CN111186585A - Multi-battery-module electric airplane power system and electric airplane - Google Patents
Multi-battery-module electric airplane power system and electric airplane Download PDFInfo
- Publication number
- CN111186585A CN111186585A CN201811354972.5A CN201811354972A CN111186585A CN 111186585 A CN111186585 A CN 111186585A CN 201811354972 A CN201811354972 A CN 201811354972A CN 111186585 A CN111186585 A CN 111186585A
- Authority
- CN
- China
- Prior art keywords
- battery
- electric
- motor
- module
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control; Arrangement thereof
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention belongs to the technical field of electric airplanes, and particularly relates to a multi-battery-module electric airplane power system and an electric airplane, wherein the multi-battery-module electric airplane power system comprises a motor, a propeller, a plurality of battery modules, a battery management system and an airplane power control system; the aircraft power control system is electrically connected with the battery management system, the motor and the plurality of battery modules through buses; the battery management system is electrically connected with the motor; the motor is connected with the propeller. The invention also relates to an electric aircraft with a multi-battery module power system. The aircraft power control system controls the battery modules deployed at different parts of the electric aircraft to supply power to the motor through the battery management system, and the motor drives the propeller coaxially connected with the motor to rotate to provide flight power.
Description
Technical Field
The invention belongs to the technical field of electric airplanes, and particularly relates to a multi-battery-module electric airplane power system and an electric airplane.
Background
With the increasing energy density of power batteries, electric airplanes powered by power batteries have come along. Whether electric aircraft are used as general purpose aircraft or branch transport aircraft, safety, efficiency, and comfort in operation are always goals of the aviation industry.
The electric aircraft on the market at present generally adopts a single power battery module, or a power battery module is formed by a plurality of battery units, and meanwhile, a set of battery management system and a single propeller propulsion power system mode are shared. Although such electric aircrafts can perform basic flight tasks, a series of problems still exist, and at the same time, the technical advantages of the electric aircrafts are not exerted. Firstly, for an electric airplane provided with a single battery management system and a single power battery pack, if the battery management system and the power battery pack fail or have deteriorated functions in the flying process, the thrust of the airplane is directly reduced or the airplane is stopped in the air, and particularly in the takeoff stage of the airplane, the result is particularly serious; secondly, the mass of the power battery pack is concentrated at a certain part of the airplane due to the fact that the electric airplane is provided with the single power battery pack or a plurality of battery units which are concentrated, and in order to solve the problems, the body structure of the part is often required to be strengthened; thirdly, the configuration of a single power battery pack for the electric airplane has serious influence on the gravity center position of the airplane, and is not beneficial to improving the maneuvering performance and the falling adaptability of the airplane; fourthly, the single power battery pack has large volume, needs to occupy large airplane structure space, and influences airplane driving and riding comfort; fifthly, after the flight of the electric airplane with the single power battery pack is finished, the power battery pack needs to be integrally charged or integrally replaced no matter how the power consumption is; sixth, the design of a single power battery module results in a large capacity of the battery module, and due to the limitation of battery technology, the problem of inconsistent performance of battery units caused by a large capacity is more serious, which directly affects the dynamic performance, reliability and service life of the airplane.
Disclosure of Invention
The invention provides a multi-battery-module electric airplane power system and an electric airplane, which can solve the technical problems of poor operation safety of the electric airplane in the prior art and low operation efficiency and poor comfort of the electric airplane in the prior art.
In order to solve the problems, the invention provides a multi-battery module electric airplane power system and an electric airplane, and the technical scheme is as follows:
a multi-battery module electric aircraft power system, comprising: a motor, a propeller, a plurality of battery modules, a Battery Management System (BMS), and an aircraft power control system (PCU); the motor is arranged on the electric airplane and is coaxially connected with the propeller; the plurality of battery modules are arranged at the same part or different parts (preferably different parts) of the electric airplane, are electrically connected with the motor and are used for supplying power to the motor; the battery management system is electrically connected with the plurality of battery modules; the aircraft power control system is electrically connected with the battery management system, the motor and the plurality of battery modules through a bus and is used for providing operation control and implementing a propulsion scheme for the operation of the electric aircraft.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the plurality of battery modules are connected in series and electrically connected with the aircraft power control system and the battery management system; the aircraft power control system controls the power supply state of the battery module with abnormal state through the on-off of the battery module in the circuit controlled by the battery management system, and controls the rest of the battery modules to be connected in series for power supply. After the performance of one battery module is attenuated or failed, the aircraft power control system cuts off the connection of the battery module through the battery management system, and the rest battery modules are continuously connected in series to supply power for the motor.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the aircraft power control system controls the balanced use and the sequential use of the electric energy of the plurality of battery modules through the battery management system.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the battery module comprises a module box body and a plurality of soft package battery units; the inner wall of the module box body is provided with a heat insulation layer, and the front side surface and the rear side surface of the module box body are provided with ventilation openings; and the soft package battery units are connected in series in the module box body.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the module box body is made of light metal; the heat-insulating layer is made of fireproof foam materials.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the battery management system comprises an acquisition module for acquiring the working voltage, the output current and the temperature of each battery module.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the aircraft power control system calculates the output power of the motor and the aircraft performance requirement, and combines the health state of the motor and each battery module to implement a control scheme.
In the multi-battery-module electric aircraft power system described above, it is further preferable that: the motor has a generator function, and charges at least one battery module through the battery management system under a certain flight condition.
The multi-battery-module electric aircraft power system as described above is more preferably; the battery management system is one and is respectively and electrically connected with the aircraft power control system and the plurality of battery modules.
The multi-battery-module electric aircraft power system as described above is more preferably; the aircraft power control system comprises a plurality of battery management systems, each battery management system is electrically connected with one battery module correspondingly, and each battery management system is electrically connected with the aircraft power control system.
An electric airplane with a multi-battery-module power system comprises an airplane body, wherein an airplane power control system, a battery management system, a motor, a propeller and a plurality of battery modules are mounted on the airplane body; the motor is coaxially connected with the propeller; the plurality of battery modules are electrically connected with the motor; the battery management system is electrically connected with the plurality of battery modules; the aircraft power control system is electrically connected with the battery management system, the motor and the plurality of battery modules through buses.
The electric aircraft with the multi-battery module power system as described above is further preferably: the propeller and the motor are respectively one, and the propeller and the motor are coaxially connected and are arranged on a longitudinal axis of the electric airplane.
The electric aircraft with the multi-battery module power system as described above is further preferably: the electric aircraft comprises a plurality of propellers and motors, wherein the propellers are coaxially connected with the motors in a one-to-one correspondence manner, and the propellers are symmetrically distributed on the wings of the electric aircraft by taking the longitudinal axis of the electric aircraft as a symmetric center.
Analysis shows that compared with the prior art, the invention has the advantages and beneficial effects that:
1. according to the invention, the plurality of battery modules are arranged at different parts of the electric airplane, so that the energy of a single battery module can be reduced, and after the single battery module fails, the rest battery modules are not influenced to provide power for the electric airplane to fly, so that the flying safety of the electric airplane is improved; meanwhile, the load from the battery module can be distributed on the body structure of the electric airplane more evenly, so that the load of the body structure of the electric airplane is optimized, and the control performance of the electric airplane is improved; through the scattered configuration of a plurality of battery modules on electric aircraft organism, can also enlarge the commercial space, improve electric aircraft's travelling comfort and carrying capacity to have that the security is strong, the nature controlled is good, operating efficiency is high, the characteristics that the travelling comfort is good.
2. The aircraft power control system is respectively electrically connected with the battery management system and the plurality of battery modules, after the performance of one battery module is attenuated or loses efficacy, the aircraft power control system can cut off the connection of the battery module through the battery management system, control the rest battery modules to be continuously connected in series for power supply, and simultaneously alarm and start an emergency flight mode, so that the aircraft power control system is safe and reliable; the aircraft power control system is matched with the battery management system, the electric energy of the plurality of battery modules can be reasonably used, and the electric aircraft has the characteristics of reasonable electric energy use, safety and reliability on the premise of ensuring the safe takeoff of the electric aircraft.
3. The battery module is in a modular design, is convenient to replace and install quickly, and can improve the service efficiency of the electric airplane; meanwhile, the operation of the battery module can be thermally managed, so that the operation efficiency of the battery module in work is improved; the battery module can also be used as an auxiliary power device to play a role, and the safety performance of the electric airplane is improved, so that the electric airplane has the characteristics of high working efficiency and high safety.
4. The invention makes full use of the characteristics of small volume and light weight of the battery management system to carry out redundancy design on the battery management system, thereby greatly improving the reliability of the electric airplane. Through the diversified design of the battery management system, the electric airplane with various takeoff weights can be covered in the application range, and the application range is wide, so that the electric airplane has the characteristics of strong reliability and wide application range.
5. The battery management system can acquire the working voltage, the output current and the temperature of the soft package battery unit of each battery module so that the aircraft power control system can implement a corresponding control scheme by combining the motor and the health state of each battery module, and has the characteristics of high safety and good controllability.
6. When the electric airplane descends to a lower altitude and reduces the speed, the electric airplane can reduce the flight energy consumption through the conversion from the motor to the generator, and has the characteristic of low flight energy consumption.
Drawings
Fig. 1 is a first connection schematic diagram of a multi-battery-module electric aircraft power system according to the present invention.
Fig. 2 is a connection schematic diagram of a multi-battery-module electric aircraft power system according to the present invention.
Fig. 3 is a third connection schematic diagram of the multi-battery module electric aircraft power system of the invention.
Fig. 4 is a first structural schematic diagram of the multi-battery-module electric aircraft power system according to the present invention.
Fig. 5 is a top view of fig. 4.
Fig. 6 is a connection block diagram of the multi-battery module electric aircraft power system of the present invention.
Fig. 7 is a logic diagram of a multi-battery module electric aircraft power system of the present invention.
Fig. 8 is a schematic structural diagram of a multi-battery-module electric aircraft power system according to a second embodiment of the present invention.
Fig. 9 is a top view of fig. 8.
Fig. 10 is a first schematic diagram of an electric aircraft having a multi-battery module power system in accordance with the present invention.
Fig. 11 is a top view of fig. 10.
Fig. 12 is a second schematic diagram of an electric aircraft having a multi-battery module power system in accordance with the present invention.
Fig. 13 is a top view of fig. 12.
In the figure: 1-a battery module; 2, a propeller; 3, a motor; 4-an aircraft power control system; 5-battery management system.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are for convenience of description of the present invention only and do not require that the present invention must be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. The terms "connected" and "connected" used herein should be interpreted broadly, and may include, for example, a fixed connection or a detachable connection; they may be directly connected or indirectly connected through intermediate members, and specific meanings of the above terms will be understood by those skilled in the art as appropriate.
As shown in fig. 1 to 5, the present invention provides a multi-battery module electric aircraft power system, which mainly includes a motor 3, a propeller 2, a plurality of battery modules 1, a battery management system 5 and an aircraft power control system 4; the motor 3 is arranged on the electric airplane and is coaxially connected with the propeller 2; the plurality of battery modules 1 are arranged at the same part or different parts of the electric airplane, are electrically connected with the motor 3 and are used for supplying power to the motor 3; the battery management system 5 is electrically connected with the plurality of battery modules 1; the aircraft power control system 4 is electrically connected with the battery management system 5, the motor 3 and the plurality of battery modules 1 through a bus, and is used for providing operation control and implementing a propulsion scheme of the operation of the electric aircraft, wherein the bus comprises a high-bit data line (CAN-H) and a low-bit data line (CAN-L).
Specifically, the airplane power control system 4 of the multi-battery-module electric airplane power system controls the plurality of battery modules 1 to supply power to the motor 3 through the battery management system 5, and the motor 3 drives the propeller 2 coaxially connected with the motor to rotate so as to provide flight power for the electric airplane. According to the invention, a plurality of battery modules 1 are arranged at different positions of the electric airplane, and the structural space mainly used for installation comprises the front and rear parts of a cockpit and the front and rear double beams of a wing. According to the invention, the plurality of battery modules 1 are arranged at different positions of the electric airplane body, so that the energy of a single battery module 1 can be reduced, and after the single battery module 1 fails, the rest battery modules 1 are not influenced to provide power for the electric airplane to fly, thereby being beneficial to improving the flying safety of the electric airplane; by distributing and configuring the plurality of battery modules 1, the loads from the battery modules 1 can be more evenly distributed on the body structure of the electric airplane, so that structural failure caused by overload (such as deformation or fracture failure of structural members at the mass concentration part of the body of the electric airplane caused by heavy landing or air bump) is avoided, the load of the body structure of the electric airplane is favorably optimized, and the control performance of the electric airplane is improved; through the scattered configuration of a plurality of battery module 1 on electric aircraft organism, can enlarge the commercial space, improve electric aircraft's travelling comfort and carrying capacity to have that the security is strong, the nature controlled is good, operating efficiency is high, the characteristics that the travelling comfort is good.
As shown in fig. 1, 6 and 7, the aircraft power control system 4 of the present invention mainly includes a central display unit, an inverter unit, a bus communication unit and a central control unit, and the aircraft power control system 4 is used for collecting and processing signals, providing operation control for the electric aircraft, and implementing a propulsion scheme required by the flight performance of the electric aircraft. The battery management system 5 is used for monitoring and managing the battery module 1. Battery management system 5 detects every battery module 1's operating voltage, output current, the three parameter of temperature, the health status of every group battery module 1 can be judged to the central control unit in view of the above (when using lithium ion battery unit to constitute battery module 1, average laminate polymer battery unit operating voltage is less than 2.5V, or average laminate polymer battery unit output current is less than 0.2C multiplying power and discharges, or laminate polymer battery unit temperature is higher than 60 degrees centigrade, battery management system 5 judges this battery module 1 inefficacy), simultaneously, central display unit reports an emergency and asks for help or increased vigilance to the driver. The inverter unit of the airplane power control system 4 is electrically connected with the motor 3, the tail end mutual inductance circuit of the inverter unit can acquire the working current and the working voltage of the motor 3, after digital-to-analog conversion, the central control unit calculates and determines the actual power of the motor 3, the actual power is displayed on the central display unit, and the actual power is used as a key parameter of flight capacity in different flight stages and is displayed on an operation interface of the electric airplane.
In order to improve the flight safety of the present invention, as shown in fig. 4, 5, 8, and 9, a plurality of battery modules 1 of the present invention are connected in series and electrically connected to an aircraft power system and a battery management system 5; the aircraft power control system 4 controls the on-off of the battery module 1 in an abnormal state (the battery management system 5 judges that the battery module 1 is invalid) through the battery management system 5, and controls the series connection of the other battery modules 1 to supply power, and specifically, the battery management system 5 controls the on-off of each battery module 1 in a circuit through a relay. After the performance of one battery module 1 is attenuated or failed (if the working voltage output is lower than the lowest discharge threshold value of the battery module 1 or the temperature exceeds the limit, namely the failure condition of the battery module 1 is met), the aircraft power control system 4 cuts off the connection of the battery module 1 through the battery management system 5, the rest battery modules 1 are continuously connected in series to supply power to the motor 3, an alarm is given on the operation interface of the electric aircraft, an emergency flight mode is started (landing as soon as possible), and the flight safety of the electric aircraft is conveniently ensured, so that the aircraft power control system has the characteristics of safety and reliability.
In order to reasonably use electric energy, as shown in fig. 1 and 7, the aircraft power control system 4 controls the plurality of battery modules 1 to use electric energy in a balanced manner or in a sequential manner according to flight performance requirements through the battery management system 5, and is completed by a balanced control unit of the battery management system 5, and whether the battery modules 1 supply power or not is controlled according to actual requirements. In the takeoff stage of the electric airplane, all the battery modules 1 provide power output to ensure enough power output, so that the flight safety is ensured; the multi-battery module 1 balance power supply scheme is suitable for long-range and long-time flight tasks; in the flight task of carrying out short voyage, short flight time, the aircraft uses the electric power of all battery module 1 to take off the back, and the pilot can manually operation aircraft power control system 4, selects the working method that uses battery module 1 electric quantity in proper order, can only change the outfit fast or charge insufficient voltage battery module 1 after carrying out the short time flight task, is favorable to improving operating efficiency, carries out next flight preparation after the flight task of being convenient for is accomplished. The electric airplane has the advantage that the electric energy of the plurality of battery modules 1 is reasonably used through the battery management system 5, and the electric airplane has the characteristic of reasonable electric energy use on the premise of ensuring the safe takeoff of the electric airplane.
In order to further improve the safety of the present invention, as shown in fig. 4 and 8, the battery module 1 of the present invention may be mounted on the wing of an electric aircraft as a "non-replaceable structure" and may function as an auxiliary power unit (EAPU). The battery module 1 arranged on the wing part of the electric airplane makes full use of the wing to provide direct lift force, the flight performance can be greatly improved, the structure of the airplane is optimized, and the battery module 1 of the part is inspected regularly and charged for maintenance, so that the electric airplane has the characteristic of high safety.
In order to improve the use efficiency of the electric airplane and facilitate the management of the battery module 1, as shown in fig. 1, the battery module 1 of the present invention includes a module case and a plurality of soft-package battery units; the inner wall of the box body is provided with a heat insulation layer, the front side surface and the rear side surface of the box body are provided with ventilation openings, and the ventilation openings correspond to air entraining valves of the electric airplane and are used for cooling the battery module 1 by air cooling; and the soft package battery units are connected in series in the box body. Preferably, the module box body is made of light metal materials, such as light aluminum alloy; the heat-insulating layer is made of fireproof foam materials. The battery module 1 adopts a modular design, so that the quick replacement of part or all of the battery modules 1 in the landing clearance of the electric airplane is facilitated, and the use efficiency of the electric airplane is improved; meanwhile, the invention utilizes the characteristic that the atmospheric temperature descends along with the rise of the altitude, introduces the high altitude atmosphere outside the electric aircraft body to carry out air cooling on the battery module 1, and is beneficial to reducing the heat concentration of the battery module 1; and when flying in cold environment, can heat battery module 1 before electric aircraft takes off, and the module incasement wall of battery module 1 is equipped with the heat preservation, can keep warm to battery module 1 after the heating, does not carry out the forced air cooling this moment, can guarantee the temperature of electric aircraft flight in-process battery module 1, makes battery module 1 move in best discharge environment (20 ℃ to 50 ℃), realizes the thermal management of battery module 1. According to the invention, through the modularized design of the battery module 1 and the heat management of the operation of the battery module 1, the use frequency of the electric airplane and the operation efficiency of the battery module 1 during operation can be improved, so that the electric airplane has the characteristics of high use efficiency and convenience in management.
In order to improve the operability of the present invention, as shown in fig. 1 and fig. 6, the battery management system 5 of the present invention includes collecting modules (battery module voltage and temperature collecting units) for respectively collecting the operating voltage, the output current and the temperature of each battery module 1. The acquisition module mainly comprises an A/D converter, a shunt and a temperature sensor, the acquisition module selects the A/D converter with 12-bit precision for voltage sampling, the working voltage of each battery module 1 can be detected and calculated through a serial bus, and the current of the battery modules 1 is obtained by performing digital-to-analog conversion after the shunt is detected; the temperature sensor is installed in each soft package battery unit of each battery module 1, the type of the temperature sensor is preferably a digital temperature sensor, the type of the digital temperature sensor can be DS18B20, and the digital temperature sensor is used for detecting the temperature of a test point in each battery module 1. The aircraft power control system 4 calculates the output power of the motor 3 and the aircraft performance requirements, displays the output power and the aircraft performance requirements on a flight operation interface of the electric aircraft, and implements a corresponding control scheme by combining the motor 3 and the health state of each battery module 1. In different flight stages, the power control system 4 of the airplane adjusts the output power of the motor 3 to realize the flight performance required by the electric airplane. In the takeoff stage, the aircraft power control system 4 calculates the required output power of the motor 3 according to environmental parameters such as field pressure, atmospheric temperature, runway gradient, pavement condition, wind speed and the like and performance data of the electric aircraft, and the required output power is used as the lowest power required by takeoff, when the maximum takeoff power is lower than the lowest power, the operation interface of the electric aircraft gives an alarm, and the takeoff is terminated; in the cruising stage, the aircraft power control system 4 can change the thrust of the electric aircraft by adjusting the output power of the motor 3, and different flight postures are realized by combining the operation of the flight control surface of the electric aircraft, so that the invention has the characteristics of strong safety and good controllability.
In order to further reduce the flight energy consumption of the present invention, as shown in fig. 1, the motor 3 of the present invention has a function of a generator 3, and under a certain condition, the motor 3 is converted into the generator 3, and the battery management system 5 feeds back the power to at least one battery module 1 for charging. Wherein, certain conditions mean that the motor 3 is converted into the feedback power of the generator 3 under two flight conditions, namely, descending altitude and descending speed. The descending height can cause the flying speed of the electric airplane to be increased, and the feedback moment generated by the electricity generation of the motor 3 is used for reducing the windmill effect of the propeller 2 and preventing the rotating speed of the propeller 2 from being increased; in the process of the flat flight deceleration of the electric airplane, the rotating speed of the propeller 2 can be reduced by the feedback torque generated by the power generation of the motor 3. When the motor 3 of the present invention is used as the generator 3 to feed back electric power, the battery management system 5 controls the charging current through the pulse width modulation circuit, thereby limiting the feedback torque. When the electric airplane descends to a lower altitude and reduces the speed, the flying energy consumption of the electric airplane can be reduced through the conversion from the motor 3 to the generator 3, and the electric airplane has the characteristic of low flying energy consumption.
In order to expand the application range of the present invention, as shown in fig. 1 and 2, one battery management system 5 of the present invention is electrically connected to the aircraft power control system 4 and the plurality of battery modules 1. The multi-battery module 1 electric aircraft power system adopting the single battery management system 5 comprises an aircraft power control system 4, a battery management system 5, a plurality of battery modules 1, a motor 3 and a propeller 2. The airplane power control system 4 is electrically connected with the battery management system 5 and the motor 3 through a bus, the working states of the motor 3 and the battery module 1 are monitored in real time, and corresponding propulsion schemes are implemented according to performance requirements or under the conditions of performance attenuation and failure of partial power systems. The electric energy management scheme required by the flight performance of the electric airplane is implemented by the airplane power control system 4 through the unique battery management system 5, the electric energy management scheme comprises the steps of balancing or sequentially using the plurality of battery modules 1, feeding back and charging the motor 3 under a specific flight condition, and responding to an emergency when part of the battery modules 1 fail, and the electric energy management scheme is suitable for unmanned planes and small airplanes. As a further popularization, the number of the battery management systems 5 is multiple, each battery management system 5 is correspondingly and electrically connected with one battery module 1, and each battery management system 5 is electrically connected with the aircraft power control system 4. The battery management system 5 has the characteristics of high power load and small volume, and the working reliability of the battery management system is directly related to flight safety. The invention makes full use of the characteristics of small volume and light weight of the battery management system 5 to carry out redundancy design on the battery management system 5, thereby greatly improving the reliability of the electric airplane. The multi-battery module 1 electric airplane power system adopting the multiple battery management systems 5 comprises an airplane power control system 4, the multiple battery management systems 5, the multiple battery modules 1, a motor 3 and a propeller 2. The aircraft power control system 4 is electrically connected with the battery management systems 5 and the motor 3 through a bus, the working states of the motor 3 and the battery module 1 are monitored in real time, and a corresponding propulsion scheme is implemented according to performance requirements or under the condition that the performance of part of power systems is attenuated and fails. The airplane power control system 4 implements an electric energy management scheme required by the flight performance of the electric airplane through the battery management systems 5 corresponding to the battery modules 1 one by one, and comprises the steps of balancing or sequentially using the battery modules 1, feeding back and charging the motor 3 under a specific flight condition, and responding emergently under the condition that part of the battery modules 1 and part of the battery management systems 5 are invalid, and the airplane power control system is suitable for branch-line aviation passenger transport or freight transport electric airplanes. The battery management system 5 is designed in a diversified manner, the application range of the battery management system covers various types of electric airplanes, the application range of the battery management system is further expanded, and the battery management system has the characteristic of wide application range.
As shown in fig. 1, 3, 10 to 13, the present invention further provides an electric airplane with a multi-battery module power system, which comprises an airframe, wherein an airplane power control system 4, a battery management system 5, a motor 3, a propeller 2 and a plurality of battery modules 1 are installed on the airframe; the motor 3 is coaxially connected with the propeller 2; the plurality of battery modules 1 are electrically connected with the motor 3; the battery management system 5 is electrically connected with the plurality of battery modules 1; the aircraft power control system 4 is electrically connected with the battery management system 5, the motor 3 and the plurality of battery modules 1 through a bus. The electric airplane provided by the invention is provided with the airplane power control system 4, the battery management system 5, the motor 3, the propeller 2 and the plurality of battery modules 1, and has the characteristics of strong safety, good controllability, strong carrying capacity, good comfort and high use efficiency of a multi-battery-module electric airplane power system.
In order to expand the application range of the invention, as shown in fig. 1, fig. 3, fig. 10 to fig. 13, the propeller 2 and the motor 3 of the invention are respectively one, the propeller 2 and the motor 3 are coaxially connected and are arranged on the longitudinal axis of the electric airplane, and further, the propeller 2 is arranged at the front end of the nose or the rear end of the cabin of the electric airplane and is suitable for unmanned planes and small airplanes. The propellers 2 and the motors 3 can be respectively multiple, the propellers 2 and the motors 3 are coaxially connected in a one-to-one correspondence mode, the propellers are symmetrically distributed on the wings of the electric airplane by taking the longitudinal axis of the electric airplane as a symmetric center, and the electric airplane is suitable for branch aviation passenger transport or freight transport electric airplanes, so that the electric airplane has the characteristic of wide application range.
Example 1:
as shown in fig. 1, 10 and 11, the model of the electric aircraft provided in this embodiment is a small unmanned plane or a light sports aircraft, and the rotary propeller 2 is installed in front of the nose of the electric aircraft. One battery management system 5 corresponds to a plurality of battery modules 1, for example, five battery modules 1, four battery modules 1 are respectively mounted on both wings of the electric aircraft, and one battery module 1 is mounted at the rear of the cabin of the electric aircraft. The electric aircraft is used for entertainment and sports flight, aerial photography and aerial survey or as an unmanned aerial vehicle flight platform.
Example 2:
as shown in fig. 2, 10 and 11, the model of the electric airplane provided by this embodiment may be a small airplane, the seat number is 4, the maximum take-off total weight is 1000-. The plurality of battery management systems 5 correspond to the plurality of battery modules 1 one to one, for example, five battery modules 1 are provided, four battery modules 1 are respectively installed on both wings of the electric aircraft, and one battery module 1 is installed at the rear part of the cabin of the electric aircraft. The electric aircraft is now used for flight training, personal flight, aerial surveying, etc.
Example 3:
as shown in fig. 3, 12 and 13, the model of the electric airplane provided by the present embodiment may be a medium-or large-sized branch airplane, in which the propellers 2 are installed on both wings of the electric airplane. The number of the propellers 2 is two, the two propellers 2 are symmetrically distributed by taking the longitudinal axis of the electric airplane as a reference, and each propeller 2 corresponds to one motor 3. The plurality of battery management systems 5 correspond to the plurality of battery modules 1 one to one, for example, five battery modules 1 are provided, four battery modules 1 are respectively installed on both wings of the electric aircraft, and one battery module 1 is installed at the rear part of the cabin of the electric aircraft. The fixed wing electric aircraft is now used for branch line airline passenger or freight transportation.
It will be appreciated by those skilled in the art that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The embodiments disclosed above are therefore to be considered in all respects as illustrative and not restrictive. All changes which come within the scope of or equivalence to the invention are intended to be embraced therein.
Claims (10)
1. A multi-battery module electric aircraft power system, comprising:
the system comprises a motor, a propeller, a plurality of battery modules, a battery management system and an aircraft power control system;
the motor is arranged on the electric airplane and is connected with the propeller;
the plurality of battery modules are mounted on the electric airplane and electrically connected with the motor;
the battery management system is electrically connected with the plurality of battery modules;
the aircraft power control system is electrically connected with the battery management system, the motor and the plurality of battery modules through a bus and used for providing operation control.
2. The multi-battery module electric aircraft power system of claim 1, characterized in that:
the aircraft power control system is used for controlling the power supply state of the battery modules through the battery management system.
3. The multi-battery module electric aircraft power system of claim 1, characterized in that:
the battery module comprises a module box body and a plurality of soft package battery units; the inner wall of the module box body is provided with a heat insulation layer, and the front side surface and the rear side surface of the module box body are provided with ventilation openings; and the soft package battery units are connected in series in the module box body.
4. The multi-battery module electric aircraft power system of claim 1, characterized in that:
the battery management system is provided with an acquisition module for acquiring a plurality of signals of the battery modules.
5. The multi-battery module electric aircraft power system of claim 1, characterized in that:
the motor has a generator function and is used for driving the propeller and charging at least one battery module through the battery management system.
6. The multi-battery module electric aircraft power system according to any one of claims 1 to 5, characterized in that:
the battery management system is one and is respectively and electrically connected with the aircraft power control system and the plurality of battery modules.
7. The multi-battery module electric aircraft power system according to any one of claims 1 to 5, characterized in that:
the aircraft power control system comprises a plurality of battery management systems, each battery management system is electrically connected with one battery module correspondingly, and each battery management system is electrically connected with the aircraft power control system.
8. An electric aircraft with many battery module driving system, includes organism its characterized in that:
the aircraft body is provided with an aircraft power control system, a battery management system, a motor, a propeller and a plurality of battery modules;
the motor is connected with the propeller; the plurality of battery modules are electrically connected with the motor; the battery management system is electrically connected with the plurality of battery modules; the aircraft power control system is electrically connected with the battery management system, the motor and the plurality of battery modules through buses.
9. The electric aircraft with the multi-battery module power system of claim 8, wherein:
the propeller and the motor are respectively one, and the propeller is connected with the motor and is arranged on the longitudinal axis of the electric airplane.
10. The electric aircraft with the multi-battery module power system of claim 8, wherein:
the electric aircraft comprises a plurality of propellers and motors, wherein the propellers are connected with the motors in a one-to-one correspondence mode, and the propellers and the motors are symmetrically distributed on the wings of the electric aircraft by taking the longitudinal axis of the electric aircraft as a symmetric center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811354972.5A CN111186585A (en) | 2018-11-14 | 2018-11-14 | Multi-battery-module electric airplane power system and electric airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811354972.5A CN111186585A (en) | 2018-11-14 | 2018-11-14 | Multi-battery-module electric airplane power system and electric airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111186585A true CN111186585A (en) | 2020-05-22 |
Family
ID=70703228
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811354972.5A Pending CN111186585A (en) | 2018-11-14 | 2018-11-14 | Multi-battery-module electric airplane power system and electric airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111186585A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113871739A (en) * | 2021-09-03 | 2021-12-31 | 上海智光电力技术有限公司 | Switching device and system of battery module and battery information acquisition control method |
| CN113991263A (en) * | 2021-10-09 | 2022-01-28 | 广东汇天航空航天科技有限公司 | Power system and flyable device |
| CN113998123A (en) * | 2021-10-09 | 2022-02-01 | 广东汇天航空航天科技有限公司 | Power system, flyable device and power control method |
| US11420534B1 (en) * | 2021-10-30 | 2022-08-23 | Beta Air, Llc | System and methods for preconditioning a power source of an electric aircraft |
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
| WO2023091235A3 (en) * | 2021-10-30 | 2023-10-19 | Beta Air, Llc | System and methods for preconditioning a power source of an electric aircraft |
| US11835591B2 (en) * | 2021-11-18 | 2023-12-05 | Beta Air, Llc | Electric aircraft battery pack and methods of use |
-
2018
- 2018-11-14 CN CN201811354972.5A patent/CN111186585A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113871739A (en) * | 2021-09-03 | 2021-12-31 | 上海智光电力技术有限公司 | Switching device and system of battery module and battery information acquisition control method |
| CN113871739B (en) * | 2021-09-03 | 2024-03-29 | 上海智光电力技术有限公司 | Switching device and system of battery module and battery information acquisition control method |
| CN113991263A (en) * | 2021-10-09 | 2022-01-28 | 广东汇天航空航天科技有限公司 | Power system and flyable device |
| CN113998123A (en) * | 2021-10-09 | 2022-02-01 | 广东汇天航空航天科技有限公司 | Power system, flyable device and power control method |
| CN113998123B (en) * | 2021-10-09 | 2023-06-02 | 广东汇天航空航天科技有限公司 | Power system, flyable device and power control method |
| CN113991263B (en) * | 2021-10-09 | 2023-06-02 | 广东汇天航空航天科技有限公司 | Power system and flyable device |
| US11420534B1 (en) * | 2021-10-30 | 2022-08-23 | Beta Air, Llc | System and methods for preconditioning a power source of an electric aircraft |
| WO2023091235A3 (en) * | 2021-10-30 | 2023-10-19 | Beta Air, Llc | System and methods for preconditioning a power source of an electric aircraft |
| US11835591B2 (en) * | 2021-11-18 | 2023-12-05 | Beta Air, Llc | Electric aircraft battery pack and methods of use |
| CN115347336A (en) * | 2022-10-18 | 2022-11-15 | 中国空气动力研究与发展中心空天技术研究所 | Unmanned aerial vehicle distributed power battery |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111186585A (en) | Multi-battery-module electric airplane power system and electric airplane | |
| CN110650889B (en) | EVTOL aircraft using large-scale variable-speed tilting rotor | |
| US20220011782A1 (en) | Method And System For Safely Landing A Battery Powered Electric VTOL Aircraft In A Low Charge Condition | |
| CN207697997U (en) | A kind of more rotors of measurement type are tethered at unmanned vehicle system | |
| US20210269152A1 (en) | Distributed electric energy pods network and associated electrically powered vehicle | |
| CN107074366B (en) | Helicopter | |
| CN108116668B (en) | Air-ground dual-purpose all-electric multi-rotor manned aircraft | |
| US20210221526A1 (en) | Parallel hybrid electric propulsion motor and electric power module | |
| KR102004227B1 (en) | VERTICAL TAKE OFF AND LANDING AIRCRAFT USING HYBRID-ELECTRIC PROPULSION SYSTEM and THE CONTROL METHOD | |
| KR101970601B1 (en) | Vertical takeoff and landing aircraft using hybrid-electric propulsion system | |
| CN105173073A (en) | Composite lift force type unmanned aerial vehicle realizing vertical take-off and landing | |
| WO2020107373A1 (en) | Power assembly, power system and unmanned aerial vehicle | |
| CN205675239U (en) | Hybrid power four dual rotation propeller tiltrotor | |
| CN110683051B (en) | Electric power supply system for an aircraft and corresponding aircraft | |
| CN103600843B (en) | The unmanned plane that hand-thrown takes off | |
| Gnadt et al. | Hybrid turbo-electric STOL aircraft for urban air mobility | |
| Ugwueze et al. | Investigation of a mission-based sizing method for electric VTOL aircraft preliminary design | |
| GB2576250A (en) | Aircraft | |
| CN102673769A (en) | Photovoltaic buoyancy biplane, photovoltaic buoyancy flying saucer and photovoltaic buoyancy unmanned plane | |
| CN112912310A (en) | Unmanned transport aircraft with distributed batteries and power supply method thereof | |
| RU147731U1 (en) | AIRCRAFT | |
| CN211592930U (en) | Small-size electronic coaxial reverse double-deck rotor manned helicopter | |
| CN112407269A (en) | Mixed aircraft of stationary vane rotor | |
| CN209290703U (en) | More battery modules electric airplane dynamical systems and electric airplane | |
| RU2694695C1 (en) | Method of distribution and control of rotorcraft with helicopter drive hybrid system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |