CN-120756693-B - Unmanned aerial vehicle power management and information monitoring system

CN120756693BCN 120756693 BCN120756693 BCN 120756693BCN-120756693-B

Abstract

The invention relates to an unmanned aerial vehicle power supply management and information monitoring system which comprises power supply management and information monitoring equipment, wherein the power supply management and information monitoring equipment is connected among an unmanned aerial vehicle power supply, an unmanned aerial vehicle flight control and an unmanned aerial vehicle load set, a unified power supply management module is integrated in the power supply management and information monitoring equipment and is used for receiving electric energy of the unmanned aerial vehicle power supply and providing one or more kinds of transformed stable power supply for the unmanned aerial vehicle load set, and an information and control hub module is used as an information and control relay between the unmanned aerial vehicle flight control and unmanned aerial vehicle load set and a sensor. The invention aims to solve the problems of complex flight control interface, excessive operation load, low system integration and insufficient reliability caused by power supply decentralized management caused by direct data and control interaction between a plurality of airborne devices and a flight controller in the existing unmanned aerial vehicle system.

Inventors

Lv Ziang
SONG HUI
WU ZONGWANG
GUO XINYUAN

Assignees

力泰航空设备(广州)有限公司

Dates

Publication Date: 20260508
Application Date: 20250905

Claims (9)

1. An unmanned aerial vehicle power management and information monitoring system, comprising: a power management and information monitoring device (200), the power management and information monitoring device (200) being connected between a drone power supply (100), a drone flight control (300) and a drone load set (400); wherein, the power management and information monitoring device (200) is internally integrated with: the unified power supply management module is used for receiving the electric energy of the unmanned aerial vehicle power supply (100) and providing one or more transformed stable power supplies for the unmanned aerial vehicle load set (400); The information and control hub module is used as an information and control relay between the unmanned aerial vehicle flight control (300) and the unmanned aerial vehicle load set (400) and sensors; wherein the information and control hub module is configured to: collecting equipment state information related to the unmanned plane load set (400) and the sensor, integrating and packaging the equipment state information and then sending the packaged equipment state information to the unmanned plane flight control (300), and Receiving a control instruction from the unmanned aerial vehicle flight control (300), and generating a corresponding control signal based on the control instruction to control an execution mechanism in the unmanned aerial vehicle load set (400); the singlechip (208) in the information and control hub module is also configured to: executing a dynamic power consumption allocation mechanism, which is specifically configured to: The method comprises the steps of performing time integration on the collected total current of a main power supply bus, and performing calibration by combining real-time voltage with a pre-stored battery open circuit voltage-SoC characteristic curve, and calibrating a state of charge calculation result obtained through time integration when the unmanned aerial vehicle is light in load so as to estimate the state of charge of the unmanned aerial vehicle power supply (100); Calculating an estimated remaining operating time by multiplying the difference between the current estimated state of charge and a set safe charge threshold by the rated capacity of the power supply, and dividing by the average operating current obtained by running average calculation of the recent total current; According to the current task stage information received from the unmanned aerial vehicle flight control (300), inquiring a task-load priority mapping table stored in a nonvolatile memory in the singlechip (208) so as to determine the necessity level of a specific load; Selectively controlling power on and power off of specific loads in the unmanned aerial vehicle load set (400) based on an estimation result of the state of charge of the unmanned aerial vehicle power supply (100), the estimated remaining operation duration and the determined necessity level and according to an energy state decision matrix; The energy state decision matrix prescribes that if a certain load priority is high, power supply is kept no matter how the energy state is, and if the priority is low and the state of charge is lower than a preset energy saving threshold value, a turn-off operation is executed; And Executing a load health monitoring mechanism specifically configured to: Recording the current range of each load in the unmanned plane load set (400) in a normal working mode in a system initialization stage so as to establish a current characteristic baseline in the normal working state; Monitoring the actual working current of the load in real time in operation, comparing the actual working current with a current characteristic baseline to judge whether the load has a hard fault or a soft fault with performance degradation, and executing differentiated response operation based on a judging result: If the actual current is judged to be far beyond the hard fault of the upper limit of the reference base line, the SCM (208) cuts off the power supply of the controllable power supply branch to immediately execute fault isolation operation through the power supply control module (204), and generates and reports fault position and type fault alarm information containing the load to the unmanned aerial vehicle flight control (300); If the actual current is determined to be continuous and slightly deviates from the soft fault of the performance decline of the reference baseline, the power supply is not immediately cut off, a piece of maintenance recommended information is generated and sent to the unmanned aerial vehicle flight control (300) through the communication interface (502), so that ground personnel can obtain a prompt before the fault is worsened, and the targeted overhaul is conveniently carried out after the task.
2. The unmanned aerial vehicle power management and information monitoring system of claim 1, wherein the unified power management module comprises a plurality of isolated power modules, each isolated power module configured as a DC-DC converter with input side and output side electrical isolation functions for converting voltages from the unmanned aerial vehicle power source (100) to output voltages of different voltage classes for powering each unmanned aerial vehicle load in the unmanned aerial vehicle load set (400), respectively.
3. The system according to claim 2, wherein an input end of each of the isolated power modules is connected to a front stage filter circuit, and an output end thereof is connected to a rear stage filter circuit.
4. The unmanned aerial vehicle power management and information monitoring system of claim 1, wherein the unmanned aerial vehicle power source (100) comprises a heuristic power source (102) and a backup battery (103); The unified power management module further comprises a standby battery interface circuit, wherein an ideal diode controller (201) and a MOSFET (metal-oxide-semiconductor field effect transistor) controlled by the ideal diode controller (201) are arranged in the standby battery interface circuit, and the ideal diode controller (201) and the MOSFET are connected in series on a power supply path of the standby battery (103); wherein the ideal diode controller (201) is configured to control the MOSFET to be turned off and on when the voltage of the heuristic power supply (102) is detected to be higher than the voltage of the backup battery (103).
5. The unmanned aerial vehicle power management and information monitoring system of claim 2, wherein the power management and information monitoring device (200) further comprises a power supply control module (204); The power supply control module (204) is connected between a singlechip (208) in the information and control hub module and the input end of one of the isolation power supply modules, and is used for controlling the on-off of the input of the isolation power supply module according to a control signal sent by the singlechip (208).
6. The system for managing and monitoring the power of the unmanned aerial vehicle according to claim 1, wherein the information and control hub module comprises an information acquisition interface (501), and the information acquisition interface (501) comprises a plurality of signal input ends, a decoder and a single chip microcomputer (208); the I/O port of the singlechip (208) is connected with the selection control end of the decoder through an optical coupler isolator; and a front-stage signal processing circuit, a linear signal isolator and a rear-stage processing circuit are sequentially connected in series between the output end of the decoder and the A/D acquisition interface of the singlechip (208).
7. The system of claim 6, wherein the plurality of signal inputs are configured to receive voltage, current, or resistance signals from various sensors on the drone; The pre-stage signal processing circuit is configured to amplify and filter the signal gated by the decoder; the linear signal isolator is used for realizing the isolated transmission of the signal amplitude; And the signal which is transmitted in an isolated way is processed by the post-processing circuit so as to match the input requirement of the A/D acquisition interface of the singlechip (208).
8. The unmanned aerial vehicle power management and information monitoring system of claim 1, wherein the information and control hub module comprises a communication interface (502); An electrical isolation device and a bus transceiver are sequentially arranged on a communication circuit of the communication interface (502); The communication controller pin of the singlechip (208) in the information and control hub module is connected to the input side of the electrical isolation device, the output side of the electrical isolation device is connected to the bus transceiver, and the bus transceiver is connected to an external communication bus.
9. The unmanned aerial vehicle power management and information monitoring system of claim 1, wherein the information and control hub module comprises a control interface (503); An electrical isolation device is arranged on a control signal output circuit of the control interface (503); the electric isolation device is arranged between a control signal output pin of a singlechip (208) in the information and control hub module and a driving circuit for driving the actuating mechanism, wherein the singlechip (208) can output control signals including PWM control signals, D/A output analog signals and IO port high-low level switch control signals.

Description

Unmanned aerial vehicle power management and information monitoring system Technical Field The invention relates to the technical field of unmanned aerial vehicle communication control, in particular to an unmanned aerial vehicle power supply management and information monitoring system. Background In recent years, unmanned aerial vehicle technology has developed rapidly, and the application field of unmanned aerial vehicle is expanded from consumer grade aerial photography to a plurality of aspects such as industrial inspection, agricultural plant protection, logistics transportation and even military application. In order to meet increasingly complex task demands, unmanned aerial vehicles are continually evolving towards large-load, long-endurance and multifunctional loads. This trend has placed higher demands on the reliability and efficiency of the unmanned aerial vehicle's on-board system architecture, in particular the power supply system, the communication links and the control logic. In the traditional unmanned aerial vehicle system architecture, particularly for large and medium unmanned aerial vehicles with complex functions, various airborne equipment are provided, including engines, generators, various task loads (such as high-definition cameras and laser radars), navigation modules (GPS and IMU), data chains, a large number of servo steering engines and the like. Typically, these devices all need to communicate data and interact commands independently with the core controller of the unmanned aerial vehicle, the flight controller (for short, flight control). This direct, point-to-point star topology in practice exposes a series of technical bottlenecks. First, the flight control is overly burdened. The flight control not only needs to run the core flight attitude control and navigation algorithm, but also needs to separate a large amount of hardware and software resources to manage the connection with a plurality of peripheral devices. This requires that the flight controls must reserve a large number of different electrical standards (e.g., UART, CAN, I, 2, C, PWM) and physical interfaces for the communication protocols, resulting in complex and costly hardware designs. And meanwhile, heterogeneous data streams from a plurality of devices are processed, so that huge operation burden is caused to a flight control CPU, and the instantaneity and stability of executing a core flight task are affected. Second, the power management scheme is decentralized and poorly scalable. The unmanned aerial vehicle is usually powered by a single battery pack, and is difficult to meet the requirements of long-endurance and high-power tasks. While the stability requirements of the devices on the large unmanned aerial vehicle on the power supply voltage and current are different (for example, the steering engine needs 8V, the communication device may need 12V, and the task load may need 24V or higher). To meet these various requirements, the existing solutions often employ a plurality of independent DC-DC power conversion modules distributed throughout the fuselage. The mode not only causes the power supply circuit of the whole machine to be complicated, increases the wiring difficulty and the system weight, but also is extremely easy to cause the problem of electromagnetic compatibility (EMC), such as crosstalk between power supply wires, and influences the precision of sensitive sensors such as GPS and the like. In addition, the distributed power modules are difficult to realize unified monitoring and management, and accurate real-time statistics and intelligent distribution of the power consumption of the whole machine cannot be realized. Third, the system integration level is low, and the reliability and the safety are insufficient. The scattered connection of each device makes the circuit of the whole machine complicated, and the number of connectors is numerous, thereby not only increasing the difficulty of assembly and troubleshooting, but also becoming a weak link of system reliability, and the looseness or the circuit abrasion of the connector is a common fault source. Meanwhile, if the electrical connection among different devices does not have effective isolation measures, a ground wire loop is easily generated due to ground potential difference, noise interference is introduced, and signal quality is reduced. More seriously, when an electrical fault such as a short circuit occurs in a certain load device, the fault can be conducted to a flight control or other key devices through a shared power supply or signal line, so that a chain reaction is caused, and the safety of the whole unmanned aerial vehicle is seriously threatened. Therefore, in the prior art, when dealing with the complexity of a large-scale and multifunctional unmanned aerial vehicle system, the problems of heavy flight control burden, disordered power management, low system integration level and reliability and the like are commonly exis