Unmanned aerial vehicle power system and unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle power system and an unmanned aerial vehicle, the unmanned aerial vehicle power system comprises a multi-stage supercharging subsystem, and the multi-stage supercharging subsystem comprises a low-pressure-stage supercharger, a high-pressure-stage supercharger and an electric supercharger; the low-pressure-stage supercharger comprises a low-pressure-stage gas compressor and a low-pressure-stage turbine; the high-pressure-stage supercharger comprises a high-pressure-stage gas compressor and a high-pressure-stage turbine; the electric supercharger comprises an electric pressurizing compressor and a pressurizing motor; air inlets of the low-pressure-stage compressor, the high-pressure-stage compressor, the electric pressurizing compressor and the engine are connected in series through air inlet pipes, and air outlets of the low-pressure-stage turbine, the high-pressure-stage turbine and the engine are connected in series through air outlet pipes. According to the unmanned aerial vehicle power system and the unmanned aerial vehicle, step-by-step pressurization can be conducted on external air before the external air enters the engine through the multi-stage pressurization subsystem, the pressure of the engine is improved, the requirement for controlling the pressurization ratio of the engine of the unmanned aerial vehicle is met, and the unmanned aerial vehicle power system can provide sufficient power for the unmanned aerial vehicle.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a unmanned aerial vehicle power system and a unmanned aerial vehicle. Background Art

[0002] Near-space is the space environment above sea level, between 20 km and 100 km. Its space altitude is between aircraft and satellites, and includes three areas: one is the part of the stratosphere with an altitude of 20 km to 55 km; the second is the entire atmosphere with an altitude of 55 km to 85 km; and the third is a small amount of thermosphere with an altitude of 85 km to 100 km. As the "third pole" independent of the air and the sky, near-space "can enter the sky and control the sky; it can control the air and the ground" and has great application value and unique status in the fields of remote sensing, communication, meteorological detection, etc. It has become an emerging space that countries are competing to develop. Near-space aircraft include near-space airships, high-altitude free-floating balloons filled with helium, high-altitude long-endurance drones in the stratosphere, and long-distance remote-controlled gliders. Near-space aircraft can effectively relay and connect air-space-ground information in terms of early warning, reconnaissance and surveillance, communication support, electronic countermeasures, navigation and positioning. Moreover, since near-space aircraft can easily achieve long-term hypersonic flight, they are increasingly becoming a hot spot for long-range rapid strike weapons.

[0003] Although a large number of near-space UAV projects have been carried out abroad, most of them have not yet been realized. Among them, the development of propulsion technology is one of the biggest challenges. Since the mission requirements and flight environment of near-space UAVs are significantly different from those of traditional aircraft and UAVs, UAVs flying in near-space are prone to problems such as insufficient power and short flight time. Utility Model Content

[0004] In view of this, the purpose of the present application is to propose a UAV power system and a UAV.

[0005] Based on the above purpose, the first aspect of the present application provides a UAV power system, including: an engine, a first clutch, a drive motor, a propeller and a multi-stage supercharging subsystem; the output shaft of the engine is connected to the input end of the first clutch, and the output end of the first clutch is connected to the first end of the rotor shaft of the drive motor; the second end of the rotor shaft is connected to the propeller; when the first clutch is closed, the UAV power system is in a driving state in which the engine, the drive motor and the propeller rotate coaxially; the multi-stage supercharging subsystem includes a low-pressure stage supercharger, a high-pressure stage supercharger and an electric supercharger; the low-pressure stage supercharger includes a low-pressure stage compressor and a low-pressure stage turbine connected to each other; the high-pressure stage supercharger includes a high-pressure stage compressor and a high-pressure stage turbine connected to each other; the electric supercharger includes an electric supercharger compressor and a supercharging motor connected to each other; the low-pressure stage compressor, the high-pressure stage compressor, the electric supercharger compressor and the air intake of the engine are connected in series through an air intake pipe, and the low-pressure stage turbine, the high-pressure stage turbine and the exhaust port of the engine are connected in series through an exhaust pipe.

[0006] Optionally, the multi-stage boost subsystem includes a low-pressure stage intercooler and a high-pressure stage intercooler connected to the intake pipe, the low-pressure stage intercooler is arranged between the low-pressure stage compressor and the high-pressure stage compressor, and the high-pressure stage intercooler is arranged between the high-pressure stage compressor and the electric boost compressor.

[0007] Optionally, the multi-stage boost subsystem further includes an intake branch pipe connected in parallel with the electric boost compressor, and the intake branch pipe is provided with an electric boost compressor bypass valve.

[0008] Optionally, the multi-stage supercharging subsystem further includes a first exhaust branch pipe connected in parallel with the high-pressure stage turbine, and the first exhaust branch pipe is provided with a high-pressure stage exhaust bypass valve.

[0009] Optionally, the multi-stage supercharging subsystem further includes a second exhaust branch pipe connected in parallel with the low-pressure stage turbine, and the second exhaust branch pipe is provided with a low-pressure stage exhaust bypass valve.

[0010] Optionally, the UAV power system includes a UAV controller, a battery management module, an engine controller, a drive motor controller and a battery; the engine controller is electrically connected to the engine and the UAV controller, respectively, the drive motor controller is electrically connected to the drive motor and the UAV controller, respectively, the battery management module is electrically connected to the UAV controller and the battery, and the battery is also electrically connected to the drive motor.

[0011] Optionally, the multi-stage pressurization subsystem includes an ambient air pressure sensor, and the ambient air pressure sensor is connected to the drone controller.

[0012] Optionally, the multi-stage boost subsystem includes a boost controller, a low-pressure intercooler, a high-pressure intercooler, a low-pressure exhaust bypass valve, a high-pressure exhaust bypass valve and an electric boost compressor bypass valve; the boost controller is electrically connected to the UAV controller, the low-pressure intercooler, the high-pressure intercooler, the low-pressure exhaust bypass valve, the high-pressure exhaust bypass valve, the boost motor and the electric boost compressor bypass valve, respectively.

[0013] Optionally, the UAV power system also includes a second clutch, a transmission and a reducer, the input end of the second clutch is connected to the second end of the rotor shaft, the output end of the second clutch is connected to the input shaft of the transmission, the output shaft of the transmission is connected to the input shaft of the reducer, and the output shaft of the reducer is connected to the propeller.

[0014] Based on the same inventive concept, the second aspect of the present application also provides a UAV, including the UAV power system as described in the first aspect.

[0015] As can be seen from the above, the UAV power system and UAV provided by the present application, by setting a low-pressure stage supercharger, a high-pressure stage supercharger and an electric supercharger in a multi-stage supercharging subsystem to form an ultra-high pressure ratio composite supercharging system, can supercharge the external air step by step before it enters the engine, increase its pressure, meet the engine's intake pressure requirements, meet the near-control UAV engine supercharging ratio requirements, achieve UAV high-altitude supercharging pressure adaptation, and enable the UAV power system to provide sufficient power for the UAV. At the same time, taking into account the power, economy, layout difficulty and battery usage of near-space UAVs, a parallel hybrid power system is designed to provide two power sources, an engine and a drive motor. The two power sources cooperate with each other to enable the UAV power system to always work in a high-efficiency range, and compared with the power system using the engine as a single power source, the UAV power system of this embodiment has lower fuel consumption, which helps to extend the flight time of the UAV and improve the flight characteristics of the UAV in near-space, which is of great significance to expanding the combat dimension of the space field and enhancing the combat force of new domains and new qualities. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the present application or related technologies, the drawings required for use in the embodiments or related technical descriptions are briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 A schematic diagram of a UAV power system according to an embodiment of the present application;

[0018] Figure 2 A schematic diagram of a multi-stage boost subsystem of a UAV power system according to an embodiment of the present application;

[0019] Figure 3 Schematic diagram of the flow of the UAV power system control method according to an embodiment of the present application.

[0020] Description of reference numerals:

[0021] 1. Engine; 2. First clutch; 3. Driving motor; 301. First end of rotor shaft; 302. Second end of rotor shaft; 4. Propeller;

[0022] 5. Multi-stage boost subsystem;

[0023] 501, low-pressure stage supercharger; 501-1, low-pressure stage compressor; 501-2, low-pressure stage turbine;

[0024] 502, high pressure stage supercharger; 502-1, high pressure stage compressor; 502-2, high pressure stage turbine;

[0025] 503, electric supercharger; 503-1, electric supercharger compressor; 503-2, supercharger motor;

[0026] 504, intake pipe; 505, exhaust pipe; 506, low-pressure intercooler; 507, high-pressure intercooler; 508, intake branch pipe; 509, electric boost compressor bypass valve; 5010, first exhaust branch pipe; 5011, low-pressure exhaust bypass valve; 5012, second exhaust branch pipe; 5013, high-pressure exhaust bypass valve; 5014, ambient air pressure sensor; 5015, boost controller; 5016, intermediate;

[0027] 6. UAV controller; 7. Battery management module; 8. Engine controller; 9. Drive motor controller; 10. Battery; 11. Second clutch; 12. Transmission; 13. Reducer. DETAILED DESCRIPTION

[0028] In order to make the objectives, technical solutions and advantages of the present application more clearly understood, the present application is further described in detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0029] It should be noted that the relative arrangement of the components, the numerical expressions and numerical values ​​set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise.

[0030] At the same time, it should be understood that for the convenience of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0031] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the present application, its application, or uses.

[0032] It should be noted that, unless otherwise defined, the technical terms or scientific terms used in the embodiments of the present application should be the usual meanings understood by people with ordinary skills in the field to which the present application belongs. The "first", "second" and similar words used in the embodiments of the present application do not represent any order, quantity or importance, but are only used to distinguish different components. "Including" or "comprising" and similar words mean that the elements or objects appearing in front of the word cover the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0033] The applicant's research found that the upgrade and innovation of the near-space UAV power system is bound to face many technical constraints, mainly in terms of compression ratio, temperature, Reynolds number and power.

[0034] Specifically, as the altitude increases, the density and pressure of the air decrease significantly. When the drone rises to an altitude of 25km, the atmospheric pressure in its environment will drop to 0.025bar, which is equivalent to about 2% of the sea level. At this time, in order to achieve higher lift efficiency, the drone's engine requires an extremely high boost ratio.

[0035] In view of this, if Figure 1 and Figure 2As shown, the embodiment of the present application provides a UAV power system, including: an engine 1, a first clutch 2, a drive motor 3, a propeller 4 and a multi-stage supercharging subsystem 5; the output shaft of the engine 1 is connected to the input end of the first clutch 2, and the output end of the first clutch 2 is connected to the first end 301 of the rotor shaft of the drive motor 3; the second end 302 of the rotor shaft is connected to the propeller 4; when the first clutch 2 is closed, the UAV power system is in a driving state in which the engine 1, the drive motor 3 and the propeller 4 rotate coaxially; the multi-stage supercharging subsystem 5 includes a low-pressure stage supercharger 501, a high-pressure stage supercharger 502 and an electric supercharger 503; the low-pressure stage supercharger The device 501 includes a low-pressure compressor 501-1 and a low-pressure turbine 501-2 connected to each other; the high-pressure supercharger 502 includes a high-pressure compressor 502-1 and a high-pressure turbine 502-2 connected to each other; the electric supercharger 503 includes an electric supercharger compressor 503-1 and a supercharger motor 503-2 connected to each other; the low-pressure compressor 501-1, the high-pressure compressor 502-1, the electric supercharger compressor 503-1 and the air intake of the engine 1 are connected in series through an air intake pipe 504, and the low-pressure turbine 501-2, the high-pressure turbine 502-2 and the exhaust port of the engine 1 are connected in series through an exhaust pipe 505.

[0036] Exemplarily, the low-pressure stage supercharger 501 includes an intermediate body 5016, and the impeller in the low-pressure stage compressor 501-1 and the turbine in the low-pressure stage turbine 501-2 are connected through the intermediate body 5016. When the engine 1 is working, the exhaust gas can drive the turbine of the low-pressure stage turbine 501-2 to rotate, and the turbine can drive the impeller of the low-pressure stage compressor 501-1 to rotate through the intermediate body 5016, thereby supercharging the air flowing through the low-pressure stage compressor 501-1 along the intake pipe 504. Similarly, the high-pressure stage supercharger 502 also includes an intermediate body 5016, and the impeller of the high-pressure stage compressor 502-1 and the turbine of the high-pressure stage turbine 502-2 are connected through the intermediate body 5016.

[0037] Exemplarily, the impeller of the electric boost compressor 503 - 1 is connected to the output shaft of the boost motor 503 - 2 , and the boost motor 503 - 2 can drive the impeller of the electric boost compressor 503 - 1 to rotate, thereby supercharging the air flowing through the electric boost compressor 503 - 1 along the intake pipe 504 .

[0038] For example, along the flow direction of air in the intake pipe 504 (eg Figure 2 The low-pressure stage compressor 501-1, the high-pressure stage compressor 502-1 and the electric boost compressor 503-1 are arranged in sequence (in the direction of the white arrow in the figure).

[0039] For example, along the flow direction of the gas in the exhaust pipe 505 (eg Figure 2The high-pressure stage turbine 502-2 and the low-pressure stage turbine 501-2 are arranged in sequence (in the direction of the black arrow in FIG).

[0040] When the UAV power system of this embodiment is working, air with a relatively low external pressure (hereinafter referred to as external air) first enters the low-pressure compressor 501-1, and the low-pressure compressor 501-1 performs initial compression on the air passing through. The compressed air can flow into the high-pressure compressor 502-1 for a second compression. The air after the second compression can also flow into the electric boost compressor 503-1 for a third compression, so that the external air can increase its own pressure to a higher level before reaching the air intake of the engine 1, thereby meeting the air intake pressure requirement of the engine 1.

[0041] At the same time, in order to reduce the fuel consumption of the engine 1, the UAV power system of this embodiment adds a drive motor 3 on the basis of the engine 1. The UAV power system of this embodiment has different power output modes adapted to various working conditions, as shown in Table 1.

[0042] Table 1. Hybrid power control strategy of UAV power system in different working conditions

[0043]

[0044] In conjunction with Table 1, when the required torque of the propeller 4 of the drone is small, that is, the required torque is in the high efficiency range of the drive motor 3, the engine 1 does not work, and the first clutch 2 is disconnected. The drive motor 3, as the power source of the drone power system, provides power to the propeller 4 alone, drives the propeller 4 to rotate and drives the drone to fly. At this time, the drone power system is in the electric drive mode.

[0045] When the required torque of the propeller 4 is in the high-efficiency range of the engine 1, the engine 1 is started, and the first clutch 2 is closed. The engine 1, as a single power source, drives the drive motor 3 and the propeller 4 to rotate coaxially. At the same time, the output energy of the engine 1 can also be converted into electrical energy and stored in the battery through the engine 1 accessory device or the drive motor 3 (at this time, since the rotor of the drive motor 3 rotates under the drive of the engine 1, the drive motor 3 can be used as a generator). At this time, the UAV power system is in a pure engine drive mode.

[0046] When the required torque of the propeller 4 is large, the engine 1 and the drive motor 3 can work at the same time, with the engine 1 as the main power output and the drive motor 3 as the auxiliary output. The two together provide power for the propeller 4. At this time, the UAV power system is in a hybrid drive mode. When the propeller 4 needs to be braked, the engine 1 stops outputting (which can be achieved by shutting down the engine 1 or disconnecting the first clutch 2), and the rotor of the drive motor 3 is driven by the propeller 4 to convert the rotational energy into electrical energy and store it in the battery. At this time, the UAV power system is in a regenerative braking mode.

[0047] The UAV power system of this embodiment forms an ultra-high pressure ratio composite supercharging system by arranging a low-pressure stage supercharger 501, a high-pressure stage supercharger 502 and an electric supercharger 503 in the multi-stage supercharging subsystem 5, which can supercharge the external air step by step before it enters the engine 1, increase its pressure, meet the intake pressure requirement of the engine 1, meet the supercharging ratio requirement of the near-space control UAV engine, realize the high-altitude supercharging pressure adaptation of the UAV, and enable the UAV power system to provide sufficient power for the UAV. At the same time, taking into account the power, economy, layout difficulty and battery usage of the near-space UAV, a parallel hybrid power system is designed to provide two power sources, the engine 1 and the drive motor 3. The two power sources cooperate with each other to enable the UAV power system to always work in a high-efficiency range, and compared with the power system using the engine 1 as the single power source, the UAV power system of this embodiment has lower fuel consumption, which helps to extend the flight time of the UAV and improve the flight characteristics of the UAV in near-space, which is of great significance to expanding the combat dimension of the space field and enhancing the combat force of new domain and new quality.

[0048] The applicant has found that after the engine intake is supercharged by the multi-stage supercharging subsystem 5, the temperature of the compressed air will increase, which may cause the temperature of the engine 1 in the working state to be much higher than the normal state temperature, which may have an adverse effect on the normal operation of the engine 1.

[0049] In order to improve the above situation, Figure 2 As shown, in some embodiments, the multi-stage boost subsystem 5 includes a low-pressure stage intercooler 506 and a high-pressure stage intercooler 507 connected to the intake pipe 504, the low-pressure stage intercooler 506 is arranged between the low-pressure stage compressor 501-1 and the high-pressure stage compressor 502-1, and the high-pressure stage intercooler 507 is arranged between the high-pressure stage compressor 502-1 and the electric boost compressor 503-1.

[0050] After the outside air is initially compressed by the low-pressure compressor 501-1, the temperature of the air will rise. After the high-temperature air flows out of the low-pressure compressor 501-1, it enters the low-pressure intercooler 506 along the intake pipe 504 for initial cooling to reduce the air temperature. The air after initial cooling flows into the high-pressure compressor 502-1 along the intake pipe 504, and the air can be compressed for the second time by the high-pressure compressor 502-1. The temperature of the air compressed for the second time will rise again. After the air flows out of the high-pressure compressor 502-1, it enters the high-pressure intercooler 507 along the intake pipe 504 for secondary cooling, and the air temperature is reduced again, so that the air can be controlled at a lower temperature before entering the engine 1, which helps to ensure the normal operation of the engine 1.

[0051] like Figure 2 As shown, in some embodiments, the multi-stage boost subsystem 5 further includes an intake branch pipe 508 connected in parallel with the electric boost compressor 503 - 1 , and the intake branch pipe 508 is provided with an electric boost compressor bypass valve 509 .

[0052] When the electric boost compressor bypass valve 509 is closed, all the air flowing out of the high-pressure intercooler 507 flows into the electric boost compressor 503-1. When the electric boost compressor bypass valve 509 is opened, part of the air flowing out of the high-pressure intercooler 507 flows into the intake branch pipe 508, and this part of the air directly enters the air intake of the engine 1 without undergoing the third compression. In other words, after the electric boost compressor bypass valve 509 is opened, part of the air entering the air intake of the engine 1 has undergone the third compression, and part of the air has not undergone the third compression. By adjusting the opening of the electric boost compressor bypass valve 509, the proportion of air that has not undergone the third compression can be controlled, thereby adjusting the intake pressure of the engine 1.

[0053] like Figure 2 As shown, in some embodiments, the multi-stage supercharging subsystem 5 further includes a first exhaust branch pipe 5010 connected in parallel with the high-pressure stage turbine 502 - 2 , and the first exhaust branch pipe 5010 is provided with a high-pressure stage exhaust bypass valve 5013 .

[0054] When the high-pressure stage exhaust bypass valve 5013 is closed, all the gas exhausted from the engine 1 flows through the high-pressure stage turbine 502-2 to drive the turbine in the high-pressure stage turbine 502-2 to rotate. When the high-pressure stage exhaust bypass valve 5013 is opened, a portion of the gas exhausted from the engine 1 flows into the first exhaust branch pipe 5010, and the portion of the gas bypasses the high-pressure stage turbine 502-2.

[0055] In other words, after the high-pressure stage exhaust bypass valve 5013 is opened, part of the gas exhausted from the engine 1 will flow through the high-pressure stage turbine 502-2 to drive the high-pressure stage supercharger 502, while the other part will bypass the high-pressure stage turbine 502-2 and flow backward along the exhaust pipe 505, and will not be used to drive the high-pressure stage supercharger 502. By adjusting the opening of the high-pressure stage exhaust bypass valve 5013, the proportion of gas that does not work on the high-pressure stage turbine 502-2 can be controlled, thereby adjusting the supercharging effect of the high-pressure stage supercharger 502 on the air in the intake pipe 504, and further adjusting the intake pressure of the engine 1.

[0056] like Figure 2 As shown, in some embodiments, the multi-stage supercharging subsystem 5 further includes a second exhaust branch pipe 5012 connected in parallel with the low-pressure stage turbine 501 - 2 , and the second exhaust branch pipe 5012 is provided with a low-pressure stage exhaust bypass valve 5011 .

[0057] When the low-pressure exhaust bypass valve 5011 is closed, the gas flowing through the high-pressure turbine 502-2 and bypassing the high-pressure turbine 502-2 will all flow through the low-pressure turbine 501-2 to drive the turbine in the low-pressure turbine 501-2 to rotate. When the low-pressure exhaust bypass valve 5011 is opened, a portion of the gas flowing through the high-pressure turbine 502-2 and bypassing the high-pressure turbine 502-2 will flow into the second exhaust branch pipe 5012, and this portion of gas bypasses the low-pressure turbine 501-2 and is directly discharged to the outside.

[0058] In other words, after the low-pressure exhaust bypass valve 5011 is opened, part of the gas flowing through the high-pressure turbine 502-2 and bypassing the high-pressure turbine 502-2 will flow through the low-pressure turbine 501-2 to drive the low-pressure supercharger 501, while the other part bypasses the low-pressure turbine 501-2 and flows out to the outside along the exhaust pipe 505, and is not used to drive the low-pressure supercharger 501. By adjusting the opening of the low-pressure exhaust bypass valve 5011, the proportion of gas that does not work on the low-pressure turbine 501-2 can be controlled, thereby adjusting the supercharging effect of the low-pressure supercharger 501 on the air in the intake pipe 504, and then adjusting the intake pressure of the engine 1.

[0059] like Figure 1 As shown, in some embodiments, the UAV power system includes a UAV controller 6 (ECU), a battery management module 7, an engine controller 8, a drive motor controller 9 and a battery 10; the engine controller 8 is electrically connected to the engine 1 and the UAV controller 6 respectively, the drive motor controller 9 is electrically connected to the drive motor 3 and the UAV controller 6 respectively, the battery management module 7 is electrically connected to the UAV controller 6 and the battery 10 respectively, and the battery 10 is also electrically connected to the drive motor 3.

[0060] Exemplarily, the battery 10 may be a high-voltage battery.

[0061] The drone controller 6 can control the voltage and / or current of the battery 10 during charging and discharging through the battery management module 7. The drone controller 6 can control the start, stop and output power of the engine 1 through the engine controller 8. The drone controller 6 can control the start, stop and output power of the drive motor 3 through the drive motor controller 9.

[0062] like Figure 2 As shown, in some embodiments, the multi-stage pressurization subsystem 5 includes an ambient air pressure sensor 5014, and the ambient air pressure sensor 5014 is connected to the drone controller 6.

[0063] Exemplarily, the ambient air pressure sensor 5014 may be an air pressure sensor.

[0064] The ambient air pressure sensor 5014 can obtain the current air pressure value of the environment in real time, and send an atmospheric pressure signal that can reflect the air pressure value to the drone controller 6. The drone controller 6 can obtain the current air pressure value of the environment based on the atmospheric pressure signal and convert it into the current sea wave height value.

[0065] like Figure 2 As shown, in some embodiments, the multi-stage boost subsystem 5 includes a boost controller 5015 (TCU); the boost controller 5015 is electrically connected to the UAV controller 6, the low-pressure stage intercooler 506, the high-pressure stage intercooler 507, the low-pressure stage exhaust bypass valve 5011, the high-pressure stage exhaust bypass valve 5013, the boost motor 503-2 and the electric boost compressor bypass valve 509 respectively.

[0066] Exemplarily, the drone controller 6 and the boost controller 5015 are connected via a CAN bus.

[0067] Exemplarily, the low-pressure stage exhaust bypass valve 5011 , the high-pressure stage exhaust bypass valve 5013 and the electric boost compressor bypass valve 509 may be solenoid valves.

[0068] The UAV controller 6 can control the start and stop and output power of the low-pressure intercooler 506, the start and stop and output power of the high-pressure intercooler 507, the opening of the low-pressure exhaust bypass valve 5011, the opening of the high-pressure exhaust bypass valve 5013, the start and stop and output power of the boost motor 503-2, and the opening of the electric boost compressor bypass valve 509 through the boost controller 5015.

[0069] like Figure 1As shown, in some embodiments, the UAV power system also includes a second clutch 11, a transmission 12 and a reducer 13, the input end of the second clutch 11 is connected to the second end 302 of the rotor shaft, the output end of the second clutch 11 is connected to the input shaft of the transmission 12, the output shaft of the transmission 12 is connected to the input shaft of the reducer 13, and the output shaft of the reducer 13 is connected to the propeller 4.

[0070] Exemplarily, the output shaft of the reducer 13 is a half shaft.

[0071] When the second clutch 11 is closed, the rotor shaft of the drive motor 3 can transmit power to the propeller 4 through the transmission 12 and the reducer 13 to drive the propeller 4 to rotate; or when the second clutch 11 is closed and the propeller 4 is braked, the propeller 4 transmits the power generated by inertia to the rotor shaft of the drive motor 3 through the reducer 13 and the transmission 12, so that the drive motor 3 generates electricity and stores the electrical energy in the battery 10.

[0072] Based on the same inventive concept and in combination with the description of the UAV power systems of the above-mentioned embodiments, this embodiment provides a UAV having the corresponding technical effects of the UAV power systems of the above-mentioned embodiments, which will not be described in detail herein.

[0073] Based on the same inventive concept and in combination with the description of the UAV power system of each of the above embodiments, this embodiment provides a UAV power system control method, which has the corresponding technical effects of the UAV power system of each of the above embodiments, and will not be repeated here.

[0074] The applicant found that the Reynolds number of a drone flying at an altitude of 20 km is 1.0×10 6 The lower the value of this indicator, the lower the flow rate of both the fan and the compressor, and the lower the actual flow area of ​​the turbine, which means that the flow capacity and efficiency of the main components of the engine are also smaller, the speed decreases and the thrust decreases. The direct result of the reduction in the efficiency of the main components is a significant increase in fuel flow, a significant increase in the turbine inlet temperature, and a significant increase in fuel consumption.

[0075] At the same time, in order to adapt to the needs of complex and diverse tasks, this type of UAV has put forward more stringent requirements on the power extraction of the engine. The working environment of UAVs has its own particularity. The atmospheric density is relatively thin, and the engine compressor is very likely to surge at this time. High power greatly increases the frequency of surge, and the stability and balance of the engine are inevitably disturbed.

[0076] In order to improve the above problems, it is necessary to control the multi-stage boost subsystem more accurately, such as Figure 3As shown, this embodiment provides a method for controlling a UAV power system, which is used to control the UAV power system as described in the above embodiments, and the method includes:

[0077] Step S100, obtaining the altitude value and the engine speed value in real time.

[0078] The drone controller 6 can obtain the current external air pressure value in real time through the ambient air pressure sensor 5014, and convert the obtained pressure value into a sea wave height value.

[0079] The drone controller 6 can receive a speed signal sent by the engine controller 8 or the engine 1 , where the speed signal includes a current speed value of the engine 1 .

[0080] Step S200, determining a wave height interval corresponding to the wave height value and a speed interval corresponding to the engine speed value.

[0081] As shown in Table 2, the altitude from 0 to near space can be divided into three altitude intervals, and the engine speed can be divided into three speed intervals.

[0082] Table 2. UAV power system control strategy at different altitudes

[0083]

[0084] According to the acquired altitude value X and Table 2, the current altitude interval can be determined. For example, if the current altitude value X is 5 km, the current altitude interval is the altitude interval of 0<X≤5 km in Table 2.

[0085] Alternatively, the current altitude range can be determined based on the acquired current environment air pressure value Y and Table 2. For example, if the current air pressure value Y is 54 kPa, the current altitude range is the altitude range of 0<X≤5 km in Table 2.

[0086] According to the acquired speed value Z and Table 2, the speed range of the current engine can be determined. For example, if the current speed value Z is 2000r / min, the speed range of the current engine is the speed range of Z<2500r / min in Table 2.

[0087] Step S300, controlling the low-pressure stage supercharger, the high-pressure stage supercharger and the electric supercharger respectively according to the wave height range and the speed range.

[0088] For example, the altitude interval of 0<X≤5km is called the first altitude interval, the altitude interval of 5km<X≤10km is called the second altitude interval, and the altitude interval of 10km<X≤25km is called the third altitude interval. The speed interval of Z<2500r / min is called the first speed interval, the speed interval of 2500r / min≤Z≤5500r / min is called the second speed interval, and the speed interval of Z>5500r / min is called the third speed interval.

[0089] In combination with Table 2, when in the first altitude interval and the first speed interval, the UAV controller 6 sends a control signal to the boost motor 503-2 through the boost controller 5015 to control the boost motor 503-2 to be turned off, sends a control signal to the electric boost compressor bypass valve 509 to control the electric boost compressor bypass valve 509 to be turned off, sends a control signal to the high-pressure stage exhaust bypass valve 5013 to control the high-pressure stage exhaust bypass valve 5013 to be turned off, sends a control signal to the low-pressure stage exhaust bypass valve 5011 to control the low-pressure stage exhaust bypass valve 5011 to be opened and controls the opening of the low-pressure stage exhaust bypass valve 5011 to gradually increase until the intake pressure requirement of the engine 1 is met.

[0090] When in the first altitude range and the second speed range, the UAV controller 6 controls the boost motor 503-2, the electric boost compressor bypass valve 509 and the high-pressure stage exhaust bypass valve 5013 to remain closed through the boost controller 5015, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to gradually increase until the intake pressure requirement of the engine 1 is met.

[0091] When in the first altitude range and the third speed range, the UAV controller 6 controls the boost motor 503-2, the electric boost compressor bypass valve 509 and the high-pressure stage exhaust bypass valve 5013 to remain closed through the boost controller 5015, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to increase or decrease until the intake pressure requirement of the engine 1 is met.

[0092] In summary, it can be seen that when in the first altitude interval, the high-pressure stage supercharger 502 and the low-pressure stage supercharger 501 are working, and the electric supercharger 503 is not working. By adjusting the opening of the low-pressure stage exhaust bypass valve 5011, the boost ratio of the low-pressure stage supercharger 501 to the air in the intake pipe 504 is controlled so that the boosted air can meet the intake pressure requirement of the engine 1.

[0093] When in the second altitude interval and the first speed interval, the UAV controller 6 controls the boost motor 503-2 and the electric boost compressor bypass valve 509 to remain closed through the boost controller 5015, controls the high-pressure stage exhaust bypass valve 5013 to open and gradually increase its opening, and at the same time controls the low-pressure stage exhaust bypass valve 5011 to increase or decrease its opening until the intake pressure requirement of the engine 1 is met.

[0094] When in the second altitude range and the second speed range, the UAV controller 6 controls the boost motor 503-2 and the electric boost compressor bypass valve 509 to remain closed through the boost controller 5015, controls the opening of the high-pressure stage exhaust bypass valve 5013 to gradually increase, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to increase or decrease until the intake pressure requirement of the engine 1 is met.

[0095] When in the second altitude interval and the third speed interval, the UAV controller 6 can control the boost motor 503-2 to turn on (the boost motor 503-2 can work at a lower output power at this time) through the boost controller 5015, and the electric boost compressor bypass valve 509 remains closed, so that the electric supercharger 503 starts to work, and at the same time, the opening of the high-pressure stage exhaust bypass valve 5013 is controlled to increase or decrease, and the opening of the low-pressure stage exhaust bypass valve 5011 is controlled to increase or decrease until the intake pressure requirement of the engine 1 is met. At this time, the high-pressure stage supercharger 502, the low-pressure stage supercharger 501 and the electric supercharger 503 can compress the air in the intake pipe 504 at the same time.

[0096] In summary, it can be seen that when in the second altitude range, the pressure ratio of the high-pressure stage supercharger 502 to the air in the intake pipe 504 can be controlled mainly by adjusting the opening of the high-pressure stage exhaust bypass valve 5013, so that the pressurized air can meet the intake pressure requirement of the engine 1.

[0097] When in the third altitude interval and the first speed interval, the UAV controller 6 controls the boost motor 503-2 to turn on through the boost controller 5015 (the boost motor 503-2 can work at a higher output power at this time), controls the opening of the electric boost compressor bypass valve 509 to gradually increase, and at the same time, controls the opening of the high-pressure stage exhaust bypass valve 5013 to increase or decrease, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to increase or decrease until the intake pressure requirement of the engine 1 is met.

[0098] When in the third altitude interval and the second speed interval, the UAV controller 6 controls the boost motor 503-2 to remain turned on through the boost controller 5015, controls the opening of the electric boost compressor bypass valve 509 to gradually increase, and at the same time, controls the opening of the high-pressure stage exhaust bypass valve 5013 to increase or decrease, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to increase or decrease until the intake pressure requirement of the engine 1 is met.

[0099] When in the third altitude interval and the third speed interval, the UAV controller 6 controls the boost motor 503-2 to remain on through the boost controller 5015, and at the same time, controls the opening of the electric boost compressor bypass valve 509 to increase or decrease, controls the opening of the high-pressure stage exhaust bypass valve 5013 to increase or decrease, and controls the opening of the low-pressure stage exhaust bypass valve 5011 to increase or decrease until the intake pressure requirement of the engine 1 is met.

[0100] In summary, it can be seen that when in the third altitude range, the boost ratio of the electric supercharger 503 to the air in the intake pipe 504 can be controlled mainly by adjusting the opening of the electric supercharger compressor bypass valve 509, so that the boosted air can meet the intake pressure requirement of the engine 1.

[0101] For example, when the vehicle is in the third altitude interval, the boost ratio of the low-pressure stage supercharger 501 to the air in the intake pipe 504 may be gradually increased.

[0102] The UAV power system control method provided in this embodiment is a high-efficiency energy allocation control method suitable for distributed propulsion multi-type load characteristics, which can perform high-efficiency energy management on the UAV power system of each of the above embodiments, and form a 100kW-class UAV multi-energy matching solution for complex mission envelopes. The UAV power system can achieve traction indicators: the hybrid power allocation capacity in the UAV power system is not less than (≮) 100kW; the fuel consumption of the UAV power system is reduced by not less than 20% compared with the fuel consumption of a pure oil engine; the power-to-weight ratio of the UAV power system is not less than 2.0; the UAV power performance at an altitude of 30km is restored to not less than 80% of the rated power at an altitude of 0km.

[0103] It should be noted that the above describes some embodiments of the present application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the above embodiments and still achieve the desired results. In addition, the processes depicted in the accompanying drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0104] The various embodiments in the present application are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0105] The description of the present application is given for the purpose of illustration and description, and is not intended to be exhaustive or to limit the present application to the disclosed form. Many modifications and variations are obvious to those of ordinary skill in the art. The embodiments are selected and described in order to better illustrate the principles and practical applications of the present application, and to enable those of ordinary skill in the art to understand the present application and thus design various embodiments with various modifications suitable for specific purposes.

[0106] Those skilled in the art should understand that the discussion of any of the above embodiments is merely illustrative and is not intended to imply that the scope of the present application (including the claims) is limited to these examples. In line with the concept of the present application, the technical features in the above embodiments or different embodiments may be combined, the steps may be implemented in any order, and there are many other variations of the different aspects of the embodiments of the present application as described above, which are not provided in detail for the sake of simplicity.

[0107] Although the present application has been described in conjunction with specific embodiments thereof, many alternatives, modifications and variations of these embodiments will be apparent to those skilled in the art in light of the foregoing description.

[0108] The embodiments of the present application are intended to cover all such substitutions, modifications and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the embodiments of the present application should be included in the scope of protection of the present application.

Claims

1. A UAV power system, characterized in that: include: Engine, first clutch, drive motor, propeller and multi-stage supercharging subsystem; The output shaft of the engine is connected to the input end of the first clutch, and the output end of the first clutch is connected to the first end of the rotor shaft of the drive motor; the second end of the rotor shaft is connected to the propeller; when the first clutch is closed, the UAV power system is in a driving state in which the engine, the drive motor and the propeller rotate coaxially; The multi-stage supercharging subsystem includes a low-pressure stage supercharger, a high-pressure stage supercharger and an electric supercharger; the low-pressure stage supercharger includes a low-pressure stage compressor and a low-pressure stage turbine connected to each other; the high-pressure stage supercharger includes a high-pressure stage compressor and a high-pressure stage turbine connected to each other; the electric supercharger includes an electric supercharger compressor and a supercharger motor connected to each other; The low-pressure stage compressor, the high-pressure stage compressor, the electric supercharger and the air intake of the engine are connected in series through an air intake pipe, and the low-pressure stage turbine, the high-pressure stage turbine and the exhaust port of the engine are connected in series through an exhaust pipe.

2. The UAV power system according to claim 1, characterized in that: The multi-stage supercharging subsystem includes a low-pressure intercooler and a high-pressure intercooler connected to the intake pipe, the low-pressure intercooler is arranged between the low-pressure compressor and the high-pressure compressor, and the high-pressure intercooler is arranged between the high-pressure compressor and the electric supercharging compressor.

3. The UAV power system according to claim 1, characterized in that: The multi-stage supercharging subsystem further includes an intake branch pipe connected in parallel with the electric supercharging compressor, and the intake branch pipe is provided with an electric supercharging compressor bypass valve.

4. The UAV power system according to claim 1, characterized in that: The multi-stage supercharging subsystem further includes a first exhaust branch pipe connected in parallel with the high-pressure stage turbine, wherein the first exhaust branch pipe is provided with a high-pressure stage exhaust bypass valve.

5. The UAV power system according to claim 1, characterized in that: The multi-stage supercharging subsystem further includes a second exhaust branch pipe connected in parallel with the low-pressure stage turbine, and the second exhaust branch pipe is provided with a low-pressure stage exhaust bypass valve.

6. The UAV power system according to claim 1, characterized in that: The UAV power system includes a UAV controller, a battery management module, an engine controller, a drive motor controller and a battery; The engine controller is electrically connected to the engine and the drone controller respectively, the drive motor controller is electrically connected to the drive motor and the drone controller respectively, the battery management module is electrically connected to the drone controller and the battery respectively, and the battery is also electrically connected to the drive motor.

7. The UAV power system according to claim 6, characterized in that: The multi-stage pressurization subsystem includes an ambient air pressure sensor, and the ambient air pressure sensor is connected to the drone controller.

8. The UAV power system according to claim 6, characterized in that: The multi-stage supercharging subsystem includes a supercharging controller, a low-pressure stage intercooler, a high-pressure stage intercooler, a low-pressure stage exhaust bypass valve, a high-pressure stage exhaust bypass valve and an electric supercharging compressor bypass valve; The boost controller is electrically connected to the UAV controller, the low-pressure intercooler, the high-pressure intercooler, the low-pressure exhaust bypass valve, the high-pressure exhaust bypass valve, the boost motor and the electric boost compressor bypass valve respectively.

9. The UAV power system according to claim 1, characterized in that: The UAV power system also includes a second clutch, a transmission and a reducer, the input end of the second clutch is connected to the second end of the rotor shaft, the output end of the second clutch is connected to the input shaft of the transmission, the output shaft of the transmission is connected to the input shaft of the reducer, and the output shaft of the reducer is connected to the propeller.

10. A drone, characterized in that: Comprising a UAV power system as described in any one of claims 1 to 9.

Images