Avionics system of electric aircraft

Abstract

The invention relates to the field of avionics systems, and discloses an avionics system of an electric aircraft, which comprises an indication recording unit, a communication unit, a navigation unit and an electric propulsion acquisition unit, and the communication unit, the navigation unit and the electric propulsion acquisition unit are electrically connected with the indication recording unit. The indication recording unit is used for displaying, recording and processing flight parameters, and the communication unit is used for communicating with other aircrafts and a ground station. The navigation unit is used for collecting attitude parameters of the airplane and external atmospheric environment parameters and automatically receiving and responding to inquiry signals of the ground station. The electric propulsion acquisition unit is used for acquiring parameters of a propulsion motor, a motor controller and a battery pack. According to the avionics system of the electric aircraft, parameters of the propulsion motor, the motor controller and the battery pack in the electric propulsion system can be collected through the electric propulsion collection unit, the collected information is integrated into the indication recording unit to be displayed, a pilot can conveniently monitor the state of the electric propulsion system, and the avionics system is suitable for the electric aircraft.

Description

Technical Field

[0001] The present invention relates to the field of avionics systems, and in particular to an avionics system for an electric aircraft. Background Art

[0002] The integrated avionics system is developed in contrast to the traditional discrete instrument system. It integrates the flight instruments, engine instruments, fuel instruments and navigation instruments that were originally displayed independently into one display for information display and management. For general aircraft, the integrated avionics system is used by pilots to monitor the aircraft status, communicate with the ground or other aircraft, guide the flight, store flight records, and ensure safer and more efficient flight of the aircraft.

[0003] Existing avionics systems are all designed for traditional fuel-powered aircraft. With the rapid development of battery technology, it has become possible to realize electric aircraft that use electric motors as the source of flight power. Traditional avionics systems are not suitable for electric aircraft, and it is necessary to develop an avionics system suitable for electric aircraft. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, an object of the present invention is to provide an avionics system for an electric aircraft, which can collect and process parameters of an electric propulsion system and is suitable for an electric aircraft.

[0005] To solve the above problems, the technical solution adopted by the present invention is as follows: an avionics system of an electric aircraft, comprising: an indication and recording unit, used for displaying, recording and processing flight parameters; a communication unit, electrically connected to the indication and recording unit, used for communicating with other aircraft and ground stations; a navigation unit, electrically connected to the indication and recording unit, used for collecting the aircraft's attitude parameters and external atmospheric environment parameters, and automatically receiving and responding to the inquiry signal of the ground station; an electric propulsion collection unit, electrically connected to the indication and recording unit, used for collecting parameters of the propulsion motor, motor controller and battery pack.

[0006] Compared with the prior art, the beneficial effect of the present invention is that the parameters of the propulsion motor, motor controller and battery pack can be collected through the electric propulsion collection unit, so that the status of the electric propulsion system can be integrated into the indication and recording unit for display, which is convenient for the pilot to monitor the status of the electric propulsion system. It is suitable for electric aircraft that use motors and batteries as power sources.

[0007] The avionics system of the above-mentioned electric aircraft, the indication and recording unit includes an integrated display controller, an electric propulsion system parameter acquisition processor and a power distribution and protection device, the power distribution and protection device is electrically connected to the integrated display controller, the electric propulsion acquisition unit is electrically connected to the integrated display controller through the electric propulsion system parameter acquisition processor, the communication unit and the navigation unit are electrically connected to the integrated display controller, the integrated display controller is used to display, record and process the obtained flight parameters, and the electric propulsion system parameter acquisition processor is used to convert the analog quantity output by the electric propulsion acquisition unit into a digital quantity and then transmit it to the integrated display controller.

[0008] In the avionics system of the above-mentioned electric aircraft, the integrated display and controller is electrically connected to the communication subsystem, the electric propulsion system parameter acquisition processor, the navigation unit and the power distribution and protection device through a CAN bus.

[0009] In the avionics system of the above-mentioned electric aircraft, the communication unit includes a very high frequency radio, an earphone microphone assembly and a radio antenna, the radio antenna and the earphone microphone assembly are electrically connected to the very high frequency radio, and the very high frequency radio is electrically connected to the indication and recording unit.

[0010] The avionics system of the above-mentioned electric aircraft, the navigation unit includes a pitot tube, an atmospheric data processor, an atmospheric temperature sensor, a heading reference system, a transponder and a transponder antenna, the pitot tube is telecommunication-connected to the atmospheric temperature sensor and the atmospheric data processor, the transponder antenna is electrically connected to the transponder, the atmospheric data processor, the heading reference system and the transponder are all electrically connected to the indication and recording unit, and the atmospheric data processor is used to convert the analog quantities output by the pitot tube and the atmospheric temperature sensor into digital quantities and then transmit them to the indication and recording unit.

[0011] In the above-mentioned avionics system of the electric aircraft, the transponder is an S-mode transponder.

[0012] The avionics system of the above-mentioned electric aircraft, the electric propulsion acquisition unit includes a motor sensor group, a controller sensor group and a battery sensor group, the motor sensor group is used to collect parameters of the propulsion motor, the controller sensor group is used to collect parameters of the motor controller, and the battery sensor is used to collect parameters of the battery group, and the motor sensor group, the controller sensor group and the battery sensor group are all electrically connected to the indication and recording unit.

[0013] In the above-mentioned avionics system of the electric aircraft, the motor sensor group includes a motor speed sensor and a motor temperature sensor.

[0014] In the above-mentioned avionics system of the electric aircraft, the controller sensor group includes a controller temperature sensor.

[0015] In the above-mentioned avionics system of the electric aircraft, the battery sensor group includes a power sensor, a voltage sensor, a current sensor and a battery temperature sensor.

[0016] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 4 is a principle block diagram of an avionics system of an electric aircraft according to an embodiment of the present invention. DETAILED DESCRIPTION

[0018] The embodiments of the present invention are described in detail below. Figure 1 An embodiment of the present invention provides an avionics system for an electric aircraft, including an indication and recording unit, a communication unit, a navigation unit, and an electric propulsion acquisition unit. The communication unit, the navigation unit, and the electric propulsion acquisition unit are all electrically connected to the indication and recording unit, and the indication and recording unit is used to display, record, and process flight parameters. The communication unit is used to communicate with other aircraft and ground stations, the navigation unit is used to collect aircraft attitude parameters and external atmospheric environment parameters, automatically receive and respond to inquiry signals from the ground station, and the electric propulsion acquisition unit is used to collect parameters of the propulsion motor, motor controller, and battery pack.

[0019] The avionics system of the electric aircraft in the embodiment of the present invention can collect parameters of the motor, motor controller and battery pack of the electric propulsion system of the electric aircraft through the electric propulsion collection unit, so that the status of the electric propulsion system can be integrated into the indication and recording unit for display, which is convenient for the pilot to monitor the status of the electric propulsion system. It is suitable for light electric aircraft that use motors and batteries as power sources, can reduce the number of instruments in the electric aircraft, facilitate equipment maintenance and improvement, and can exert better utilization efficiency.

[0020] Reference Figure 1In this embodiment, the indication and recording unit includes an integrated display controller, an electric propulsion system parameter acquisition processor, and a power distribution and protection device. The power distribution and protection device is used to supply power to the integrated display controller. The electric propulsion acquisition unit is electrically connected to the integrated display controller through the electric propulsion system parameter acquisition processor. The electric propulsion system parameter acquisition processor is used to collect the analog quantity output by the electric propulsion acquisition unit, and convert these analog quantities into digital quantities and transmit them to the integrated display controller. The communication unit and the navigation unit are electrically connected to the integrated display controller. The integrated display controller is an integrated machine of a controller and a display with internally integrated memory, Bluetooth, WIFI, TF memory card and other interfaces. In this embodiment, the communication unit, the navigation unit, the electric propulsion acquisition unit, the power distribution and protection device and other units or devices are electrically connected through the CAN bus to communicate, and the data collected from each unit and device are visualized and displayed. The power distribution and protection device is a device that can allocate multiple low-voltage power supplies to airborne equipment and provide overload protection. The current threshold setting and real-time electric energy value of each circuit are displayed through the integrated display controller, and manual reset after overload can be performed through the integrated display controller.

[0021] Reference Figure 1 In this embodiment, the communication unit includes a VHF radio, an earphone microphone assembly and a radio antenna. The radio antenna and the earphone microphone assembly are electrically connected to the VHF radio. The VHF radio is electrically connected to the integrated display controller, and parameters such as the frequency range and transmission power of the VHF radio can be displayed through the integrated display controller.

[0022] Reference Figure 1 In this embodiment, the navigation unit includes a pitot tube, an atmospheric data processor, an atmospheric temperature sensor, an attitude reference system, a transponder, and a transponder antenna. The pitot tube and the atmospheric temperature sensor are both electrically connected to the atmospheric data processor, the transponder and the transponder antenna are electrically connected, and the attitude reference system, the atmospheric data processor, and the transponder are all electrically connected to the integrated display and controller. The atmospheric data processor is used to convert the analog quantity output by the pitot tube and the atmospheric temperature sensor into a digital quantity and then transmit it to the integrated display and controller. The pitot tube is used to detect the total pressure and static pressure of the external atmosphere. The attitude reference system includes multiple axial sensors for detecting the roll and rollover information of the aircraft. The transponder is used to automatically identify and respond to the inquiries of the secondary radar of the ground station. In this embodiment, the transponder is an S-mode transponder.

[0023] Reference Figure 1In this embodiment, the electric propulsion acquisition unit includes a motor sensor group, a controller sensor group and a battery sensor group, which are all electrically connected to the electric propulsion system parameter acquisition processor and are used to collect parameters of the propulsion motor, the motor controller and the battery group respectively. The motor sensor group includes a motor speed sensor and a motor temperature sensor, the controller sensor group includes a controller temperature sensor, and the battery sensor group includes a power sensor, a voltage sensor, a current sensor and a battery temperature sensor. The electric propulsion acquisition unit collects information such as motor speed, motor temperature, motor controller temperature, battery temperature and battery charge state through the above sensors, and transmits it to the integrated display controller for real-time graphical display.

[0024] It should be noted that in the description of the present invention, if there are any orientation descriptions, such as up, down, front, back, left, right, etc., the orientations or positional relationships indicated are all based on the orientations or positional relationships shown in the drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed or operated in a specific orientation, and cannot be understood as a limitation on the present invention.

[0025] In the description of the present invention, "several" means one or more, "more" means two or more, "greater than", "less than", "exceed" etc. are understood to exclude the number itself, and "above", "below", "within" etc. are understood to include the number itself. If there is a description of "first" or "second", it is only used to distinguish the technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0026] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0027] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. An avionics system for an electric aircraft, characterized in that: include: Indication and recording unit, used for displaying, recording and processing flight parameters; a communication unit, electrically connected to the indication recording unit, for communicating with other aircraft and a ground station; A navigation unit, electrically connected to the indication and recording unit, for collecting aircraft attitude parameters and external atmospheric environment parameters, and automatically receiving and responding to interrogation signals from a ground station; The electric propulsion acquisition unit is electrically connected to the indication recording unit and is used to acquire parameters of the propulsion motor, the motor controller and the battery pack.

2. The avionics system of the electric aircraft according to claim 1, characterized in that: The indication and recording unit includes an integrated display and controller, an electric propulsion system parameter acquisition processor and a power distribution and protection device. The power distribution and protection device is electrically connected to the integrated display and controller. The electric propulsion acquisition unit is electrically connected to the integrated display and controller through the electric propulsion system parameter acquisition processor. The communication unit and the navigation unit are electrically connected to the integrated display and controller. The integrated display and controller is used for displaying, recording and processing the obtained flight parameters. The electric propulsion system parameter acquisition processor is used for converting the analog quantity output by the electric propulsion acquisition unit into a digital quantity and then transmitting it to the integrated display and controller.

3. The avionics system of the electric aircraft according to claim 2, characterized in that: The integrated display and controller is electrically connected to the communication subsystem, the electric propulsion system parameter acquisition processor, the navigation unit and the power distribution and protection device through a CAN bus.

4. The avionics system of the electric aircraft according to claim 1, characterized in that: The communication unit comprises a very high frequency radio, an earphone microphone assembly and a radio antenna. The radio antenna and the earphone microphone assembly are electrically connected to the very high frequency radio, and the very high frequency radio is electrically connected to the indication and recording unit.

5. The avionics system of the electric aircraft according to claim 1, characterized in that: The navigation unit includes a pitot tube, an atmospheric data processor, an atmospheric temperature sensor, a heading reference system, a transponder and a transponder antenna. The pitot tube is telecommunication-connected to the atmospheric temperature sensor and the atmospheric data processor, the transponder antenna is electrically connected to the transponder, the atmospheric data processor, the heading reference system and the transponder are all electrically connected to the indication and recording unit, and the atmospheric data processor is used for converting analog quantities output by the pitot tube and the atmospheric temperature sensor into digital quantities and then transmitting the digital quantities to the indication and recording unit.

6. The avionics system of the electric aircraft according to claim 5, characterized in that: The transponder is a Mode S transponder.

7. The avionics system of the electric aircraft according to claim 1, characterized in that: The electric propulsion acquisition unit includes a motor sensor group, a controller sensor group and a battery sensor group. The motor sensor group is used to collect parameters of the propulsion motor, the controller sensor group is used to collect parameters of the motor controller, and the battery sensor is used to collect parameters of the battery group. The motor sensor group, the controller sensor group and the battery sensor group are all electrically connected to the indication and recording unit.

8. The avionics system of the electric aircraft according to claim 7, characterized in that: The motor sensor group includes a motor speed sensor and a motor temperature sensor.

9. The avionics system of the electric aircraft according to claim 7, characterized in that: The controller sensor group includes a controller temperature sensor.

10. The avionics system of the electric aircraft according to claim 7, characterized in that: The battery sensor group includes a power sensor, a voltage sensor, a current sensor and a battery temperature sensor.

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