Electronic horizon sensor

Abstract

The embodiment of the utility model discloses an electronic horizon sensor, which comprises a posture module, a display module, an interface module, a temperature control module, a power supply module and a display screen, the posture module, the display module, the interface module, the temperature control module and the power supply module are arranged on a mother board in the form of a back board, and the display screen is arranged on a casing; the attitude module is used for measuring and resolving associated angle information and sending the information to the display module and the interface module; the interface module is used for converting the associated angle information into an analog signal for output, receiving a flight guide instruction, converting the analog signal into flight guide information and sending the flight guide information to the display module; the display module is used for generating display information according to the associated angle information and the flight guide information and sending the display information to the display screen for display; the temperature control module is used for controlling the internal working temperature of the electronic horizon sensor; the power supply module is used for supplying power to each functional module. According to the technical scheme of the embodiment of the utility model, the data display precision of the horizon sensor can be improved.

Description

Technical Field

[0001] The embodiment of the utility model relates to the technical field of aviation equipment, and in particular to an electronic horizon. Background Art

[0002] The attitude indicator is widely used on various types of aircraft. During the flight, the aircraft will make various flight postures and headings. The pilot cannot observe the flight attitude of the aircraft in the cockpit. The role of the attitude indicator is to provide the pilot with the real flight status of the aircraft and display the image information of the aircraft's tilt and pitch.

[0003] At present, the attitude indicators used in aircraft are usually mechanical attitude indicators, which have low display data accuracy and cannot meet the needs of high-precision data display. Utility Model Content

[0004] The embodiment of the utility model provides an electronic horizon instrument, which can improve the accuracy of the data displayed by the horizon instrument.

[0005] According to one aspect of the utility model, an electronic horizon instrument is provided, comprising a posture module, a display module, an interface module, a temperature control module, a power module and a display screen, wherein the posture module, the display module, the interface module, the temperature control module and the power module are mounted on a motherboard of the electronic horizon instrument in the form of a backplane, and the display screen is mounted on a housing of the electronic horizon instrument; wherein:

[0006] The posture module is used to measure and solve the associated angle information, and send the associated angle information to the display module and the interface module;

[0007] The interface module is used to convert the associated angle information into an analog signal output, receive a flight guidance instruction analog signal, convert the flight guidance instruction analog signal into flight guidance information and send it to the display module;

[0008] The display module is used to generate display information according to the associated angle information and the flight guidance information, and send the display information to the display screen for display;

[0009] The temperature control module is used to control the internal working temperature of the electronic horizon;

[0010] The power module is used to supply power to the posture module, the display module, the interface module and the temperature control module.

[0011] Optionally, the posture module includes an inertial measurement unit, a sensor sampling unit, a processor and an external interface; wherein: the inertial measurement unit is communicatively connected to the sensor sampling unit, used to collect posture-related data, and send the posture-related data to the sensor sampling unit; wherein the posture-related data includes acceleration and angular velocity; the sensor sampling unit is communicatively connected to the processor, used to sample the posture-related data, obtain sampled posture-related data, and send the sampled posture-related data to the processor; the processor is used to perform posture calculation on the sampled posture-related data, obtain the associated angle information, and send the associated angle information to the external interface; the external interface is communicatively connected to the processor, used to send the associated angle information to the display module and the interface module.

[0012] Optionally, the display module is used to load a graphic interface on the display screen according to graphic software, and send the display information to the graphic interface of the display screen for display.

[0013] Optionally, the interface module includes a first programmable amplifier and a second programmable amplifier; wherein: the first programmable amplifier is connected in parallel with the second programmable amplifier, and is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain a sine component; and the second programmable amplifier is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain a cosine component.

[0014] Optionally, the temperature control module includes a temperature sensor, a detection circuit, a microprocessor, a drive circuit and a power resistor; wherein: the temperature sensor is electrically connected to the detection circuit, and is used to collect a temperature signal and send the temperature signal to the detection circuit; the detection circuit is communicatively connected to the microprocessor, and is used to perform signal modulation, filtering and bias processing on the temperature signal, and then perform A / D conversion to obtain an actual collected temperature value in digital form, and send the actual collected temperature value in digital form to the microprocessor; the microprocessor is communicatively connected to the drive circuit, and is used to perform a difference operation between a set expected temperature value and the actual collected temperature value in digital form to obtain a temperature error, and output a pulse width modulation wave with a corresponding duty cycle according to the temperature error and send it to the drive circuit; the drive circuit is electrically connected to the power resistor, and is used to perform an on-off operation according to the pulse width modulation wave with the corresponding duty cycle, and control the heat generation of the power resistor so that the current temperature reaches the expected temperature value.

[0015] Optionally, the temperature sensor and the power resistor are installed inside the casing of the electronic horizon.

[0016] Optionally, the power supply module is used to: convert an input voltage into a first power supply; and convert the first power supply into a second power supply using a voltage conversion chip.

[0017] Optionally, the analog power supply and digital power supply in the electronic horizon are isolated by a power isolation circuit.

[0018] The embodiment of the utility model constructs an electronic horizon instrument by using a posture module, a display module, an interface module, a temperature control module, a power module and a display screen, wherein the posture module, the display module, the interface module, the temperature control module and the power module are installed on the motherboard of the electronic horizon instrument in the form of a backplane, and the display screen is installed on the housing of the electronic horizon instrument. The electronic horizon instrument measures and solves the associated angle information through the posture module, and sends the associated angle information to the display module and the interface module. The interface module can convert the associated angle information into an analog signal output, and receive the flight guidance instruction analog signal, convert the flight guidance instruction analog signal into flight guidance information and send it to the display module. The display module can generate display information according to the associated angle information and the flight guidance information, and send the display information to the display screen for display. The temperature control module can control the internal working temperature of the electronic horizon instrument. The power module can supply power to the above-mentioned posture module, display module, interface module and temperature control module. The above-mentioned electronic horizon instrument can solve the problem of poor display data accuracy of the existing horizon instrument, and can improve the accuracy of the horizon instrument data display.

[0019] It should be understood that the contents described in this section are not intended to identify the key or important features of the embodiments of the present utility model, nor are they intended to limit the scope of the present utility model. Other features of the present utility model will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0021] Figure 1 It is a structural schematic diagram of an electronic horizon provided by an embodiment of the utility model;

[0022] Figure 2 It is a schematic diagram of the internal structure of a posture module provided by an embodiment of the utility model;

[0023] Figure 3 It is a schematic diagram of a flow chart of posture calculation by a posture module provided by an embodiment of the utility model;

[0024] Figure 4 It is a schematic diagram of a development process of a display screen provided by an embodiment of the utility model;

[0025] Figure 5 It is a structural schematic diagram of an interface module provided by an embodiment of the utility model;

[0026] Figure 6 This is a schematic diagram of the system structure of a temperature control module provided by an embodiment of the utility model;

[0027] Figure 7 The present invention is a schematic diagram of the layout structure of various internal modules of an electronic horizon provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0028] In order to enable those skilled in the art to better understand the solution of the utility model, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all of the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the utility model.

[0029] It should be noted that the terms "first", "second", etc. in the specification and claims of the utility model and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the utility model described here can be implemented in an order other than those illustrated or described here. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0030] Figure 1 Schematic diagram of the structure of an electronic horizon provided by an embodiment of the utility model. Figure 1 As shown, the structure of the electronic horizon instrument includes: a posture module 110, a display module 120, an interface module 130, a temperature control module 140, a power module 150 and a display screen 160. The posture module 110, the display module 120, the interface module 130, the temperature control module 140 and the power module 150 are installed on a motherboard 170 of the electronic horizon instrument in the form of a backplane, and the display screen 160 is installed on the outside of a housing 180 of the electronic horizon instrument; wherein:

[0031] The posture module 110 is used to measure and calculate the associated angle information, and send the associated angle information to the display module 120 and the interface module 130 .

[0032] The associated angle information may include information of attitude angles. Exemplarily, the attitude angle information may include but is not limited to pitch angle, tilt angle, and sideslip angle.

[0033] The attitude module 110 can measure the three-axis angular velocity and the three-axis acceleration, and calculate the measured information to obtain the attitude angle, and then output the attitude information to the display module 120 and the interface module 130 through the bus.

[0034] The interface module 130 may convert the associated angle information into an analog signal output, receive a flight guidance instruction analog signal, convert the flight guidance instruction analog signal into flight guidance information, and send it to the display module 120 .

[0035] Exemplarily, the flight guidance instruction analog signal may be an analog signal light of the tilt and pitch control instructions of the flight guidance. The flight guidance information may be digital information obtained by converting the flight guidance instruction analog signal.

[0036] Specifically, the interface module can convert the associated angle information in digital form sent by the attitude module 110 into a CKT (circuit-derived) analog signal output, and at the same time can receive the analog signals of the tilt and pitch control instructions of the flight guidance, and convert the flight guidance instruction analog signals into digital flight guidance information and send them to the display module 120 for display.

[0037] The display module 120 may generate display information according to the associated angle information and the flight guidance information, and send the display information to the display screen 160 for display.

[0038] That is, the display module 120 can generate display information from the received pitch angle, bank angle, sideslip angle and other related angle information and flight guidance information, and send the display information to the display screen 160 for display. Optionally, the display information can be displayed in the same manner as the mechanical horizon.

[0039] The temperature control module 140 can control the internal working temperature of the electronic horizon instrument. The temperature control module 140 is mainly used to ensure that the internal temperature of the electronic horizon instrument is always within the normal working temperature range when the electronic horizon instrument is in a low temperature working environment.

[0040] The power module 150 can supply power to the posture module 110, the display module 120, the interface module 130 and the temperature control module 140. Specifically, the power module 150 can convert the DC 27V voltage input by the system into the working voltage required by different functional modules.

[0041] Figure 2 Schematic diagram of the internal structure of a posture module provided by an embodiment of the utility model. In an optional embodiment of the utility model, Figure 1 and Figure 2 As shown, the posture module 110 may include an inertial measurement unit, a sensor sampling unit, a processor, and an external interface. Among them: the inertial measurement unit is connected in communication with the sensor sampling unit, and is used to collect posture-related data and send the posture-related data to the sensor sampling unit; wherein the posture-related data includes acceleration and angular velocity; the sensor sampling unit is connected in communication with the processor, and is used to sample the posture-related data, obtain the sampled posture-related data, and send the sampled posture-related data to the processor; the processor is used to perform posture calculation on the sampled posture-related data, obtain the associated angle information, and send the associated angle information to the external interface; the external interface is connected in communication with the processor, and is used to send the associated angle information to the display module 120 and the interface module 130.

[0042] The posture-related data may be data such as angular velocity and acceleration that can be used to calculate posture information. Optionally, the angular velocity may be a three-axis angular velocity, and the acceleration may be a three-axis acceleration. The sampled posture-related data may be data obtained by sampling the posture-related data at a sampling frequency.

[0043] Optionally, the required inertial measurement unit can be selected according to the system attitude measurement accuracy index requirements. The attitude measurement accuracy of the attitude module is mainly determined by the accelerometer, among which the noise and sensitivity of the accelerometer directly affect the attitude solution. Figure 2As shown, the inertial measurement unit may include a three-axis accelerometer, a three-axis gyroscope, and a temperature sensor. Both the three-axis gyroscope and the three-axis accelerometer have their own dynamic compensation formulas, which can provide accurate sensor measurements. During use, the inertial measurement unit can be driven through the SPI (Serial Peripheral Interface) serial interface. First, the inertial measurement unit is initialized, the internal sampling clock of the inertial measurement unit is set to 819.2SPS, and a fourth-order mean filter is used. Then, the dynamic measurement range of each sensor and the internal digital FIR (Finite Impulse Response, finite unit impulse response filter) filter (including the number of filter taps) are configured, the inertial measurement unit is reset by software, and then the six-axis self-test task of the inertial measurement unit is started. After the inertial measurement unit is successfully initialized, data acquisition and data processing operations such as the three-axis gyroscope, the three-axis accelerometer, and the temperature sensor can be performed to achieve navigation solution. Temperature has a great influence on inertial devices. In order to enhance the environmental adaptability of the inertial measurement unit, the three-axis gyroscope and the three-axis accelerometer therein can be temperature compensated to give them better temperature characteristics, so that the inertial measurement unit has higher measurement accuracy under various temperature conditions.

[0044] When each device in the inertial measurement unit collects data, it is output to the sensor sampling unit. After the sensor sampling unit samples the data, the sampled attitude associated data is obtained and output to the processor, and the processor calibrates and solves the sampled attitude associated data. Exemplarily, the processor can use a CPU (Central Processing Unit) or an ARM (Advanced RISC Machine), etc. The embodiment of the utility model does not limit the type of processor. Specifically, the processor can perform attitude solution on the sampled attitude associated data, obtain associated angle information, and send the associated angle information to an external interface. Optionally, the external interface can include, but is not limited to, an RS232 digital output interface and an analog output interface, etc.

[0045] Figure 3 FIG. 1 is a flow chart of a posture calculation process performed by a posture module according to an embodiment of the present utility model. Figure 3 As shown, the attitude module can use the following process to solve the attitude:

[0046] First, acceleration is used for initial alignment to obtain the initial attitude angle. The attitude angle can be continuously updated by iterating the gyro data and accelerometer data.

[0047] When the navigation system is just started, the orientation of each axis of its carrier coordinate system relative to the reference navigation coordinate system is completely unknown or not accurate enough, and it is impossible to enter the navigation state. Therefore, the spatial orientation of the carrier coordinate system relative to the navigation coordinate system must be determined first, which is equivalent to a process of finding a reference navigation coordinate system from the perspective of inertial navigation. Taking the geographic coordinate system as the reference navigation coordinate system as an example, its three-axis orientations are east, north and celestial, where the celestial direction is defined according to the gravitational acceleration. With the celestial direction, the horizontal plane is determined, and the initial alignment of the attitude angle can be achieved using an accelerometer. The horizon system of the embodiment of the utility model outputs only the horizontal attitude angle, so only the horizontal attitude angle needs to be initially aligned.

[0048] During the initial alignment, the system is in a stationary state. At this time, the three-axis acceleration measured in the body coordinate system is:

[0049]

[0050] Among them, f b represents the three-axis acceleration vector, and Indicates the acceleration in the three coordinate directions. b indicates the body coordinate system.

[0051] In the above formula, f b It is mainly the component of gravity acceleration on the three axes of the body coordinate system. Based on this acceleration, the initial pitch angle θ and tilt angle γ can be calculated respectively:

[0052]

[0053] The attitude update of the attitude angle can use the following differential equation:

[0054]

[0055] in, is a four-element vector, is the angular velocity measured by the three-axis gyroscope, q0, q1, q2, q3 are real numbers, and solving this differential equation yields From this, the final attitude angle can be calculated:

[0056] arcsin[2(q2q3+qoq1)]

[0057]

[0058] The above-mentioned posture solving algorithm can be implemented in the processor of the posture module by programming.

[0059] In an optional embodiment of the present invention, the display module 120 can load a graphic interface on the display screen according to the graphic software, and send the display information to the graphic interface of the display screen 160 for display.

[0060] It is understandable that the most important function of the attitude indicator is to display information such as pitch status, roll status and heading. In order to smoothly display the moving pictures of the above parameters, the display picture update rate must be high enough. Usually the display update rate of pitch angle and roll angle is not less than 20Hz, otherwise it will cause the picture to be not smooth and the information display will lag. Therefore, in addition to the functional requirements such as beauty and accuracy, the electronic attitude indicator graphic display also includes real-time requirements as an important constraint for the development of flight displays.

[0061] In order to ensure the real-time display of pitch and roll status of the electronic horizon, the display interface of the horizon display can be developed based on the graphics library. Since some graphics libraries have cross-platform characteristics, the graphics software can be developed in advance on the Unix (an operating system) or Windows (an operating system) platform and then loaded into the embedded device, which greatly simplifies the development process of the embedded graphical interface and improves the reusability of the software. The display control software can be developed on the Windows platform through relevant development software and then loaded into the horizon, which can shorten the display software development cycle and improve the efficiency of design and verification. The display screen generated by this method is better than the display screen developed by the traditional C / C++ language, and the development process is simple.

[0062] Figure 4 is a schematic diagram of a development process of a display screen provided by an embodiment of the utility model. In a specific example, Figure 4 As shown, the development process of the entire display screen can include two processes: graphic behavior definition and graphic drawing. Among them, the graphic behavior definition can include defining input-defining display architecture-defining display model-adding logic and other links. Graphic drawing can include laying out interface-setting running time-adding external running interface and other links. Specifically, in the graphic behavior definition stage, the introduction variable is set when defining the behavior of the group or element. Through the graphic organization structure tree, the corresponding group or element can be selected to define its internal variables. The internal variables are the variables that control the pitch and roll scale movement inside the electronic horizon. These variables will eventually be associated with the data input by the external device to realize the real-time and dynamic indication of the external data. In the graphic drawing stage, when the main interface of the display screen is entered using the relevant software configuration, the workspace can be saved. The workspace will provide a structure tree storage for the entire design project, thereby ensuring development efficiency. In the workspace, editing the relevant files can directly draw the display screen of the horizon through the graphical design method.

[0063] Figure 5 Schematic diagram of the structure of an interface module provided by an embodiment of the utility model. In an optional embodiment of the utility model, Figure 1 and Figure 5 As shown, the interface module 130 may include a first programmable amplifier and a second programmable amplifier; wherein: the first programmable amplifier is connected in parallel with the second programmable amplifier, and is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain a sine component; the second programmable amplifier is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain a cosine component.

[0064] In the embodiment of the utility model, the interface module is mainly used to realize the output of pitch angle and tilt angle. It can convert the input single-phase AC frequency (400±8) Hz, voltage The volt power supply is used for orthogonal rotation, and then output to the system that uses the pitch angle and tilt angle information. The specific schematic diagram is as follows Figure 5 As shown, this can be achieved using two programmable amplifiers.

[0065] Figure 6 is a schematic diagram of the system structure of a temperature control module provided by an embodiment of the utility model. In an optional embodiment of the utility model, Figure 1 and Figure 6 As shown, the temperature control module 140 may include a temperature sensor, a detection circuit, a microprocessor, a drive circuit and a power resistor; wherein: the temperature sensor is electrically connected to the detection circuit, and is used to collect a temperature signal and send the temperature signal to the detection circuit; the detection circuit is communicatively connected to the microprocessor, and is used to perform signal modulation, filtering and bias processing on the temperature signal and then perform A / D conversion to obtain an actual collected temperature value in digital form, and send the actual collected temperature value in digital form to the microprocessor; the microprocessor is communicatively connected to the drive circuit, and is used to perform a difference operation between the set expected temperature value and the actual collected temperature value in digital form to obtain a temperature error, and output a pulse width modulation wave of a corresponding duty cycle according to the temperature error and send it to the drive circuit; the drive circuit is electrically connected to the power resistor, and is used to perform an on-off operation according to the pulse width modulation wave of the corresponding duty cycle, and control the heat generated by the power resistor so that the current temperature reaches the expected temperature value.

[0066] Among them, the microprocessor in the temperature control module can use an ARM processor as the calculation and control core, which is responsible for temperature collection, control algorithm calculation and power circuit control to ensure that the temperature in the electronic horizon is maintained within the range required by the LCD screen.

[0067] like Figure 6As shown, the main principle of temperature control module to achieve temperature control is: use the temperature sensor to obtain the temperature signal and send it to the detection circuit. After the detection circuit performs signal modulation, filtering, and bias processing on the temperature signal, it is converted into the actual collected temperature value of the digital signal through A / D conversion and input into the microprocessor. The microprocessor can perform a difference operation between the set expected temperature value and the actual collected temperature value to obtain the temperature error. The microprocessor is integrated with a temperature control algorithm, and the calculated temperature error can be further input into the temperature control algorithm, and a pulse width modulation wave with a corresponding duty cycle is output through the calculation, and a PWM wave is output through the PWM (Pulse-Width Modulation) interface and sent to the drive circuit, so as to control the on and off of the power drive circuit through the PWM wave, thereby controlling the heat generated by the power resistor, and finally converging the output temperature to the expected value, so that the temperature range inside the electronic horizon is maintained. Among them, Figure 6 The power module in Figure 1 The power module 150 in.

[0068] Figure 7 Schematic diagram of the internal module layout structure of an electronic horizon provided by the embodiment of the utility model. In a specific example, Figure 7 As shown, the electronic horizon can also use the same interface as the 96D mechanical horizon, and the interface definition also uses the same definition method as the 96D mechanical horizon. The interface can be deployed on the rear panel of the electronic horizon. The power resistor in the temperature control module can be used as a heating component, and the temperature sensor and the heating component can be installed on the inner side of the housing 180 of the electronic horizon. Optionally, the number of temperature sensors and heating components can be configured as needed, and the embodiment of the utility model does not limit the number of temperature sensors and heating components.

[0069] The housing of the electronic horizon can also be equipped with reliable and stable structural support and electrical connections to ensure that the horizon can work stably and reliably in a vibrating environment. There are heat dissipation holes on the housing. Optionally, a heating component can be installed near the front panel display screen, and the temperature control module can be used to control the temperature accordingly to ensure that the operating temperature inside the electronic horizon can cover the range of -20℃ to +55℃. The housing can be made of all-metal and the housing can be reliably grounded to ensure electromagnetic compatibility and lightning protection requirements.

[0070] In order to make the structural design of the electronic horizon meet the corresponding environmental test standards, electromagnetic compatibility requirements and three-proof design requirements, locking devices can be installed on each functional module inside the digital horizon (i.e., attitude module, display module, interface module, temperature control module and power module, etc.), which can fasten each functional module to the chassis, and at the same time, a special locking device can be used to firmly fix it to the chassis. Furthermore, the module components and motherboard connections can also be reinforced, such as using screws to prevent them from falling off, and some screws are painted and sealed. The chassis body can be processed from this Ayong aluminum alloy material, treated with chemical conductive oxidation, and sprayed with black aircraft skin paint on the outer surface. It has reliable three-proof performance, and stainless steel fasteners are used for installation and connection with the body of the electronic horizon.

[0071] In an optional embodiment of the utility model, the power module 150 is used to: convert the input voltage into a first power supply; and convert the first power supply into a second power supply using a voltage conversion chip. The analog power supply and the digital power supply in the electronic horizon are isolated by a power isolation circuit.

[0072] The first power supply and the second power supply may be two types of power supplies with different voltage values. The analog power supply may be used to power analog circuits, and the digital power supply may be used to power digital circuits.

[0073] The system operating voltage range of the electronic horizon instrument is 5V-36V, but the power supply voltage required by each device is different. For example, the power supply voltage required by the ARM processor and the inertial measurement unit is usually 3.3V, the power supply voltage of the data communication module is 5V; the power supply voltage of the DA (digital-to-analog conversion) conversion module is 5V and ±15V. Therefore, the task of the power module is to input 5V-36V and output three power supplies of 3V, 5V and ±15V. First, the system uses the power module to convert the input voltage 5V-36V into the first power supply of ±15V and +5V, and then uses the voltage conversion chip to realize 5V to 3.3V according to the first power supply to obtain the second power supply. In order to avoid interference between the digital circuit and the analog circuit and improve the stability of the system analog output and digital output, the power supply of the analog circuit needs to be isolated from the power supply of the digital circuit. Optionally, the B0505 ​​chip can be used to design a power isolation circuit, and the analog power supply and digital power supply in the electronic horizon instrument can be isolated through the power isolation power supply.

[0074] The above-mentioned attitude indicator is used to provide the aircraft pilot with angle information such as bank angle, pitch angle, sideslip angle, etc. It can also provide the display function of bank and pitch control command information issued by the aircraft automatic control system, and can also send bank signals and pitch signals to external users.

[0075] The embodiment of the utility model constructs an electronic horizon instrument by using a posture module, a display module, an interface module, a temperature control module, a power module and a display screen, wherein the posture module, the display module, the interface module, the temperature control module and the power module are installed on the motherboard of the electronic horizon instrument in the form of a backplane, and the display screen is installed on the housing of the electronic horizon instrument. The electronic horizon instrument measures and solves the associated angle information through the posture module, and sends the associated angle information to the display module and the interface module. The interface module can convert the associated angle information into an analog signal output, and receive the flight guidance instruction analog signal, convert the flight guidance instruction analog signal into flight guidance information and send it to the display module. The display module can generate display information according to the associated angle information and the flight guidance information, and send the display information to the display screen for display. The temperature control module can control the internal working temperature of the electronic horizon instrument. The power module can supply power to the above-mentioned posture module, display module, interface module and temperature control module. The above-mentioned electronic horizon instrument can solve the problem of poor display data accuracy of the existing horizon instrument, and can improve the accuracy of the horizon instrument data display.

Claims

1. An electronic horizon, characterized in that: The electronic horizon instrument comprises a posture module, a display module, an interface module, a temperature control module, a power module and a display screen, wherein the posture module, the display module, the interface module, the temperature control module and the power module are mounted on a motherboard of the electronic horizon instrument in the form of a backplane, and the display screen is mounted on a housing of the electronic horizon instrument; wherein: The posture module is used to measure and solve the associated angle information, and send the associated angle information to the display module and the interface module; The interface module is used to convert the associated angle information into an analog signal output, receive a flight guidance instruction analog signal, convert the flight guidance instruction analog signal into flight guidance information and send it to the display module; The display module is used to generate display information according to the associated angle information and the flight guidance information, and send the display information to the display screen for display; The temperature control module is used to control the internal working temperature of the electronic horizon; The power module is used to supply power to the posture module, the display module, the interface module and the temperature control module.

2. The electronic horizon instrument according to claim 1, characterized in that: The attitude module includes an inertial measurement unit, a sensor sampling unit, a processor and an external interface; wherein: The inertial measurement unit is in communication connection with the sensor sampling unit, and is used to collect attitude-related data, and send the attitude-related data to the sensor sampling unit; wherein the attitude-related data includes acceleration and angular velocity; The sensor sampling unit is communicatively connected to the processor, and is used to sample the posture-related data to obtain the sampled posture-related data, and send the sampled posture-related data to the processor; The processor is used to perform posture calculation on the sampled posture associated data to obtain the associated angle information, and send the associated angle information to the external interface; The external interface is in communication with the processor and is used to send the associated angle information to the display module and the interface module.

3. The electronic horizon instrument according to claim 1, characterized in that: The display module is used to load a graphic interface on the display screen according to the graphic software, and send the display information to the graphic interface of the display screen for display.

4. The electronic horizon instrument according to claim 1, characterized in that: The interface module includes a first program-controlled amplifier and a second program-controlled amplifier; wherein: The first programmable amplifier is connected in parallel with the second programmable amplifier, and is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain sinusoidal components; The second programmable amplifier is used to perform orthogonal rotation on the associated angle information and the flight guidance information to obtain cosine components.

5. The electronic horizon instrument according to claim 1, characterized in that: The temperature control module includes a temperature sensor, a detection circuit, a microprocessor, a drive circuit and a power resistor; wherein: The temperature sensor is electrically connected to the detection circuit, and is used to collect a temperature signal and send the temperature signal to the detection circuit; The detection circuit is in communication connection with the microprocessor, and is used for performing signal modulation, filtering and bias processing on the temperature signal and then performing A / D conversion to obtain an actual collected temperature value in digital form, and sending the actual collected temperature value in digital form to the microprocessor; The microprocessor is in communication connection with the drive circuit, and is used for performing a difference operation between the set expected temperature value and the actual collected temperature value in digital form to obtain a temperature error, and outputting a pulse width modulation wave with a corresponding duty cycle according to the temperature error and sending it to the drive circuit; The driving circuit is electrically connected to the power resistor and is used to perform on-off operations according to the pulse width modulation wave of the corresponding duty cycle to control the heating value of the power resistor so that the current temperature reaches the expected temperature value.

6. The electronic horizon instrument according to claim 5, characterized in that: The temperature sensor and the power resistor are installed inside the casing of the electronic horizon.

7. The electronic horizon instrument according to claim 1, characterized in that: The power module is used for: converting an input voltage into a first power supply; The first power source is converted into a second power source by using a voltage conversion chip.

8. The electronic horizon instrument according to claim 1, characterized in that: The analog power supply and the digital power supply in the electronic horizon are isolated by a power isolation circuit.

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