CN211981524U - Aircraft power management system - Google Patents
Aircraft power management system Download PDFInfo
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- CN211981524U CN211981524U CN202020188224.0U CN202020188224U CN211981524U CN 211981524 U CN211981524 U CN 211981524U CN 202020188224 U CN202020188224 U CN 202020188224U CN 211981524 U CN211981524 U CN 211981524U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02B—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO BUILDINGS, e.g. HOUSING, HOUSE APPLIANCES OR RELATED END-USER APPLICATIONS
- Y02B70/00—Technologies for an efficient end-user side electric power management and consumption
- Y02B70/30—Systems integrating technologies related to power network operation and communication or information technologies for improving the carbon footprint of the management of residential or tertiary loads, i.e. smart grids as climate change mitigation technology in the buildings sector, including also the last stages of power distribution and the control, monitoring or operating management systems at local level
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y04—INFORMATION OR COMMUNICATION TECHNOLOGIES HAVING AN IMPACT ON OTHER TECHNOLOGY AREAS
- Y04S—SYSTEMS INTEGRATING TECHNOLOGIES RELATED TO POWER NETWORK OPERATION, COMMUNICATION OR INFORMATION TECHNOLOGIES FOR IMPROVING THE ELECTRICAL POWER GENERATION, TRANSMISSION, DISTRIBUTION, MANAGEMENT OR USAGE, i.e. SMART GRIDS
- Y04S20/00—Management or operation of end-user stationary applications or the last stages of power distribution; Controlling, monitoring or operating thereof
- Y04S20/20—End-user application control systems
Abstract
The utility model provides an aircraft power management system, including main power source module and a N power management module, parallelly connected setting between a N power management module, N more than or equal to 1, main power source module include the main battery and with main battery electric connection's constant voltage current limiter, the constant voltage current limiter is used for fixing the discharge current of main battery. The utility model discloses an aircraft power management system improves the battery capacity under the same battery weight to improve the aircraft energy-to-weight ratio, improve energy efficiency, strengthen the duration of the aircraft; each module battery is used as a backup emergency battery to supply power to each module under special conditions, so that the safety and reliability of the aircraft are enhanced; the structure is clear, and the debugging and the maintenance of being convenient for, discharge current is less is favorable to protecting each module battery and main battery, increases life, reduces the maintenance cost.
Description
Technical Field
The utility model belongs to the technical field of power management system, particularly, relate to an aircraft power management system.
Background
At present, most of unmanned aerial vehicles on the market are driven by motors, the energy of the whole unmanned aerial vehicle is provided by batteries, and the places where the unmanned aerial vehicle needs to be powered are more, such as the motors, flight controls, loads, steering engines, navigation lamps and the like, so that power management is indispensable for modern unmanned aerial vehicles.
Most power supplies used by the unmanned aerial vehicle are lithium ion batteries and lithium polymer batteries, wherein the common lithium ion batteries are 18650 (the diameter of a battery cell is 18mm, the length of the battery cell is 65 mm) and 21700 (the diameter of the battery cell is 18mm, the length of the battery cell is 65 mm), and the lithium ion batteries have the advantages of high energy density, but generally have lower discharge rate, namely, the allowable maximum discharge current is smaller; the lithium polymer battery has the advantages that the lithium polymer battery has higher discharge rate, but the energy density of the lithium polymer battery is not as high as that of the lithium ion battery, meanwhile, the battery with high energy density and high capacity has higher manufacturing cost, and in general, the discharge rate is inversely proportional to the energy density.
In the flight process of the unmanned aerial vehicle, when taking off and landing vertically, the vertical take-off and landing motor works at high power, the passing current is up to dozens of A, the process lasts for 2-3 minutes, when cruising and flying, the cruising motor keeps normal power to work, when performing maneuvering actions such as turning, climbing and the like, the cruising motor can work at high power continuously, the current is up to hundreds of A, and for a battery with high capacity and low discharge rate, the current exceeds the current allowed by a power supply; the vertical take-off and landing process of the vertical take-off and landing fixed-wing unmanned aerial vehicle generally lasts within ten minutes, so that the electric energy distributed to the vertical take-off and landing system by a power supply system is less, the vertical take-off and landing process can only be completed by the aircraft safely once, and the aircraft cannot be vertically taken off and landed or hovered for many times under the condition that batteries are not replaced.
The prior product has the following problems:
firstly, due to the current limit of a motor, the selection of a battery is determined by considering not only high energy density but also high discharge rate, so that the battery which enables the energy-to-weight ratio of the whole energy system to be maximum cannot be selected;
secondly, because all the systems share a power supply, when the aircraft is in cruising, excessive power consumption can cause insufficient electric energy to land during vertical landing, and even cause the key parts of the aircraft such as flight control, a steering engine and the like to be powered off;
third, the power system driven by single power or double power supplies, the wiring of the flat cable is more complicated; the vertical take-off and landing motor and the cruise motor are far away from the battery bin, and wires which need to carry large current are conveyed for a long distance, so that the weight and the line loss are increased; the debugging of the aircraft before takeoff uses the electric energy of part of power supply, so that the aircraft cannot take off in full power, and the endurance performance is influenced;
fourthly, the maximum allowable current is often approached or reached in the use process of the power supply, so that the power supply is damaged or damaged, the service life is reduced, and the maintenance cost is increased;
and fifthly, the capacity of the vertical take-off and landing power supply is small, and the power required by multiple times of vertical take-off and landing or hovering cannot be provided.
Therefore, it is very important to design and manufacture an aircraft power management system.
Disclosure of Invention
In order to solve the technical problem, the utility model discloses an aircraft power management system, including main power source module and N power management modules, parallelly connected setting between the N power management modules, N more than or equal to 1, main power source module includes main battery and the constant voltage current limiter with main battery electric connection, the constant voltage current limiter is used for fixing the discharge current of main battery;
the power supply management module comprises a voltage-stabilizing current-limiting power supply manager, a module battery, N motors and N electronic speed regulators, wherein N is larger than 1, the module battery, the N motors and the N electronic speed regulators are connected in series to form a loop, and the voltage-stabilizing current-limiting power supply manager is connected to two ends of a power supply in parallel;
the main power supply module is connected with the N power supply management modules through leads to charge the batteries of the modules in a constant-voltage current-limiting mode.
The voltage-stabilizing current-limiting power supply manager comprises a detection module connected with the module battery in series, the detection module detects the cell voltage value of the module battery, and the cell voltage value in the module battery is also acquired during charging.
The main battery adopts a low discharge rate high capacity battery.
The module battery includes, but is not limited to, a lithium polymer battery.
Compared with the prior art, the utility model discloses following beneficial effect has:
1. the utility model discloses an in the setting, this invention is through the method of supplying each module battery with each module battery separation, large capacity battery for the large capacity main battery can select for use the battery of low discharge rate high capacity, thereby increases the electric energy that whole aircraft carried, strengthens the duration of aircraft greatly, under the same battery weight, improves the battery capacity thereby improves the aircraft can the weight ratio, improves energy efficiency, strengthens the duration of aircraft.
2. The utility model has the advantages that the battery modules are separated from each other and do not interfere with each other, thereby avoiding the problem of a certain module which affects the power supply of the whole machine; if the electric energy is divided into the vertical take-off and landing part and the cruising part before taking off, the situation that the vertical take-off and landing part or the cruising module battery wastes part of the electric energy is inevitable; the capacity of each module battery can be used as a standby power supply to support the forced landing process of the aircraft when the electric energy of the main battery is exhausted or an emergency occurs, so that the safety and the reliability of the aircraft are improved.
3. The utility model discloses power management system layout is simple, and the debugging is easy and the debugging does not influence each module battery power; the charging current between the main battery and each module battery is small, and the weight of the aircraft can be reduced by selecting thin wires.
4. The utility model discloses a setting, the module that the electric current is higher can select the lithium polymer battery of high discharge rate for use like the module battery of VTOL module and cruise module, the actual electric current when its electric current that allows through far exceeds the aircraft use, consequently, can not cause the damage to each module battery, the high power state at times is like climbing at the aircraft, VTOL, during the turn, main electric energy is provided by each module battery, the main battery charges for each module battery with level pressure current-limiting form, consequently, the discharge current of main battery also is less than its electric current that allows far away, the life of main battery compares other energy systems and can improve greatly.
5. The utility model discloses power management system can be according to the aircraft task difference, and intelligent distribution main battery electric energy, winter or cold area can be through power management system for the aircraft lasts the power supply, utilizes each system operation to generate heat for the battery loading and leads to suitable temperature, can guarantee that the aircraft normally works under the condition that keeps each battery on the aircraft full charge, and the VTOL power of general aircraft can only carry the electric energy of accomplishing a VTOL safely; the power management system can complete multiple vertical take-off and landing or hovering without replacing the battery.
Drawings
Fig. 1 is a structural diagram of the power management system of the present invention.
Fig. 2 is a diagram of a power management module installation method of the present invention.
Fig. 3 is a schematic structural diagram of the positions of the main power source and the power sources of the modules of the present invention on the aircraft.
Detailed Description
The invention will be further described with reference to the accompanying drawings 1 to 3:
example 1:
as shown in fig. 1, a structure diagram of a power management system of the aircraft is shown, the aircraft selects a high-capacity low-discharge-rate 18650 lithium battery as a main power supply, has a capacity of 1800W · h, and is divided into three modules, namely a vertical take-off and landing module, a cruise module, an equipment module and the like;
the installation mode of the power supply management module takes a cruise module as an example, as shown in fig. 2, a main power supply loop in the figure is a main power supply module in fig. 1, current output from a main power supply to a constant-voltage current limiter passes through a voltage-stabilizing current-limiting power supply manager, and when a cruise motor works normally, the voltage-stabilizing current-limiting power supply manager is directly output to an electronic speed regulator and the cruise motor;
when the aircraft is in maneuvering action, the detection module is disconnected due to the limitation of the output current of the current-limiting power manager, and the cruise power supply simultaneously supplies power to the electronic speed regulator and the cruise motor,
after the maneuvering action of the aircraft is completed, the detection module is closed, and the power manager simultaneously outputs the normal working current of the cruise motor and the charging current of the cruise power supply until the battery of the cruise module is fully charged.
The vertical take-off and landing module is divided into two parts according to a left tail stay rod and a right tail stay rod, a voltage-stabilizing current-limiting power supply manager of a voltage-stabilizing current-limiting 18A is selected for each vertical module battery, and a lithium polymer battery with 79 W.h capacity and 75C discharge rate is selected for the vertical module battery;
when the aircraft vertically takes off and lands, the instantaneous current can reach about 130A, and at the moment, the energy of the vertical take-off and landing motor is mainly supplied by the vertical module battery;
after the vertical take-off and landing is finished, the voltage of the vertical module battery is reduced due to the discharge voltage, the voltage-stabilizing current-limiting power supply manager can charge the vertical module battery by using the current of 18A until the vertical module battery is fully charged, and the next vertical take-off and landing or hovering action can be carried out after the vertical module battery is fully charged.
The cruise module consists of a lithium polymer battery with 235 W.h capacity and 75C discharge rate and a power supply manager with voltage stabilization and current limitation of 25A;
when the aircraft normally navigates and flies horizontally, the consumed power is low, the power supply manager directly supplies power to the electric regulator and the motor, and when the aircraft performs maneuvering action, the battery of the cruise module discharges large current to supplement the lacking power; after the maneuver is completed, the power manager charges the cruise module battery with a current of 25A until full.
The device module comprises a control part, a load part and a steering engine part, wherein the control part comprises a 6s voltage device battery, a flight control device and a radio station, the flight control device and the radio station are responsible for control and communication of the unmanned aerial vehicle, the load part is various instrument devices carried by the unmanned aerial vehicle for completing flight tasks, the voltage used by the steering engine and the navigation lamp is 2s, and therefore a voltage-stabilizing current-limiting power supply manager is independently arranged. Although the batteries of the equipment module do not need to improve the heavy current discharge, when the flight process of the aircraft goes wrong, the batteries of the equipment module can be used as emergency power supplies to provide electric energy required by flight control, radio stations and forced landing of steering engines, and meanwhile, the time for storing data of load equipment is also given, so that the equipment is prevented from being powered off suddenly and losing data.
Example 2:
an aircraft power management system comprises a main power supply module and N power supply management modules, wherein the N power supply management modules are arranged in parallel, N is more than or equal to 1, the main power supply module comprises a main battery and a constant voltage current limiter electrically connected with the main battery, and the constant voltage current limiter is used for fixing the discharge current of the main battery;
the power supply management module comprises a voltage-stabilizing current-limiting power supply manager, a module battery, N motors and N electronic speed regulators, wherein N is larger than 1, the module battery, the N motors and the N electronic speed regulators are connected in series to form a loop, and the voltage-stabilizing current-limiting power supply manager is connected to two ends of a power supply in parallel;
the main power supply module is connected with the N power supply management modules through leads to charge the batteries of the modules in a constant-voltage current-limiting mode.
When the aircraft performs the action associated with the current voltage-stabilizing current-limiting power supply manager, the module battery simultaneously supplies power to the electronic speed regulator and the motor due to the limitation of the output current of the voltage-stabilizing current-limiting power supply manager; after the association action of the aircraft and the current voltage-stabilizing current-limiting power supply manager is finished, the voltage-stabilizing current-limiting power supply manager simultaneously outputs the normal working current of the cruise motor and the charging current of the module battery until the battery is fully charged.
The voltage-stabilizing current-limiting power manager comprises a detection module connected with the module battery in series, the detection module is used for detecting the cell voltage value of the module battery, acquiring the cell voltage value of the module battery during charging, and sending a signal to the voltage-stabilizing current-limiting power manager when the module battery reaches the cell voltage value or the total voltage of the battery pack reaches a cut-off voltage, so as to disconnect the corresponding voltage-stabilizing current-limiting power manager; the detection module disconnects the connection with the module battery when the aircraft performs the action associated with the current voltage-stabilizing current-limiting power supply manager; and the detection module is used for opening the connection with the module battery when the correlation action of the aircraft and the current voltage-stabilizing current-limiting power supply manager is completed.
The main battery adopts a low discharge rate high capacity battery.
The module battery includes, but is not limited to, a lithium polymer battery.
Utilize technical scheme, or technical personnel in the field are in the utility model discloses under technical scheme's the inspiration, design similar technical scheme, and reach above-mentioned technological effect, all fall into the utility model discloses a protection scope.
Claims (4)
1. An aircraft power management system, characterized by: the main power supply module comprises a main battery and a constant voltage current limiter electrically connected with the main battery, wherein the constant voltage current limiter is used for fixing the discharge current of the main battery;
the power supply management module comprises a voltage-stabilizing current-limiting power supply manager, a module battery, N motors and N electronic speed regulators, wherein N is larger than 1, the module battery, the N motors and the N electronic speed regulators are connected in series to form a loop, and the voltage-stabilizing current-limiting power supply manager is connected to two ends of a power supply in parallel;
the main power supply module is connected with the N power supply management modules through leads to charge the batteries of the modules in a constant-voltage current-limiting mode.
2. An aircraft power management system according to claim 1, wherein: the voltage-stabilizing current-limiting power manager comprises a detection module connected with the module battery in series, and the detection module detects the voltage value of a battery cell of the module battery.
3. An aircraft power management system according to claim 1, wherein: the main battery adopts a low discharge rate high capacity battery.
4. An aircraft power management system according to claim 1, wherein: the module battery includes a lithium polymer battery.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020188224.0U CN211981524U (en) | 2020-02-20 | 2020-02-20 | Aircraft power management system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020188224.0U CN211981524U (en) | 2020-02-20 | 2020-02-20 | Aircraft power management system |
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| Publication Number | Publication Date |
|---|---|
| CN211981524U true CN211981524U (en) | 2020-11-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020188224.0U Active CN211981524U (en) | 2020-02-20 | 2020-02-20 | Aircraft power management system |
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| CN (1) | CN211981524U (en) |
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2020
- 2020-02-20 CN CN202020188224.0U patent/CN211981524U/en active Active
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