An airborne charging device for a power battery pack of an electric propulsion system of an aircraft

Abstract

The application provides an aircraft electric propulsion system power battery pack air charging device, which comprises an air charging host, carries a gas turbine, is connected with an impeller set, the impeller set is connected with a generator, the generator is connected with a voltage stabilizer, the voltage stabilizer is connected with a comprehensive power management module, the comprehensive power management module is connected with a mode selection switch, the mode selection switch is connected with a direct charging transformer and an energy storage rectifier, the direct charging transformer is connected with a primary coil, the energy storage rectifier is connected with an energy storage charger, the energy storage charger is connected with an energy storage battery, the energy storage battery is connected with an energy storage inverter, the energy storage inverter is connected with an energy storage transformer, the energy storage transformer is connected with the primary coil, and the primary coil is stretched out outside the air charging host body. The aircraft electric propulsion system power battery pack air charging device further comprises a secondary coil, which is stretched out outside the aircraft body and can be inserted into the primary coil, is connected with a charging rectifier, the charging rectifier is connected with a charging charger, and the charging charger is connected with the aircraft electric propulsion system power battery pack.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of in-flight charging of power battery packs of an electric propulsion system of an airplane, and particularly relates to an in-flight charging device for power battery packs of an electric propulsion system of an airplane. BACKGROUND

[0002] The electric propulsion technology is to set an electric propulsion system in an airplane, drive an electric motor by a power battery pack, drive a fan to rotate, and provide power for the airplane, which is small in noise, easy to control, and clean and environmentally friendly.

[0003] The range and loitering time of the airplane using the electric propulsion technology are limited by the power of the power battery pack, and it is difficult to complete the demand for long-range and long-loitering time tasks.

[0004] The present application is proposed in view of the existence of the above technical defects.

[0005] It should be noted that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0006] The purpose of the present application is to provide an in-flight charging device for power battery packs of an electric propulsion system of an airplane to overcome or alleviate at least one aspect of the known technical defects.

[0007] The technical solution of the present application is:

[0008] An in-flight charging device for power battery packs of an electric propulsion system of an airplane, comprising an in-flight charging mother machine;

[0009] The in-flight charging mother machine is equipped with a gas turbine, the gas turbine is connected to an impeller set, the impeller set is connected to a generator, the generator is connected to a voltage stabilizer, the voltage stabilizer is connected to a comprehensive power management module, the comprehensive power management module is connected to a mode selection switch, the mode selection switch is connected to a direct charging transformer and an energy storage rectifier, the direct charging transformer is connected to a primary coil, the energy storage rectifier is connected to an energy storage charger, the energy storage charger is connected to an energy storage battery, the energy storage battery is connected to an energy storage inverter, the energy storage inverter is connected to an energy storage transformer, the energy storage transformer is connected to the primary coil, and the primary coil extends outside the in-flight charging mother machine body;

[0010] The in-flight charging device for power battery packs of an electric propulsion system of an airplane further comprises a secondary coil;

[0011] The secondary coil extends outside the airplane body and can be inserted into the primary coil, the secondary coil is connected to a charging rectifier, the charging rectifier is connected to a charging charger, and the charging charger is connected to the power battery packs of the electric propulsion system of the airplane;

[0012] The aircraft electric propulsion system power battery pack in-flight charging device has:

[0013] The direct charging state, the mode selection switch on the in-flight charging host machine controls the comprehensive power management module to connect the direct charging transformer;

[0014] The energy storage charging state, the mode selection switch on the in-flight charging host machine controls the comprehensive power management module to connect the energy storage rectifier.

[0015] According to at least one embodiment of the present application, in the aircraft electric propulsion system power battery pack in-flight charging device described above, the primary coil and the secondary coil are respectively wound on the corresponding hollow thin-walled cylinders, fixed by vulcanization process, and the hollow thin-walled cylinders are made of non-magnetic material, specifically nylon material.

[0016] According to at least one embodiment of the present application, in the aircraft electric propulsion system power battery pack in-flight charging device described above, the comprehensive power management module and the mode selection switch on the in-flight charging host machine are connected to the host machine central controller, the host machine central controller can collect comprehensive power management module information and control the mode selection switch, and the host machine data receiving module and the host machine command sending module are connected to the host machine wifi antenna.

[0017] The power battery pack on the aircraft is connected to the aircraft central controller, the aircraft central controller can collect power battery pack information, and the aircraft data sending module and the aircraft command receiving module are connected to the aircraft wifi antenna.

[0018] The aircraft central controller on the aircraft can transmit aircraft power battery pack information to the central controller on the in-flight charging host machine through the aircraft data sending module, the aircraft wifi antenna, the host machine wifi antenna, and the host machine data receiving module.

[0019] The host machine central controller on the in-flight charging host machine can transmit command signals to the aircraft central controller on the aircraft through the host machine command sending module, the host machine wifi antenna, the aircraft wifi antenna, and the aircraft command receiving module.

[0020] According to at least one embodiment of the present application, in the aircraft electric propulsion system power battery pack in-flight charging device described above, the host machine wifi antenna on the in-flight charging host machine is connected to the hollow thin-walled cylinder on which the primary coil is wound.

[0021] The aircraft wifi antenna on the aircraft is connected to the hollow thin-walled cylinder on which the secondary coil is wound.

[0022] According to at least one embodiment of the present application, in the aircraft electric propulsion system power battery pack airborne charging device, the airborne charging host machine central controller and the aircraft central controller are embedded PC using a Windows operating system.

[0023] According to at least one embodiment of the present application, in the aircraft electric propulsion system power battery pack airborne charging device, the airborne charging host machine central controller is connected to the host computer. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 is a schematic diagram of the aircraft electric propulsion system power battery pack airborne charging device provided by the embodiments of the present application.

[0025] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and in addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0026] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below with reference to the drawings, it can be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not limited to the present application. It should be noted that, in order to facilitate the description, only the parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design, in the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0027] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as the general meaning understood by those of ordinary skill in the art to which the present application belongs. The words of orientation such as "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like used in the description of the present application only indicate relative directions or positional relationships, and are not intended to imply that the device or element must have a particular orientation, be constructed and operated in a particular orientation, and the relative positional relationship thereof can also change accordingly when the absolute position of the described object changes, therefore it cannot be understood as a limitation on the present application. The terms "first", "second", "third" and the like used in the description of the present application are only for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The terms "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the number, but should be understood as the presence of at least one. The terms "include" or "contain" and the like used in the description of the present application mean that the elements or objects appearing before the word are encompassed by the elements or objects listed after the word and their equivalents, without excluding other elements or objects.

[0028] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be a fixed connection, or a detachable connection, or an integral connection; it can be a mechanical connection, or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or a connection between two elements, and those skilled in the art can understand its specific meaning in the present application according to the specific circumstances.

[0029] The following will be described in detail with reference to the accompanying drawings Figure 1 The present application will be further described in detail.

[0030] An aircraft electric propulsion system power battery pack airborne charging device, comprising an airborne charging mother machine;

[0031] The airborne charging mother machine is equipped with a gas turbine, the gas turbine is connected with an impeller set, the impeller set is connected with a generator, the generator is connected with a voltage stabilizer, the voltage stabilizer is connected with a comprehensive power management module, the comprehensive power management module is connected with a mode selection switch, the mode selection switch is connected with a direct charging transformer and an energy storage rectifier, the direct charging transformer is connected with a primary coil, the energy storage rectifier is connected with an energy storage charger, the energy storage charger is connected with an energy storage battery, the energy storage battery is connected with an energy storage inverter, the energy storage inverter is connected with an energy storage transformer, the energy storage transformer is connected with the primary coil, and the primary coil extends outside the airborne charging mother machine body;

[0032] The aircraft electric propulsion system power battery pack airborne charging device further comprises a secondary coil.

[0033] The secondary coil is extended outside the aircraft body and can be inserted into the primary coil, the secondary coil is connected to a charging rectifier, the charging rectifier is connected to a charging charger, and the charging charger is connected to the aircraft electric propulsion system power battery pack.

[0034] The aircraft electric propulsion system power battery pack in-flight charging device has:

[0035] The direct charging state, the mode selection switch on the in-flight charging mother machine controls the comprehensive power management module to connect the direct charging transformer.

[0036] The energy storage charging state, the mode selection switch on the in-flight charging mother machine controls the comprehensive power management module to connect the energy storage rectifier.

[0037] The in-flight charging mother machine can adopt a distributed turbine electric propulsion system, carry a gas turbine, and drive the impeller set to rotate, and then drive the generator to work, generate alternating current, and after voltage stabilization by the voltage stabilizer, it is connected to the comprehensive power management system, which can be used for the propulsion system, charging system and other onboard systems of the in-flight charging mother machine.

[0038] Under normal circumstances, the mode selection switch on the in-flight charging mother machine can control the comprehensive power management module to connect the energy storage rectifier to enter the energy storage charging state, convert alternating current into direct current, charge the energy storage battery with the energy storage charger, and store it. A separate switch control can be provided on this line.

[0039] When the aircraft electric propulsion system power battery pack needs to be charged in flight, the aircraft can be aligned with the in-flight charging mother machine, the secondary coil on the aircraft is inserted into the primary coil on the in-flight charging mother machine, the mode selection switch on the in-flight charging mother machine can control the comprehensive power management module to connect the direct charging transformer to enter the direct charging state, boost the alternating current, and input the primary coil on the in-flight charging mother machine. A separate switch control can be provided on this line. Using the principle of electromagnetic induction, alternating current is generated in the secondary coil on the aircraft, which is converted into direct current by the aircraft rectifier on the aircraft, and the power battery pack is charged by the aircraft charger on the aircraft. The in-flight charging of the aircraft electric propulsion system power battery pack can meet the needs of long-range and long-time tasks.

[0040] When the aircraft electric propulsion system power battery pack is charged in flight, the energy storage battery on the in-flight charging mother machine can also be used to convert the direct current in the energy storage battery into alternating current by the energy storage inverter, and the energy storage transformer is used to boost the voltage and input the primary coil on the in-flight charging mother machine, thereby realizing the in-flight charging of the aircraft electric propulsion system power battery pack.

[0041] The primary coil on the airborne charging female machine can be provided with a plurality of primary coils, so that the airborne charging of a plurality of aircraft electric propulsion system power battery packs can be simultaneously realized. The primary coil on the airborne charging female machine and the secondary coil on the aircraft can be designed to be lifted and pushed out only when the aircraft electric propulsion system power battery pack needs to be charged in the air. After the charging is completed, the primary coil on the airborne charging female machine and the secondary coil on the aircraft are retracted into the body, so as to protect the primary coil on the airborne charging female machine and the secondary coil on the aircraft and reduce the possibility of being damaged by external factors.

[0042] The aircraft electric propulsion system power battery pack airborne charging device disclosed in the above embodiment designs an airborne charging female machine, uses the principle of electromagnetic induction to realize the airborne charging of the aircraft electric propulsion system power battery pack, is a non-contact charging device, has relatively loose requirements for the relative position accuracy of the airborne charging female machine and the aircraft, can avoid bump damage, and is convenient to operate.

[0043] In some optional embodiments, the aircraft electric propulsion system power battery pack airborne charging device disclosed above, the primary coil and the secondary coil are respectively wound on corresponding hollow thin-walled cylinders and are fixed by vulcanization process. The hollow thin-walled cylinder is made of non-magnetic material, specifically nylon material.

[0044] In some optional embodiments, the aircraft electric propulsion system power battery pack airborne charging device disclosed above, the comprehensive power management module and the mode selection switch on the airborne charging female machine are connected to the female machine central controller. The female machine central controller can collect comprehensive power management module information and control the mode selection switch. The female machine data receiving module and the female machine command sending module are connected to the female machine wifi antenna.

[0045] The aircraft power battery pack is connected to the aircraft central controller. The aircraft central controller can collect power battery pack information and is connected to the aircraft data sending module and the aircraft command receiving module. The aircraft data sending module and the aircraft command receiving module are connected to the aircraft wifi antenna.

[0046] The aircraft central controller on the aircraft can transmit the aircraft power battery pack information to the central controller on the airborne charging female machine through the aircraft data sending module, the aircraft wifi antenna, the female machine wifi antenna, and the female machine data receiving module. The central controller on the airborne charging female machine can control the comprehensive power management module and the mode selection switch and transmit the aircraft flight information and state sensing information.

[0047] The air charging mother machine central controller can transmit command signals to the aircraft central controller on the aircraft through the mother machine command starting module, the mother machine wifi antenna, the aircraft wifi antenna, and the aircraft command receiving module, control and manage the power battery pack on the aircraft, and transmit flight control instructions.

[0048] In some optional embodiments of the aircraft electric propulsion system power battery pack air charging device, the air charging mother machine wifi antenna is connected to the hollow thin-walled cylinder wound with the primary coil, and the aircraft wifi antenna is connected to the hollow thin-walled cylinder wound with the secondary coil. The air charging mother machine wifi antenna and the aircraft wifi antenna can be extended out of the aircraft body and close to each other when the aircraft electric propulsion system power battery pack is being charged in the air, so as to ensure that the information interaction between the air charging mother machine central controller and the aircraft central controller is timely and accurate when the aircraft electric propulsion system power battery pack is being charged in the air.

[0049] In some optional embodiments of the aircraft electric propulsion system power battery pack air charging device, the air charging mother machine central controller and the aircraft central controller use an embedded PC based on an operating system.

[0050] In some optional embodiments of the aircraft electric propulsion system power battery pack air charging device, the air charging mother machine central controller is connected to an upper computer, and information can be displayed through an interactive interface, so that the staff on the air charging mother machine can easily and timely understand the power and signal transmission situation.

[0051] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0052] In addition, those skilled in the art should also realize that the related modules and units involved in the aircraft electric propulsion system power battery pack air charging device disclosed in the embodiments can be realized by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, the embodiments are described in general terms in this application. Whether the functions are executed in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can choose different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered beyond the scope of the application.

[0053] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. An in-flight charging device for a power battery pack of an aircraft electric propulsion system, characterized in that, Including aerial charging mother machines; The aerial charging mothership is equipped with a gas turbine, which is connected to a turbine generator set. The turbine generator set is connected to a generator, which is connected to a voltage regulator. The voltage regulator is connected to an integrated power management module, which is connected to a mode selection switch. The mode selection switch is connected to a direct charging transformer and an energy storage rectifier. The direct charging transformer is connected to the primary coil, the energy storage rectifier is connected to an energy storage charger, the energy storage charger is connected to an energy storage battery, the energy storage battery is connected to an energy storage inverter, the energy storage inverter is connected to an energy storage transformer, and the energy storage transformer is connected to the primary coil. The primary coil extends outside the aerial charging mothership. The in-flight charging device for the power battery pack of the aircraft electric propulsion system also includes a secondary coil; The secondary coil extends outside the aircraft body and can be inserted into the primary coil. The secondary coil is connected to the charging rectifier, the charging rectifier is connected to the charging charger, and the charging charger is connected to the power battery pack of the aircraft's electric propulsion system. The in-flight charging device for the power battery pack of the aircraft electric propulsion system has the following features: In direct charging mode, the mode selection switch on the over-the-air charging mother machine controls the integrated power management module to connect the direct charging transformer; In the energy storage charging state, the mode selection switch on the air-to-ground charging mother machine controls the integrated power management module to connect the energy storage rectifier.

2. The in-flight charging device for the power battery pack of the aircraft electric propulsion system according to claim 1, characterized in that, The primary and secondary coils are wound on corresponding hollow thin-walled cylinders and fixed by a vulcanization process. The hollow thin-walled cylinders are made of non-magnetic material, specifically nylon.

3. The in-flight charging device for the power battery pack of the aircraft electric propulsion system according to claim 2, characterized in that, The integrated power management module and mode selection switch on the in-flight charging mother aircraft are connected to the mother aircraft's central controller. The mother aircraft's central controller can collect information from the integrated power management module and control the mode selection switch, and is connected to the mother aircraft's data receiving module and command activation module. The mother aircraft's data receiving module and command activation module are connected to the mother aircraft's Wi-Fi antenna. The aircraft's power battery pack is connected to the aircraft's central controller. The aircraft's central controller can collect information from the power battery pack and connect to the aircraft's data transmission module and command receiving module. The aircraft's data transmission module and command receiving module are connected to the aircraft's Wi-Fi antenna. The aircraft's central controller can transmit information about the aircraft's power battery pack to the central controller on the in-flight charging mother aircraft via the aircraft data transmission module, the aircraft's Wi-Fi antenna, the mother aircraft's Wi-Fi antenna, and the mother aircraft's data receiving module. The central controller on the in-flight charging mother aircraft can transmit command signals to the central controller on the aircraft via the mother aircraft command activation module, the mother aircraft Wi-Fi antenna, the aircraft Wi-Fi antenna, and the aircraft command receiving module.

4. The in-flight charging device for the power battery pack of the aircraft electric propulsion system according to claim 3, characterized in that, The mother ship's Wi-Fi antenna on the in-flight charging mother ship is connected to a hollow thin-walled cylinder on which the primary coil is wound. The airplane's Wi-Fi antenna is connected to a hollow, thin-walled cylinder with a secondary coil wound around it.

5. The in-flight charging device for the power battery pack of the aircraft electric propulsion system according to claim 4, characterized in that, The central controller on the mothership and the central controller on the aircraft both use embedded PCs with operating systems.

6. The in-flight charging device for the power battery pack of the aircraft electric propulsion system according to claim 5, characterized in that, The central controller of the aerial charging mother machine is connected to the host computer.

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