. An aircraft attitude detection system according to any one of claims 1 to 6, characterized in that: The program interface uses QML+Widget.

9. An aircraft attitude detection system according to any one of claims 1 to 6, characterized in that: The simulated animation interface images are in SVG vector graphics format.

10. A method for detecting aircraft attitude, characterized in that, An aircraft attitude detection system as described in any one of claims 1 to 9, comprising: The aircraft's attitude signal is obtained based on its flight attitude. The acquired attitude signal is filtered and amplitude conditioned. Determine if the A / D acquisition is idle; if not, re-determine; if so, perform A / D conversion on the conditioned attitude signal to convert it into a digital signal. Determine if the conversion is complete; if not, re-determine; if yes, read the value and calculate. Display the calculated data.

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