CN118323458A - Aircraft energy control method and system - Google Patents

Abstract

The invention relates to the technical field of aircraft energy management, in particular to an aircraft energy control method and system. The method comprises the following steps: step S11, based on the fact that the aircraft is in a working state and the electric load of the aircraft energy control system fluctuates, the electric load of the aircraft energy control system is obtained. And step S12, based on the fact that the electric load is increased to the first set threshold value and the first load unit is operated, the energy storage component is controlled to increase the electric energy supplied to the load component, and the electric energy supplied by the energy component and the electric energy supplied by the engine component are kept unchanged. And step S13, controlling the energy storage component to stop supplying electric energy to the load component based on the fact that the electric load is increased to the second set threshold value and the first load unit is operated, and enabling the energy source component to increase the electric energy supplied to the load component, wherein the electric energy supplied by the engine component is kept unchanged. Thus, the problem of how to efficiently distribute the energy of the aircraft is solved.

Description

Aircraft energy control method and system

Technical Field

The invention relates to the technical field of aircraft energy management, in particular to an aircraft energy control method.

Background

The energy control system of the aircraft is a system generic term for executing flight guarantee functions on the aircraft, and comprises subsystems such as hydraulic, environment control, fuel oil, electric power, auxiliary power and the like, wherein the advancement of the energy control system directly influences the overall performance of the aircraft. The power requirement and the heat dissipation requirement of the future aircraft platform are greatly improved, and new energy management requirements are provided for the aircraft energy control system.

The existing aircraft energy control system adopts independent hydraulic, environmental control, fuel oil, auxiliary power and other systems, each system independently performs energy utilization and heat management, the electric energy source of each electric equipment is a main engine, and when a plurality of equipment is started simultaneously, the burden of the main engine is overlarge, the performance and the service life of the main engine are influenced, and even the electricity utilization requirement of high-power electric equipment cannot be met. And the system lacks autonomous adaptability to operating mode changes. The energy sources and the thermal management methods of the devices in different operation modes are fixed, no adaptive change is made according to the characteristics of the different modes, the energy efficiency of the system is low to be further optimized.

Disclosure of Invention

The invention provides an aircraft energy control method and system for solving the problem of how to efficiently distribute aircraft energy.

In a first aspect, the present invention provides an aircraft energy control method comprising:

Step S11, acquiring the electric load of an aircraft energy control system based on the fact that the aircraft is in a working state and the electric load of the aircraft energy control system fluctuates;

step S12, based on the fact that the electric load is increased to a first set threshold value and the first load unit is operated, the energy storage component is controlled to increase the electric energy supplied to the load component, and the electric energy supplied by the energy component and the electric energy supplied by the engine component are kept unchanged; wherein the aircraft energy control system comprises the energy storage assembly, the energy source assembly, the engine assembly and the load assembly; the energy storage component is electrically connected with the energy source component; the engine assembly is electrically connected with the energy storage assembly; the engine assembly is electrically connected with the energy source assembly; the load assembly includes the first load unit; the first load unit is electrically connected with the energy source assembly, the energy storage assembly and the engine assembly respectively;

Step S13, based on the fact that the electric load is increased to a second set threshold value and the first load unit is operated, the energy storage component is controlled to stop supplying electric energy to the load component, the energy source component increases the electric energy supplied to the load component, and the electric energy supplied by the engine component is kept unchanged; wherein the second set threshold is greater than the first set threshold.

In some embodiments, the aircraft energy control method further comprises:

Controlling the energy storage component and the energy source component to jointly supply electric energy to the load component based on the fact that the electric load is increased to a third set threshold value and the first load unit is operated, wherein the electric energy supplied by the engine component to the load component is kept unchanged; wherein the third set threshold is greater than the second set threshold.

In some embodiments, the aircraft energy control method further comprises:

Based on the electric load increasing to a fourth set threshold value and the second load unit operating, controlling the energy storage component to increase the electric energy supplied to the load component to the maximum output power, wherein the electric energy supplied by the energy source component and the electric energy supplied by the engine component are kept unchanged; wherein the fourth set threshold is greater than the third set threshold; the load assembly further includes the second load unit; the second load unit is electrically connected with the energy storage component, the energy source component and the engine component respectively.

In some embodiments, the aircraft energy control method comprises:

Based on the electrical load increasing to a fourth set threshold and the energy storage assembly increasing to a maximum output power for electrical energy supplied to the load assembly, the cooling turbine of the energy assembly increasing an amount of cooling gas supplied to the energy storage assembly, the second load unit, reducing an amount of cooling gas supplied to the first load unit; the energy source assembly comprises the cooling turbine, a starting generator, a gas compressor and a heat exchanger; the cooling turbine, the starting generator and the compressor are coaxially connected; the compressor is communicated with the cooling turbine through the heat exchanger; the energy storage assembly is communicated with the cooling turbine; the first load unit is in communication with the cooling turbine; the second load unit is in communication with the cooling turbine.

In some embodiments, the aircraft energy control method further comprises:

Acquiring a temperature of an actuating portion of the second load unit based on the electric load increasing to a fourth set threshold; wherein the second load unit comprises the actuating part, a heat storage part and a heat dissipation part; the actuating part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the actuating part and the heat storage part conduct heat transfer; the heat dissipation part and the heat storage part conduct heat transfer; the heat dissipation part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the heat dissipation part is communicated with the cooling turbine;

Based on the temperature of the actuating part reaching a first temperature threshold, the heat storage part exchanges heat with the actuating part;

the cooling turbine supplies cooling gas to the heat dissipation portion, which cools the heat storage portion, based on the temperature of the heat storage portion reaching a second temperature threshold.

In some embodiments, the aircraft energy control method comprises:

Acquiring an electric quantity state of the energy storage component based on the fact that the aircraft is in a working state;

Controlling the energy source assembly to increase the electric energy supplied to the energy storage assembly based on the state of charge of the energy storage assembly being less than a first electric quantity threshold;

Acquiring the output electric energy of the engine assembly and the actual use electric energy of the load assembly based on the electric quantity state of the energy storage assembly being greater than the first electric quantity threshold and less than the second electric quantity threshold;

And controlling the engine assembly to supply the residual electric energy to the energy storage assembly based on the fact that the output electric energy of the engine assembly is larger than the actual use electric energy of the load assembly, wherein the electric energy supplied by the energy storage assembly by the energy source assembly is kept unchanged.

In some embodiments, the aircraft energy control method further comprises:

acquiring output electric energy of the engine assembly and actual use electric energy of the load assembly based on the electric quantity state of the energy storage assembly being greater than the second electric quantity threshold;

and controlling the engine assembly to supply the remaining electric energy to the energy storage assembly based on the fact that the output electric energy of the engine assembly is larger than the actual use electric energy of the load assembly, and stopping the electric energy supply to the energy storage assembly by the energy source assembly.

In some embodiments, the aircraft energy control method comprises:

acquiring the flying height of the aircraft based on the aircraft being in a working state;

Acquiring output electric energy of the engine assembly and output electric energy of the energy assembly based on the flying height within a height set threshold range; wherein the energy source assembly further comprises a combustion chamber and a power turbine; the load assembly further includes an oil supply unit; the power turbine is coaxially connected with the compressor; the compressor is communicated with the combustion chamber; the combustion chamber is in communication with the power turbine; the engine assembly is in communication with the combustion chamber; the oil supply unit is respectively communicated with the combustion chamber and the engine assembly; the oil supply unit is respectively and electrically connected with the energy storage component, the starting generator and the engine component;

And controlling the engine assembly to reduce the amount of gas supplied to the combustion chamber based on the sum of the output electric energy of the engine assembly and the output electric energy of the energy assembly is smaller than an output set threshold value and the engine assembly supplies gas to the combustion chamber, wherein the oil supply unit increases the amount of fuel supplied to the combustion chamber and the engine assembly, and the energy storage assembly increases the electric energy supplied to the load assembly.

In a second aspect, the present invention provides an aircraft energy control system, the aircraft energy control system being applied to the aircraft energy control method of any one of the first aspects,

The aircraft energy control system includes:

An energy source assembly for supplying electrical energy and a cooling gas;

the energy storage component is electrically connected with the energy source component;

A load assembly including a first load cell; the first load unit is electrically connected with the energy source component; the first load unit is electrically connected with the energy storage component;

An engine assembly electrically connected with the energy assembly; the engine assembly is electrically connected with the energy storage assembly; the engine assembly is electrically connected with the first load unit.

In some embodiments, the energy source assembly comprises a cooling turbine, a starter generator, a compressor, a heat exchanger, a power turbine, a combustor; the cooling turbine, the starting generator, the compressor and the power turbine are coaxially connected; the compressor is communicated with the cooling turbine through the heat exchanger; the compressor is communicated with the combustion chamber; the combustion chamber is in communication with the power turbine; the combustion chamber is in communication with the engine assembly; the energy storage assembly is communicated with the cooling turbine; the first load unit is in communication with the cooling turbine; the starting generator is electrically connected with the first load unit; the power generator is electrically connected with the energy storage component; the starter generator is electrically connected with the engine assembly;

The load assembly further comprises a second load unit and an oil supply unit; the second load unit comprises an actuating part, a heat storage part and a heat dissipation part; the actuating part and the heat storage part conduct heat transfer; the heat dissipation part and the heat storage part conduct heat transfer; the heat dissipation part is communicated with the cooling turbine; the actuating part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the heat dissipation part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the oil supply unit is respectively communicated with the combustion chamber and the engine assembly; the oil supply unit is electrically connected with the energy storage component, the starting generator and the engine component respectively.

In order to solve the problem of how to efficiently distribute the energy of the aircraft, the invention has the following advantages:

When the aircraft is in a working state and the electric load of the aircraft energy control system fluctuates, the judgment can be performed by acquiring the electric load of the aircraft energy control system so as to distribute energy subsequently. The electrical load may comprise an operating power of a load assembly, which may comprise the first load unit. If the first load unit is in an operating state and the electric load is increased to a first set threshold value, the electric energy supplied by the energy storage component to the load component can be increased, and the electric energy supplied by the energy source component and the electric energy supplied by the engine component are controlled to be unchanged. If the first load unit is in an operating state and the electrical load increases to a second set threshold, the energy storage assembly can be stopped from supplying electrical energy to the load assembly, and the energy source assembly can be increased to supply electrical energy to the load assembly, so that the electrical energy supplied by the engine assembly is controlled to be unchanged. The influence of electric load fluctuation on the engine assembly can be reduced, so that the output power of the engine assembly is maintained in a small fluctuation range as long as possible, the engine assembly is in a high-efficiency working state, the energy efficiency of the aircraft energy control system is improved, and the high-efficiency distribution of the aircraft energy is realized.

Drawings

FIG. 1 illustrates a schematic diagram of an aircraft energy control method of an embodiment;

FIG. 2 illustrates a schematic diagram of an aircraft energy control system of an embodiment.

Reference numerals: 01 an energy source assembly; 11, starting a generator; a 12-compressor; 13 a combustion chamber; a 14 power turbine; 15 heat exchangers; 16 cooling the turbine; 02 load assembly; a first load unit 21; 22a second load unit; 221 actuation part; 222 heat storage parts; 223 heat dissipation part; 26 an oil supply unit; 03 an energy storage assembly; 04 engine assembly.

Detailed Description

The disclosure will now be discussed with reference to several exemplary embodiments. It should be understood that these embodiments are discussed only to enable those of ordinary skill in the art to better understand and thus practice the present disclosure, and are not meant to imply any limitation on the scope of the present disclosure.

As used herein, the term "comprising" and variants thereof are to be interpreted as meaning "including but not limited to" open-ended terms. The term "based on" is to be interpreted as "based at least in part on". The terms "one embodiment" and "an embodiment" are to be interpreted as "at least one embodiment. The term "another embodiment" is to be interpreted as "at least one other embodiment". The terms "upper", "lower", "left", "right", "front", "rear", "top", "bottom", "inner", "outer", "vertical", "horizontal", "transverse", "longitudinal", etc. refer to an orientation or positional relationship based on that shown in the drawings. These terms are only used to better describe the present application and its embodiments and are not intended to limit the scope of the indicated devices, elements or components to the particular orientations or to configure and operate in the particular orientations. Also, some of the terms described above may be used to indicate other meanings in addition to orientation or positional relationships, for example, the term "upper" may also be used to indicate some sort of attachment or connection in some cases. The specific meaning of these terms in the present application will be understood by those of ordinary skill in the art according to the specific circumstances. Furthermore, the terms "mounted," "configured," "provided," "connected," and "connected" are to be construed broadly. For example, it may be a fixed connection, a removable connection, or a unitary construction; may be a mechanical connection, or an electrical connection; may be directly connected, or indirectly connected through intervening media, or may be in internal communication between two devices, elements, or components. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances. Furthermore, the terms "first," "second," and the like, are used primarily to distinguish between different devices, elements, or components (the particular species and configurations may be the same or different), and are not used to indicate or imply the relative importance and number of devices, elements, or components indicated. Unless otherwise indicated, the meaning of "a plurality" is two or more.

The embodiment discloses an aircraft energy control method, as shown in fig. 1, which may include:

Step S11, acquiring the electric load of the aircraft energy control system based on the fact that the aircraft is in a working state and the electric load of the aircraft energy control system fluctuates;

step S12, controlling the energy storage component 03 to increase the electric energy supplied to the load component 02 based on the electric load increasing to the first set threshold value and the first load unit 21 operating, wherein the electric energy supplied by the energy component 01 and the electric energy supplied by the engine component 04 are kept unchanged; the aircraft energy control system comprises an energy storage component 03, an energy source component 01, an engine component 04 and a load component 02; the energy storage component 03 is electrically connected with the energy source component 01; the engine assembly 04 is electrically connected with the energy storage assembly 03; the engine assembly 04 is electrically connected with the energy source assembly 01; the load assembly 02 includes a first load unit 21; the first load unit 21 is electrically connected with the energy source assembly 01, the energy storage assembly 03 and the engine assembly 04 respectively;

Step S13, controlling the energy storage assembly 03 to stop supplying the electric energy to the load assembly 02 based on the electric load increasing to the second set threshold value and the first load unit 21 operating, the energy source assembly 01 increasing the electric energy supplied to the load assembly 02, the electric energy supplied by the engine assembly 04 remaining unchanged; wherein the second set threshold is greater than the first set threshold.

In this embodiment, at present, the aircraft generally adopts independent hydraulic, environmental control, fuel oil, auxiliary power and other systems to ensure stable flight of the aircraft, each system independently performs energy utilization and thermal management, and each electric energy source of electric equipment is the engine component 04, so that when a plurality of devices are started simultaneously, the load of the engine component 04 is excessive, and the performance and the service life of the engine component 04 are affected. And the system lacks autonomous adaptability to the change of the operation mode, and the energy efficiency of the system is low. The invention provides an aircraft energy control method for solving the problem of how to efficiently distribute the aircraft energy. As shown in fig. 1, the aircraft energy control method may include steps S11 to S13, which will be described in detail below.

In step S11, when the aircraft enters the working state, the aircraft energy control system is generally required to provide electric energy, and in the execution task state or emergency, more electric energy needs to be provided to maintain the electricity demand, so that the electric load of the aircraft energy control system is easy to fluctuate, and at this time, the electric load of the aircraft energy control system can be obtained to perform subsequent judgment so as to manage the energy distribution problem. The electrical load may comprise the operating power of the load assembly 02, and the load assembly 02 may comprise the first load unit 21.

In step S12, if it is detected that the electric load increases to the first set threshold (for example, may be greater than 1 times of the normal operating power of the set load assembly 02 and less than or equal to 1.1 times of the normal operating power of the set load assembly 02), and the first load unit 21 is in the operating state, the range of the electric load increase is smaller, and the electric energy stored in the energy storage assembly 03 is sufficient to meet the electric power demand at that time. Therefore, the energy storage component 03 can be controlled to increase the electric energy supplied to the load component 02, and the electric energy supplied to the load component 02 by the energy source component 01 and the electric energy supplied to the load component 02 by the engine component 04 are controlled to be unchanged. Thus, the power demand of the high-power electric equipment is met by controlling the energy storage component 03 to increase the electric energy supplied to the load component 02, the output power of the engine component 04 can be maintained in a small fluctuation range for a long time, the fuel consumption can be reduced, the service life of the engine component 04 is prolonged, the engine component 04 can maintain a good performance level, and meanwhile, the energy efficiency of the whole aircraft energy control system can be improved. The aircraft energy control system may include, among other things, an energy storage assembly 03, an energy source assembly 01, an engine assembly 04, and a load assembly 02. The energy storage component 03 can be electrically connected with the energy source component 01, current can be transmitted between the energy storage component 03 and the energy source component 01, and the energy source component 01 can supply electric energy for the energy storage component 03. The engine assembly 04 may be electrically connected to the energy storage assembly 03, and the engine assembly 04 may supply and store electrical energy to the energy storage assembly 03. The engine assembly 04 may be electrically connected to the energy source assembly 01, and the engine assembly 04 may supply electrical energy to the energy source assembly 01. The load assembly 02 may include a first load unit 21, and the first load unit 21 may be electrically connected to the energy source assembly 01, the energy storage assembly 03, and the engine assembly 04, respectively, such that the energy source assembly 01, the energy storage assembly 03, and the engine assembly 04 power the first load unit 21.

In step S13, if the electrical load increases to a second set threshold (for example, may be greater than 1.1 times and less than or equal to 1.3 times the set normal operation power of the load assembly 02) and the first load unit 21 is in an operating state at this time, the second set threshold may be greater than the first set threshold. At this time, the energy storage module 03 may be controlled to stop supplying the electric power to the load module 02, the energy source module 01 increases the electric power supplied to the load module 02, and the electric power supplied from the engine module 04 remains unchanged. Because the power consumption demand is big at this moment, the direct increase energy source module 01 can satisfy the great power consumption demand of load module 02 to the electric energy that load module 02 supplied with, can make energy storage module 03 give energy source module 01 and engine module 04 energy supply time long moreover to improve aircraft energy control system energy utilization efficiency, engine module 04 output can maintain in a little fluctuation range for a long time, thereby realize the high-efficient distribution aircraft energy.

In some embodiments, the aircraft energy control method further comprises:

Based on the electric load increasing to the third set threshold value and the first load unit 21 operating, controlling the energy storage component 03 and the energy source component 01 to jointly supply electric energy to the load component 02, wherein the electric energy supplied by the load component 02 by the engine component 04 is kept unchanged; wherein the third set threshold is greater than the second set threshold.

In this embodiment, the aircraft energy control method may further include: when the first load unit 21 is in an operation state and the electric load increases to a third set threshold (for example, may be greater than 1.3 times of the normal operation power of the set load assembly 02 and less than or equal to 1.5 times of the normal operation power of the set load assembly 02), the third set threshold may be greater than the second set threshold, and at this time, the energy storage assembly 03 and the energy source assembly 01 may be made to supply electric energy to the load assembly 02 together, for example, the energy storage assembly 03 and the energy source assembly 01 may be controlled to supply electric energy unchanged when the amount of increase in the electric load is small, and when the amount of increase in the electric load is large, the electric energy supplied to the load assembly 02 by the energy storage assembly 03 and the energy source assembly 01 may be increased. The power supplied by the engine assembly 04 to the load assembly 02 is controlled to remain unchanged. In this way, the energy utilization efficiency of the energy control system of the aircraft can be improved, and the output power of the engine assembly 04 can be maintained in a small fluctuation range for a long time, so that the efficient distribution of the energy of the aircraft is realized.

In other embodiments, when the energy storage component 03 has no electricity, the electric energy supplied by the energy source component 01 and the engine component 04 to the load component 02 can be increased to meet the electricity demand, so that the overall energy utilization efficiency is improved, and the stable and reliable operation of the system is ensured.

In some embodiments, the aircraft energy control method further comprises:

based on the electric load increasing to the fourth set threshold value and the second load unit 22 operating, the energy storage component 03 is controlled to increase the electric energy supplied to the load component 02 to the maximum output power, and the electric energy supplied by the energy component 01 and the electric energy supplied by the engine component 04 are kept unchanged; wherein the fourth set threshold is greater than the third set threshold; the load assembly 02 further comprises a second load unit 22; the second load unit 22 is electrically connected to the energy storage module 03, the energy source module 01, and the engine module 04, respectively.

In this embodiment, the aircraft energy control method may further include:

the load assembly 02 may further include a second load unit 22, where the second load unit 22 may be some electric equipment such as radars, weapons, etc., and generally generates instantaneous high power, and the second load unit 22 may be electrically connected to the energy storage assembly 03, the energy source assembly 01, and the engine assembly 04, respectively. The fourth set threshold may be greater than the third set threshold, and when the electric load increases to the fourth set threshold (for example, may be greater than 1.5 times the set normal operating power of the load assembly 02) and the second load unit 22 is in the operating state, since the increase of the electric load is instantaneous at this time, the electric energy supplied to the load assembly 02 by the energy storage assembly 03 may be controlled to increase to the maximum output power, and the electric energy supplied to the energy source assembly 01 and the engine assembly 04 may be kept unchanged. Therefore, the power consumption requirement can be met, and the output power of the engine assembly 04 can be kept in a small fluctuation range, so that the influence on the engine assembly 04 is reduced, the stable operation of the engine assembly 04 is maintained, and the normal flight of the aircraft is ensured.

In other embodiments, when the electric load decreases, the electric energy supplied by the energy source assembly 01 to the load assembly 02 may be kept unchanged, the remaining electric power is preferentially supplied to the energy storage assembly 03 to be charged, if the energy storage assembly 03 is charged, the output electric power of the energy source assembly 01 may be preferentially reduced, and if the output electric power of the energy source assembly 01 decreases to zero, the output electric power of the engine assembly 04 is reduced. By the method, the influence of electric load fluctuation on the engine assembly 04 can be reduced, so that the engine assembly 04 is maintained in a high-efficiency working range as long as possible, and the energy efficiency of the aircraft energy control system is improved.

In some embodiments, as shown in fig. 2, the aircraft energy control method includes:

Based on the electric load increasing to the fourth set threshold and the electric energy supplied to the load assembly 02 by the energy storage assembly 03 increasing to the maximum output power, the cooling turbine 16 of the energy assembly 01 increases the amount of cooling gas output supplied to the energy storage assembly 03, the second load unit 22, and decreases the amount of cooling gas output supplied to the first load unit 21; wherein, the energy source assembly 01 comprises a cooling turbine 16, a starting generator 11, a gas compressor 12 and a heat exchanger 15; the cooling turbine 16, the starting generator 11 and the compressor 12 are coaxially connected; the compressor 12 is communicated with a cooling turbine 16 through a heat exchanger 15; the energy storage assembly 03 is in communication with the cooling turbine 16; the first load unit 21 communicates with the cooling turbine 16; the second load unit 22 communicates with the cooling turbine 16.

In this embodiment, as shown in fig. 2, the energy source assembly 01 may include a cooling turbine 16, a starter generator 11, a compressor 12, and a heat exchanger 15. The cooling turbine 16, the starter generator 11, and the compressor 12 may be coaxially connected. The coaxial connection reduces the space occupation of the interior, making the overall structure more compact. This compact structure helps reduce the overall size and weight of the aircraft, thereby increasing its maneuverability and efficiency. Since these components share a single rotational axis, energy losses are reduced. This design may increase the energy efficiency of the overall system. The compressor 12 may be in communication with the cooling turbine 16 via a heat exchanger 15, and the gas output by the compressor 12 directly enters the cooling turbine 16, and the cooling turbine 16 rotates by the energy of the gas, while reducing the temperature and pressure of the gas. This energy conversion process enables the cooling turbine 16 to produce power or electrical energy. The energy storage assembly 03 may be in communication with the cooling turbine 16 for storing electrical energy generated by the cooling turbine 16. The first load unit 21 may be in communication with the cooling turbine 16; the second load unit 22 may be in communication with the cooling turbine 16. And the cooling gas is output for heat dissipation. The aircraft energy control method may include:

when the electric load increases to the fourth set threshold and the electric energy supplied by the energy storage component 03 to the load component 02 increases to the maximum output power, a large amount of heat is generated by the energy storage component 03 and the second load unit 22, so that the cooling turbine 16 of the energy source component 01 can be controlled to increase the output of the cooling gas supplied to the energy storage component 03 and the second load unit 22 and reduce the output of the cooling gas supplied to the first load unit 21 in order to maintain the performance of the energy storage component 03 and prolong the service life of the second load unit 22. Facilitating rapid heat dissipation from the energy storage assembly 03 and the second load unit 22.

In some embodiments, as shown in fig. 2, the aircraft energy control method further comprises:

Acquiring a temperature of the operating portion 221 of the second load unit 22 based on the electric load increasing to the fourth set threshold; the second load unit 22 includes an operation portion 221, a heat storage portion 222, and a heat dissipation portion 223; the actuating part 221 is electrically connected with the energy storage component 03, the starting generator 11 and the engine component 04 respectively; the operation portion 221 and the heat storage portion 222 perform heat transfer; the heat radiating portion 223 and the heat storage portion 222 perform heat transfer; the heat dissipation part 223 is electrically connected with the energy storage component 03, the generator 11 and the engine component 04 respectively; the heat dissipation portion 223 communicates with the cooling turbine 16;

Based on the temperature of the operation portion 221 reaching the first temperature threshold, the heat storage portion 222 exchanges heat with the operation portion 221;

Based on the temperature of the heat storage portion 222 reaching the second temperature threshold, the cooling turbine 16 supplies cooling gas to the heat dissipation portion 223, and the heat dissipation portion 223 cools the heat storage portion 222.

In the present embodiment, as shown in fig. 2, the second load unit 22 may include an operation portion 221, a heat storage portion 222, and a heat dissipation portion 223. The actuating portion 221 may be electrically connected to the energy storage assembly 03, the generator 11, and the engine assembly 04, respectively, so as to obtain electrical energy. The actuating part 221 can transfer heat with the heat storage part 222, so that heat generated in the operation process of the actuating part 221 can be conveniently dissipated in time, the performance is maintained, and the service life is prolonged. The heat dissipation portion 223 may transfer heat to the heat storage portion 222, dissipate the heat stored in the heat storage portion 222, and the heat dissipation portion 223 may be electrically connected to the energy storage module 03, the generator 11, and the engine module 04, respectively. The heat sink 223 may be in communication with the cooling turbine 16. The cooling turbine 16 is facilitated to provide a cooling gas for cooling. The aircraft energy control method may further include:

When the electric load increases to the fourth set threshold value, the temperature of the operating portion 221 of the second load unit 22 may be acquired at this time.

When the temperature of the operation portion 221 reaches the first temperature threshold, the heat storage portion 222 may exchange heat with the operation portion 221 at this time, and heat generated during the operation of the operation portion 221 may be stored by the heat storage portion 222. Preventing overheat of the actuator 221 from affecting performance and lifetime.

When the temperature of the heat storage portion 222 reaches the second temperature threshold, the heat storage portion 222 absorbs a large amount of heat at this time, and the cooling turbine 16 can supply cooling gas to the heat radiation portion 223, and the heat radiation portion 223 cools the heat storage portion 222 to thereby cool down. The temperature of the second load unit 22 is prevented from being too high, so that the second load unit 22 can maintain good performance and the service life of the second load unit 22 can be prolonged during operation.

In some embodiments, an aircraft energy control method includes:

Acquiring the electric quantity state of the energy storage component 03 based on the working state of the aircraft;

Controlling the energy source assembly 01 to increase the electric energy supplied to the energy storage assembly 03 based on the electric quantity state of the energy storage assembly 03 being smaller than the first electric quantity threshold value;

Acquiring the output electric energy of the engine assembly 04 and the actual use electric energy of the load assembly 02 based on the electric quantity state of the energy storage assembly 03 being greater than the first electric quantity threshold and less than the second electric quantity threshold;

Based on the output electric energy of the engine assembly 04 being greater than the actual use electric energy of the load assembly 02, the engine assembly 04 is controlled to supply the surplus electric energy to the energy storage assembly 03, and the electric energy supplied to the energy storage assembly 03 by the energy source assembly 01 is kept unchanged.

In this embodiment, the aircraft energy control method may include:

The state of charge of the energy storage assembly 03 can be acquired when the aircraft is in operation. The energy storage component 03 is convenient to control the electric energy supplied by the energy source component 01 and the engine component 04 through judging the electric quantity state.

When the state of charge of the energy storage component 03 is less than the first power threshold (for example, 30% of the full power of the energy storage component 03), the energy source component 01 can be directly controlled to increase the power supplied to the energy storage component 03. So that the energy storage assembly 03 can store electric quantity.

When the state of charge of the energy storage component 03 is greater than the first power threshold and less than the second power threshold (e.g., 50% of the full power of the energy storage component 03), the power of the energy storage component 03 is slightly higher. The output electric power of the engine assembly 04 and the actual use electric power of the load assembly 02 can be obtained.

If the output electric energy of the engine assembly 04 is greater than the actual use electric energy of the load assembly 02, the engine assembly 04 is controlled to supply the residual electric energy to the energy storage assembly 03, so that the output fluctuation of the engine assembly 04 is reduced, the engine assembly 04 is maintained in a high-efficiency working range as long as possible, the performance of the engine assembly 04 can be improved, and the energy efficiency of the energy control system of the aircraft is improved. The energy source assembly 01 maintains the power supplied to the energy storage assembly 03 unchanged so that the energy storage assembly 03 can obtain sufficient power.

In some embodiments, the aircraft energy control method further comprises:

Acquiring output electric energy of the engine assembly 04 and actual use electric energy of the load assembly 02 based on the electric quantity state of the energy storage assembly 03 being greater than a second electric quantity threshold;

Based on the output electric energy of the engine assembly 04 being greater than the actual use electric energy of the load assembly 02, the engine assembly 04 is controlled to supply the remaining electric energy to the energy storage assembly 03, and the energy source assembly 01 stops the supply of electric energy to the energy storage assembly 03.

In this embodiment, the aircraft energy control method may further include:

when the state of charge of the energy storage component 03 is greater than the second electric quantity threshold, the electric quantity of the energy storage component 03 is higher at this time, so that the output electric energy of the engine component 04 and the actual use electric energy of the load component 02 can be obtained.

If the output electric energy of the engine assembly 04 is larger than the actual use electric energy of the load assembly 02, the engine assembly 04 can be controlled to supply the residual electric energy to the energy storage assembly 03, so that the output fluctuation of the engine assembly 04 is ensured to be small, the output power of the engine assembly 04 is kept in a small fluctuation range as long as possible, the engine assembly 04 is in a high-efficiency working state, the energy efficiency of an aircraft energy control system can be improved, and the high-efficiency distribution of aircraft energy is realized. At this time, the electric energy supplied by the engine assembly 04 to the energy storage assembly 03 may already meet the electric energy requirement of the energy storage assembly 03, and the energy source assembly 01 may stop supplying electric energy to the energy storage assembly 03.

In some embodiments, as shown in fig. 2, the aircraft energy control method includes:

acquiring the flying height of the aircraft based on the working state of the aircraft;

acquiring output electric energy of the engine assembly 04 and output electric energy of the energy assembly 01 based on the flying height within a height set threshold range; wherein, the energy source assembly 01 also comprises a combustion chamber 13 and a power turbine 14; the load assembly 02 further includes an oil supply unit 26; the power turbine 14 is coaxially connected with the compressor 12; the compressor 12 is communicated with the combustion chamber 13; the combustion chamber 13 is in communication with a power turbine 14; the engine assembly 04 communicates with the combustion chamber 13; the oil supply unit 26 is respectively communicated with the combustion chamber 13 and the engine assembly 04; the oil supply unit 26 is electrically connected with the energy storage component 03, the starting generator 11 and the engine component 04 respectively;

The fuel supply unit 26 increases the amount of fuel supplied to the combustion chamber 13 and the engine block 04, and the energy storage block 03 increases the amount of electric energy supplied to the load block 02, based on the sum of the electric energy output from the engine block 04 and the electric energy output from the energy source block 01 being smaller than the output set threshold value and the engine block 04 supplying gas to the combustion chamber 13, and controlling the engine block 04 to reduce the amount of gas supplied to the combustion chamber 13.

In the present embodiment, as shown in fig. 2, the energy source assembly 01 may further include a combustion chamber 13, a power turbine 14, and the load assembly 02 may further include an oil supply unit 26. The power turbine 14 may be coaxially coupled with the compressor 12, making the system more compact and efficient. The energy loss and mechanical abrasion caused by mismatching of the rotating speeds can be reduced, and the reliability and durability of the system are improved. The compressor 12 may be in communication with the combustion chamber 13 for providing high pressure gas, the combustion chamber 13 may be in communication with the power turbine 14, the energy generated by the combustion may be provided to the power turbine 14 for operation of the aircraft, the engine assembly 04 may be in communication with the combustion chamber 13 for providing gas to the combustion chamber 13, and the oil supply unit 26 may be in communication with the combustion chamber 13, the engine assembly 04, respectively, for providing a steady supply of fuel. The oil supply unit 26 may be electrically connected to the energy storage assembly 03, the starter generator 11, and the engine assembly 04, respectively.

An excessive aircraft altitude may result in insufficient performance of the engine assembly 04 due to a combination of factors such as lean air, reduced cooling, reduced intake pressure, and design constraints of the engine assembly 04. Corresponding measures are therefore required to ensure safe flight of the aircraft. The aircraft energy control method may include:

when the aircraft is in an operating state, the flying height of the aircraft can be obtained. And subsequent operation is convenient to be carried out by judging the flying height of the aircraft.

If the flying height is within the height setting threshold, the output power of the engine assembly 04 and the output power of the energy assembly 01 can be obtained.

If the sum of the output electric power of the engine assembly 04 and the energy source assembly 01 is smaller than the output set threshold value and the engine assembly 04 supplies gas to the combustion chamber 13, it is indicated that the output electric power of the engine assembly 04 cannot meet the electricity demand. The engine assembly 04 may be controlled to reduce the amount of gas supplied to the combustion chamber 13, thereby reducing the performance impact of the gas supplied to the combustion chamber 13 on the engine assembly 04. The fuel supply unit 26 can increase the fuel amount supplied to the combustion chamber 13 and the engine assembly 04, and the energy storage assembly 03 can increase the electric energy supplied to the load assembly 02 so as to compensate the electric energy gap caused by the insufficient performance of the engine assembly 04.

In this embodiment, an aircraft energy control system is provided, which may be applied to the aircraft energy control method in any one of the foregoing embodiments, as shown in fig. 2, where the aircraft energy control system includes:

An energy source assembly 01, the energy source assembly 01 being for supplying electric energy and cooling gas;

The energy storage component 03, the energy storage component 03 is electrically connected with the energy source component 01;

A load assembly 02, the load assembly 02 comprising a first load unit 21; the first load unit 21 is electrically connected with the energy source assembly 01; the first load unit 21 is electrically connected with the energy storage component 03;

An engine assembly 04, the engine assembly 04 being electrically connected to the energy assembly 01; the engine assembly 04 is electrically connected with the energy storage assembly 03; the engine assembly 04 is electrically connected to the first load unit 21.

In this embodiment, as shown in FIG. 2, the aircraft energy control system may include: an energy source assembly 01, an energy storage assembly 03, a load assembly 02 and an engine assembly 04. The energy source assembly 01 may be used for supplying electric energy and cooling gas, and the energy storage assembly 03 may be electrically connected to the energy source assembly 01 for transmitting electric current. The load assembly 02 may comprise a first load unit 21, the first load unit 21 may be electrically connected with the energy source assembly 01, and the first load unit 21 may be electrically connected with the energy storage assembly 03. The energy storage assembly 03 and the energy source assembly 01 are facilitated to supply power to the first load unit 21. The engine assembly 04 may be electrically connected to the energy source assembly 01 such that the energy source assembly 01 may power the engine assembly 04 and the engine assembly 04 may also power the energy source assembly 01. The engine assembly 04 can be electrically connected with the energy storage assembly 03, and redundant electric energy of the engine assembly 04 can be supplied to the energy storage assembly 03 for storage, so that the energy utilization efficiency is improved. The engine assembly 04 may be electrically connected with the first load unit 21, and may provide electrical energy to the first load unit 21.

In some embodiments, the energy source assembly 01 includes a cooling turbine 16, a starter generator 11, a compressor 12, a heat exchanger 15, a power turbine 14, a combustor 13; the cooling turbine 16, the starter generator 11, the compressor 12 and the power turbine 14 are coaxially connected; the compressor 12 is communicated with a cooling turbine 16 through a heat exchanger 15; the compressor 12 is communicated with the combustion chamber 13; the combustion chamber 13 is in communication with a power turbine 14; the combustion chamber 13 communicates with the engine assembly 04; the energy storage assembly 03 is in communication with the cooling turbine 16; the first load unit 21 communicates with the cooling turbine 16; the starter generator 11 is electrically connected to the first load unit 21; the generator 11 is electrically connected with the energy storage component 03; the starter generator 11 is electrically connected with the engine assembly 04; the load assembly 02 further comprises a second load unit 22, an oil supply unit 26; the second load unit 22 includes an operation portion 221, a heat storage portion 222, and a heat dissipation portion 223; the operation portion 221 and the heat storage portion 222 perform heat transfer; the heat radiating portion 223 and the heat storage portion 222 perform heat transfer; the heat dissipation portion 223 communicates with the cooling turbine 16; the actuating part 221 is electrically connected with the energy storage component 03, the starting generator 11 and the engine component 04 respectively; the heat dissipation part 223 is electrically connected with the energy storage component 03, the generator 11 and the engine component 04 respectively; the oil supply unit 26 is respectively communicated with the combustion chamber 13 and the engine assembly 04; the oil supply unit 26 is electrically connected to the energy storage module 03, the starter generator 11, and the engine module 04, respectively.

In this embodiment, the energy source assembly 01 may include a cooling turbine 16, a starter generator 11, a compressor 12, a heat exchanger 15, a power turbine 14, a combustor 13. The cooling turbine 16, the starter generator 11, the compressor 12, and the power turbine 14 may be coaxially connected. The energy generated by the power turbine 14 can be transmitted to the compressor 12 and the generator 11, so that the loss of the energy in the process of multiple conversion and transmission is reduced, and the energy efficiency of the whole system is improved. Coaxial connections, because of the reduced transmission components and connection points, can reduce potential failure points in the system, thereby improving overall system reliability. The compressor 12 can be communicated with the cooling turbine 16 through the heat exchanger 15, and high-pressure gas generated by the compressor 12 can be transmitted to the cooling turbine 16 through the heat exchanger 15 for utilization. The compressor 12 communicates with the combustion chamber 13, and the combustion chamber 13 may communicate with the power turbine 14 by high pressure gas generated by the compressor 12 being transported to the combustion chamber 13. The kinetic energy generated in the combustion chamber 13 may be converted into mechanical energy of a turbine, and the combustion chamber 13 may be in communication with the engine assembly 04, facilitating the engine assembly 04 to supply gas to the combustion chamber 13. The energy storage assembly 03 may be in communication with the cooling turbine 16, the cooling turbine 16 providing cooling gas to cool the energy storage assembly 03, and the first load unit 21 may be in communication with the cooling turbine 16, so as to provide cooling gas to cool the first load unit 21. The starter generator 11 may be electrically connected to the first load unit 21 to supply power to the first load unit 21. The starting generator 11 can be electrically connected with the energy storage component 03, and can supply electric energy to the energy storage component 03 for storage, and the starting generator 11 can be electrically connected with the engine component 04, so that current is conveniently transmitted between the engine component 04 and the starting generator 11. The load assembly 02 may further include a second load unit 22, an oil supply unit 26. The second load unit 22 may include an operation part 221, a heat storage part 222, and a heat dissipation part 223. The actuating part 221 can transfer heat with the heat storage part 222, so that heat generated in the operation process of the actuating part 221 can be conveniently dissipated in time, the performance is maintained, and the service life is prolonged. The heat sink 223 may transfer heat to the heat storage 222, and dissipate heat stored in the heat storage 222. The heat sink 223 may be in communication with the cooling turbine 16 to facilitate cooling the cooling turbine 16 to provide cooling gas. The actuating portion 221 may be electrically connected to the energy storage assembly 03, the generator 11, and the engine assembly 04, respectively, and the heat dissipating portion 223 may be electrically connected to the energy storage assembly 03, the generator 11, and the engine assembly 04, respectively, so that when the second load unit 22 operates, it is convenient to supply electric power to the actuating portion 221 and the heat dissipating portion 223. The oil supply unit 26 may be in communication with the combustion chamber 13 and the engine assembly 04, respectively, so as to supply fuel to the combustion chamber 13 and the engine assembly 04. The oil supply unit 26 can be electrically connected with the energy storage component 03, the generator 11 and the engine component 04 respectively, and can acquire electric energy to facilitate work.

It will be understood by those of ordinary skill in the art that the foregoing embodiments are specific examples of implementing the disclosure, and that various changes in form and details may be made therein without departing from the spirit and scope of the disclosure.

Claims (10)

1. An aircraft energy control method, the aircraft energy control method comprising:

Step S11, acquiring the electric load of an aircraft energy control system based on the fact that the aircraft is in a working state and the electric load of the aircraft energy control system fluctuates;

step S12, based on the fact that the electric load is increased to a first set threshold value and the first load unit is operated, the energy storage component is controlled to increase the electric energy supplied to the load component, and the electric energy supplied by the energy component and the electric energy supplied by the engine component are kept unchanged; wherein the aircraft energy control system comprises the energy storage assembly, the energy source assembly, the engine assembly and the load assembly; the energy storage component is electrically connected with the energy source component; the engine assembly is electrically connected with the energy storage assembly; the engine assembly is electrically connected with the energy source assembly; the load assembly includes the first load unit; the first load unit is electrically connected with the energy source assembly, the energy storage assembly and the engine assembly respectively;

Step S13, based on the fact that the electric load is increased to a second set threshold value and the first load unit is operated, the energy storage component is controlled to stop supplying electric energy to the load component, the energy source component increases the electric energy supplied to the load component, and the electric energy supplied by the engine component is kept unchanged; wherein the second set threshold is greater than the first set threshold.

2. An aircraft energy control method according to claim 1, characterized in that,

The aircraft energy control method further comprises the following steps:

Controlling the energy storage component and the energy source component to jointly supply electric energy to the load component based on the fact that the electric load is increased to a third set threshold value and the first load unit is operated, wherein the electric energy supplied by the engine component to the load component is kept unchanged; wherein the third set threshold is greater than the second set threshold.

3. An aircraft energy control method according to claim 2, characterized in that,

The aircraft energy control method further comprises the following steps:

Based on the electric load increasing to a fourth set threshold value and the second load unit operating, controlling the energy storage component to increase the electric energy supplied to the load component to the maximum output power, wherein the electric energy supplied by the energy source component and the electric energy supplied by the engine component are kept unchanged; wherein the fourth set threshold is greater than the third set threshold; the load assembly further includes the second load unit; the second load unit is electrically connected with the energy storage component, the energy source component and the engine component respectively.

4. A method of controlling energy of an aircraft according to claim 3,

The aircraft energy control method comprises the following steps:

Based on the electrical load increasing to a fourth set threshold and the energy storage assembly increasing to a maximum output power for electrical energy supplied to the load assembly, the cooling turbine of the energy assembly increasing an amount of cooling gas supplied to the energy storage assembly, the second load unit, reducing an amount of cooling gas supplied to the first load unit; the energy source assembly comprises the cooling turbine, a starting generator, a gas compressor and a heat exchanger; the cooling turbine, the starting generator and the compressor are coaxially connected; the compressor is communicated with the cooling turbine through the heat exchanger; the energy storage assembly is communicated with the cooling turbine; the first load unit is in communication with the cooling turbine; the second load unit is in communication with the cooling turbine.

5. A method of controlling energy of an aircraft according to claim 4,

The aircraft energy control method further comprises the following steps:

Acquiring a temperature of an actuating portion of the second load unit based on the electric load increasing to a fourth set threshold; wherein the second load unit comprises the actuating part, a heat storage part and a heat dissipation part; the actuating part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the actuating part and the heat storage part conduct heat transfer; the heat dissipation part and the heat storage part conduct heat transfer; the heat dissipation part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the heat dissipation part is communicated with the cooling turbine;

Based on the temperature of the actuating part reaching a first temperature threshold, the heat storage part exchanges heat with the actuating part;

the cooling turbine supplies cooling gas to the heat dissipation portion, which cools the heat storage portion, based on the temperature of the heat storage portion reaching a second temperature threshold.

6. An aircraft energy control method according to claim 1, characterized in that,

The aircraft energy control method comprises the following steps:

Acquiring an electric quantity state of the energy storage component based on the fact that the aircraft is in a working state;

Controlling the energy source assembly to increase the electric energy supplied to the energy storage assembly based on the state of charge of the energy storage assembly being less than a first electric quantity threshold;

Acquiring the output electric energy of the engine assembly and the actual use electric energy of the load assembly based on the electric quantity state of the energy storage assembly being greater than the first electric quantity threshold and less than the second electric quantity threshold;

And controlling the engine assembly to supply the residual electric energy to the energy storage assembly based on the fact that the output electric energy of the engine assembly is larger than the actual use electric energy of the load assembly, wherein the electric energy supplied by the energy storage assembly by the energy source assembly is kept unchanged.

7. The method of claim 6, wherein,

The aircraft energy control method further comprises the following steps:

acquiring output electric energy of the engine assembly and actual use electric energy of the load assembly based on the electric quantity state of the energy storage assembly being greater than the second electric quantity threshold;

and controlling the engine assembly to supply the remaining electric energy to the energy storage assembly based on the fact that the output electric energy of the engine assembly is larger than the actual use electric energy of the load assembly, and stopping the electric energy supply to the energy storage assembly by the energy source assembly.

8. A method of controlling energy of an aircraft according to claim 4,

The aircraft energy control method comprises the following steps:

acquiring the flying height of the aircraft based on the aircraft being in a working state;

Acquiring output electric energy of the engine assembly and output electric energy of the energy assembly based on the flying height within a height set threshold range; wherein the energy source assembly further comprises a combustion chamber and a power turbine; the load assembly further includes an oil supply unit; the power turbine is coaxially connected with the compressor; the compressor is communicated with the combustion chamber; the combustion chamber is in communication with the power turbine; the engine assembly is in communication with the combustion chamber; the oil supply unit is respectively communicated with the combustion chamber and the engine assembly; the oil supply unit is respectively and electrically connected with the energy storage component, the starting generator and the engine component;

And controlling the engine assembly to reduce the amount of gas supplied to the combustion chamber based on the sum of the output electric energy of the engine assembly and the output electric energy of the energy assembly is smaller than an output set threshold value and the engine assembly supplies gas to the combustion chamber, wherein the oil supply unit increases the amount of fuel supplied to the combustion chamber and the engine assembly, and the energy storage assembly increases the electric energy supplied to the load assembly.

9. An aircraft energy control system for use in an aircraft energy control method according to any one of claims 1 to 8,

The aircraft energy control system includes:

An energy source assembly for supplying electrical energy and a cooling gas;

the energy storage component is electrically connected with the energy source component;

A load assembly including a first load cell; the first load unit is electrically connected with the energy source component; the first load unit is electrically connected with the energy storage component;

An engine assembly electrically connected with the energy assembly; the engine assembly is electrically connected with the energy storage assembly; the engine assembly is electrically connected with the first load unit.

10. An aircraft energy control system according to claim 9, wherein,

The energy source component comprises a cooling turbine, a starting generator, a gas compressor, a heat exchanger, a power turbine and a combustion chamber; the cooling turbine, the starting generator, the compressor and the power turbine are coaxially connected; the compressor is communicated with the cooling turbine through the heat exchanger; the compressor is communicated with the combustion chamber; the combustion chamber is in communication with the power turbine; the combustion chamber is in communication with the engine assembly; the energy storage assembly is communicated with the cooling turbine; the first load unit is in communication with the cooling turbine; the starting generator is electrically connected with the first load unit; the power generator is electrically connected with the energy storage component; the starter generator is electrically connected with the engine assembly;

The load assembly further comprises a second load unit and an oil supply unit; the second load unit comprises an actuating part, a heat storage part and a heat dissipation part; the actuating part and the heat storage part conduct heat transfer; the heat dissipation part and the heat storage part conduct heat transfer; the heat dissipation part is communicated with the cooling turbine; the actuating part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the heat dissipation part is respectively and electrically connected with the energy storage component, the starting generator and the engine component; the oil supply unit is respectively communicated with the combustion chamber and the engine assembly; the oil supply unit is electrically connected with the energy storage component, the starting generator and the engine component respectively.