CN111169647A - Contra-rotating propeller serial driving system of electric aircraft and electric aircraft - Google Patents
Contra-rotating propeller serial driving system of electric aircraft and electric aircraft Download PDFInfo
- Publication number
- CN111169647A CN111169647A CN201811332086.2A CN201811332086A CN111169647A CN 111169647 A CN111169647 A CN 111169647A CN 201811332086 A CN201811332086 A CN 201811332086A CN 111169647 A CN111169647 A CN 111169647A
- Authority
- CN
- China
- Prior art keywords
- power source
- electric
- electric power
- contra
- brake
- 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
- 238000001514 detection method Methods 0.000 claims description 35
- 238000012423 maintenance Methods 0.000 abstract description 18
- 238000013461 design Methods 0.000 abstract description 6
- 230000005540 biological transmission Effects 0.000 abstract description 5
- 230000008439 repair process Effects 0.000 abstract description 5
- 239000011295 pitch Substances 0.000 description 10
- 238000009413 insulation Methods 0.000 description 6
- 238000006243 chemical reaction Methods 0.000 description 5
- 230000036541 health Effects 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 230000008901 benefit Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000004044 response Effects 0.000 description 4
- 238000009423 ventilation Methods 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002441 reversible effect Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
- 238000012549 training Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
-
- 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)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention belongs to the technical field of electric airplanes, and particularly relates to a contra-rotating propeller serial driving system of an electric airplane and the electric airplane, wherein the contra-rotating propeller serial driving system of the electric airplane comprises a contra-rotating propeller, a first electric power source, a second electric power source, a braking unit and a power control unit; the first screw propeller of the contra-rotating screw propeller is arranged on the first electric power source, the second screw propeller of the contra-rotating screw propeller is arranged on the second electric power source, and the braking unit and the power control unit are respectively connected with the first electric power source and the second electric power source. The invention also provides an electric airplane with the contra-rotating propeller tandem driving system. The invention removes the structure of the transmission of the gear box, adopts the redundancy design and has the characteristics of strong safety, long range, low flight noise and convenient maintenance and repair.
Description
Technical Field
The invention belongs to the technical field of electric airplanes, and particularly relates to a contra-rotating propeller serial driving system of an electric airplane and the electric airplane.
Background
The electric airplane has the characteristics of safety, reliability, environmental protection, good maintainability and low operation cost, and has wide application prospect along with the continuous improvement of the energy density of the battery and the application of novel solid batteries and fuel cells. However, as the power system of the aircraft, there are many problems in practical use, whether the power system is a traditional piston engine, a turboprop engine, or a single-engine single-propeller system using a motor as a power device to drive a single propeller directly or through a gear box: firstly, the power device generates a reverse moment to the airframe, which brings inconvenience to flight operation, and even a series of asymmetric designs need to be carried out on the airplane in order to overcome the reverse moment; secondly, the single propeller power system has low efficiency and directly influences the range of the electric airplane; thirdly, the single-propeller electric airplane has low reliability, and after the motor fails, the flight safety is difficult to guarantee; fourth, single propeller power systems are noisy.
Contra-rotating propeller power system can effectively solve the drawback of single screw power system, however when the contra-rotating propeller solves above-mentioned problem, there is the additional problem, promptly: when two propellers are used for coaxial contrarotation to offset the reverse moment generated by the propellers on the machine body, a gear box is generally added between the power device and the propellers. However, in either form, the gearbox adds to the weight of the aircraft, as well as to the complexity of the power system and the maintenance and repair costs associated with its use.
The application discloses an electric double-coaxial same-side reverse-rotation tilt rotor craft, and the power scheme of the craft is that two motors are arranged, the two motors are oppositely arranged and coaxial, power generated by the motors is transmitted to a rotor inner shaft and a rotor outer shaft through a transmission mechanism, the rotation directions of the rotor inner shaft and the rotor outer shaft are opposite, the rotor inner shaft drives a first rotor to synchronously rotate, and the rotor outer shaft drives a second rotor to synchronously rotate. The gear transmission mechanism comprises a first gear fixedly connected with a rotor wing outer shaft, a second gear fixedly connected with a motor shaft of one motor, a third gear fixedly connected with a rotor wing inner shaft and a fourth gear fixedly connected with a motor shaft of the other motor, the first gear and the third gear are arranged oppositely, the second gear and the fourth gear are arranged oppositely, the second gear is meshed with the first gear and the third gear, and the fourth gear is also meshed with the first gear and the third gear. First gear, second gear, third gear, fourth gear are bevel gear, and first gear and third gear are coaxial setting, and second gear and fourth gear are coaxial setting, and first gear and second rotor set up respectively in the outer one end of rotor, and third gear and first rotor set up respectively in the interior one end of rotor. Although the scheme can realize the driving of the coaxial contra-rotating propellers, the defects of complex structure of a transmission system, poor flight safety performance, high maintenance and repair cost, dead weight of the airplane added by the transmission system and influence on the range exist.
As can be seen from the above analysis, the conventional electric aircraft has the following disadvantages:
1. the power system of the existing electric airplane has complex structure, poor safety performance and high maintenance cost;
2. the self-weight of the power system of the existing electric airplane influences the airplane voyage.
Disclosure of Invention
The invention provides a contra-rotating propeller serial driving system of an electric airplane and the electric airplane, which can solve the technical problems of poor safety performance of a power system of the electric airplane in the prior art and high maintenance cost and short range of the power system of the electric airplane in the prior art.
In order to solve the problems, the invention provides a contra-rotating propeller serial driving system of an electric airplane and the electric airplane, and the technical scheme is as follows:
an electric aircraft contra-rotating propeller tandem drive system, comprising: the contra-rotating propeller, the first electric power source, the second electric power source, the brake unit and the power control unit; the first electric power source and the second electric power source are connected in series; the first power output shaft of the first electric power source is inserted into the second power output shaft of the second electric power source and is coaxial with the second power output shaft; the brake unit is respectively connected with the first electric power source and the second electric power source; the power control unit is electrically connected with the first electric power source, the second electric power source and the brake unit respectively; the first screw propeller of the contra-rotating screw propeller is installed on the first power output shaft, the second screw propeller of the contra-rotating screw propeller is installed on the second power output shaft, and the first electric power source and the second electric power source are used for driving the contra-rotating screw propeller to rotate coaxially.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the brake unit comprises a first brake and a second brake, and the first brake is connected with the first power output shaft; the second brake is connected with the second power output shaft, and the brake unit is used for realizing the braking of the contra-rotating propeller.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the first brake is a hydraulic disc brake and comprises a brake caliper, a brake disc, a hydraulic cylinder and a hydraulic pump; the brake disc is installed on the first power output shaft, the brake caliper is installed on an electric aircraft body and matched with the brake disc, the hydraulic cylinder is installed on the brake caliper and connected with the hydraulic pump through a hydraulic pipeline, and the hydraulic pump is electrically connected with the power control unit.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the first brake further comprises an accumulator connected with the hydraulic pump.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the power control unit comprises a first power control unit and a second power control unit; the first power control unit and the second power control unit are connected in parallel; the first power control unit is electrically connected with the first electric power source, and the second power control unit is electrically connected with the second electric power source.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the first power control unit comprises a battery pack, an inverter, an electric power source detection device, a main display and a steering subsystem; the battery pack is electrically connected with the first electric power source through the inverter; the electric power source detection device is electrically connected with the battery pack and the inverter respectively and is used for detecting the running states of the battery pack and the first electric power source; the main display is electrically connected with the electric power source detection device and used for displaying parameter information of the battery pack and the first electric power source; the manipulation subsystem is respectively electrically connected with the electric power source detection device, the inverter and the battery pack and used for responding to the operation of a pilot.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the contra-rotating propeller is a fixed-distance propeller, and the pitch of the contra-rotating propeller can be adjusted when the contra-rotating propeller is parked on the ground.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the first electric power source and the second electric power source correspond to a motor respectively.
In the contra-rotating propeller tandem drive system for an electric aircraft as described above, it is more preferable that: the first electric power source and the second electric power source respectively correspond to a group of motors, and the motors in each group of motors are connected in series.
The invention also provides an electric airplane with the contra-rotating propeller tandem driving system.
Analysis shows that compared with the prior art, the invention has the advantages and beneficial effects that:
1. according to the invention, through a serial driving mode that the first electric power source is connected with the first propeller and the second electric power source is connected with the second propeller, the dead weight of the electric airplane body is reduced, and the operation maintenance and later maintenance cost is low; the contra-rotating propellers are adopted to output power, so that the torques acted on the electric airplane body by the contra-rotating propellers are mutually offset, the reaction torque generated by a single propeller is avoided, a series of corresponding designs of the electric airplane body can be reduced, the structure of the electric airplane is simplified, and the flying operation and automatic driving of the electric airplane are facilitated; meanwhile, the redundant design that the first electric power source and the second electric power source are used, the power control unit controls the first electric power source and the second electric power source respectively, and the braking unit brakes the first electric power source and the second electric power source respectively is adopted, so that the single propeller can run in emergency, and the flight safety of the electric airplane is improved; furthermore, the dynamic characteristics of the contra-rotating propellers are utilized, so that the energy consumption of the electric airplane can be obviously reduced, the range of the electric airplane is increased, the flight noise is reduced, the ultra-silent electric flight is realized, and the electric airplane has the characteristics of strong safety, long range, low flight noise and convenience in maintenance and repair.
2. The invention adopts a mode of respectively braking the first electric power source and the second electric power source, thereby improving the flight safety; meanwhile, the flight resistance can be reduced, the range can be prolonged, and the emergency response capability of the electric airplane can be improved during emergency flight, so that the electric airplane has the characteristics of high safety and strong emergency response capability; a first power control unit is respectively and electrically connected with a first electric power source and a first brake; the second power control unit is respectively electrically connected with the second electric power source and the second brake, can realize a propulsion mode equivalent to that of a traditional double-engine and has the characteristic of strong risk resistance.
3. The first brake and the second brake adopt hydraulic type ventilation disc type brakes, so that the braking is stable, the heat dissipation is fast during the braking, the braking failure is not easy to occur, and the safety is high; the energy accumulator can recover and store energy in the hydraulic circuit, buffer hydraulic impact and prolong the service life of the hydraulic brake system, so that the hydraulic brake system has the characteristics of convenience in braking, high safety and long service life.
4. The invention fully exerts the characteristics of large motor power, easy control, small volume and strong short-time overload capacity, improves the flight safety and has the characteristic of high safety. The invention can provide different electric power source driving schemes for the electric airplanes with different required powers, adopts the mode of the serial motor or the serial motor group to drive the electric airplanes, can be suitable for the electric airplanes with different takeoff weights, and has the characteristic of wide application range.
5. The first propeller and the second propeller of the contra-rotating propeller are fixed-distance propellers, the pitch of the contra-rotating propeller can be adjusted when the electric airplane is parked on the ground, the advantage of motor driving is fully utilized, the structure of the electric airplane is simplified, the reliability of the contra-rotating propeller and the convenience of maintenance are improved, the pitch is convenient to adjust, and the contra-rotating propeller has the characteristics of simple structure, high reliability and easiness in maintenance.
Drawings
Fig. 1 is a first connection diagram of the contra-rotating propeller serial driving system of the electric aircraft according to the present invention.
Fig. 2 is a second connection schematic diagram of the contra-rotating propeller serial driving system of the electric aircraft.
Fig. 3 is a third schematic connection diagram of the contra-rotating propeller serial driving system of the electric aircraft according to the present invention.
Fig. 4 is a schematic connection diagram of the first power control unit of the present invention.
FIG. 5 is a logic schematic of the power control unit of the present invention.
In the figure: 1-a brake handle; 2-liquid storage cylinder; 3-a hydraulic pump; 4-a first electric power source; 5-a first power take-off shaft; 6-a first power control unit; 7-a second power control unit; 8-a brake caliper; 9-a brake disc; 10-a second electric power source; 11-a second power take-off shaft; 12-a second propeller; 13-a first propeller; 14-a battery pack; 15-a temperature sensor; a 16-DC power supply; 17-a dc converter; 18-an inverter; 19-electric power source detection means; 20-a main display; 21-a steering subsystem; 22-throttle handle; 23-bus disconnecting switch; 24-an accumulator; 25-bus switch.
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, 2 and 3, the present invention provides an electric aircraft contra-rotating propeller serial driving system, which mainly comprises a contra-rotating propeller, a first electric power source 4, a second electric power source 10, a braking unit and a power control unit; the first electric power source 4 and the second electric power source 10 are connected in series; the first power output shaft 5 of the first electric power source 4 is inserted into the second power output shaft 11 of the second electric power source 10 and is coaxial with the second power output shaft 11; the brake unit is respectively connected with the first electric power source 4 and the second electric power source 10; the power control unit is respectively electrically connected with the first electric power source 4, the second electric power source 10 and the brake unit; the first propeller 13 of the contra-rotating propeller is arranged on the first power output shaft 5, the second propeller 12 of the contra-rotating propeller is arranged on the second power output shaft 11, and the first electric power source 4 and the second electric power source 10 are used for driving the contra-rotating propeller to rotate coaxially.
Specifically, a first electric power source 4 and a second electric power source 10 are connected in series, a second power output shaft 11 of the second electric power source 10 is in a hollow tubular shape, a first power output shaft 5 of the first electric power source 4 is inserted into the second power output shaft 11 in a penetrating mode, the first power output shaft 5 and the second power output shaft 11 achieve coaxial rotation through a bearing, the first power output shaft 5 is clamped on an inner ring of the bearing, and the inner wall of the second power output shaft 11 is clamped on an outer ring of the bearing. The first power output shaft 5 is fixedly connected with the first propeller 13, the second power output shaft 11 is fixedly connected with the second propeller 12, the coaxial lines of the first power output shaft 5 and the second power output shaft 11 rotate oppositely, the coaxial lines of the first propeller 13 and the second propeller 12 of the contra-rotating propellers can be contra-rotated, the contra-rotating propellers can be driven under the condition without a gear box, the structure is simple, the technical advantages of the contra-rotating propellers are fully exerted, the flight performance is improved, the structure of the airplane is simplified, the flight operation of the electric airplane is facilitated, the flight noise is reduced, the flight safety is improved, and the convenience in maintenance is improved. The first electric power source 4 and the second electric power source 10 are relatively independent, so that the rotation of the first propeller 13 and the second propeller 12 are not affected by each other, namely, the first propeller and the second propeller can rotate simultaneously or independently. The braking unit is respectively connected with the first electric power source 4 and the second electric power source 10 and used for providing braking, and the power control unit is respectively electrically connected with the first electric power source 4 and the second electric power source 10 and used for providing electric energy and operation control for the first electric power source 4 and the second electric power source 10. According to the tandem driving mode that the first electric power source 4 is connected with the first propeller 13 and the second electric power source 10 is connected with the second propeller 12, the problem that the contra-rotating propellers of a traditional piston engine or a turboprop engine must be driven through a gear box is solved, the self weight of an electric airplane body is reduced, and the operation, maintenance and later-period maintenance cost is low; the contra-rotating propellers are adopted to output power, so that the torques acted on the electric airplane body by the contra-rotating propellers are mutually offset, the reaction torque generated by a single propeller is avoided, a series of corresponding designs of the electric airplane body can be reduced, the structure of the electric airplane is simplified, and the flying operation and automatic driving of the electric airplane are facilitated; meanwhile, the redundant design that the first electric power source 4 and the second electric power source 10 are used, the power control unit respectively controls the first electric power source and the second electric power source and the brake unit respectively brakes the first electric power source and the second electric power source is adopted, the single propeller can run in case of emergency, and the flight safety of the electric airplane is improved; furthermore, the dynamic characteristics of the contra-rotating propellers are utilized, so that the energy consumption of the electric airplane can be obviously reduced, the range of the electric airplane is increased, the flight noise is reduced, the ultra-silent electric flight is realized, and the electric airplane has the characteristics of strong safety, long range, low flight noise and convenience in maintenance and repair.
In order to improve the flight safety of the present invention and at the same time facilitate the braking of the electric aircraft in a ground parking state or in an air emergency, as shown in fig. 1, 2 and 3, the braking unit of the present invention comprises a first brake and a second brake, the first brake being connected to the first power take-off shaft 5; the second brake is connected with the second power output shaft 11, and the brake unit is used for realizing the braking of the contra-rotating propeller. The first brake of the present invention is used for braking the first power output shaft 5, the second brake is used for braking the second power output shaft 11, and the first electric power source 4 and the second electric power source 10 are respectively braked, so that the flight safety of the present invention can be improved. Meanwhile, when the first electric power source 4 or the second electric power source 10 of the invention fails, the failed propeller is in a windmill working state and can bring resistance to emergency flight of the electric airplane when the contra-rotating propeller is in a single-propeller running state, and the failed propeller can be in a fixed state by independently braking the failed propeller by adopting the braking unit, so that the flight resistance is reduced, the range is prolonged, and the emergency response capability of the electric airplane is improved, so that the invention has the characteristics of high safety and strong emergency response capability.
In order to improve the braking safety of the present invention, as shown in fig. 1, 2 and 3, the first brake of the present invention is a hydraulic type ventilated disc brake including a caliper 8, a brake disc 9, a hydraulic cylinder and a hydraulic pump 3. The brake disc 9 is mounted on the first power output shaft 5; the brake caliper 8 is arranged on the electric airplane body and matched with the brake disc 9, so that the brake disc 9 is positioned in the U-shaped jaw of the brake caliper 8; the first brake of the invention also comprises a brake handle 1 and a liquid storage cylinder 2, wherein the brake handle 1 is arranged in a cabin of the electric airplane, and the liquid storage cylinder 2 is connected with the hydraulic pump 3 and is used for supplementing brake liquid for the hydraulic pump 3. Further preferably, the second brake of the present invention is configured in the same manner as the first brake, and is used for braking the second power output shaft 11. The first brake and the second brake adopt hydraulic type ventilation disc type brakes, so that the braking is stable, the heat dissipation is fast during the braking, the braking failure is not easy to occur, the safety is high, and the hydraulic type ventilation disc type brake has the characteristics of convenience in braking and high safety.
In order to increase the service life of the brake unit of the invention, the first brake of the invention further comprises an accumulator 24, as shown in fig. 4, the accumulator 24 being connected to the hydraulic pump 3. The energy accumulator 24 is connected between the hydraulic pump 3 and the hydraulic cylinder of the first brake in series, so that the energy in the hydraulic circuit can be recovered and stored, and the hydraulic impact is buffered, thereby prolonging the service life of the hydraulic brake.
In order to improve the risk resistance of the present invention, as shown in fig. 1, 2 and 3, the power control unit of the present invention includes a first power control unit 6 and a second power control unit 7; the first power control unit 6 and the second power control unit 7 are connected in parallel; the first power control unit 6 is electrically connected to the first electric power source 4, and the second power control unit 7 is electrically connected to the second electric power source 10. More preferably, the first power control unit 6 and the second power control unit 7 are electrically isolated and operate independently without interfering with each other. The first power control unit 6 is respectively electrically connected with the first electric power source 4 and the first brake; the second power control unit 7 is respectively electrically connected with the second electric power source 10 and the second brake, the first propeller 13 and the second propeller 12 of the contra-rotating propellers are completely and independently driven on an electric link, and the propulsion mode which is equal to that of the traditional double-engine (comprising a double-engine piston or a double-engine turbine power system) is realized, so that the risk resistance of the invention is improved, and the invention has the characteristic of strong risk resistance.
As shown in fig. 1 to 4, the first power control unit 6 of the present invention includes a battery pack 14, an inverter 18, an electric power source detection device 19, a main display 20, and a steering sub-system 21; the battery pack 14 is electrically connected with the first electric power source 4 through an inverter 18, and the battery pack 14 is used for supplying power to the first electric power source 4; the electric power source detection device 19 is electrically connected with the battery pack 14 and the inverter 18 respectively and is used for detecting the running states of the battery pack 14 and the first electric power source 4; the main display 20 is electrically connected with the electric power source detection device 19 and is used for displaying the parameter information of the battery pack 14 and the first electric power source 4; the steering subsystem 21 is electrically connected to the electric power source detection device 19, the inverter 18, and the battery pack 14, respectively, for responding to pilot operation.
As shown in fig. 1 to 4, the first power control unit 6 of the present invention further includes a direct current converter 17(DC/DC) and a DC power supply 16; a DC converter 17 converts the DC source from the battery pack 14 or other DC source of the electric aircraft (e.g., solid state batteries) to 12V DC for charging the DC power supply 16, the DC power supply 16 being used to power the first power control unit 6.
As shown in fig. 1 to 4, the internal parts of the first power control unit 6 of the present invention are connected by a bus, which includes a high data line (CAN-H) and a low data line (CAN-L); the battery pack 14 includes a plurality of battery cells connected in series; the electric power source detection device 19 is electrically connected with the battery pack 14, and when the electric power source detection device 19 detects the battery pack 14, the detection parameters include the output voltage, the working current and the temperature of each detection point of the battery pack 14, and the direct-current high-voltage insulation detection of the battery pack 14 is also included. A plurality of temperature sensors 15 of the electric power source detection device 19 are installed in the battery pack 14 for detecting the temperature at each detection point in the battery pack 14; the A/D converter of the electric power source detection device 19 is electrically connected with the battery pack 14 and is used for sampling the voltage of the battery pack 14, and the electric power source detection device 19 can detect and calculate the working voltage of each battery pack 14 through a serial bus; the shunt of the electric power source detection device 19 is electrically connected to the battery pack 14, and detects the output current of the battery pack 14 through digital-to-analog conversion after the shunt detects the battery pack 14. The electric power source detection device 19 detects three parameters of the working voltage, the output current and the temperature of the battery pack 14; meanwhile, the battery pack 14 and the electric aircraft body are subjected to insulation detection through low-frequency signals by adopting a signal injection method. Accordingly, the first power control unit 6 can determine the state of health of each group of battery packs 14. When the electric power source detection device 19 determines that the state of health of the battery pack 14 is out of limit, the first power control unit 6 cuts off the power supply to the battery pack 14 through the dc isolator, and the main display unit gives an alarm to the driver. The parameter indexes for judging the health state of the battery pack 14 are as follows: whether the average cell operating voltage satisfies 2.5V; whether the average cell unit output current meets 0.2C rate discharge or not; whether the cell temperature is less than 60 ℃; and whether the leakage index meets the requirement of being higher than 100 omega/V or not during insulation detection, if one of the leakage indexes does not meet the requirement, the health state of the battery pack 14 is out of limit, and if all the leakage indexes meet the requirement, the health state of the battery pack 14 meets the requirement.
As shown in fig. 1 to 4, the inverter 18 of the present invention is electrically connected to the first electric power source 4, the tail end mutual inductance circuit of the inverter 18 can collect the output current and the working voltage output from the first power control unit 6 to the first electric power source 4, after digital-to-analog conversion, the first power control unit 6 calculates and determines the actual power of the first electric power source 4, and outputs the actual power to the electric power source detection device 19 through the bus, and displays the actual power on the main display unit, and the electric power source detection device 19 uses the actual power as a key parameter of the flight capability of the electric aircraft in different flight phases, and at the same time, the electric power source detection device 19 further detects the temperature of the first electric power source 4 through the temperature sensor.
As shown in fig. 1-4, the steering subsystem 21 of the present invention is electrically connected to the electric power source detection device 19; the steering subsystem 21 is electrically connected with the inverter 18; the steering subsystem 21 is electrically connected to the battery pack 14 through a bus switch 25; the control subsystem 21 is also electrically connected with a throttle handle 22, a brake handle 1 and a bus isolating switch 23 in the cabin of the electric aircraft. The control subsystem 21 is used for responding to the operation of a pilot, and particularly, the pilot controls the on and off of a bus switch 25 through a bus isolating switch 23 so as to control the power supply of the battery pack 14; whether the brake unit is braked is controlled by the brake handle 1; the power of the contra-rotating propeller is controlled by a throttle lever 22.
As shown in fig. 1 to 5, the second power control unit 7 of the present invention is preferably configured in the same manner as the first power control unit 6. The first power control unit 6 and the second power control unit 7 of the invention are completely independent on an electric link, and after one of the power control units is invalid or has reduced performance, the other power control unit is not influenced, thereby ensuring the other power control unit and the corresponding propeller to work normally, and simultaneously, the main display 20 gives an alarm to prompt, and corresponding emergency operation is adopted, thereby ensuring the flight safety to the maximum extent. The working power of the first electric power source 4 and the second electric power source 10 is directly related to whether the electric airplane can complete the flight mission and the flight safety of the electric airplane, therefore, the invention provides electric power for the first electric power source 4 through the first power control unit 6, and judges the working state of the first electric power source 4 by monitoring the working power and the working temperature of the first electric power source 4, thereby monitoring the flight capability of the electric airplane. When the working power of the first electric power source 4 is lower than the normal working power by 15%, the first electric power source 4 is judged to be invalid, at the moment, the first power control unit 6 triggers an emergency program to cut off the power supply of the first electric power source 4, controls the first brake to brake the first power output shaft 5, and provides the power required by the flight by the second propeller 12. When the temperature of the first electric power source 4 exceeds the limit (the temperature exceeds 60 ℃), the first power control unit 6 triggers a power reduction operation program to reduce the rotating speed of the first propeller 13, so that the power of the first electric power source 4 is reduced, and heat generation is reduced. When the first electric power source 4 operates in a power-down mode, the main display 20 prompts the pilot to be in an emergency flight state at present, and prompts the pilot to increase the power of the second electric power source 10, so that the total working power of the first electric power source 4 and the second electric power source 10 can meet the flight power, and the flight task is ended as soon as possible. And vice versa. If the actual working power of the first electric power source 4 is 15% of the normal working power, it is determined that the first electric power source 4 is open-circuited, and it is determined that the first electric power source 4 is failed, at this time, the first power control unit 6 triggers an emergency program to cut off the power supply of the first electric power source 4, and controls the first brake to brake the first power output shaft 5, and the second propeller 12 provides the power required by the flight.
As shown in fig. 4, the type of the temperature sensor 15 of the present invention is preferably a digital temperature sensor, and the type of the digital temperature sensor can be selected from DS18B 20; the A/D converter selects an A/D converter with 12-bit precision; the isolator adopts a direct current isolator.
In order to improve the reliability and maintenance convenience of the contra-rotating propeller of the present invention, as shown in fig. 1, 2 and 3, the first propeller 13 and the second propeller 12 of the contra-rotating propeller of the present invention are fixed-pitch propellers, and the contra-rotating propellers can adjust the pitch when the electric aircraft is parked on the ground. Specifically, each blade of the contra-rotating propeller can be detached and adjusted, when the electric airplane is parked on the ground, a maintenance worker can loosen a pressure plate of a central hub of the propeller and manually adjust the pitch of the blade, and the pitch is unchanged in the flying process of the electric airplane, so that the first propeller 13 and the second propeller 12 of the contra-rotating propeller are fixed-distance propellers with adjustable pitches. The invention fully utilizes the advantages of motor drive, realizes the drive of the contra-rotating propeller without a gear box, is not provided with a hydraulic or mechanical device for adjusting the pitch of the contra-rotating propeller, simplifies the structure of the electric airplane, improves the reliability of the contra-rotating propeller and the convenience of maintenance, can adjust the pitch of the contra-rotating propeller according to the actual flying environment and the performance requirement of the electric airplane required by flying, and has the characteristics of simple structure, high reliability and easy maintenance.
In order to further improve the safety of the present invention, as shown in fig. 1 and 2, the first electric power source 4 and the second electric power source 10 of the present invention correspond to one motor, and are suitable for an electric aircraft with a small flying power. The invention selects the motor as a power source, the rotating shaft of one motor is inserted into the rotating shaft of the other motor to form a serial structure, and the serial motor is used for driving the electric airplane, so that the power system of the contra-rotating propeller of the electric airplane can be optimized, the characteristics of large motor power, easy control, small volume and strong short-time overload capacity are fully exerted, the flight safety is improved, and the invention has the characteristic of high safety.
In order to expand the application range of the present invention, as shown in fig. 3 and 4, the first electric power source 4 and the second electric power source 10 of the present invention may also correspond to a set of motors, each motor in each set of motors shares a rotating shaft, and the rotating shaft of one set of motors is inserted into the rotating shaft of the other set of motors to form a serial structure. The inverters 18 in the first electric power source 4 and the second electric power source 10 are electrically connected with all motors in the motor set, the tail end mutual inductance circuit of the inverter 18 can collect the working current and the working voltage of all the motors, the actual power of the motor set is calculated and determined after digital-to-analog conversion, the actual power is displayed on the main display unit, and the parameter is used as a key parameter of flight capacity in different flight stages. Preferably, the invention adopts a ventilation disc type motor, liquid cooling is carried out on the stator, and the high-power contra-rotating propeller can be driven and the problem of heat dissipation of the motor is solved. The invention provides different electric power source driving schemes for the electric airplanes with different required powers, adopts the mode of the serial motor or the serial motor group to drive the electric airplanes, can be suitable for the electric airplanes with different takeoff weights, and has the characteristic of wide application range.
The invention also provides an electric airplane with the contra-rotating propeller serial driving system, wherein the contra-rotating propeller serial driving system is arranged on the longitudinal axis of the electric airplane; or the electric aircraft wing mounting structure is arranged on the wings of the electric aircraft and symmetrically distributed by taking the longitudinal axis of the electric aircraft as a reference. As a further preference, the contra-rotating propeller tandem drive system, when mounted on the longitudinal axis of the electric aircraft, is located at the nose of the electric aircraft or mounted at the rear end of the cabin of the electric aircraft to provide thrust.
As shown in fig. 1 to 5, the working process of the present invention is explained in detail as follows:
starting up, initializing the power control unit, sequentially detecting the output voltage, the working current and the temperature of each detection point of the battery pack 14 corresponding to the first electric power source 4 by the first power control unit 6, sequentially detecting the output voltage, the working current and the temperature of each detection point of the battery pack 14 corresponding to the second electric power source 10 by the second power control unit 7, and simultaneously, performing insulation detection on the battery pack 14 by the first power control unit 6 and the second power control unit 7 to detect the insulation resistance value of the battery pack 14. And if any one of the output voltage, the working current, the temperature of each detection point and the insulation resistance value does not meet the index, the main display 20 gives an alarm.
The pilot assigns the parameters such as air pressure, temperature and takeoff performance requirements to the initialized power control unit according to the airplane parameters, the power control unit calculates the takeoff required power of the electric airplane, and after takeoff and running, the takeoff required power of the electric airplane is compared with the total output power of the first electric power source 4 and the second electric power source 10 detected by the inverter 18. If the total output power is larger than the required power, the electric airplane normally operates, and the takeoff operation is carried out according to the normal operation rule; comparing the output power of the first electric power source 4 and the output power of the second electric power source 10 detected by the inverter 18 with the power of the first electric power source 4 and the power of the second electric power source 10 required by the take-off of the electric airplane, and if the output power of the first electric power source and the power of the second electric power source are larger than the required power, the electric airplane normally takes off; if not, the first electric power source 4 and the second electric power source 10 are closed, the contra-rotating propellers are braked through the brake unit, meanwhile, an alarm is given immediately, the pilot is prompted to stop taking off, an emergency program is started, and the flight operation is finished.
Example 1:
as shown in fig. 1, the contra-rotating propeller serial drive system mounted on the electric aircraft includes a contra-rotating propeller, a first electric power source 4, a second electric power source 10, a brake unit, and a power control unit. The first electric power source 4 and the second electric power source 10 correspond to one motor respectively, the first power control unit 6 is electrically connected with one motor, the second power control unit 7 is electrically connected with the other motor, and meanwhile, the first power control unit 6 is connected with the second power control unit 7 in parallel. 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, the contra-rotating propeller serial drive system mounted on the electric aircraft includes a contra-rotating propeller, a first electric power source 4, a second electric power source 10, a brake unit, and a power control unit. The first electric power source 4 and the second electric power source 10 correspond to one motor respectively, the first power control unit 6 is electrically connected with one motor, the second power control unit 7 is electrically connected with the other motor, and the first power control unit 6 and the second power control unit 7 are isolated from each other on an electric link. The electric aircraft is now used for flight training, personal flight, aerial surveying, etc.
Example 3:
as shown in fig. 3, the contra-rotating propeller serial drive system mounted on the electric aircraft includes a contra-rotating propeller, a first electric power source 4, a second electric power source 10, a brake unit, and a power control unit. The first electric power source 4 and the second electric power source 10 correspond to a group of motors respectively, the first power control unit 6 is electrically connected with the first group of motors, the second power control unit 7 is electrically connected with the other group of motors, each group of motors comprises two motors which are connected in series, and the first power control unit 6 is connected with the second power control unit 7 in parallel. The electric aircraft is then used for branch-line air passenger transport or freight transport.
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. An electric aircraft contra-rotating propeller tandem drive system, comprising:
the contra-rotating propeller, the first electric power source, the second electric power source, the brake unit and the power control unit;
the first electric power source and the second electric power source are connected in series; the first power output shaft of the first electric power source is inserted into the second power output shaft of the second electric power source and is coaxial with the second power output shaft;
the brake unit is respectively connected with the first electric power source and the second electric power source; the power control unit is electrically connected with the first electric power source, the second electric power source and the brake unit respectively;
the first screw propeller of the contra-rotating screw propeller is installed on the first power output shaft, the second screw propeller of the contra-rotating screw propeller is installed on the second power output shaft, and the first electric power source and the second electric power source are used for driving the contra-rotating screw propeller to rotate coaxially.
2. The electric aircraft contra-rotating propeller tandem drive system according to claim 1, wherein:
the brake unit comprises a first brake and a second brake, and the first brake is connected with the first power output shaft; the second brake is connected with the second power output shaft.
3. The electric aircraft contra-rotating propeller tandem drive system according to claim 2, wherein:
the first brake is a hydraulic disc brake and comprises a brake caliper, a brake disc, a hydraulic cylinder and a hydraulic pump; the brake disc is installed on the first power output shaft, the brake caliper is installed on an electric aircraft body and matched with the brake disc, the hydraulic cylinder is installed on the brake caliper and connected with the hydraulic pump through a hydraulic pipeline, and the hydraulic pump is electrically connected with the power control unit.
4. The electric aircraft contra-rotating propeller tandem drive system of claim 3, wherein:
the first brake further comprises an accumulator connected with the hydraulic pump.
5. The electric aircraft contra-rotating propeller tandem drive system according to claim 1, wherein:
the power control unit comprises a first power control unit and a second power control unit; the first power control unit and the second power control unit are connected in parallel; the first power control unit is electrically connected with the first electric power source, and the second power control unit is electrically connected with the second electric power source.
6. The electric aircraft contra-rotating propeller tandem drive system of claim 5, wherein:
the first power control unit comprises a battery pack, an inverter, an electric power source detection device, a main display and a steering subsystem; the battery pack is electrically connected with the first electric power source through the inverter; the electric power source detection device is electrically connected with the battery pack and the inverter respectively; the main display is electrically connected with the electric power source detection device; the manipulation subsystem is respectively electrically connected with the electric power source detection device, the inverter and the battery pack and used for responding to the operation of a pilot.
7. The electric aircraft contra-rotating propeller tandem drive system according to claim 1, wherein:
the contra-rotating propellers are fixed-distance propellers.
8. The electric aircraft contra-rotating propeller tandem drive system according to any one of claims 1 to 7, wherein:
the first electric power source and the second electric power source correspond to a motor respectively.
9. The electric aircraft contra-rotating propeller tandem drive system according to any one of claims 1 to 7, wherein:
the first electric power source and the second electric power source correspond to a group of motors respectively.
10. An electric aircraft having the contra-rotating propeller tandem drive system of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811332086.2A CN111169647A (en) | 2018-11-09 | 2018-11-09 | Contra-rotating propeller serial driving system of electric aircraft and electric aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811332086.2A CN111169647A (en) | 2018-11-09 | 2018-11-09 | Contra-rotating propeller serial driving system of electric aircraft and electric aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111169647A true CN111169647A (en) | 2020-05-19 |
Family
ID=70649830
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811332086.2A Pending CN111169647A (en) | 2018-11-09 | 2018-11-09 | Contra-rotating propeller serial driving system of electric aircraft and electric aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111169647A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101348171A (en) * | 2007-04-10 | 2009-01-21 | 欧洲直升机德国有限责任公司 | Rotor brake for a rotary-wing aircraft |
| CN103832584A (en) * | 2012-11-26 | 2014-06-04 | 罗勇 | Contra-rotating rotor wing airplane with stationary wings and foldable empennage |
| US20170210480A1 (en) * | 2016-01-27 | 2017-07-27 | Sikorsky Aircraft Corporation | Rotor systems for rotorcraft |
| CN107662703A (en) * | 2017-10-30 | 2018-02-06 | 中电科芜湖通用航空产业技术研究院有限公司 | Electronic double coaxial homonymy reversion tiltrotor aircrafts |
| CN108528695A (en) * | 2018-06-03 | 2018-09-14 | 王继华 | Electronic coaxial aircraft control dynamical system design |
| CN209305858U (en) * | 2018-11-09 | 2019-08-27 | 高洪江 | Electric airplane co-axial contra rotating propeller tandem drive system and electric airplane |
-
2018
- 2018-11-09 CN CN201811332086.2A patent/CN111169647A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101348171A (en) * | 2007-04-10 | 2009-01-21 | 欧洲直升机德国有限责任公司 | Rotor brake for a rotary-wing aircraft |
| CN103832584A (en) * | 2012-11-26 | 2014-06-04 | 罗勇 | Contra-rotating rotor wing airplane with stationary wings and foldable empennage |
| US20170210480A1 (en) * | 2016-01-27 | 2017-07-27 | Sikorsky Aircraft Corporation | Rotor systems for rotorcraft |
| CN107662703A (en) * | 2017-10-30 | 2018-02-06 | 中电科芜湖通用航空产业技术研究院有限公司 | Electronic double coaxial homonymy reversion tiltrotor aircrafts |
| CN108528695A (en) * | 2018-06-03 | 2018-09-14 | 王继华 | Electronic coaxial aircraft control dynamical system design |
| CN209305858U (en) * | 2018-11-09 | 2019-08-27 | 高洪江 | Electric airplane co-axial contra rotating propeller tandem drive system and electric airplane |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10661896B2 (en) | Helicopter | |
| CN102971216B (en) | For hybrid electric drive system and the energy system of aircraft | |
| US10301011B2 (en) | Electrified rotorcraft | |
| EP2962885B1 (en) | Hybrid power system for piston engine aircrafts | |
| CN110650889A (en) | EVTOL aircraft using large variable-speed tiltrotors | |
| CN111186585A (en) | Multi-battery-module electric airplane power system and electric airplane | |
| CN109094790B (en) | Power configuration scheme and control method for hybrid power system of helicopter | |
| CN105026228B (en) | The method saved the electrical brake system of electric power and operate the system | |
| CN112046763B (en) | Multi-power-source tandem type hybrid unmanned aerial vehicle and control method thereof | |
| GB2576250A (en) | Aircraft | |
| EP3476731B1 (en) | Rotorcraft anti-torque system | |
| CN101367436B (en) | Miniature hybrid power flying platform and implementing method thereof | |
| CN113306354A (en) | Air-water integrated propulsion system of amphibious aircraft | |
| Gnadt et al. | Hybrid turbo-electric STOL aircraft for urban air mobility | |
| CN112373684A (en) | Aircraft and driving system thereof | |
| CN209305857U (en) | Fixed-wing electric airplane co-axial contra rotating propeller dynamical system and fixed-wing electric airplane | |
| CN209305858U (en) | Electric airplane co-axial contra rotating propeller tandem drive system and electric airplane | |
| CN104925250A (en) | Multi-rotor craft | |
| CN111169647A (en) | Contra-rotating propeller serial driving system of electric aircraft and electric aircraft | |
| RU2694695C1 (en) | Method of distribution and control of rotorcraft with helicopter drive hybrid system | |
| CN209290703U (en) | More battery modules electric airplane dynamical systems and electric airplane | |
| KR102490173B1 (en) | VERTICAL TAKE OFF AND LANDING AIRCRAFT USING HYBRID PROPULSION SYSTEM and THE CONTROL METHOD | |
| RU2554043C1 (en) | Hybrid short takeoff and landing electric aircraft | |
| CN111099025A (en) | Contra-rotating propeller power system of fixed-wing electric aircraft and fixed-wing electric aircraft | |
| CN211253047U (en) | Power umbrella based on electric multi-propeller power device |
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 |