CN-122024531-A - Avionics system architecture based on wireless communication

CN122024531ACN 122024531 ACN122024531 ACN 122024531ACN-122024531-A

Abstract

The invention provides an avionics system architecture based on wireless communication, which relates to the technical field of unmanned aerial vehicles and comprises a central flight control unit for generating flight control instructions, a main communication module connected with the central flight control unit and a plurality of power systems distributed on an aircraft body; according to the invention, by completely eliminating the physical signal cable between the central flight control unit and the power system, the fault modes such as cable abrasion, circuit breaking, poor connector contact and the like caused by machine body vibration are eliminated, the single-point fault probability is reduced, and the flight safety is improved.

Inventors

HE YANFENG
JIANG GUOLONG

Assignees

苏州九十度航空科技有限公司

Dates

Publication Date: 20260512
Application Date: 20260401

Claims (9)

1. The avionics system architecture based on wireless communication is characterized by comprising a central flight control unit, a main communication module and a plurality of power systems, wherein the central flight control unit is used for generating flight control instructions, the main communication module is connected with the central flight control unit, the power systems are distributed on an aircraft body, each power system is integrated with a power communication module, an electronic speed regulator and a motor, no physical signal cable is connected between the central flight control unit and the power systems, a wireless communication link is established between the main communication module and each power communication module, and control instructions generated by the central flight control unit are converted into wireless signals through the main communication module and transmitted, and are received and demodulated by each power communication module to control the corresponding electronic speed regulator to drive the motor to operate.
2. The avionics system architecture based on wireless communication of claim 1, wherein the wireless communication links comprise a first wireless communication link operating in a first frequency band and a second wireless communication link operating in a second frequency band, the center frequency of the first frequency band being lower than the center frequency of the second frequency band; the main communication module selects to transmit data through the first wireless communication link according to the channel quality, selects to transmit data through the second wireless communication link according to the channel quality, or simultaneously transmits redundant data through the first wireless communication link and the second wireless communication link.
3. The avionics system architecture based on wireless communication of claim 1, wherein the central flight control unit is integrated with a master clock source through which clock synchronization is performed, the clock synchronization comprising: The method comprises the steps of initializing clock calibration, wherein the central flight control unit periodically broadcasts a synchronous packet containing the current main clock source moment to each power system, and each power system calculates clock offset with the central flight control unit through a round trip time measuring method and establishes a logic clock synchronous with the central flight control unit according to the clock offset; The link quality monitoring, wherein the main communication module continuously monitors the transmission characteristic of a wireless link and calculates the execution advance according to the historical transmission delay mean value, the standard deviation of delay jitter, the reliability coefficient and the processing time consumption of a power system; the synchronous judgment and instruction execution comprises the steps that the central flight control unit calculates a target execution time stamp, the target execution time stamp is equal to the sum of the current main clock time and the execution advance, then each power system compares a logic clock of the power system with the target execution time stamp after receiving a control instruction, the execution mode comprises the steps that the instructions of each power system are stored in a buffer until the logic clock reaches the target execution time stamp to be executed when the logic clock is earlier than the target execution time stamp, the instructions are forcedly executed by each power system when the logic clock is equal to the target execution time stamp, and the instructions are forcedly executed by each power system when the logic clock is later than the target execution time stamp under the specific condition, and meanwhile asynchronous prompts are returned to the central flight control unit through a wireless communication link.
4. The avionics system architecture based on wireless communication of claim 3, wherein initializing the clock calibration comprises: the central flight control unit sends out a request at a first moment, the power system receives the request at a second moment and replies at a third moment, and the central flight control unit receives the reply at a fourth moment; Calculating the difference between the difference of the fourth moment minus the first moment and the difference of the third moment minus the second moment to obtain the round trip time; then the clock offset is obtained by subtracting the calculation of the second moment from the sum of the first moment and half of the round trip time; And finally, calculating the logic clock of the power system through the sum of the local clock of the power system and the clock offset.
5. The avionics system architecture based on wireless communication of claim 3, wherein the execution advance satisfies the following relationship: the execution advance is equal to the sum of the historical transmission delay average value and the first product and the logic processing time consumption of the power system; the first product is equal to the reliability coefficient multiplied by the standard deviation of the delay jitter; The reliability coefficient is a positive number greater than or equal to 3.
6. The avionics system architecture based on wireless communication of claim 3, further performing anomaly prompting and alert classification, the anomaly prompting and alert classification step comprising: when the power system monitors that the logic clock is later than the target execution time stamp, the power system returns an asynchronous prompt to the central flight control unit while executing the instruction forcefully; And under the condition that the asynchronous prompt is triggered in a continuous preset number of control periods, the system judges that the link quality does not meet the safety requirement and sends out a serious alarm.
7. The avionics system architecture based on wireless communication of claim 2, wherein the main communication module and the power communication module are pre-configured with the same pseudo-random sequence; The main communication module and the power communication module are configured to perform synchronous frequency hopping within the bandwidth range of the first frequency band according to the pseudo-random sequence in the communication process; the main communication module and the power communication module are configured to perform synchronous frequency hopping within the bandwidth range of the second frequency band according to the pseudo-random sequence in the communication process.
8. The avionics system architecture based on wireless communication of claim 1, wherein the power system only maintains a DC power interface for connecting with an onboard power source, and the power system obtains electric energy for driving a motor and powering the power communication module through the DC power interface.
9. The avionics system architecture based on wireless communication of claim 1, further comprising a multi-frequency high-gain flexible antenna configured to provide communication conditions for a central flight control unit and a power system, the multi-frequency high-gain flexible antenna being embedded in a surface of the aircraft body.

Description

Avionics system architecture based on wireless communication Technical Field The invention relates to the technical field of unmanned aerial vehicles, in particular to an avionics system architecture based on wireless communication. Background Avionic systems are called avionics systems for short, are the general term for all electronic systems on an aircraft, and cover communication, navigation, display, management and multiple task systems, and are used for guaranteeing flight safety, completing flight tasks and providing pilot interaction interfaces, and the reliability, response speed and architecture rationality of the avionic systems directly determine the flight safety and performance of the aircraft. In practical use, the existing avionics system has the following disadvantages, such as: In the aspect of flight safety, in the existing avionic architecture based on physical cable connection, signal transmission is realized between a flight control computer and each electronic speed regulator through point-to-point hard connection, the physical cable is easy to wear due to high-frequency vibration in the flight process of an aircraft, a connector is easy to loose or poor in contact, power loss and out-of-control accidents are caused due to the fact that any one key signal line is broken or short-circuited, single-point failure probability is obviously increased due to the fact that a large number of cables and the connector exist, and average failure-free time of the whole system is severely restricted; in terms of synchronous control and reliability, although the traditional wired architecture has no delay jitter problem of wireless transmission, a large number of cables are laid in parallel with high-voltage power cables in a limited body space, even if shielding measures are adopted, electromagnetic coupling among physical cables under high-power working conditions can still cause jitter or loss of control signals, the architecture completely passes through the reliability of physical connectors, and a redundancy mechanism for signal link faults is lacking, when a certain connector has intermittent poor contact due to vibration or aging, the system cannot maintain reliable transmission of control instructions through a standby path; In the aspect of structural design and maintainability, the cable avionics architecture enables the machine body structural design to be highly coupled with avionics layout, a designer must reserve complex wiring channels and threading holes in the inner parts of a horn and a machine body, the structural integrity of a composite material is destroyed, the freedom degree of pneumatic appearance design is limited, threading, crimping terminals and welding connectors are required to be completed manually in a large number in a production link, automatic assembly is difficult to realize, a large number of machine body structures can be disassembled to check and replace wiring harnesses once line faults occur during maintenance, the maintenance period is long, the full life cycle cost is high, and meanwhile, a large number of copper core signal cables, shielding layers and metal connectors form significant dead weight of the structure, so that the effective load and the cruising ability of the aircraft are directly weakened. The present invention therefore proposes an avionics system architecture based on wireless communication to solve the above-mentioned problems. Disclosure of Invention The invention aims to solve the defects in the prior art and provides an avionics system architecture based on wireless communication. In order to achieve the purpose, the avionic system framework based on wireless communication comprises a central flight control unit for generating flight control instructions, a main communication module connected with the central flight control unit and a plurality of power systems distributed on an aircraft body, wherein each power system is integrated with a power communication module, an electronic speed regulator and a motor, no physical signal cable is connected between the central flight control unit and the power systems, a wireless communication link is established between the main communication module and each power communication module, and control instructions generated by the central flight control unit are converted into wireless signals through the main communication module and sent to be received and demodulated by each power communication module so as to control the corresponding electronic speed regulator to drive the motor to operate. Further, the wireless communication link comprises a first wireless communication link working in a first frequency band and a second wireless communication link working in a second frequency band, and the center frequency of the first frequency band is lower than that of the second frequency band; the main communication module selects to transmit data through the first wireless communication link accordin