CN118739542A - Electric power system of hypersonic aircraft - Google Patents
Electric power system of hypersonic aircraft Download PDFInfo
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- 238000000034 method Methods 0.000 description 9
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- 150000002430 hydrocarbons Chemical class 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000004080 punching Methods 0.000 description 2
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
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Abstract
The invention discloses an electric power system of a hypersonic aircraft, which relates to the technical field of aircrafts and comprises: the device comprises an oil gas turbine, a first generator, a flywheel energy storage device, a lithium battery and a super capacitor, wherein the flywheel energy storage device comprises a flywheel and a second generator; the output of the oil gas turbine is respectively connected with the first generator and the flywheel, and the flywheel is connected with the second generator; the oil-gas turbine is used for converting heat energy into mechanical energy at the high Mach stage of the hypersonic aircraft to generate power for the first generator and simultaneously storing energy for the flywheel device; the flywheel energy storage device is used for charging the lithium battery and the super capacitor; the lithium battery, the flywheel energy storage device and the super capacitor are used for jointly supplying power to the pulse load when the pulse load is input; the flywheel energy storage device is used for replacing corresponding components to supply power to the load when the first generator, the lithium battery and the super capacitor are in fault. The invention improves the energy utilization rate, and ensures that the architecture has high robustness and full-band reconstruction capability.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an electric power system of a hypersonic aircraft.
Background
Since the 21 st century, hypersonic aircraft (also commonly referred to as high Mach number aircraft, cruise speed. Gtoreq.3Ma) became the key area of development worldwide. Currently, the problems of shortage of onboard energy and impulse loading shock that are typical of high-speed aircraft carrying impulse loading are very prominent.
In order to stabilize impact of pulse load on a system, current researches are mainly divided into two modes of adopting a hybrid energy storage inhibition mode at a power supply side and adopting charge and discharge of a decoupling capacitor at a direct current side of a converter as a pulse source stabilizing circuit at a load side. The pulse power stabilizing circuit is adopted at the load side to stabilize pulse load impact, so that large high-frequency instantaneous power can be effectively provided for the pulse load, but the method can lead to redundant design of the capacity of the generator, the pulse load has low-frequency impact on the generator, the power supply quality of the system and the stability of the system are affected, and under extreme conditions and when faults occur, the problems of task failure, even system breakdown and the like can be caused.
In the research of stabilizing the pulse load by using the hybrid energy storage, the pulse load is supplied by adopting a combination form of a lithium battery and a super capacitor and a fuel battery-storage battery-super capacitor hybrid energy storage form, and the dynamic characteristics of different energy storage devices are complemented to ensure the power supply requirement of the pulse load. But if any component in the architecture fails or performance declines, this will lead to failure of system tasks and more serious possible aircraft power safety. The requirements of special heat multiple energy less, quick storage and quick release, wide-band range reconstruction and high robustness and high safety of the hypersonic aircraft cannot be met.
Disclosure of Invention
The invention aims to provide a power system of a hypersonic aircraft, which realizes the utilization and storage of heat energy in the flight process of the hypersonic aircraft, thereby improving the energy utilization rate.
In order to achieve the above object, the present invention provides the following solutions:
An electrical power system of a hypersonic aircraft, comprising: the device comprises an oil gas turbine, a first generator, a flywheel energy storage device, a lithium battery and a super capacitor, wherein the flywheel energy storage device comprises a flywheel and a second generator; the output of the oil gas turbine is respectively connected with a first generator and the flywheel, and the flywheel is connected with the second generator;
the oil-gas turbine is used for converting heat energy into mechanical energy at a high Mach stage of the hypersonic aircraft; the flywheel energy storage device is used for charging a lithium battery and a super capacitor;
The lithium battery, the flywheel energy storage device and the super capacitor are used for supplying power to the pulse load in a combined mode when the pulse load is input.
Optionally, the electric power system of the hypersonic aircraft further comprises a fuel cell;
When a lithium battery fails or a super capacitor fails before pulse load is put into operation, controlling the output power frequency bandwidth of the flywheel energy storage device to cover the output frequency range of the failure device, and simultaneously controlling the fuel battery to respond to a key load; the fault device is the lithium battery or the super capacitor;
Optionally, when the first generator fails, a general load is disconnected, a pulse load is not input, and the fuel cell, the flywheel energy storage device and the lithium battery jointly supply power for a key load; the general load is a load other than a critical load in the power system.
When the flywheel energy storage device, the lithium battery and the super capacitor are in failure, the general load is disconnected, the pulse load is not put in, and the first generator and the fuel battery supply power for the key load in a combined mode.
Optionally, the power system of the hypersonic aircraft further comprises a starter generator and a first AC/DC converter, the starter generator being connected to the direct current bus through the first AC/DC converter.
Optionally, the power system of the hypersonic aircraft further comprises a gas turbine engine, wherein the gas turbine engine is connected with the starter generator and is used for providing electric energy in a low Mach stage.
Optionally, the electric power system of the hypersonic aircraft further comprises: a second AC/DC converter, a DC/DC converter, a first bidirectional DC/DC converter, a bidirectional AC/DC converter, and a second bidirectional DC/DC converter;
the first generator is connected to the direct current bus through the second AC/DC converter;
The fuel cell is connected to the direct current bus through the DC/DC converter;
the lithium battery is connected to the direct current bus through the first bidirectional DC/DC converter;
the second generator is connected to the direct current bus through the bidirectional AC/DC converter;
The super capacitor is connected to the direct current bus through the second bidirectional DC/DC converter.
Optionally, the power system of the hypersonic aircraft further comprises a first solid state power controller and a second solid state power controller which are sequentially arranged on the direct current bus, wherein the direct current bus is sequentially divided into a first section, a second section and a third section by the first solid state power controller and the second solid state power controller;
The first solid state power controller is arranged between the output of the second AC/DC converter and the output of the DC/DC converter on the direct current bus;
the second solid-state power controller is arranged between the output of the DC/DC converter and the output of the first bidirectional DC/DC converter on the direct current bus;
the first segment is used to power an electrically active load and a critical load, and the third segment is used to power a pulsed load.
Optionally, when a pulse load is input, the flywheel energy storage device responds to a low-frequency power component of the pulse load, the lithium battery responds to an intermediate-frequency power component of the pulse load, and the super capacitor responds to a high-frequency power component of the pulse load.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
According to the invention, the oil-gas turbine is used for converting heat energy into mechanical energy at the high Mach stage of the hypersonic aircraft, the mechanical energy is stored by the flywheel energy storage device, and the lithium battery and the super capacitor are charged, so that the utilization and storage of the heat energy in the flying process of the hypersonic aircraft are realized, the energy utilization rate is improved, and the flywheel energy storage device is used for replacing corresponding components to supply power for loads when the first generator, the lithium battery and the super capacitor are in failure, so that the framework has high robustness and full-band reconstruction capability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic diagram of an electric power system of a hypersonic aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of power flow of an electric power system under a fault condition according to an embodiment of the present invention;
fig. 3 is a schematic diagram of power flow of an electric power system under a limit condition according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a power system of a hypersonic aircraft, which realizes the utilization and storage of heat energy in the flight process of the hypersonic aircraft, thereby improving the energy utilization rate.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
The invention relates to a power system of a hypersonic aircraft, in particular to a power system framework of a multi-source interconnection-multi-storage sharing power system of a high-speed aircraft carrying a pulse load.
The architecture comprises: the system comprises an oil gas turbine, a first generator, a fuel cell, a flywheel energy storage device, a super capacitor, a lithium battery, a key load, an energy feedback load and a pulse load.
The structure fully utilizes heat energy in the running process of the aircraft, utilizes the oil gas turbine to convert the heat energy into mechanical energy at a high Mach stage with sufficient heat energy, and utilizes the first generator and the flywheel energy storage device to realize power generation and waste heat storage.
The framework can be based on a flywheel energy storage device, and can charge the lithium battery and the super capacitor in the system when power is not supplied by the energy storage component, so that the energy storage device is in a fully charged state before pulse load input is ensured, and further, the reliable power supply of the pulse load is ensured. Meanwhile, the first generator can be prevented from influencing the power supply quality of the steady-state load when the first generator charges energy storage.
The framework utilizes a multi-source interconnection-multi-storage sharing power supply mode, and reliable power supply of loads under fault and limit conditions can be realized. When the lithium battery or the super capacitor fails before the pulse load is put into operation or the heat energy of the system is insufficient to cause the output power of the generator to be reduced, the output frequency bandwidth of the flywheel energy storage device is controlled to cover the output frequency range of the failure device, and meanwhile, the fuel battery is put into operation to respond to the long-time steady-state load, and the power supply requirement of the pulse load can be met through system reconstruction.
The architecture utilizes a power supply form of multi-energy source 'multi-source interconnection-multi-storage sharing', and can realize reliable power supply of loads under limit conditions: when the system has a fault of the first generator and the flywheel energy storage device and a multipoint fault of the system, the common load is cut off, and meanwhile, the fuel cell, the flywheel and the storage battery are combined to supply power for the key load, so that the pulse load is not input.
According to the invention, the combined power supply of the first generator and the fuel cell, the flywheel energy storage device, the lithium battery and the super capacitor and the utilization and storage of heat energy by the first generator and the flywheel energy storage device are considered in the framework, so that the framework has the advantages of high robustness, high efficiency, wide stability margin, full-band reconstruction, high flexibility and high reliable redundancy fault tolerance, and the problem that the existing framework cannot meet the requirements of high-speed aircrafts such as 'heat energy less', 'fast storage and fast release' and wide-band range reconstruction is successfully solved.
The power system of the hypersonic aircraft comprises a power generation system formed by an oil gas turbine, a first generator and a fuel cell, an energy storage system formed by a flywheel energy storage device, a lithium battery and a super capacitor, and further comprises a key load, an energy feedback load (an electric actuation load) and a plurality of load types of pulse loads.
The key load is equipment for guaranteeing the safety of the aircraft, the key load is a preset load, the key load comprises a plurality of loads, and as a specific implementation mode, the key load comprises engine operation control, aircraft manipulation control, fire prevention, navigation, communication, undercarriage retraction and the like. The critical loads need to be powered even in emergency situations, ensuring minimum flight safety.
As shown in fig. 1, an electric power system of a hypersonic aircraft in this embodiment includes: the device comprises an oil gas turbine, a first generator, a flywheel energy storage device, a lithium battery and a super capacitor, wherein the flywheel energy storage device comprises a flywheel and a second generator; the output of the oil gas turbine is respectively connected with a first generator and the flywheel, and the flywheel is connected with the second generator.
The oil-gas turbine is used for converting heat energy into mechanical energy for the first generator to generate electricity in a high Mach stage of the hypersonic aircraft, and simultaneously for the flywheel device to store energy; the flywheel energy storage device is used for charging the lithium battery and the super capacitor. And the heat energy utilization and storage system is based on the oil gas turbine-first generator and the oil gas turbine-flywheel energy storage device. The system fuel generates high-temperature and high-pressure micromolecular gaseous hydrocarbon through the reforming device based on heat energy in the system, drives the oil-gas turbine to drive the first generator to generate electricity through expansion, drives the flywheel to rotate, and can realize the utilization and storage of the heat energy of the system.
The lithium battery, the flywheel energy storage device and the super capacitor are used for supplying power to the pulse load in a combined mode when the pulse load is input.
When a lithium battery fails or a super capacitor fails before pulse load is put into operation, controlling the output power frequency bandwidth of the flywheel energy storage device to cover the output frequency range of the failure device, and simultaneously controlling the fuel battery to respond to a key load; the fault device is the lithium battery or the super capacitor.
The invention uses flywheel energy storage device to store energy and charge lithium battery and super capacitor in the system. The flywheel energy storage device is based on an oil-gas turbine to store heat energy to mechanical energy. Therefore, when the system load power is small, the load is powered by the first generator, and the flywheel energy storage device is always in a charging state. After the energy of the lithium battery and the super capacitor is reduced due to the input of the pulse load or the starting process of the first engine, the lithium battery and the super capacitor can be charged based on the flywheel energy storage device, the preparation can be made for the input of the next pulse load, and the power supply stability of the generator can not be affected.
The power system of the hypersonic aircraft further comprises a fuel cell.
The invention can realize reliable power supply of the load under the system fault condition. As shown in fig. 2, the system faults mainly include when a lithium battery and a super capacitor fail or when the system heat energy is in shortage in the running process of the high-speed aircraft (hypersonic aircraft), and the task requirements can be guaranteed to be realized through the redundant robust design of the system architecture. The system mainly comprises working conditions of failure of a lithium battery or a super capacitor before pulse load input, decline of output power of a first generator caused by insufficient system heat energy and the like, and the output frequency range of a failure device is covered by adjusting the frequency bandwidth of the output power of a flywheel, and meanwhile, the fuel battery is input to respond to long-time steady-state load, so that the power supply requirement of the pulse load can be met through system reconstruction.
The invention can realize reliable power supply of the load under the limit condition of the system. As shown in fig. 3, when the system limit working mode mainly includes that the first generator and flywheel are in fault and the system is in multipoint fault, the critical load can be ensured to be supplied with power without interruption and the aircraft can return safely through the power redundancy fault-tolerant design and load management of the system architecture, and the pulse load does not have the input operation condition. For example, when the first generator fails, a general load is disconnected, a pulse load is not input, and key loads are jointly supplied with power through the fuel cell, the flywheel energy storage device and the lithium battery; the general load is a load other than a critical load in the power system. When the flywheel energy storage device, the lithium battery and the super capacitor are in failure, the general load is disconnected, the pulse load is not input, the first generator and the fuel battery supply power for the key load in a combined mode, and the key load is guaranteed to supply power without interruption and the aircraft is safely returned.
The hypersonic aircraft power system further comprises a starter generator and a first AC/DC converter, wherein the starter generator is connected to the DC bus through the first AC/DC converter.
The hypersonic aircraft power system further comprises a gas turbine engine, wherein the gas turbine engine is connected with the starter generator and is used for providing electric energy in a low Mach stage.
The electric power system of hypersonic aircraft, still include: a second AC/DC converter, a DC/DC converter, a first bidirectional DC/DC converter, a bidirectional AC/DC converter, and a second bidirectional DC/DC converter.
The first generator is connected to the direct current bus through the second AC/DC converter.
The fuel cell is connected to the direct current bus through the DC/DC converter.
The lithium battery is connected to the direct current bus through the first bidirectional DC/DC converter.
The second generator is connected to the direct current bus through the bi-directional AC/DC converter.
The super capacitor is connected to the direct current bus through the second bidirectional DC/DC converter.
The power system of the hypersonic aircraft considers the cooperative power supply of various energy storage, and has various nonlinear high-power and strong impact loads such as pulse loads, energy feedback loads and the like. The power system is characterized in that a sectional bus exists, and a starter generator is independently mounted on one bus to supply power for a key load and an energy feedback load; the first generator is independently mounted on a bus bar and supplies power for the key load and the energy feedback load. The fuel cell is independently mounted on one bus bar, when the output power of the generator is reduced due to the reduction of heat energy in the system, the fuel cell is connected with the generator in parallel to supply power, and when the energy storage output power of the lithium battery or the flywheel is insufficient, the fuel cell is connected with the lithium battery, the flywheel energy storage device and the super capacitor bus bar in parallel to supply power. The flywheel energy storage, the lithium battery and the super capacitor are mounted on a single bus to supply power for the pulse load. The hybrid energy storage bus is isolated from the generator bus, and the power supply quality of the rest bus bars is not affected when pulse loads in the system are input.
The power system of the hypersonic aircraft further comprises a first solid-state power controller and a second solid-state power controller which are sequentially arranged on the direct-current bus, wherein the direct-current bus is sequentially divided into a first section, a second section and a third section by the first solid-state power controller and the second solid-state power controller.
The first solid state power controller is disposed on the DC bus between the output of the second AC/DC converter and the output of the DC/DC converter.
The second solid state power controller is disposed on the DC bus between the output of the DC/DC converter and the output of the first bi-directional DC/DC converter.
Bi DC SSPC, bi DC SSPC_BAT, bi DC SSPC_FW, bi DC SSPC_SC, bi DC SSPC_1 in FIG. 1 are all Bi-directional solid state power controllers, SSPC_GEN1, SSPC_GEN2, DC SSPC_FC, DC SSPC_2 and DC SSPC_3 are all unidirectional solid state power controllers.
The first segment is used to power an electrically active load and a critical load, and the third segment is used to power a pulsed load.
The pulse load is divided into a low frequency power component, an intermediate frequency power component, and a high frequency power component by performing fourier decomposition on the pulse load and dividing the frequency band. The Fourier decomposition result of the pulse load is divided into a low-frequency power component, an intermediate-frequency power component and a high-frequency power component, so that when the pulse load is input, the flywheel energy storage device responds to the low-frequency power component of the pulse load, the lithium battery responds to the intermediate-frequency power component of the pulse load, and the super capacitor responds to the high-frequency power component of the pulse load.
The invention adopts different power supply combination modes according to different flying speeds.
At flying speeds less than 3Ma, critical loads in the system are powered by the starter generator; when the flying speed is greater than 3Ma, the performance of the traditional jet engine is deteriorated due to the outstanding pneumatic heating problem of the airplane, the temperature before the turbine breaks through the material limit, and the gas turbine engine cannot continue to work, so that the oil gas turbine and the first generator are adopted to supply power for key loads in the system, and at the moment, the fuel of the system is based on heat energy in the system, and small-molecular gaseous hydrocarbon with high temperature and high pressure is generated through cracking reaction to act on the oil gas turbine. The oil gas turbine provides mechanical energy for the first generator and the flywheel and drives the first generator and the second generator to output electric energy respectively. The back end of the first generator is connected with a second AC/DC converter, and the alternating current output by the first generator is rectified into direct current to supply power for the system. The rear end of the second generator is connected with a bidirectional AC/DC converter, when the flywheel energy storage device (flywheel and the second generator) is in an output power state, the bidirectional converter is in an AC/DC working mode, and the alternating current output by the first generator is rectified into direct current to supply power for the system; when the flywheel energy storage device (flywheel and second generator) is in a power absorption state, the bidirectional converter is in a DC/AC working mode, and converts electric energy in the system into mechanical energy to be stored by the flywheel; when the heat energy in the system is sufficient and the system load does not need the flywheel energy storage device to supply power, the mechanical energy generated by the oil gas turbine can be directly stored in the flywheel. The fuel cell in the framework can utilize hydrogen generated by catalytic reforming to generate electricity as an auxiliary power supply in the system. The pulsed load in the system is represented by the hybrid energy storage system in the system: the lithium battery, the flywheel energy storage device and the super capacitor are used for supplying power, so that the instantaneous high-power requirement of the pulse load is ensured.
The working modes of the electric power system comprise a pre-task preparation stage, a driving-in and taking-off and turbine power climbing stage, a combined power climbing and jet precooling stage, a mode conversion stage, a punching power climbing stage, a cruising stage, a pulse load input stage, a cruising return stage, an unpowered deceleration sliding down stage, a punching air turbine exiting operation stage and a turbine engine air restarting and powered return landing stage; the flight Mach number of the entering and taking-off stage and the turbine power climbing stage is smaller than 3, and the flight Mach number of the combined power climbing and jet precooling stage is larger than or equal to 3.
And in the pre-task preparation stage, the lithium battery is adopted to supply power for the starting generator, and the starting generator supplies power for loads of the power system.
And in the driving-in and taking-off and turbine power climbing stages, the gas turbine engine is adopted to supply power for the starter generator, namely the gas turbine engine consumes fuel oil to drive the output power of the starter generator, and the starter generator supplies power for the load of the power system. Although the lithium battery consumes energy in the starting and generating stage, the stage generator cannot charge energy storage because of high engine load in the take-off and climbing stages; and the electrical load demand is large in the climbing stage, so that the system has no power redundancy.
In the combined power climbing and jet precooling stage, although the lithium battery consumes energy in the starting and generating stage, the engine load is large in the takeoff and climbing stage, so that the stage generator cannot charge energy storage; and the electric load demand is large in the climbing stage, so that the system has no power redundancy, and the combination of the starting generator and the first generator is adopted to supply power for the load of the electric power system so as to meet the power demand of the aircraft combined power climbing stage.
In the mode conversion stage, load power is jointly supplied by a starter generator and a first generator to supply power to a load in a combined mode, but the power gap of the system is caused to be the power gap, so that the power gap is complemented by a fuel cell, and the starter generator, the first generator and the fuel cell are jointly used for supplying power to the load of the power system in the mode conversion stage.
And in the step of stamping power climbing, after the mode switching is completed, the gas turbine engine exits the system, the starting generator stops working, and the first generator is adopted to supply power for the load of the power system. There is no power redundancy at this stage and therefore no conditions for charging lithium batteries are provided.
In the cruising stage, the flying speed is increased sufficiently with heat energy, and the load power is reduced compared with the climbing stage, so that the first generator is adopted to charge the lithium battery, and preparation is made for pulse load input.
In the pulse load input stage, when the pulse load is put into operation, the first generator is adopted to supply power for the key load, and the flywheel energy storage device, the lithium battery and the super capacitor are adopted to jointly supply power for the pulse load, so that the instantaneous high-power requirement of the pulse load is ensured. The flywheel energy storage device (flywheel and second generator) responds to the impulse load low-frequency power component, the lithium battery responds to the impulse load medium-frequency power component and the super capacitor responds to the impulse load high-frequency power component.
In the cruising return stage, the lithium battery consumes energy in the pulse load input stage, and in order to ensure that the follow-up task is reliably completed, a first generator or the flywheel energy storage device is adopted to charge the lithium battery.
In the unpowered deceleration downslide stage, the output power of the first generator is gradually reduced along with the gradual reduction of the flying speed; and the first generator, the fuel cell, the flywheel energy storage device and the lithium battery are combined to supply power for the load of the power system, so that the key load power requirement is met.
And in the stage that the ram air turbine exits from the operation, the load is powered by a fuel cell as a main power supply, the fuel cell is adopted to power the load of the power system, and further, whether the parallel lithium battery, the flywheel energy storage device and the fuel cell are required to cooperatively power is determined by considering the SOC of the lithium battery and the flywheel energy storage device.
And restarting the gas turbine engine in an air restarting and powered return-to-ground landing stage of the turbine engine, and powering loads of the power system by adopting the starting generator to provide power for the loads in the powered return-to-ground and landing stage.
The beneficial effects of the invention are as follows:
By introducing the oil gas turbine-first generator and the oil gas turbine-flywheel energy storage device into the system, the utilization and storage of heat energy in the flight process of the high-speed aircraft are realized, and the problem of insufficient energy during high-speed operation of the aircraft can be solved.
Compared with the prior art, the flywheel energy storage device is used for charging the rest energy storage in the system architecture. The flywheel energy storage device realizes energy storage based on conversion of heat energy and mechanical energy, so that a generator is not required to charge the flywheel energy storage device, and meanwhile, the flywheel energy storage device can charge the rest energy storage in the system, so that the power supply quality of steady-state loads in the system is ensured.
Compared with the prior art, the invention uses flywheel energy storage, fuel cell, lithium cell and super capacitor to jointly supply power in the system architecture. Because the flywheel energy storage device has a wide output power frequency band, and the output power range of the flywheel energy storage device is adjustable, when the lithium battery or the super capacitor breaks down before the pulse load is put into operation and the system heat energy is insufficient to cause the output power of the generator to be reduced, the flywheel can be adjusted to adjust the frequency band of the output power of the second generator so as to cover the output frequency range of the fault device, and meanwhile, the fuel battery is put into the fuel battery to respond to the long-term steady-state load, and the power supply requirement of the pulse load can be met through the system reconstruction. When the first generator fails, the general load is cut off, the fuel cell-flywheel energy storage device-lithium battery combined power supply is used for supplying power to the key load, and the pulse load is not input. When the flywheel energy storage device, the lithium battery and the super capacitor are simultaneously disabled, the pulse load is not input at the moment, and the first generator and the fuel cell are combined to ensure that the key load does not interrupt power supply and the aircraft safely returns. The architecture has the advantages of high robustness, high efficiency, wide stability margin, full-band reconstruction, high flexibility and high reliable redundancy fault tolerance, and successfully solves the problem that the existing architecture can not meet the requirements of high-speed aircrafts such as 'heat multiple energy less', 'fast storage and fast release' and wide-band range reconstruction.
The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. An electrical power system for a hypersonic aircraft, comprising: the device comprises an oil gas turbine, a first generator, a flywheel energy storage device, a lithium battery and a super capacitor, wherein the flywheel energy storage device comprises a flywheel and a second generator; the output of the oil gas turbine is respectively connected with a first generator and the flywheel, and the flywheel is connected with the second generator;
The oil-gas turbine is used for converting heat energy into mechanical energy in a high Mach stage of the hypersonic aircraft, and the mechanical energy is used for the first generator to generate electricity and simultaneously used for the flywheel device to store energy; the flywheel energy storage device is used for charging a lithium battery and a super capacitor;
The lithium battery, the flywheel energy storage device and the super capacitor are used for supplying power to the pulse load in a combined mode when the pulse load is input.
2. The hypersonic aircraft electrical power system of claim 1 further comprising a fuel cell;
When a lithium battery fails or a super capacitor fails before pulse load is put into operation, controlling the output power frequency bandwidth of the flywheel energy storage device to cover the output frequency range of the failure device, and simultaneously controlling the fuel battery to respond to a key load; the fault device is the lithium battery or the super capacitor.
3. The hypersonic aircraft power system of claim 2 wherein when a first generator fails, a normal load is disconnected, a pulsed load is not put in, the fuel cell, flywheel energy storage device and lithium battery jointly power critical loads; the general load is a load other than a critical load in the power system;
When the flywheel energy storage device, the lithium battery and the super capacitor are in failure, the general load is disconnected, the pulse load is not put in, and the first generator and the fuel battery supply power for the key load in a combined mode.
4. The hypersonic aircraft power system of claim 2 further comprising a starter generator and a first AC/DC converter, the starter generator being connected to a direct current bus through the first AC/DC converter.
5. The hypersonic aircraft electrical power system of claim 4 further comprising a gas turbine engine connected to the starter generator, the gas turbine engine for providing electrical energy at a low mach stage.
6. The hypersonic aircraft electrical power system of claim 5 further comprising: a second AC/DC converter, a DC/DC converter, a first bidirectional DC/DC converter, a bidirectional AC/DC converter, and a second bidirectional DC/DC converter;
the first generator is connected to the direct current bus through the second AC/DC converter;
The fuel cell is connected to the direct current bus through the DC/DC converter;
the lithium battery is connected to the direct current bus through the first bidirectional DC/DC converter;
the second generator is connected to the direct current bus through the bidirectional AC/DC converter;
The super capacitor is connected to the direct current bus through the second bidirectional DC/DC converter.
7. The hypersonic aircraft power system of claim 6 further comprising a first solid state power controller and a second solid state power controller disposed in sequence on the dc bus, the dc bus being divided into a first segment, a second segment, and a third segment in sequence by the first solid state power controller and the second solid state power controller;
The first solid state power controller is arranged between the output of the second AC/DC converter and the output of the DC/DC converter on the direct current bus;
the second solid-state power controller is arranged between the output of the DC/DC converter and the output of the first bidirectional DC/DC converter on the direct current bus;
the first segment is used to power an electrically active load and a critical load, and the third segment is used to power a pulsed load.
8. The hypersonic aircraft power system of claim 1 wherein the flywheel energy storage device is responsive to a low frequency power component of the pulsed load, the lithium battery is responsive to a medium frequency power component of the pulsed load, and the supercapacitor is responsive to a high frequency power component of the pulsed load when the pulsed load is thrown.
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| CN202410744104.7A CN118739542A (en) | 2024-06-11 | 2024-06-11 | Electric power system of hypersonic aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410744104.7A CN118739542A (en) | 2024-06-11 | 2024-06-11 | Electric power system of hypersonic aircraft |
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