Novel aircraft electronic equipment cabin

Abstract

The invention provides a novel aircraft electronic equipment cabin. The novel aircraft electronic equipment cabin comprises a comprehensive control unit, an inertial measurement unit, a telemetering unit, a primary power supply unit, a flexible cable and a structural frame, the comprehensive control unit, the inertial measurement unit, the telemetering unit, the primary power supply unit and the flexible cable are respectively integrated and then mounted on the structural frame through fasteners; the space utilization rate of the electronic equipment cabin is improved through deep integration of equipment distributed in a scattered state in the aircraft; a traditional cable is replaced by the FPC flexible cable, and the FPC flexible cable penetrates through the whole complex electronic equipment cabin with narrow space and extremely high assembly density according to the characteristic that the FPC flexible cable can be dynamically bent, so that flexible interconnection of the system is realized; electromagnetic protection design is carried out from the whole cabin, and the electromagnetic protection difficulty is reduced.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aircraft design, and particularly relates to a novel aircraft electronic equipment cabin applied to power supply and distribution management, flight attitude, navigation and control of various aerial guided aircrafts. BACKGROUND

[0002] At present, aerial guided aircrafts in China are various in type, different in function and rapidly developed. Due to the multiple types of equipment on the aircraft, the system integration degree is not high, which leads to low space utilization rate on the aircraft. The larger the distribution range of the avionics equipment is, the more complex the electromagnetic emission characteristics are, and the more difficult the electromagnetic protection is, which brings greater protection difficulty and challenge to RE and CE related electromagnetic compatibility tests. Moreover, the cable net on the traditional aircraft is a whole bundle of cables, which needs to penetrate the whole aircraft to realize the interconnection between various devices. The design is complex, and the soldering points of the wire harness and the connector are prone to false welding, short circuit and other welding problems. The production cycle is long, and it is difficult to mass-produce. The installation process of the complex cable net on the aircraft is difficult, and the cable is prone to be pulled and bent during assembly, which may cause welding point fracture quality problems, making it difficult to maintain and high in maintenance cost. In order to realize the new requirements of low cost, miniaturization, light weight, strong electromagnetic compatibility and stability and reliability of the aerial guided aircraft, the overall design of the equipment on the aircraft needs to be optimized. SUMMARY

[0003] In order to overcome the deficiencies in the prior art, the present application provides a novel aircraft electronic equipment cabin, which improves the space utilization rate of the electronic equipment cabin through deep integration of the equipment distributed in the aircraft. FPC flexible cable is used instead of traditional cable, and the flexible interconnection of the system is realized by using the dynamic bending characteristics of the FPC flexible cable to penetrate the whole complex, narrow space and high assembly density electronic equipment cabin. The electromagnetic protection design is carried out from the whole cabin to reduce the difficulty of electromagnetic protection.

[0004] The technical scheme provided by the present application is as follows:

[0005] A novel aircraft electronic equipment cabin, comprising a comprehensive control unit, an inertial measurement unit, a telemetry unit, a primary power supply unit, a flexible cable and a structural frame; the comprehensive control unit, the inertial measurement unit, the telemetry unit, the primary power supply unit and the flexible cable are each integrated and installed on the structural frame by fasteners;

[0006] The multi-module in the comprehensive control unit is stacked in layers and installed in the middle of the structural frame by fasteners, which is used for unified power distribution management of the aircraft system, collection of received measurement information during flight and completion of attitude control calculation, sending of rudder deflection instructions to control the aircraft attitude in real time.

[0007] The function modules of the inertial measurement unit are packaged in independent shells and mounted on the front end of the structural frame by fasteners, and are used for measuring the attitude, speed and position information of the aircraft and providing the information to the integrated control unit;

[0008] The function modules of the telemetry unit are packaged in independent shells and mounted on the bottom of the structural frame by fasteners, and are used for measuring the environmental parameters and working parameters of the aircraft during flight and providing the telemetry data to the ground receiving station;

[0009] The battery pack in the primary power supply unit is packaged in an independent shell and mounted on the rear end of the structural frame by fasteners, and is used for providing primary DC power for the systems on the aircraft after being activated by the integrated control unit;

[0010] The flexible cable penetrates through the entire electronic equipment cabin and realizes flexible interconnection of the devices in the electronic equipment cabin.

[0011] The novel aircraft electronic equipment cabin provided by the application has the following beneficial effects:

[0012] (1) The novel aircraft electronic equipment cabin provided by the application integrates the integrated control unit, the inertial measurement unit, the telemetry unit, the primary power supply unit and the flexible cable, and installs them on the structural frame by fasteners, thereby improving the space utilization of the electronic equipment cabin through deep integration of the devices distributed in the aircraft.

[0013] (2) The novel aircraft electronic equipment cabin provided by the application uses FPC flexible cables instead of traditional cables, and uses the dynamic bending characteristics of the FPC flexible cables to penetrate through the entire complex, narrow and high-density electronic equipment cabin, thereby realizing flexible interconnection of the system; the traditional cables will cause poor contact due to tension or vibration during the launch or high-speed flight of the aircraft, the FPC flexible cables have the characteristics of anti-vibration and high overload resistance, thereby ensuring stable transmission of signals and power supply, and meeting the high reliability requirements of the aircraft in harsh flight environments; the light and thin characteristics of the FPC flexible cables can realize the weight reduction requirement of the aircraft, and the lightweight electronic equipment cabin provides performance improvement space for the damage unit or power unit of the aircraft.

[0014] (3) The novel aircraft electronic equipment cabin provided by the application is designed for electromagnetic protection from the entire cabin, and each unit is well connected to the structural shell, thereby providing a stable low-impedance loop, enabling the interference noise to be quickly discharged to the shell, reducing the crosstalk and noise interference on the signal line, improving the integrity and anti-interference ability of the signal, and ensuring the stability and reliability of the flight control and execution system of the aircraft, thereby solving the problems of traditional avionics equipment, such as dispersion, complex electromagnetic emission characteristics, great electromagnetic protection difficulty, and long-distance transmission of control lines being easily coupled and interfered by electromagnetic noise.

[0015] (4) The application provides a novel aircraft electronic equipment cabin, each unit adopts modular design, rapid replacement of the aircraft electronic equipment cabin can be realized, use requirements of multiple types of aircrafts are met, the aircraft has higher striking precision and combat flexibility, late maintenance is simple, and maintenance cost is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a structural layout diagram of the novel aircraft electronic equipment cabin.

[0017] DETAILED DESCRIPTION

[0018] 1-comprehensive control unit; 2-inertial measurement unit; 3-telemetry unit; 4-primary power supply unit; 5-flexible cable; 6-structural frame. DETAILED DESCRIPTION

[0019] The characteristics and advantages of the application will become more apparent from the following detailed description of the application.

[0020] The special word 'exemplary' herein means 'as an example, embodiment or illustration'. Any embodiment described herein as 'exemplary' is not necessarily to be construed as being superior to or better than other embodiments.

[0021] DETAILED DESCRIPTION Figure 1 The application provides a novel aircraft electronic equipment cabin, which comprises a comprehensive control unit 1, an inertial measurement unit 2, a telemetry unit 3, a primary power supply unit 4, a flexible cable 5 and a structural frame 6; the comprehensive control unit 1, the inertial measurement unit 2, the telemetry unit 3, the primary power supply unit 4 and the flexible cable 5 are each integrated and then installed on the structural frame 6 through fasteners.

[0022] The multi-module is layered and stacked in the comprehensive control unit 1, is installed in the middle part of the structural frame 6 through fasteners, is used for unified power distribution management of an aircraft system, collects and receives measurement information in a flight process and completes attitude control calculation, sends rudder deflection instructions to control a rudder machine to correct an aircraft attitude in real time;

[0023] Each functional module in the inertial measurement unit 2 is packaged in an independent shell through vibration reduction design and is installed at the front end of the structural frame 6 through fasteners, is used for measuring attitude, speed and position information of the aircraft, and provides reliable key data for the comprehensive control unit 1;

[0024] Each functional module in the telemetry unit 3 is packaged in an independent shell and is installed at the bottom of the structural frame 6 through fasteners, is used for telemetry of environmental parameters (such as pressure and flight height) and working parameters (such as power supply voltage, rudder deflection information and navigation information) of the aircraft in a flight process, and provides telemetry data to a ground receiving station;

[0025] The battery pack in the primary power supply unit 4 is packaged in a separate shell, is installed at the rear end of the structural frame 6 through fasteners, and provides primary direct-current power for the system on the aircraft after being activated by the integrated control unit 1.

[0026] The flexible cable 5 is used to pass through the entire electronic equipment cabin which is complex, narrow in space and high in assembly density, and realizes flexible interconnection of the equipment in the electronic equipment cabin by using the dynamic bending characteristics.

[0027] In the application, the integrated control unit 1 comprises a main control module, a power management module, a communication interface module, an activation control module and a rudder drive control module; the main control module is used for sending control instructions, information processing and calculation; the power management module is used for power filtering and system secondary power conversion; the communication interface module is used for data communication between the integrated control unit 1 and other units; the activation control module is used for controlling external device switches through P-channel MOS transistors; and the rudder drive control module is used for controlling rudder actuators.

[0028] The main control module comprises a main processor, a field programmable gate array logic device, a data storage, a reset chip, a crystal oscillator and a multi-channel DC / DC stabilizer; the main processor is used for main control module information processing; the data storage is used for storing flight control programs; the reset chip is used for providing a reset signal for the main control module; the crystal oscillator is used for providing a clock signal for the main control module; and the multi-channel DC / DC stabilizer is used for power supply for the main control module.

[0029] The power management module comprises an input-output filter and a secondary isolation power supply; the input-output filter is used for power filtering; and the secondary isolation power supply is used for system secondary power conversion.

[0030] The communication interface module comprises a serial interface transceiver, a CAN bus and a 1553B bus; the serial interface transceiver is used for realizing data sending and receiving on a serial communication interface; the CAN bus is used for communication between devices with low real-time requirements; and the 1553B bus is used for communication between devices with high real-time requirements.

[0031] The rudder drive control module comprises a potentiometer acquisition module and a pulse width modulation signal power amplification module; the potentiometer acquisition module is used for acquiring potentiometer signals of the rudder actuators; and the pulse width modulation signal power amplification module is used for driving motors of the rudder actuators.

[0032] In the application, the inertial measurement unit 2 comprises a micro gyroscope, an accelerometer and a signal processing module in a shell; the micro gyroscope is used for measuring angular rate of the aircraft; the accelerometer is used for measuring acceleration of the aircraft; and the signal processing module is used for conditioning and converting angular rate and acceleration signals to supply the integrated control unit 1.

[0033] In the present application, the telemetry unit 3 comprises a signal modulation module and a wireless transmitter in the shell, the signal modulation module is used for converting telemetry data into high frequency signals for specific channel transmission, and the wireless transmitter is used for transmitting the modulated signals to the ground receiving station.

[0034] In the present application, the flexible cable 5 is a FPC flexible cable, which adopts a high-performance polymer film as a base material, and a copper foil trace is formed on the base material by etching, which is used for conducting current and signals, and the dynamic bending characteristic is used to penetrate the entire complex, narrow space and high assembly density electronic equipment cabin, to realize flexible interconnection of the system

[0035] The aircraft electronic equipment cabin deeply integrates the equipment distributed in the aircraft, the integrated control unit integrates multiple sensing functions, realizes high integration of navigation, guidance and flight control, and uses the dynamic bending characteristic of the FPC flexible cable to penetrate the entire complex, narrow space and high assembly density aircraft electronic equipment cabin, to realize flexible interconnection of the system. The FPC flexible cable is connected to the high-density rectangular connector at the front and rear ends of the electronic equipment cabin, the rectangular connector is connected with external sensors and rudder actuators as a communication and power supply interface, to complete unified power supply management of the aircraft system, activation control, and multiple tasks such as collecting and receiving measurement information during flight, completing attitude control calculation, sending rudder deflection instructions to control rudder to correct the attitude of the aircraft, etc.

[0036] The present application has been described in detail in combination with specific embodiments and exemplary examples, but these descriptions cannot be understood as limitations of the present application. Those skilled in the art understand that the technical solutions and embodiments of the present application can be variously replaced, modified or improved without departing from the spirit and scope of the present application, and these all fall within the scope of the present application. The protection scope of the present application is subject to the appended claims.

[0037] The contents not described in detail in the specification of the present application are the known technology of those skilled in the art.

Claims

1. A novel aircraft electronics bay, characterized in that, It includes an integrated control unit (1), an inertial measurement unit (2), a telemetry unit (3), a primary power supply unit (4), a flexible cable (5), and a structural frame (6); the integrated control unit (1), the inertial measurement unit (2), the telemetry unit (3), the primary power supply unit (4), and the flexible cable (5) are each integrated and installed on the structural frame (6) by fasteners; The integrated control unit (1) has multiple modules stacked in layers and installed in the middle of the structural frame (6) by fasteners. It is used for unified power distribution management of the aircraft system, collecting and receiving measurement information during flight and completing attitude control calculation, and sending rudder deflection commands to control the servo motor to correct the aircraft attitude in real time. Each functional module in the inertial measurement unit (2) is encapsulated in an independent shell with vibration reduction design and is installed at the front end of the structural frame (6) by fasteners. It is used to measure the attitude, speed and position information of the aircraft and provide it to the integrated control unit (1). Each functional module in the telemetry unit (3) is encapsulated in an independent shell and installed at the bottom of the structural frame (6) by fasteners. It is used for telemetry of environmental parameters and working parameters during the flight of the aircraft and provides telemetry data to the ground receiving station. The battery pack in the primary power supply unit (4) is encapsulated in an independent housing and installed at the rear end of the structural frame (6) by fasteners. After being activated by the integrated control unit (1), it provides primary DC power to the systems on the aircraft. The flexible cable (5) runs through the entire electronic equipment compartment, completing the flexible interconnection of various devices in the electronic equipment compartment.

2. The novel aircraft electronic equipment bay according to claim 1, characterized in that, The integrated control unit (1) includes a main control module, a power management module, a communication interface module, an activation control module, and a servo drive control module; the main control module is used to send control commands, process information, and perform calculations. The power management module is used for power filtering and secondary power conversion in the system. The communication interface module is used for data communication between the integrated control unit (1) and other units; The activation control module is used to control the switching of external devices via P-channel MOS transistors; the servo drive control module is used to control the servo actuator.

3. The novel aircraft electronic equipment bay according to claim 2, characterized in that, The main control module includes a main processor, a field-programmable gate array (FPGA) logic device, a data memory, a reset chip, a crystal oscillator, and a multi-channel DC / DC regulator. The main processor is used for information processing in the main control module; the data memory is used to store flight control programs; the reset chip is used to provide a reset signal to the main control module; the crystal oscillator is used to provide a clock signal to the main control module; and the multi-channel DC / DC regulator is used to power the main control module.

4. The novel aircraft electronic equipment bay according to claim 2, characterized in that, The power management module includes an input / output filter and a secondary isolation power supply. The input / output filter is used for power filtering, and the secondary isolation power supply is used for secondary power conversion in the system.

5. The novel aircraft electronic equipment bay according to claim 2, characterized in that, The communication interface module includes a serial interface transceiver, a CAN bus, and a 1553B bus. The serial interface transceiver is used to send and receive data on the serial communication interface, while the CAN bus and 1553B bus are used for communication between devices.

6. The novel aircraft electronic equipment bay according to claim 2, characterized in that, The servo drive control module includes a potentiometer acquisition module and a pulse width modulation signal power amplification module. The potentiometer acquisition module is used to acquire the potentiometer signal of the servo actuator, and the pulse width modulation signal power amplification module is used to drive the motor of the servo actuator.

7. The novel aircraft electronics bay according to claim 1, characterized in that, The inertial measurement unit (2) includes a miniature gyroscope, an accelerometer, and a signal processing module located inside the housing. The miniature gyroscope is used to measure the angular rate of the aircraft; the accelerometer is used to measure the acceleration of the aircraft; and the signal processing module is used to condition and convert the angular rate and acceleration signals and supply them to the integrated control unit (1).

8. The novel aircraft electronics bay according to claim 1, characterized in that, The telemetry unit (3) includes a signal modulation module and a wireless transmitter located inside the housing. The signal modulation module is used to convert telemetry data into signals for transmission through a specific channel; the wireless transmitter is used to transmit the modulated signals to the ground receiving station.

9. The novel aircraft electronics bay according to claim 1, characterized in that, The flexible cable (5) is an FPC flexible cable, which uses a high-performance polymer film as a substrate and etches copper foil traces on the substrate for conducting current and signals. High-density rectangular connectors are connected to the FPC flexible cables at both ends of the electronic equipment compartment. The rectangular connectors serve as communication and power supply interfaces and are connected to external sensors and servo actuators.

10. The novel aircraft electronics bay according to claim 1, characterized in that, The integrated control unit (1), inertial measurement unit (2), telemetry unit (3) and primary power supply unit (4) are all connected to the structural shell ground.

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