Emergency power supply system and method for long-endurance aircraft

Abstract

The invention discloses an emergency power supply system and method for a long-endurance aircraft. The system comprises a solar cell installed on the upper surface of an aircraft wing; the wind power generation equipment is used for converting wind energy into electric energy; the wind-solar complementary controller is electrically connected with the solar cell and the wind power generation equipment respectively, the electric energy converted by the solar cell and the wind power generation equipment is subjected to buck-boost conversion through the wind-solar complementary controller, and the voltage grade is adjusted to the voltage grade of the weak current power supply bus; and the emergency battery is electrically connected with the weak current power supply bus, and the emergency battery is used for providing electric energy for the weak current equipment through the emergency battery when the aircraft has a fault of a strong current power supply system or a power distribution system and the converted electric energy cannot meet the power utilization requirement of the weak current equipment. The problem that when the solar aircraft encounters a power supply system fault, the reliable return flight of the aircraft is not supported only by the electric quantity of the emergency battery is solved, and the reliability and safety of the solar aircraft are improved.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft energy technology, and more specifically, relates to an emergency power supply system and method for a long-flight aircraft. Background Art

[0002] With the rapid development of the industrial and aerospace fields, the number of near-space long-endurance aircraft is increasing. In the event of an emergency such as a failure in the strong power supply system or the power distribution system, the emergency power supply system of the aircraft is often an emergency battery, which is used to power the necessary weak power supply equipment such as the flight control system and the link system to ensure their short-term normal operation. However, there is a problem that the power of the emergency battery alone is often not enough to support the reliable return of the aircraft.

[0003] The information disclosed in the background technology section of the present invention is only intended to deepen the understanding of the general background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Summary of the invention

[0004] The purpose of the present invention is to provide an emergency power supply system and method for long-flight aircraft, so as to solve the problem that when a solar-powered aircraft encounters a power supply system failure, the emergency battery power alone is insufficient to support the aircraft's reliable return, thereby improving the reliability and safety of the solar-powered aircraft.

[0005] To achieve the above objectives, the present invention proposes an emergency power supply system and method for a long-flight aircraft.

[0006] According to a first aspect of the present invention, a long-flight aircraft emergency power supply system is proposed, comprising:

[0007] A solar cell is installed on the upper surface of the aircraft wing, and the solar cell is electrically connected to the strong power supply system;

[0008] Wind power generation equipment, used to convert wind energy into electrical energy;

[0009] A wind-solar hybrid controller is electrically connected to the solar cell and the wind power generation equipment, respectively, and the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cell and the wind power generation equipment, and adjusts the voltage level to the voltage level of the weak current power supply bus;

[0010] The emergency battery is electrically connected to the weak-current power supply bus. The emergency battery is used to provide electrical energy to the weak-current equipment through the emergency battery when the strong-current power supply system or the power distribution system of the aircraft fails and the converted electrical energy cannot meet the power demand of the weak-current equipment.

[0011] Optionally, the wind power generation equipment includes:

[0012] Its own power system;

[0013] or

[0014] Ducted fan generator.

[0015] Optionally, the wind-solar hybrid controller includes:

[0016] A rectifier module, a first buck-boost module, a second buck-boost module and a control module;

[0017] Optionally, the input end of the rectifier module is electrically connected to the wind power generation equipment, the output end of the rectifier module is electrically connected to the input end of the first buck-boost module, and the output end of the first buck-boost module is electrically connected to the weak current power supply bus.

[0018] Optionally, an input end of the second buck-boost module is electrically connected to the solar cell, and an output end of the second buck-boost module is electrically connected to the weak current power supply bus.

[0019] Optionally, the controller is communicatively connected with the flight control system of the aircraft, the first buck-boost module and the second buck-boost module respectively.

[0020] Optionally,

[0021] When the aircraft operates normally, the flight control system controls the wind-solar hybrid controller to be in a silent state through the controller;

[0022] When the strong power supply system or the power distribution system of the aircraft fails, the flight control system controls the wind-solar hybrid controller to enter a working state through the controller, and provides power to the weak current equipment through the emergency battery;

[0023] During the day, the solar cell and wind power generation equipment transmit the electric energy to the wind-solar hybrid controller and then to the weak current power supply bus and emergency battery;

[0024] At night, the wind power generation equipment transmits electric energy to the wind-solar hybrid controller and then to the weak-current bus and emergency battery.

[0025] Optionally, when the aircraft is operating normally, the ducted fan generator is located in an equipment compartment of the aircraft;

[0026] When a high-voltage power supply system or a power distribution system failure occurs in the aircraft, the ducted fan generator is released from the equipment compartment and is located at the bottom of the aircraft.

[0027] Optionally, the voltage level of the weak current power supply bus is:

[0028] 28V.

[0029] According to a second aspect of the present invention, a long-flight aircraft emergency power supply method is provided, based on the long-flight aircraft emergency power supply system according to any one of the first aspects, comprising:

[0030] When the aircraft is operating normally, the wind-solar hybrid controller is in silent state;

[0031] When the aircraft has a high-voltage power supply system or a power distribution system failure, the wind-solar hybrid controller is controlled to enter a working state;

[0032] During the day, the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cell and the wind power generation equipment, adjusts the voltage level to the voltage level of the weak current power supply bus, and provides it to the weak current power supply bus, and supplies power to the weak current equipment and the emergency battery through the weak current power supply bus;

[0033] At night, the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the wind power generation equipment, adjusts the voltage level to the voltage level of the weak-current power supply bus, and provides it to the weak-current power supply bus, and supplies power to the weak-current equipment and the emergency battery through the weak-current power supply bus;

[0034] When the converted electric energy cannot meet the power demand of the weak-current equipment, the emergency battery provides electric energy to the weak-current equipment.

[0035] The beneficial effects of the present invention are as follows: the present invention performs step-up and step-down conversion on the electric energy converted by solar cells and wind power generation equipment through a wind-solar hybrid controller, adjusts the voltage level to the voltage level of a weak current power supply bus, provides the voltage to the weak current power supply bus, supplies power to weak current equipment through the weak current power supply bus, and supplies power to emergency batteries, thereby solving the problem that when a solar aircraft encounters a power supply system failure, the emergency battery power alone is insufficient to support the reliable return of the aircraft, thereby improving the reliability and safety of the solar aircraft.

[0036] The system of the present invention has other characteristics and advantages, which will be apparent from the drawings incorporated herein and the following detailed description, or will be described in detail in the drawings incorporated herein and the following detailed description, which together serve to explain the specific principles of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, in which like reference numerals generally represent like components.

[0038] Figure 1A schematic diagram of an emergency power supply system for a long-flight aircraft according to a first embodiment of the present invention is shown.

[0039] Figure 2 A schematic diagram of a wind-solar hybrid controller according to the first embodiment of the present invention is shown.

[0040] Figure 3 A schematic diagram of the appearance of a long-flight solar-powered aircraft according to the first embodiment of the present invention is shown.

[0041] Figure 4 A schematic structural diagram of a ducted fan wind power generation device according to the first embodiment of the present invention is shown. DETAILED DESCRIPTION

[0042] The present invention will be described in more detail below with reference to the accompanying drawings. Although preferred embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0043] A long-flight aircraft emergency power supply system according to the present invention comprises:

[0044] Solar cells are installed on the upper surface of the aircraft wing, and the solar cells are electrically connected to the strong power supply system;

[0045] Wind power generation equipment, used to convert wind energy into electrical energy;

[0046] The wind-solar hybrid controller is electrically connected to the solar cell and the wind power generation equipment respectively, and the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cell and the wind power generation equipment, and adjusts the voltage level to the voltage level of the weak current power supply bus;

[0047] The emergency battery is electrically connected to the weak-current power supply bus. The emergency battery is used to provide power to weak-current equipment when the aircraft's strong-current power supply system or distribution system fails and the converted electricity cannot meet the power demand of the weak-current equipment.

[0048] Specifically, the long-flight aircraft emergency power supply system of the present invention comprises: solar cells, wind power generation equipment, a wind-solar hybrid controller and an emergency battery. The wind-solar hybrid controller is electrically connected to the solar cells and the wind power generation equipment, respectively. The wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cells and the wind power generation equipment, and adjusts the voltage level to the voltage level of the weak-current power supply bus. The emergency battery is electrically connected to the weak-current power supply bus. When the strong-current power supply system or the power distribution system of the aircraft fails, the present invention performs step-up and step-down conversion on the electric energy converted by the solar cells and the wind power generation equipment during the day through the wind-solar hybrid controller, and adjusts the voltage level to the voltage level of the weak-current power supply bus. The wind-solar hybrid controller is used to perform step-up and step-down conversion on the electric energy converted by the wind power generation equipment at night, and the voltage level is adjusted to the voltage level of the weak-current power supply bus, and the electric energy is provided to the weak-current power supply bus, and the weak-current equipment is powered through the weak-current power supply bus, as well as the emergency battery; when the converted electric energy cannot meet the power demand of the weak-current equipment, the emergency battery is used to provide electric energy to the weak-current equipment; the problem that the emergency battery alone is insufficient to support the reliable return of the solar-powered aircraft when the power supply system fails is solved, thereby improving the reliability and safety of the solar-powered aircraft.

[0049] In one example, a wind power plant includes:

[0050] Its own power system;

[0051] or

[0052] Ducted fan generator.

[0053] In one example, the wind-solar hybrid controller includes:

[0054] A rectifier module, a first buck-boost module, a second buck-boost module and a control module;

[0055] In one example, the input end of the rectifier module is electrically connected to the wind power generation equipment, the output end of the rectifier module is electrically connected to the input end of the first buck-boost module, and the output end of the first buck-boost module is electrically connected to the weak current power supply bus.

[0056] In one example, an input end of the second buck-boost module is electrically connected to the solar cell, and an output end of the second buck-boost module is electrically connected to the weak current power supply bus.

[0057] In one example, the controller is communicatively connected with the flight control system of the aircraft, the first buck-boost module, and the second buck-boost module respectively.

[0058] In one example,

[0059] When the aircraft is operating normally, the flight control system controls the wind-solar hybrid controller to be in silent state through the controller;

[0060] When the aircraft's high-voltage power supply system or power distribution system fails, the flight control system controls the wind-solar hybrid controller to enter the working state through the controller, and provides power to the weak-voltage equipment through the emergency battery;

[0061] During the day, the electric energy is transmitted to the wind-solar hybrid controller through solar cells and wind power generation equipment and then transmitted to the weak current power supply bus and emergency battery;

[0062] At night, the wind power generation equipment transmits the electric energy to the wind-solar hybrid controller and then to the weak current bus and emergency battery.

[0063] In one example, during normal operation of the aircraft, the ducted fan generator is located in an equipment bay of the aircraft;

[0064] When the aircraft's high-voltage power supply system or power distribution system fails, the ducted fan generator is released from the equipment compartment and located at the bottom of the aircraft.

[0065] In one example, the voltage level of the weak current power supply bus is:

[0066] 28V.

[0067] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but is not intended to be limiting of the present invention. It should be noted that the embodiments and features in the embodiments of the present invention may be combined with each other without conflict.

[0068] Embodiment 1

[0069] like Figure 1 As shown, this embodiment provides an emergency power supply system for a long-flight aircraft, including:

[0070] Wind power generation equipment (plus wind power generation equipment or aircraft power system motors and propellers), solar cells, wind-solar hybrid controllers, emergency batteries, weak current power supply networks;

[0071] The additional wind power generation equipment is arranged in the equipment cabin. It does not affect the aerodynamic performance of the aircraft during normal flight. When the strong electric bus or the distributor fails, the flight controller controls it to be released from the equipment cabin. The aircraft descends to drive the propeller in the duct of the additional wind power generation equipment to rotate. The generator will generate electricity and transmit it to the wind-solar hybrid controller.

[0072] When the aircraft is working normally, the motor controller draws power from the strong power bus to control the motor to rotate according to the command speed, providing flight power for the aircraft. When the strong power bus or the distributor fails, the aircraft is in an emergency state and needs to return. The power system is running in a windmill state, and the ground operator sends a control command to connect the motor three-phase line to the wind-solar hybrid controller;

[0073] When the aircraft is working normally, the solar cells generate electricity and the power controller converts the electricity into the strong power bus voltage to provide power supply for the whole aircraft. When the strong power bus or the distributor fails, the flight control system controls the switching of some solar cells of the aircraft to the wind-solar hybrid controller.

[0074] When the aircraft is working normally, the wind-solar hybrid controller is in silent state. When the aircraft's strong power bus or distribution network fails, the wind-solar hybrid controller will convert the power generated by the wind power generation equipment and solar cells connected to it, and convert the voltage level to DC28V to power the weak current network equipment and store energy for the emergency battery.

[0075] like Figure 2 As shown, the wind-solar hybrid controller includes a rectifier unit and two buck-boost modules, wherein the power generated by the wind power generation equipment is first rectified by the rectifier unit, and then the voltage level is changed to DC28V by the buck-boost module 1, and the solar cell power is directly converted to DC28V by the buck-boost module 2, and finally output to the weak current bus;

[0076] like Figure 3 As shown, the solar cells are arranged on the upper surface 3 of the main wing, the wind-solar hybrid controller is arranged in the equipment cabin 1, and the power system 2 is located at the leading edge of the aircraft fuselage.

[0077] like Figure 4 As shown, the wind power generation equipment is a ducted fan wind power generation device. The duct wall 4 of the ducted fan wind power generation device is mechanically connected and fixed to the aircraft and provides support for the internal generator. During normal flight, the entire device is arranged in the aircraft equipment cabin 1. In an emergency state, the ducted wind power generation device is released by a release device and hung at the bottom of the aircraft. The rotation of the fan blades 7 drives the generator 5 to rotate and is connected to the wind-solar hybrid controller in the equipment cabin 1 through the generator cable 6.

[0078] Embodiment 2

[0079] This embodiment provides a long-flight aircraft emergency power supply method, based on the long-flight aircraft emergency power supply system described in Embodiment 1, including:

[0080] When the aircraft is operating normally, the wind-solar hybrid controller is in silent state;

[0081] When the aircraft's high-voltage power supply system or power distribution system fails, the wind-solar hybrid controller is controlled to enter the working state;

[0082] During the day, the wind-solar hybrid controller converts the electric energy converted by solar cells and wind power generation equipment into voltage and voltage, adjusts the voltage level to the voltage level of the weak-current power supply bus, and provides it to the weak-current power supply bus. Through the weak-current power supply bus, it supplies power to weak-current equipment and emergency batteries.

[0083] At night, the wind-solar hybrid controller converts the electric energy converted by the wind power generation equipment into voltage and voltage, adjusts the voltage level to the voltage level of the weak-current power supply bus, and provides it to the weak-current power supply bus. The weak-current power supply bus supplies power to the weak-current equipment and the emergency battery.

[0084] When the converted electrical energy cannot meet the power demand of the weak-current equipment, the emergency battery is used to provide electrical energy to the weak-current equipment.

[0085] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A long-flight aircraft emergency power supply system, characterized in that: include: A solar cell is installed on the upper surface of the aircraft wing, and the solar cell is electrically connected to the strong power supply system; Wind power generation equipment, used to convert wind energy into electrical energy; A wind-solar hybrid controller is electrically connected to the solar cell and the wind power generation equipment, respectively, and the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cell and the wind power generation equipment, and adjusts the voltage level to the voltage level of the weak current power supply bus; The emergency battery is electrically connected to the weak-current power supply bus. The emergency battery is used to provide electrical energy to the weak-current equipment through the emergency battery when the strong-current power supply system or the power distribution system of the aircraft fails and the converted electrical energy cannot meet the power demand of the weak-current equipment.

2. The long-flight aircraft emergency power supply system according to claim 1, characterized in that: The wind power generation equipment comprises: Its own power system; or Ducted fan generator.

3. The long-flight aircraft emergency power supply system according to claim 1, characterized in that: The wind-solar hybrid controller comprises: A rectifier module, a first buck-boost module, a second buck-boost module and a control module.

4. The long-flight aircraft emergency power supply system according to claim 3, characterized in that: The input end of the rectifier module is electrically connected to the wind power generation equipment, the output end of the rectifier module is electrically connected to the input end of the first buck-boost module, and the output end of the first buck-boost module is electrically connected to the weak current power supply bus.

5. The long-flight aircraft emergency power supply system according to claim 4, characterized in that: The input end of the second buck-boost module is electrically connected to the solar cell, and the output end of the second buck-boost module is electrically connected to the weak current power supply bus.

6. The long-flight aircraft emergency power supply system according to claim 5, characterized in that: The controller is respectively connected to the flight control system of the aircraft, the first buck-boost module and the second buck-boost module for communication.

7. The long-flight aircraft emergency power supply system according to claim 6, characterized in that: When the aircraft operates normally, the flight control system controls the wind-solar hybrid controller to be in a silent state through the controller; When the strong power supply system or the power distribution system of the aircraft fails, the flight control system controls the wind-solar hybrid controller to enter a working state through the controller, and provides power to the weak current equipment through the emergency battery; During the day, the solar cell and wind power generation equipment transmit the electric energy to the wind-solar hybrid controller and then to the weak current power supply bus and emergency battery; At night, the wind power generation equipment transmits electric energy to the wind-solar hybrid controller and then to the weak-current bus and emergency battery.

8. The long-flight aircraft emergency power supply system according to claim 2, characterized in that: When the aircraft is operating normally, the ducted fan generator is located in the equipment compartment of the aircraft; When a high-voltage power supply system or a power distribution system failure occurs in the aircraft, the ducted fan generator is released from the equipment compartment and is located at the bottom of the aircraft.

9. The long-flight aircraft emergency power supply system according to claim 1, characterized in that: The voltage level of the weak current power supply bus is: 28V。 10. A long-flight aircraft emergency power supply method, based on the long-flight aircraft emergency power supply system according to any one of claims 1 to 9, characterized in that: include: When the aircraft is operating normally, the wind-solar hybrid controller is in silent state; When the aircraft has a high-voltage power supply system or a power distribution system failure, the wind-solar hybrid controller is controlled to enter a working state; During the day, the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the solar cell and the wind power generation equipment, adjusts the voltage level to the voltage level of the weak current power supply bus, and provides it to the weak current power supply bus, and supplies power to the weak current equipment and the emergency battery through the weak current power supply bus; At night, the wind-solar hybrid controller performs step-up and step-down conversion on the electric energy converted by the wind power generation equipment, adjusts the voltage level to the voltage level of the weak-current power supply bus, and provides it to the weak-current power supply bus, and supplies power to the weak-current equipment and the emergency battery through the weak-current power supply bus; When the converted electric energy cannot meet the power demand of the weak-current equipment, the emergency battery provides electric energy to the weak-current equipment.

Images