WO2020035042A1

WO2020035042A1 - Power supply method and device for aircraft, flight control system, and aircraft

Info

Publication number: WO2020035042A1
Application number: PCT/CN2019/100919
Authority: WO
Inventors: 秦威
Original assignee: 深圳市道通智能航空技术有限公司
Priority date: 2018-08-17
Filing date: 2019-08-16
Publication date: 2020-02-20
Also published as: CN109131841A

Abstract

A power supply method and device for an aircraft, a flight control system, and an aircraft. Said method comprises: determining the current flight phase of an aircraft (100); and controlling a battery (20), of which the discharge rate corresponds to the current flight phase, to supply power to the motor (30) of the aircraft (100).

Description

Power supply method and device for aircraft, flight control system and aircraft

Related applications cross-reference

This application claims priority from a Chinese patent application filed on August 17, 2018, with application number 201810939576.2, and application name "Aircraft Power Supply Method, Device, Flight Control System, and Aircraft", the entire contents of which are incorporated by reference in In this application.

Technical field

Embodiments of the present invention relate to the technical field of aircraft, and in particular, to a power supply method for an aircraft, a power supply device for an aircraft, a flight control system, and an aircraft having the flight control system.

Background technique

At present, aircrafts are used in various fields. Taking UAV (Unmanned Aerial Vehicle / Drones, UAV) as an example, due to its small size, low cost, convenient use, low requirements for combat environment, and strong battlefield survivability, etc. It is widely used in police, urban management, agriculture, geology, meteorology, electricity, rescue and disaster relief, video shooting and other fields. Use the aircraft's flight to complete various tasks, such as completing aerial photography, line inspection, surveying, metrology, cargo transportation and other tasks.

In the practical application of the aircraft, it is generally hoped that the flight time of the aircraft can be increased as much as possible, so that the aircraft can be better suited to complete various flight tasks. For example, in a large-scale survey, the aircraft is usually required to fly for a long time to complete Large-scale survey tasks. Therefore, how to improve the flight time of the aircraft has become a problem to be solved.

Summary of the Invention

The main object of the present invention is to provide a power supply method, device, flight control system and aircraft for an aircraft, which can improve the flight time of the aircraft.

The embodiments of the present invention disclose the following technical solutions:

To solve the above technical problems, an embodiment of the present invention provides a power supply method for an aircraft, where the method includes:

Determining the current flight phase of the aircraft;

A battery that controls a discharge rate corresponding to the current flight phase supplies power to a motor of the aircraft.

In some embodiments, before the battery that controls the discharge rate corresponding to the current flight phase powers the motor of the aircraft, the method further includes:

Obtain the correspondence between the preset flight phase and the discharge rate;

The battery that controls the discharge rate corresponding to the current flight phase to power the motor of the aircraft includes:

Determining a battery with a discharge rate corresponding to the current flight stage according to the correspondence between the preset flight stage and the discharge rate;

The determined battery is controlled to power the motor of the aircraft, and the motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase.

In some embodiments, the battery that controls the discharge rate corresponding to the current flight phase to power the aircraft includes:

When the current flight phase is a first flight phase, sending a first instruction to a first motor of the aircraft, so that a first battery supplies power to the first motor, and the first battery is connected to the first flight phase The corresponding discharge rate of the battery;

When the current flight phase is the second flight phase, a second instruction is sent to a second motor of the aircraft, so that a second battery supplies power to the second motor, and the second battery is connected to the second flight phase. The corresponding discharge rate of the battery;

Wherein, the discharge rates of the second battery and the first battery are different.

In some embodiments, the first flight phase is a take-off phase, the second flight phase is a cruise phase, and the discharge rate of the first battery is higher than the discharge rate of the second battery.

In some embodiments, determining the current flight phase of the aircraft includes:

Acquiring current flight state parameters of the aircraft;

The current flight phase of the aircraft is determined according to the current flight state parameters of the aircraft.

In some embodiments, the method further includes:

Receive power from a battery with at least one discharge rate.

In some embodiments, the at least one discharge rate battery includes at least two discharge rates batteries;

The power of the battery receiving at least one discharge rate includes:

The power of all the batteries or the power of some of the batteries receiving the at least two discharge rates.

To solve the above technical problems, an embodiment of the present invention further provides an aircraft power supply device, where the device includes:

A flight phase determination module, configured to determine a current flight phase of the aircraft;

A control module is configured to control a battery of a discharge rate corresponding to the current flight phase to power the motor of the aircraft.

In some embodiments, the apparatus further includes:

An acquisition module, for acquiring a correspondence between a preset flight phase and a discharge magnification;

The control module is specifically configured to:

Determining a battery with a discharge rate corresponding to the current flight stage according to a correspondence between a preset flight stage and a discharge rate obtained by the obtaining module;

In some embodiments, the control module is specifically configured to:

In some embodiments, the flight phase determination module is specifically configured to:

Acquiring current flight state parameters of the aircraft;

In some embodiments, the apparatus further includes:

The receiving module is configured to receive power from a battery with at least one discharge rate.

The receiving module is specifically configured to:

To solve the above technical problems, an embodiment of the present invention further provides a flight control system, including:

At least one processor; and

A memory connected in communication with the at least one processor; wherein,

The memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor, so that the at least one processor can execute the power supply method of the aircraft as described above.

In order to solve the above technical problem, an embodiment of the present invention further provides a computer program product. The computer program product includes a computer program stored on a non-volatile computer-readable storage medium. The computer program includes program instructions. When the program instructions are executed by a computer, the computer is caused to execute the power supply method of the aircraft as described above.

In order to solve the above technical problem, an embodiment of the present invention further provides a non-volatile computer-readable storage medium, where the computer-readable storage medium stores computer-executable instructions, and the computer-executable instructions are used to cause a computer to execute The power supply method of the aircraft as described above.

To solve the above technical problems, an embodiment of the present invention further provides an aircraft, including a battery, a motor, and a flight control system as described above, and the battery is connected to the flight control system and the motor, respectively.

In the embodiment of the present invention, for different flight phases of the aircraft, using a battery with a discharge rate corresponding to the flight phase of the aircraft to power the motor of the aircraft can increase the flight time of the aircraft, thereby increasing the flight time of the aircraft. range.

BRIEF DESCRIPTION OF THE DRAWINGS

One or more embodiments are exemplified by the pictures in the accompanying drawings. These exemplary descriptions do not constitute a limitation on the embodiments. Elements with the same reference numerals in the drawings are denoted as similar elements. Unless otherwise stated, the drawings in the drawings do not constitute a limitation on scale.

FIG. 1 is a schematic diagram of an application environment of an aircraft power supply method according to an embodiment of the present invention; FIG.

2 is a schematic flowchart of a power supply method for an aircraft according to an embodiment of the present invention;

3 is a schematic diagram of a specific implementation manner of a power supply method according to an embodiment of the present invention;

4 is a schematic flowchart of another power supply method for an aircraft according to an embodiment of the present invention;

5 is a schematic diagram of an isolation circuit according to an embodiment of the present invention;

6 is a schematic diagram of an aircraft power supply device according to an embodiment of the present invention;

7 is a schematic diagram of a hardware structure of a flight control system according to an embodiment of the present invention;

FIG. 8 is a schematic diagram of an aircraft provided by an embodiment of the present invention.

detailed description

In order to make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of the embodiments of the present invention, but not all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

The power supply method for an aircraft provided by the present invention can be used to power various aircraft, such as an unmanned aerial vehicle, an unmanned ship, or other movable devices. Taking a drone as an example, the drone may be a rotorcraft, for example, a multi-rotor aircraft propelled by multiple pushing devices through air. Embodiments of the present invention are not limited thereto, and the drone may also be Other types of drones, such as fixed-wing drones, drones, para-wing drones, flap-wing drones, and so on.

Please refer to FIG. 1, which is a schematic diagram of an application scenario of an aircraft power supply method according to an embodiment of the present invention. The application scenario includes: an aircraft 100. The aircraft 100 includes a flight control system 10, a battery 20 and a motor 30. The battery 20 is connected to the flight control system 10 and the motor 30, respectively, so as to provide power to the flight control system 10 and the motor 30, thereby ensuring the flight of the aircraft 100. Moreover, the flight control system 10 is communicatively connected with the motor 30 so as to send a control instruction to the motor 30 so as to control the motor 30 to be turned on or off.

Specifically, the battery 20 provides power to the flight control system 10 to ensure the normal operation of the flight control system 10, such as controlling the flight of the aircraft 100 and controlling the battery 20 to power the motor 30; the battery 20 provides power to the motor 30 to drive The propeller connected to the motor 30 rotates, thereby providing power for the flight of the aircraft 100.

The flight control system 10 (referred to as the flight control system for short) has the ability to monitor and control the flight and mission of the aircraft 100, and includes a set of equipment for controlling the launch and recovery of the aircraft 100. The flight control system 10 is used to control the flight of the aircraft 100. The flight control system 10 may include a flight controller and a sensing system. Among them, the flight controller and the sensor system are communicatively connected to transmit data or information.

The sensing system is used to measure the position parameters and status parameters of the aircraft 100 and various components of the aircraft 100, such as three-dimensional position, three-dimensional angle, three-dimensional velocity, three-dimensional acceleration and three-dimensional angular velocity, flying height, and the like. For example, when the aircraft 100 is flying, the current flight state parameters of the aircraft can be obtained in real time through a sensing system, so as to determine the flight state in which the aircraft is in real time.

The sensing system may include, for example, at least one of an infrared sensor, an acoustic wave sensor, a gyroscope, an electronic compass, an Inertial Measurement Unit (IMU), a vision sensor, a global navigation satellite system, and a barometer. For example, the global navigation satellite system may be a Global Positioning System (Global Positioning System, GPS). The IMU can measure attitude parameters during the flight of the aircraft 100, and can measure the flying height of the aircraft 100 by using an infrared sensor or an acoustic wave sensor.

The flight controller is used to control the flight of the aircraft 100. In addition, during the flight of the aircraft 100, the control battery 20 is used to provide power to the flight controller to ensure the normal operation of the flight controller, such as controlling the flight of the aircraft 100 and controlling the battery 20 to power the motor 30.

It can be understood that the flight controller may control the aircraft 100 according to a pre-programmed program instruction, and may also control the aircraft 100 by responding to one or more control instructions from other devices. For example, when the current flight phase of the aircraft 100 is determined, a control instruction is sent to the corresponding motor 30 to control the discharge rate of the battery 20 corresponding to the current flight phase to power the motor 30 so as to drive the corresponding propeller to rotate, thereby providing the aircraft with 100 flight power; or after determining the current flight phase of the aircraft 100, receive a control instruction sent by an external device such as a controller and send the control instruction to the corresponding motor 30 to control the corresponding to the current flight phase The discharge rate battery 20 supplies power to the motor 30 so as to drive the corresponding propeller to rotate, thereby providing power for the flight of the aircraft 100. The flight phase of the aircraft 100 may include, but is not limited to, a preparation phase, a take-off phase, a climb phase, a cruise phase, an approach phase, a descent phase, a leveling phase, a falling phase, a taxiing phase, and the like.

Battery 20 is a device that directly converts chemical energy into electrical energy. When charging, battery 20 uses external electrical energy to regenerate internal active materials and store electrical energy as chemical energy. When discharging, it converts chemical energy into electrical energy and outputs it. Various devices provide power. For example, power is provided to the aircraft 100 to ensure flight of the aircraft.

For an aircraft, it mainly uses flying to complete various tasks, such as completing aerial photography, line inspection, surveying, metrology, cargo transportation and other tasks. In the practical application of an aircraft, it is generally hoped that the flight time of the aircraft can be increased as much as possible, thereby increasing the flight range of the aircraft, so that the aircraft can be better adapted to complete various flight tasks. Based on this, the battery 20 in the embodiment of the present invention includes batteries with at least two discharge rates, so that the flight control system 10 uses a discharge rate corresponding to the flight stage in which the aircraft 100 is located for different flight stages in which the aircraft 100 is in. The battery 20 supplies power to the motor 30 of the aircraft 100, thereby increasing the flight time of the aircraft 100 and further increasing the flight range of the aircraft 100.

It should be noted that the batteries with at least two discharge rates may include batteries with various discharge rates in order to adapt to the power needs of various aircrafts or various stages of the aircraft. In addition, any type of battery with multiple discharge rates may include several multi-cells, and several cells are combined to form a battery with a corresponding discharge rate.

In addition, the battery 20 may be any suitable battery, such as a lithium battery, a nickel-cadmium battery, or other storage batteries.

The motor 30 is a main component of the power system of the aircraft 100. The aircraft 100 may include one or more motors, and each motor is correspondingly provided with a propeller. Each motor is connected to a corresponding propeller. In addition, in order to meet the flight needs of each flight phase of the aircraft 100, the motor 30 may include various types of motors, such as a lift motor, a cruise motor, and the like.

The motor 30 and the propeller may be provided on the fuselage of the aircraft 100; the motor 30 is used to receive a control instruction sent by the flight control system 10, and the control instruction may be used to make the battery 20 supply power to the motor 30. The battery 20 rotates when power is provided to the motor 30, thereby driving the propeller to rotate, thereby providing power for the flight of the aircraft 100. This power enables the aircraft 100 to achieve one or more degrees of freedom, such as forward and backward motion, up and down motion Wait. In some embodiments, the aircraft 100 may rotate about one or more rotation axes. For example, the rotation axis may include a roll axis, a pan axis, and a pitch axis. It can be understood that the motor 30 may be a DC motor or an AC motor. In addition, the motor 30 may be a brushless motor or a brush motor.

It can be understood that the above-mentioned naming of each component of the aircraft 100 is for identification purposes only, and should not be construed as limiting the embodiments of the present invention.

The embodiments of the present invention will be further described below with reference to the accompanying drawings.

Example 1:

FIG. 2 is a schematic flowchart of an aircraft power supply method according to an embodiment of the present invention. The power supply method of the aircraft can be applied to powering various types of aircraft, such as drones, unmanned ships, or other movable devices. The power supply method of the aircraft can be executed by any suitable type of control circuit, chip or controller with a certain logic operation or processing capability, such as the flight control system of the aircraft and the like. The following takes a flight control system of an aircraft as an example of an execution subject that executes the power supply method of the aircraft for specific description.

Referring to FIG. 2, the power supply method of the aircraft includes:

201: Determine the current flight phase of the aircraft.

The aircraft is usually used to complete various prescribed flight tasks. The aircraft to complete a flight task usually includes the following phases: preparation phase, take-off phase, climb phase, cruise phase, approach phase, glide phase, leveling phase, falling phase, taxiing phase. and many more.

For different flight phases, the power required by the motor of the aircraft is different. Therefore, before powering the motor of the aircraft, you can first determine the current flight phase of the aircraft, that is, the current flight phase of the aircraft, so as to follow-up The phase uses the corresponding battery to power the motor of the aircraft.

Wherein, the flight control system determining the current flight phase of the aircraft includes: obtaining a current flight state parameter of the aircraft; and determining the current flight phase of the aircraft according to the current flight state parameter of the aircraft.

Specifically, each sensor in the sensing system of the flight control system may be used to obtain the current flight state parameters of the aircraft, where the flight state parameters may include flight altitude and the like. For example, the flying height of an aircraft can be measured by an infrared sensor or an acoustic wave sensor in a sensing system.

For different flight phases of the aircraft, the flight altitude of the aircraft usually varies. For example, when the current flight phase of the aircraft is a cruise phase, the aircraft usually maintains a cruise flight along a pre-planned route at a preset flight altitude. Therefore, the current flight phase of the aircraft can be determined based on the flight altitude. For example, when it is detected that the current flight altitude of the aircraft is greater than a preset altitude threshold, it is determined that the current flight phase of the aircraft is a cruise phase.

It can be understood that, in some embodiments, the current flight phase of the aircraft may also be determined based on other flight state parameters, such as the flight speed and acceleration of the aircraft.

202: Obtain a correspondence between a preset flight phase and a discharge rate.

The discharge rate of a battery is used to indicate the ratio of the discharge current of the battery, that is, the rate. Discharge rate = discharge current / rated capacity in C. For example, when a battery with a rated capacity of 100Ah is discharged with 20A, its discharge rate is 0.2C.

The corresponding relationship between the preset flight phase and the discharge rate can be pre-configured in the database of the flight control system and read directly from the database of the flight control system; or, it can be obtained from other devices (such as servers or terminal devices) through the network. Etc.) Obtain the corresponding relationship between the preset flight phase and the discharge magnification.

The discharge rate corresponding to each flight stage is determined by meeting the flight needs of that flight stage. Also, the higher the discharge rate of the battery, the lower the energy / weight ratio. The minimum discharge rate under the conditions of the optimal discharge rate for the flight phase. For example, during the take-off phase, the battery discharge rate of 5C-10C can meet the flight needs during the take-off phase. At this time, the battery discharge rate of 5C is the optimal discharge rate during the take-off phase.

The preset correspondence between the flight phase and the discharge ratio may be a corresponding relationship between each flight phase and a certain discharge ratio, for example, the discharge ratio corresponding to the take-off phase is 5C. In some embodiments, the correspondence between the preset flight phase and the discharge ratio may also be a corresponding relationship between discharge ratios in a certain range for each flight phase, for example, a discharge ratio in the range of 5C-10C during the take-off phase.

The flight control system obtains a preset correspondence between a flight stage and a discharge rate, so as to determine a battery with a discharge rate corresponding to each flight stage based on the correspondence.

203: A battery that controls a discharge rate corresponding to the current flight phase supplies power to a motor of the aircraft.

The motor of the aircraft is a motor for driving a propeller of the aircraft to provide power for flight of the aircraft.

For different phases of the aircraft, the power required by the motor of the aircraft is different. In addition, in order to ensure the normal flight of the aircraft, the motors and propellers used may also be different. For example, during the take-off phase of an aircraft, a large propeller is generally installed on the aircraft as a lift-off propeller, and a higher-power motor is used as a drive motor for the lift-up propeller. The battery is used to power the drive motor to drive the lift-up propeller to rotate. As a result, the aircraft is lifted off, and when the aircraft is in the cruising phase after the liftoff, the smaller propeller is used as the attitude control paddle, and the aircraft is controlled by the aerodynamic force with a smaller power motor.

Under normal circumstances, during the flight of the aircraft, the power supply of the aircraft generally uses a discharge rate battery to supply power. This method is generally based on the take-off phase because it needs to withstand the high power requirements of the aircraft during the take-off phase. The discharge rate of the battery is designed, but the aircraft does not need such a high rate during the cruise phase, and the higher the discharge rate of the battery, the lower the energy / weight ratio. The discharge rate increases the weight of the battery, which increases the flight burden of the aircraft and affects the flight time that the aircraft can fly.

Based on this, according to the embodiments of the present invention, for different flight phases of the aircraft, motors of different discharge rates are used to power the motors of the aircraft to mention the flight time of the aircraft, so that the aircraft can better complete various flight tasks.

Specifically, the flight control system controls a battery at a discharge rate corresponding to the current flight phase to power the aircraft ’s motor, and includes: determining a relationship with the current flight stage according to the preset relationship between the preset flight phase and the discharge rate. A battery with a discharge rate corresponding to the flight phase; controlling the determined battery to power the motor of the aircraft, and the motor of the aircraft is the motor of the aircraft that needs power in the current flight phase.

After the flight control system determines a battery with a discharge rate corresponding to the current flight phase, it can control the determined battery to power the motor of the aircraft to ensure the normal flight of the aircraft. The motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase. In order to meet the flight needs of each flight phase of the aircraft, each flight phase can correspond to different motors. For example, during the take-off phase, the motor that needs to be powered is the lift motor; during the cruise phase, the motor that needs to be powered is the cruise motor, and so on. That is, in different flight phases, batteries with different discharge rates are used to power different motors respectively to improve flight time.

Specifically, the flight control system controls a battery with a discharge rate corresponding to the current flight phase to power the aircraft, including: when the current flight phase is the first flight phase, sending a first instruction to the aircraft. A first motor, so that a first battery supplies power to the first motor, the first battery is a battery with a discharge rate corresponding to a first flight phase; when the current flight phase is a second flight phase, sending A second instruction to a second motor of the aircraft, so that a second battery supplies power to the second motor, and the second battery is a battery with a discharge rate corresponding to a second flight phase; wherein the second battery and The discharge rate of the first battery is different.

The first instruction is used to turn on the first motor so that the first battery supplies power to the first motor; the second instruction is used to turn off the first motor and turn on the second motor so that the second battery supplies power to the second motor. During the flight of the aircraft, the power required during the take-off phase is greater than the power required during the cruise phase. Therefore, when the first flight phase is the take-off phase and the second flight phase is the cruise phase, the power of the first battery The discharge rate is higher than the discharge rate of the second battery. For different flight phases of the aircraft, using a battery with a discharge rate corresponding to the flight phase of the aircraft to power the motor of the aircraft can increase the flight time of the aircraft.

The following uses FIG. 3 as an example to specifically describe how to improve the flight time of the aircraft by using the power supply method of the aircraft provided in this embodiment.

As shown in FIG. 3, when the current flight phase of the aircraft is the take-off phase, the flight control system sends a first instruction to the first motor, that is, the lift motor, so that the first battery with the lift motor turned on and a high discharge rate is The lift motor drives the propeller corresponding to the lift motor to rotate, so that the aircraft rises; when the aircraft rises above a preset altitude threshold, that is, when the current flight phase of the aircraft is the cruise phase, the flight control system gives the second motor That is, the cruise motor sends a second command, so that the lift motor is turned off, the cruise motor is turned on, and the second battery with a smaller discharge rate is the lift motor, which drives the propeller corresponding to the cruise motor to rotate, so that the aircraft follows the pre-planned Cruising flight of the route, thus increasing the flight time of the aircraft.

The following set of specific data is taken as an example to specifically explain that the flight time of the aircraft can be improved by using the power supply method of the aircraft provided by the embodiment of the present invention:

Suppose that the power required by the aircraft during the take-off phase is 1400W, the flight time during the take-off phase is 1 minute, and the power required during the cruise phase is 200W. The battery uses 6 strings (6 cells in series, and the voltage of each cell is 3.8V). ) For high voltage batteries, the weight of the battery is limited to 1.5KG. Calculate the flight time of the aircraft powered by a battery with one discharge rate and the flight time of the aircraft powered by a battery with multiple discharge rates:

If it is only powered by a battery with a discharge rate: To meet the required power of 1400W during the take-off phase, and the flight time of the take-off phase in 1 minute, the energy required for the take-off phase W ₁ = 1400W * 1 / 60H≈23.33WH, take-off phase The average current I ₁ = 1400W / (3.8 * 6V) ≈ 61.4A, that is, the discharge current of the battery must be able to meet the rated discharge current of 61.4A. Since the energy of the high-voltage battery discharge rate of commercially 5C / wt ratio of around 220WH / KG, so that the maximum battery power 1.5KG _{W max1 = 220WH / KG * 1.5KG} = 330WH, in terms of the battery capacity _max1 = _330WH Q / ( 3.8 * 6V) ≈14.47AH, you can know that the rated current of the capacity battery at 5C rate is 72.35A, which can meet the take-off current and cruise current of 61.4A I ₂ = 200W / 22.8V≈8.77A. Therefore, the flight time T _{1 of} the scheme in the cruise phase = (330WH-23.33WH) / 200W ≈ 1.53H, plus the flight time (1 minute) in the take-off phase, a total of about 1.55H.

If a battery with multiple discharge rates is used for power supply: To meet the required power of 1400W during the take-off phase, and the flight time of 1 minute during the take-off phase, the energy required for the take-off phase W ₁ = 1400W * 1 / 60≈23.33WH, then The consumed capacity in the take-off phase Q ₁ = 23.33WH / 3.8 * 6V≈1.023AH, the average current in the take-off phase I1 = 1400W / 3.8 * 6V≈61.4A, that is, the battery with a higher discharge rate (corresponding to the take-off phase The discharge current of the battery (ie, the first battery) must be able to meet the discharge current of 61.4A, so the discharge rate of the battery with a higher discharge rate must reach at least 60C. Because the energy / weight ratio of the high-voltage battery with a discharge rate of 60C on the market is about 120WH / KG, the weight of the battery with a higher discharge rate M ₁ = 23.33WH / (120WH / KG) ≈0.194KG. Therefore, the weight of the battery with a lower discharge rate (the battery corresponding to the cruise stage, that is, the second battery) M ₂ = 1.5KG-M1 = 1.306KG, because the energy / weight ratio of the high-voltage battery with a discharge rate of 1C on the market is between 300WH / KG, so the maximum energy of the battery with a lower discharge rate of 1.306KG is W _max2 = 300WH / KG * 1.306KG = 391.8WH, which is converted into a battery capacity Qmax2 = 391.8WH / (3.8 * 6V) ≈17.18AH, that is, It can be known that the rated current of the capacity battery at 1C rate is 17.18A, which can meet the cruise current I _{2 of} 200W. Therefore, the flight time T _{2 of} the scheme in the cruise phase is (391.8WH-23.33WH) /200W≈1.84H, plus the flight time in the take-off phase (1 minute), which is about 1.86H in total.

It can be seen that under the same constraint conditions, a battery-powered solution that uses multiple discharge rates for different flight phases takes about 20% longer than a single discharge rate battery solution, that is, provided by the embodiment of the present invention The power supply method of the aircraft can increase the flight time of the aircraft.

It should be noted that those skilled in the art can understand from the description of the embodiments of the present invention that, in different embodiments, without conflict, the steps 201-203 may have different execution orders, for example, first execute Step 202, and then step 201 and so on. Furthermore, in some other embodiments, step 202 is not a necessary step.

Example 2:

FIG. 4 is a schematic flowchart of another power supply method for an aircraft according to an embodiment of the present invention. The power supply method of the aircraft can be applied to powering various types of aircraft, such as drones, unmanned ships, or other movable devices. The power supply method of the aircraft can be executed by any suitable type of control circuit, chip or controller with a certain logic operation or processing capability, such as the flight control system of the aircraft and the like. The following takes a flight control system of an aircraft as an example of an execution subject that executes the power supply method of the aircraft for specific description.

Referring to FIG. 4, the power supply method of the aircraft includes:

401: Determine the current flight phase of the aircraft.

402: A battery that controls a discharge rate corresponding to the current flight phase supplies power to a motor of the aircraft.

It should be noted that

steps

401 and 402 in the embodiment of the present invention are similar to

steps

201 and 203 in the foregoing embodiment, respectively. For technical details not described in detail in

steps

401 and 402, reference may be made to the foregoing embodiment. The detailed descriptions of step 201 and step 203 will not be repeated here.

403: Receive power from a battery with at least one discharge rate.

Because the flight control system also needs power to maintain its normal work, such as controlling the flight of the aircraft and controlling the battery to power the motor and so on. Therefore, during the flight of the aircraft, the flight controller receives the power of the battery with at least one discharge rate.

Wherein, the at least one discharge rate battery includes at least two discharge rates batteries. The receiving power of a battery with at least one discharge rate includes receiving power of all batteries or a part of the battery of the batteries with at least two discharge rates. For example, when the flight control system receives power from batteries with two discharge rates, it can simultaneously receive power from batteries with two discharge rates, or it can receive power from one of the batteries with one discharge rate at the same time.

For example, taking FIG. 3 as an example, according to the needs of the flight, the flight control system may receive the power provided by the first battery and the second battery at the same time; or receive the power provided by the first battery; or receive the power provided by the second battery .

The flight control system is powered by batteries with multiple discharge rates to ensure the power supply of the flight control system is stable and reliable. A variety of discharge rates of battery power supply part or all of the power supply, the flight control system can work. This is equivalent to increasing the types of power supply batteries. Compared with only one type of battery power supply, the power supply redundancy can be increased. For example, when one power supply battery fails, another power supply battery can immediately take over its work. After the power supply battery is replaced, the two power supply batteries work together.

Among them, in order to prevent mutual supply of power supply voltages, the flight control system needs to be isolated when it receives power from batteries with at least two discharge rates. Since the power consumption of the flight control system is generally small, it can be powered by diode isolation. For its isolation circuit, please refer to FIG. 5. Among them, the flight control system is powered by multiple batteries, each battery is isolated by a diode, and the voltage input by the battery is converted into a voltage output required by the flight control system through a power management chip.

It should be noted that those skilled in the art can understand from the description of the embodiments of the present invention that in different embodiments, the steps 401-403 may be performed in different order without conflict, for example, first In step 403, step 401 is performed again.

In the embodiment of the present invention, for different flight phases of the aircraft, using a battery with a discharge rate corresponding to the flight phase of the aircraft to power the motor of the aircraft can increase the flight time of the aircraft, thereby increasing the flight time of the aircraft. range. In addition, the flight control system receives power from batteries with multiple discharge rates to ensure the power supply of the flight control system is stable and reliable.

Example 3:

FIG. 6 is a schematic diagram of an aircraft power supply estimation device according to an embodiment of the present invention. The power supply device 60 of the aircraft can be applied to power various types of aircraft, such as unmanned aerial vehicles, unmanned ships, or other movable devices. The power supply device 60 of the aircraft may be configured in any suitable type of control circuit, chip, or controller with a certain logic operation or processing capability, such as the flight control system of the aircraft and the like.

Referring to FIG. 6, the power supply device of the aircraft includes a flight phase determination module 601, an acquisition module 602, a control module 603, and a receiving module 604.

Specifically, the flight phase determination module 601 is configured to determine a current flight phase of the aircraft.

The flight phase determination module 601 is specifically configured to: obtain a current flight state parameter of the aircraft; and determine a current flight stage of the aircraft according to the current flight state parameter of the aircraft. The flight status parameter may include a flight height and the like. For example, the flight phase determination module 601 may measure the flight height of the aircraft through an infrared sensor or an acoustic wave sensor in a sensing system of the flight control system to obtain the flight state parameter.

For different flight phases of an aircraft, the flight altitude of the aircraft usually varies. For example, when the current flight phase of the aircraft is a cruise phase, the aircraft usually maintains a cruise flight along a pre-planned route at a preset flight altitude. Therefore, the flight phase determination module 601 may determine the current flight phase of the aircraft based on the flight altitude. For example, when it is detected that the current flight altitude of the aircraft is greater than a preset altitude threshold, the flight phase determination module 601 determines that the current flight phase of the aircraft is a cruise phase.

Specifically, the obtaining module 602 is configured to obtain a correspondence between a preset flight phase and a discharge magnification.

The preset correspondence between the flight phase and the discharge rate can be pre-configured in the database of the flight control system and obtained by the acquisition module 602 directly from the database of the flight control system; or, it can be obtained from other devices through the network acquisition module 602 (Such as a server or a terminal device) to obtain the corresponding relationship between the preset flight phase and the discharge rate.

Specifically, the control module 603 is configured to power the motor of the aircraft through a battery with a discharge rate corresponding to the current flight phase during the current flight phase.

The control module 603 is specifically configured to determine a battery with a discharge rate corresponding to the current flight stage according to the correspondence between the preset flight stage and the discharge rate; and control the determined battery to power the motor of the aircraft, The motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase.

After the control module 603 determines the battery with the discharge rate corresponding to the current flight phase, it can control the determined battery to power the motor of the aircraft to ensure the normal flight of the aircraft. The motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase. In order to meet the flight needs of each flight phase of the aircraft, each flight phase can correspond to different motors. For example, during the take-off phase, the motor that needs to be powered is the lift motor; during the cruise phase, the motor that needs to be powered is the cruise motor, and so on. That is, in different flight phases, batteries with different discharge rates are used to power different motors respectively to improve flight time.

In some implementations, the control module 603 is specifically configured to: when the current flight phase is a first flight phase, send a first instruction to a first motor of the aircraft, so that the first battery is the first motor Power supply, the first battery is a battery with a discharge rate corresponding to the first flight phase; when the current flight phase is the second flight phase, sending a second instruction to the second motor of the aircraft, so that the first battery Two batteries supply power to the second motor, and the second battery is a battery with a discharge rate corresponding to the second flight phase, wherein the second battery has a different discharge rate from the first battery.

The first instruction is used to turn on the first motor so that the first battery supplies power to the first motor; the second instruction is used to turn off the first motor and turn on the second motor so that the second battery supplies power to the second motor. During the flight of the aircraft, the power required during the take-off phase is greater than the power required during the cruise phase. Therefore, when the first flight phase is the take-off phase and the second flight phase is the cruise phase, the power of the first battery The discharge rate is higher than the discharge rate of the second battery. Aiming at different flight phases of the aircraft, using a battery with a discharge rate corresponding to the flight phase of the aircraft to power the motor of the aircraft can increase the flight time of the aircraft.

Specifically, the receiving module 604 is configured to receive power from a battery with at least one discharge rate.

Because the flight control system also needs power to maintain its normal work, such as controlling the flight of the aircraft and controlling the battery to power the motor and so on. Therefore, during the flight of the aircraft, the power of the battery with at least one discharge rate is received by the receiving module 604.

Wherein, the at least one discharge rate battery includes at least two discharge rates batteries. The receiving module 604 is specifically configured to receive the power of all the batteries or the power of a part of the batteries among the batteries of the at least two discharge rates. For example, when the receiving module 604 receives the power of the batteries with two discharge rates, it can receive the power of the batteries with two discharge rates at the same time, or it can receive the power of the batteries with one of the discharge rates at the same time. The receiving module 604 receives battery power of multiple discharge rates to ensure that the power supply of the flight control system is stable and reliable.

Among them, in order to prevent mutual supply of power supply voltage, when the receiving module 604 receives power from batteries with at least two discharge rates, isolation is required. Since the power consumption of the flight control system is generally small, it can be powered by diode isolation.

It should be noted that in some other embodiments, the obtaining module 602 and / or the receiving module 604 are not necessary modules of the power supply device 60 of the aircraft, that is, in some other embodiments, the obtaining module 602 and / or the receiving module 604 may Omitted. For example, in some embodiments, the power supply device 60 of the aircraft may not include the obtaining module 602 and the receiving module 604.

It should also be noted that, in the embodiment of the present invention, the power supply device 60 of the aircraft can execute the power supply method of the aircraft provided by the embodiment of the present invention, and has functional modules and beneficial effects corresponding to the execution method. For technical details not described in the embodiment of the power supply device 60 of the aircraft, reference may be made to the power supply method of the aircraft provided by the embodiment of the present invention.

Example 4:

FIG. 7 is a schematic diagram of a hardware structure of a flight control system according to an embodiment of the present invention. The flight control system may be a flight control system of various aircrafts. As shown in FIG. 7, the flight control system 70 includes:

One or more processors 701 and a memory 702. In FIG. 7, one processor 701 is taken as an example.

The processor 701 and the memory 702 may be connected through a bus or in other manners. In FIG. 7, the connection through the bus is taken as an example.

The memory 702 is a non-volatile computer-readable storage medium, and can be used to store non-volatile software programs, non-volatile computer executable programs, and modules, such as programs corresponding to an aircraft power supply method in the embodiment of the present invention. Instructions / modules (for example, the flight phase determination module 601, the acquisition module 602, the control module 603, and the receiving module 604 shown in FIG. 6). The processor 701 executes various functional applications and data processing of the flight control system by running non-volatile software programs, instructions, and modules stored in the memory 702, that is, a power supply method of the aircraft that implements the method embodiment.

The memory 702 may include a storage program area and a storage data area, where the storage program area may store an operating system and applications required for at least one function; the storage data area may store data created according to the use of the flight control system, and the like. In addition, the memory 702 may include a high-speed random access memory, and may further include a non-volatile memory, such as at least one magnetic disk storage device, a flash memory device, or other non-volatile solid-state storage device. In some embodiments, the memory 702 may optionally include a memory remotely set with respect to the processor 701, and these remote memories may be connected to the flight control system through a network. Examples of the network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

The one or more modules are stored in the memory 702, and when executed by the one or more processors 701, perform the power supply method of the aircraft in the arbitrary method embodiment, for example, execute the diagram described above. Steps 401 to 403 in method 4 implement the functions of modules 601-604 in FIG.

The flight control system 70 can execute the power supply method of the aircraft provided by the method embodiment, and has corresponding function modules and beneficial effects of the execution method. For technical details that are not described in detail in the embodiment of the flight control system, reference may be made to the power supply method of the aircraft provided in the embodiment of the method invention.

An embodiment of the present invention provides a computer program product. The computer program product includes a computer program stored on a non-volatile computer-readable storage medium. The computer program includes program instructions. When the program instructions are executed by a computer, At that time, the computer is caused to execute the power supply method of the aircraft as described above. For example, the method steps 401 to 403 in FIG. 4 described above are performed to implement the functions of modules 601 to 604 in FIG. 6.

An embodiment of the present invention provides a non-volatile computer-readable storage medium, where the computer-readable storage medium stores computer-executable instructions, and the computer-executable instructions are used to cause a computer to perform power supply of an aircraft as described above method. For example, the method steps 401 to 403 in FIG. 4 described above are performed to implement the functions of modules 601 to 604 in FIG. 6.

Example 5:

FIG. 8 is a schematic diagram of an aircraft according to an embodiment of the present invention. The aircraft 80 includes a battery 801, a motor 802, and the flight control system 70 described above. The aircraft 80 includes, but is not limited to, an unmanned aerial vehicle, an unmanned ship, and the like.

The battery 801 is connected to the flight control system 70 and the motor 802, respectively. The flight control system 70 is used to control the battery 801 to provide power to the motor 802. Specifically, during the current flight phase, the flight control system 70 controls the battery 801 of the discharge rate corresponding to the current flight phase to power the motor 802 of the aircraft.

Among them, the flight control system 70 may directly control the power supply of the battery 801, or may control the power supply of the battery 801 by controlling the motor 802. For example, the flight control system 70 sends a first control instruction for controlling the power supply of the battery to the battery 801 to control the discharge rate of the battery 801 corresponding to the current flight phase to power the motor 802 of the aircraft; or The control system 70 sends a second control instruction for turning on the motor to the motor 802, so that the motor 802 is turned on, so that the battery 801 with a discharge rate corresponding to the current flight phase supplies power to the motor 802 of the aircraft.

The flight control system 70 is directed to different flight phases of the aircraft 80. The battery 801 with a discharge rate corresponding to the flight phase of the aircraft 80 is used to power the motor 802 of the aircraft, which can increase the flight time of the aircraft 80 and thus increase the aircraft 80. Range of flight.

It should be noted that the device embodiments described above are only schematic, and the modules described as separate components may or may not be physically separated, and the components displayed as modules may or may not be physical Modules can be located in one place or distributed to multiple network modules. Some or all of the modules may be selected according to actual needs to achieve the objective of the solution of this embodiment.

Through the description of the above embodiments, a person of ordinary skill in the art can clearly understand that the embodiments can be implemented by means of software plus a general hardware platform, and of course, also by hardware. Those of ordinary skill in the art can understand that all or part of the processes in the method of the embodiment can be completed by computer program instructions related hardware. The program can be stored in a computer-readable storage medium, and the program is being executed. In this case, the process of the embodiment of each method may be included. The storage medium may be a read-only memory (ROM) or a random access memory (RandomAccess Memory, RAM).

Finally, it should be noted that the above embodiments are only used to describe the technical solution of the present invention, but not limited thereto. Under the idea of the present invention, the technical features in the above embodiments or different embodiments can also be combined. The steps can be implemented in any order and there are many other variations of the different aspects of the invention as described above, for the sake of brevity they are not provided in the details; although the invention has been described in detail with reference to the foregoing embodiments, it is common in the art The skilled person should understand that they can still modify the technical solutions described in the foregoing embodiments, or equivalently replace some of the technical features; and these modifications or replacements do not deviate the essence of the corresponding technical solutions from the implementation of the present invention. Examples of technical solutions.

Claims

A method for powering an aircraft, characterized in that the method includes:

Determining the current flight phase of the aircraft;

A battery that controls a discharge rate corresponding to the current flight phase supplies power to a motor of the aircraft.
The method according to claim 1, wherein before the battery controlling the discharge rate corresponding to the current flight phase powers the motor of the aircraft, the method further comprises:

Obtain the correspondence between the preset flight phase and the discharge rate;

The battery that controls the discharge rate corresponding to the current flight phase to power the motor of the aircraft includes:

Determining a battery with a discharge rate corresponding to the current flight stage according to the correspondence between the preset flight stage and the discharge rate;

The determined battery is controlled to power the motor of the aircraft, and the motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase.
The method according to claim 1 or 2, wherein the battery that controls a discharge rate corresponding to the current flight phase to power the aircraft comprises:

When the current flight phase is a first flight phase, sending a first instruction to a first motor of the aircraft, so that a first battery supplies power to the first motor, and the first battery is connected to the first flight phase The corresponding discharge rate of the battery;

When the current flight phase is the second flight phase, a second instruction is sent to a second motor of the aircraft, so that a second battery supplies power to the second motor, and the second battery is connected to the second flight phase. The corresponding discharge rate of the battery;

Wherein, the discharge rates of the second battery and the first battery are different.
The method according to claim 3, wherein the first flight phase is a take-off phase, the second flight phase is a cruise phase, and a discharge rate of the first battery is higher than that of the second battery. Magnification.
The method according to claim 1, wherein determining the current flight phase of the aircraft comprises:

Acquiring current flight state parameters of the aircraft;

The current flight phase of the aircraft is determined according to the current flight state parameters of the aircraft.
The method according to claim 1, further comprising:

Receive power from a battery with at least one discharge rate.
The method according to claim 6, wherein the at least one battery with a discharge rate comprises at least two batteries with a discharge rate;

The power of the battery receiving at least one discharge rate includes:

The power of all the batteries or the power of some of the batteries receiving the at least two discharge rates.
An aircraft power supply device is characterized in that the device includes:

A flight phase determination module, configured to determine a current flight phase of the aircraft;

A control module is configured to control a battery of a discharge rate corresponding to the current flight phase to power the motor of the aircraft.
The apparatus according to claim 8, further comprising:

An acquisition module, for acquiring a correspondence between a preset flight phase and a discharge magnification;

The control module is specifically configured to:

Determining a battery with a discharge rate corresponding to the current flight stage according to a correspondence between a preset flight stage and a discharge rate obtained by the obtaining module;

The determined battery is controlled to power the motor of the aircraft, and the motor of the aircraft is the motor of the aircraft that needs to be powered during the current flight phase.
The device according to claim 8 or 9, wherein the control module is specifically configured to:

When the current flight phase is a first flight phase, sending a first instruction to a first motor of the aircraft, so that a first battery supplies power to the first motor, and the first battery is connected to the first flight phase The corresponding discharge rate of the battery;

When the current flight phase is the second flight phase, a second instruction is sent to a second motor of the aircraft, so that a second battery supplies power to the second motor, and the second battery is connected to the second flight phase. The corresponding discharge rate of the battery;

Wherein, the discharge rates of the second battery and the first battery are different.
The device according to claim 10, wherein the first flight phase is a take-off phase, the second flight phase is a cruise phase, and a discharge rate of the first battery is higher than a discharge of the second battery Magnification.
The apparatus according to claim 8, wherein the flight phase determination module is specifically configured to:

Acquiring current flight state parameters of the aircraft;

The current flight phase of the aircraft is determined according to the current flight state parameters of the aircraft.
The apparatus according to claim 8, further comprising:

The receiving module is configured to receive power from a battery with at least one discharge rate.
The device according to claim 13, wherein the at least one battery with a discharge rate comprises at least two batteries with a discharge rate;

The receiving module is specifically configured to:

The power of all the batteries or the power of some of the batteries receiving the at least two discharge rates.
A flight control system, comprising:

At least one processor; and

A memory connected in communication with the at least one processor; wherein,

The memory stores instructions executable by the at least one processor, and the instructions are executed by the at least one processor, so that the at least one processor can execute the one of claims 1-7. method.
An aircraft includes a battery, a motor, and the flight control system according to claim 15, wherein the battery is connected to the flight control system and the motor, respectively.