Power system, aircraft and aircraft control method

Abstract

The invention relates to a power system, an aircraft and an aircraft control method. The power system comprises a combined driving assembly which comprises an air inlet channel, a turbine driving device and a stamping driving device; the oil supply assembly comprises an oil supply device, a first oil way and a second oil way; the circulating cooling loop comprises a heat energy conversion assembly, a driving part and a circulating pipeline, the first oil way comprises an oil outlet way, a first branch and a second branch, an outlet of the oil outlet way is connected with an inlet of the first branch and an inlet of the second branch, and an outlet of the first branch is located on the upstream of an outlet of the second branch; and the first driving oil passing through the first branch can flow to the outlet of the second branch after exchanging heat with the first driving airflow. The power system provided by the invention has a good cooling effect, and it is guaranteed that the power system can work efficiently.

Description

Technical Field

[0001] The present invention relates to the field of aircraft technology, and in particular to a power system, an aircraft and an aircraft control method. Background Art

[0002] In the relevant technology, hypersonic aircraft refers to aircraft that fly at five times the speed of sound or higher in the atmosphere, and has a wide range of application fields and great application prospects. The power system is the core of hypersonic aircraft. In the power system, since a single type of engine cannot meet the full-speed requirements of hypersonic aircraft, combined engine technology has emerged. The current combined power schemes mainly include turbine-ramjet combined power (TBCC), rocket-ramjet combined power (RBCC), turbine-rocket combined power (ATR) and three-combination engine (T / RBCC). From the perspective of performance, safety and technical feasibility, the turbine-based combination engine (TBCC) is considered to be the most promising combined power technology and has received widespread attention in recent years. The turbine-ramjet combined power is a power unit composed of a turbine engine and a scramjet engine. It is powered by a turbine engine at low Mach numbers and by a ramjet engine at high Mach numbers. Generally, when the flight Mach number increases to 3 to 4, the power is converted from the turbine base to the ramjet base. During the conversion process, the turbine engine inlet temperature may be too high, resulting in a rapid decrease in thrust, also known as the "thrust gap". In order to solve the thrust gap problem of TBCC, a feasible solution is to cool the turbine engine intake. In addition, during the operation of the ramjet engine, the heat flow in the combustion chamber is very large, and conventional materials can no longer withstand it, so effective cooling must be carried out.

[0003] However, the cooling effect of the cooling device of the related combined engine is low and cannot meet the cooling demand of the combined engine. Summary of the invention

[0004] The embodiment of the present application provides a power system, which has a good cooling effect, can improve the cooling requirements of the combined engine, and improve the working efficiency of the power system.

[0005] In a first aspect, an embodiment of the present application proposes a power system, the power system comprising: a combined drive assembly, comprising an air intake duct, a turbine drive device and a ram drive device, the air intake duct being configured to provide a first drive airflow to the turbine drive device and a second drive airflow to the ram drive device; an oil supply assembly, comprising an oil supply device, a first oil circuit and a second oil circuit, the first oil circuit being connected between the oil supply device and the turbine drive device, the second oil circuit being connected between the oil supply device and the ram drive device, the oil supply device being configured to provide a first drive oil to the turbine drive device and a second drive oil to the ram drive device; a circulating cooling circuit, comprising a heat energy conversion The heat energy conversion component is connected to the turbine drive device and the ram drive device through the circulation pipeline. The drive member is configured to drive the working medium in the circulation pipeline to absorb the heat energy of the first driving airflow and the second driving airflow. At least part of the heat energy conversion component is configured to convert heat energy into electrical energy. The first oil circuit includes an oil outlet circuit, a first branch and a second branch. The outlet of the oil outlet circuit is connected to the inlet of the first branch and the inlet of the second branch. The outlet of the first branch is located upstream of the outlet of the second branch. The first driving oil through the first branch can flow to the outlet of the second branch after heat exchange with the first driving airflow.

[0006] In some embodiments, the turbine drive device includes a turbine precooling component and a turbine drive component. The turbine precooling component is located upstream of the turbine drive component and downstream of the intake duct. The first drive airflow provided by the intake duct enters the turbine drive component after passing through the turbine precooling component. The circulation pipeline passes through the turbine precooling component to allow the working fluid to exchange heat with the first drive airflow. The first branch passes through the turbine precooling component to allow the first drive oil to exchange heat with the first drive airflow.

[0007] In some embodiments, the turbine precooling assembly includes: a first part and a second part, the circulation pipeline passes through the first part, and the first branch passes through the second part; wherein one of the first part and the second part is located upstream of the other; or, the first part and the second part are arranged along a first direction, and the first direction intersects with the flow direction of the first driving airflow passing through the turbine precooling assembly.

[0008] In some embodiments, the ram drive device includes: a ram drive assembly, an air inlet duct is configured to provide a second driving airflow to the ram drive assembly, a second oil circuit is connected between the ram drive assembly and an oil supply device, the oil supply device is configured to provide a second driving oil to the ram drive assembly via the second oil circuit, the ram drive assembly includes a ram wall and a ram chamber, the ram wall encloses the ram chamber; a ram engine cooling assembly is connected to a side of the ram wall facing the ram chamber, and a circulation pipeline passes through the ram engine cooling assembly so that the working fluid absorbs the heat energy of the second driving airflow passing through the ram drive assembly.

[0009] In some embodiments, the ramjet engine cooling assembly includes: a third part, located in the ram chamber, the third part is connected to a part of the ram wall, and the circulation pipeline passes through the third part so that the working medium absorbs the heat energy of the second driving air flow passing through the ram drive assembly; a fourth part, located in the ram chamber, the fourth part is connected to another part of the ram wall, and the second oil circuit passes through the fourth part so that the second driving oil enters the ram drive assembly after heat exchange with the second driving air flow passing through the ram drive assembly.

[0010] In some embodiments, the heat energy conversion component includes a converter and a cooler, the converter is configured to convert a portion of the heat energy into electrical energy, the oil supply component also includes a converging oil circuit, one end of the converging oil circuit is connected to the oil outlet oil circuit and the second oil circuit, and the other end of the converging oil circuit is connected to the oil supply device, the first drive oil and the second drive oil are diverted to the oil outlet oil circuit and the second oil circuit after passing through the converging oil circuit, the converging oil circuit and the circulating pipeline pass through the cooler, and the cooler is configured to allow the first drive oil and the second drive oil passing through the converging oil circuit to exchange heat energy absorbed by the working fluid in the circulating pipeline.

[0011] In some embodiments, the oil supply assembly further includes: an oil return circuit connected between the oil supply device and the converging oil circuit and / or the second branch; and an oil replenishment circuit connected between the oil supply device and the converging oil circuit.

[0012] In some embodiments, the number of combined drive assemblies is more than two, and each combined drive assembly is respectively connected to the oil supply assembly and the circulating cooling circuit.

[0013] In a second aspect, an embodiment of the present application proposes an aircraft, comprising any power system of the first aspect described above.

[0014] In a third aspect, an embodiment of the present application proposes an aircraft control method, which includes: providing an aircraft, the aircraft including the power system of the first aspect; setting the aircraft operating speed to a first preset speed; controlling the oil supply device to provide a first driving oil to the turbine drive device through the oil outlet circuit and the second branch, and controlling the air inlet duct to provide a first driving airflow to the turbine drive device.

[0015] In some embodiments, the turbine drive device includes a turbine precooling component and a turbine drive component, the turbine precooling component is located upstream of the turbine drive component and downstream of the air inlet, the first driving airflow provided by the air inlet enters the turbine drive component after passing through the turbine precooling component, the oil supply device is controlled to provide fuel to the turbine drive device through the oil outlet oil circuit and the second branch, and the air inlet is controlled to provide the first driving airflow to the turbine drive device. The control method also includes: setting the aircraft operating speed to a second preset speed, the second preset speed being greater than the first preset speed; controlling the oil supply device to sequentially provide the first driving oil to the turbine drive component through the oil outlet oil circuit and the first branch and allowing the first driving oil to heat exchange with the first driving airflow; controlling the working fluid in the driving member driving circulation pipeline to pass through the turbine precooling component so that the working fluid absorbs the heat energy of the first driving airflow; controlling the oil supply device to provide the second driving oil to the ram drive device through the second oil circuit, and controlling the air inlet to provide the second driving airflow to the ram drive device; controlling the working fluid in the driving member driving circulation pipeline to pass through the ram drive device so that the working fluid absorbs the heat energy of the second driving airflow.

[0016] In some embodiments, the ram drive device includes a ram drive assembly and a ram engine cooling assembly, the air inlet is configured to provide a second driving airflow to the ram drive assembly, the second oil circuit is connected between the ram drive assembly and the oil supply device, the oil supply device is configured to provide a second driving oil to the ram drive assembly via the second oil circuit, the ram engine cooling assembly is located on at least a wall surface of the ram drive assembly, the circulation pipeline passes through the ram engine cooling assembly, the oil supply device is controlled to provide the second driving oil to the ram drive device through the second oil circuit, and the step of controlling the air inlet to provide the second driving airflow to the ram drive device includes: controlling the air inlet to provide the second driving airflow to the ram drive assembly; controlling the oil supply device to provide the second driving oil to the ram drive assembly through the second oil circuit and the ram engine cooling assembly; and controlling the driving member to drive the working fluid in the circulation pipeline through the ram drive device so that the working fluid absorbs the heat energy of the second driving airflow, including: controlling the driving member to drive the working fluid in the circulation pipeline through the ram engine cooling assembly so that the working fluid absorbs the heat energy of the second driving airflow.

[0017] In some embodiments, the heat energy conversion component includes a converter and a cooler, the converter is configured to convert a portion of the heat energy into electrical energy, the oil supply component also includes a confluence oil circuit, one end of the confluence oil circuit is connected to the oil outlet oil circuit and the second oil circuit, the confluence oil circuit and the circulation pipeline are connected through the cooler, and the cooler is configured to allow the first drive oil, the second drive oil and the heat energy absorbed by the circulating working fluid to exchange heat, the oil supply component also includes a return oil circuit and an oil replenishment oil circuit, the return oil circuit is connected between the oil supply device and the confluence oil circuit and / or the second branch, the oil replenishment oil circuit is connected between the oil supply device and the confluence oil circuit, and the control drive member drives the working fluid in the circulation pipeline through the stamping drive device so that the working fluid absorbs the heat energy of the second driving air flow. The control method also includes: the heat energy includes the first heat energy and the second heat energy, and the converter is controlled to convert the first heat energy into electrical energy; the cooler is controlled to heat exchange the second heat energy with the first drive oil and the second drive oil of the confluence oil circuit.

[0018] In some embodiments, after controlling the cooler to heat exchange the second heat energy with the first drive oil and the second drive oil of the converging oil circuit, the control method includes: judging the total amount of the first drive oil and the second drive oil passing through the cooler and the oil consumption of the ram drive assembly and / or the turbine drive assembly; if the total amount is greater than the oil consumption, controlling the oil return oil circuit to open; if the total amount is less than the oil consumption, controlling the oil replenishment oil circuit to open. In some embodiments, after controlling the drive member to drive the working fluid in the circulation pipeline through the ram drive device so that the working fluid absorbs the heat energy of the second drive airflow, the control method also includes: setting the aircraft operating speed to a third preset speed, the third preset speed being greater than the second preset speed; closing the first oil circuit; closing the circulation pipeline flowing through the turbine precooling assembly.

[0019] The power system provided in the embodiment of the present application, through the setting of a circulating cooling circuit, firstly, realizes cooling of the turbine drive device and the ram drive device by means of working fluid circulation, reduces the temperature of the first driving airflow and the second driving airflow, is beneficial to the normal operation of the turbine drive device and the ram drive device, prevents them from being damaged by high temperature due to excessive temperature, and improves working efficiency; secondly, the heat energy conversion device can convert the absorbed heat energy into electrical energy, and the electrical energy can be used to maintain the operation of various subsystems of the aircraft, reduce the weight of the battery, and improve the energy utilization efficiency; thirdly, the setting that the first driving oil through the first branch can flow to the outlet of the second branch after heat exchange with the first driving airflow, can use the fuel itself to cool down the temperature of the first driving airflow, and on the basis of allowing the circulating cooling circuit to convert part of the heat energy into electrical energy, reduce the heat load of the circulating cooling circuit, and further improve the cooling effect of the power system.

[0020] The aircraft provided in the embodiment of the present application includes a power system, and the power system includes a combined drive assembly, an oil supply assembly, and a circulating cooling circuit. The combined drive assembly includes a turbine drive device and a ram drive device, and the circulating cooling circuit and the first branch, the oil outlet branch, and the second oil circuit of the oil supply assembly simultaneously realize cooling of the first driving airflow and the second driving airflow of the turbine drive device and the ram drive device. First, it can improve the cooling effect of the aircraft; secondly, it can provide electrical energy for the aircraft; thirdly, the cooling of the combined drive assembly is realized by using a variety of methods such as working fluid cooling and fuel cooling, which can reduce the weight of the circulating cooling circuit and realize lightweighting of the entire flight system.

[0021] The aircraft control method provided in the embodiment of the present application provides energy to the turbine drive device through the fuel supply device and the air inlet duct, so that the aircraft enters a first preset speed. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The features, advantages and technical effects of exemplary embodiments of the present application will be described below with reference to the accompanying drawings.

[0023] Figure 1 It is a plan view of an embodiment of a power system of an embodiment of the present application;

[0024] Figure 2 is a plan view of another embodiment of the power system of the embodiment of the present application;

[0025] Figure 3 is a plan view of an embodiment of a turbine precooling assembly in a power system of an embodiment of the present application;

[0026] Figure 4 is a plan view of another embodiment of a turbine precooling assembly in a power system of an embodiment of the present application;

[0027] Figure 5 is a plan view of another embodiment of the power system of the embodiment of the present application;

[0028] Figure 6 It is a flowchart of an embodiment of the aircraft control method of the present application.

[0029] Description of Figure Numbers:

[0030] 100-combined drive assembly;

[0031] 110 - air intake;

[0032] 120-turbine drive device; 121-turbine precooling assembly; 1211-first part; 1212-second part; 122-turbine drive assembly;

[0033] 130-ramjet drive device; 131-ramjet drive assembly; 1311-ramjet wall; 1312-ramjet chamber; 132-ramjet engine cooling assembly; 1321-third part; 1322-fourth part;

[0034] 200-Oil supply assembly;

[0035] 210-Oil supply device;

[0036] 220-first oil circuit; 221-oil outlet circuit; 222-first branch circuit; 223-second branch circuit;

[0037] 230-second oil circuit;

[0038] 240-return oil circuit;

[0039] 250-Oil supply circuit;

[0040] 260-confluence oil circuit;

[0041] 300-circulation cooling circuit;

[0042] 310-heat energy conversion component; 311-converter; 312-cooler; 313-regenerator;

[0043] 320-driving member;

[0044] 330-Circulation pipeline.

[0045] In the drawings, the same reference numerals are used for the same components. The drawings are not drawn to scale. DETAILED DESCRIPTION

[0046] The features and exemplary embodiments of various aspects of the present application will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present application. However, it is obvious to those skilled in the art that the present application can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present application by illustrating examples of the present application. In the accompanying drawings and the following description, at least some of the known structures and technologies are not shown to avoid unnecessary ambiguity in the present application; and, for clarity, the size of some structures may be exaggerated. In addition, the features, structures or characteristics described below may be combined in one or more embodiments in any suitable manner.

[0047] The directional words appearing in the following description are all directions shown in the figures, and do not limit the specific structure of the present application. In the description of the present application, it should also be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected or indirectly connected. For ordinary technicians in this field, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0048] In the related art, TBCC is a power unit composed of a turbine engine and a scramjet / ramjet engine. The turbine engine provides power at low Mach numbers and the ramjet engine provides power at high Mach numbers. Generally, when the flight Mach number is increased to 3 to 4, the power is converted from the turbine base to the ramjet base. During the conversion process, the turbine engine inlet temperature may be too high, resulting in a rapid decrease in thrust, which is also called the "thrust gap". In order to solve the thrust gap problem of TBCC, a feasible solution is to cool the turbine engine intake. However, the cooling effect of the cooling device of the related combined engine is low and cannot meet the cooling requirements of the combined engine.

[0049] Based on the above considerations, in order to solve the problem that the cooling effect of the cooling device of the related combined engine is low and cannot meet the cooling demand of the combined engine, a power system is designed.

[0050] Please refer to Figure 1 to Figure 2 , Figure 1 is a plan view of an embodiment of a power system of the present application, Figure 2 It is a plan view of another embodiment of the power system of the embodiment of the present application.

[0051] The embodiment of the present application provides a power system, which includes a combined drive assembly 100, an oil supply assembly 200, and a circulating cooling circuit 300. The combined drive assembly 100 includes an air inlet 110, a turbine drive device 120, and a ram drive device 130. The air inlet 110 is configured to provide a first driving airflow to the turbine drive device 120 and a second driving airflow to the ram drive device 130. The oil supply assembly 200 includes an oil supply device 210, a first oil circuit 220, and a second oil circuit 230. The first oil circuit 220 is connected between the oil supply device 210 and the turbine drive device 120, and the second oil circuit 230 is connected between the oil supply device 210 and the ram drive device 130. The oil supply device 210 is configured to provide a first driving oil to the turbine drive device 120 and a second driving oil to the ram drive device 130. The circulating cooling circuit 300 includes a heat conversion component 310, a driving member 320 and a circulating pipeline 330. The heat conversion component 310 is connected to the turbine driving device 120 and the stamping driving device 130 through the circulating pipeline 330. The driving member 320 is configured to drive the working medium in the circulating pipeline 330 to absorb the heat energy of the first driving airflow and the second driving airflow. The heat conversion component 310 is configured to convert heat energy into electrical energy. Among them, the first oil circuit 220 includes an oil outlet oil circuit 221, a first branch 222 and a second branch 223. The outlet of the oil outlet oil circuit 221 is connected to the inlet of the first branch 222 and the inlet of the second branch 223. The outlet of the first branch 222 is located upstream of the outlet of the second branch 223. The first driving oil through the first branch 222 can flow to the outlet of the second branch 223 after heat exchange with the first driving airflow.

[0052] Optionally, the combined drive assembly 100 includes an air outlet device for outputting the airflow after the turbine drive device 120 and the ram drive device 130 have acted.

[0053] The oil supply device 210 includes an oil supply tank and an oil pump, and the oil pump is located downstream of the oil tank.

[0054] The driving member 320 may be a compressor.

[0055] After the working fluid absorbs the heat energy of the first driving airflow and the second driving airflow, it can release heat and expand in the heat energy conversion component 310, and the heat energy in the working fluid is converted into mechanical energy, and the mechanical energy is converted into electrical energy to power the aircraft. Optionally, the heat energy conversion component 310 includes a turbine device, which converts heat energy into electrical energy. Among them, the working fluid includes a fluid with high density and low viscosity in a supercritical state, and the types of working fluids include but are not limited to carbon dioxide, helium, etc.

[0056] The outlet of the second branch 223 is the combustion chamber of the turbine drive device 120. The first drive air flow enters the turbine drive device 120 after being cooled by the working medium and the first drive oil in the first branch 222. The first drive oil can reach the combustion chamber of the turbine drive device 120 after absorbing the heat energy of the first drive oil through the first branch 222.

[0057] Optionally, a switch control device is provided at the outlet of the oil outlet passage 221, which can selectively open and close the first branch 222 and / or the second branch 223. Exemplarily, when the first driving airflow entering the turbine drive device 120 does not need to be cooled, the second branch 223 is opened, and when part of the first driving airflow entering the turbine drive device 120 needs to be cooled, the amount of fuel flow entering the first branch 222 and the second branch 223 can be adjusted by the switch control device.

[0058] The turbine drive device 120 may include a turbine precooling assembly 121, a compressor, a turbine combustion chamber, a turbine, and a tail nozzle arranged in sequence according to the flow direction of the first driving airflow. The outlet of the second branch 223 is the turbine combustion chamber. The first branch 222 and the circulation pipeline 330 pass through the turbine precooling assembly 121 to absorb the heat energy of the first driving airflow. After that, the first driving airflow enters the compressor and is compressed into a high-density, high-pressure, and low-speed airflow to increase the efficiency of the turbine drive device 120. After that, the first driving airflow enters the turbine combustion chamber, and the fuel flowing into the turbine combustion chamber from the second branch 223 is mixed with the first driving airflow and burned. After combustion, it drives the turbine to rotate and is then discharged through the tail nozzle. The ram drive device 130 may include a ram engine cooling component 132 and a tail nozzle. The circulation pipeline 330 passes through the ram engine cooling component 132 to absorb the heat energy of the second driving airflow. The second driving airflow reaches the ram drive device 130, expands and decelerates in the ram chamber 1312 of the ram drive device 130, and the air pressure and temperature of the second driving airflow are increased and then mixed with the fuel entering the ram chamber 1312 through the second oil circuit 230 and burned.

[0059] The power system provided in the embodiment of the present application, through the setting of the circulating cooling loop 300, firstly, realizes the cooling of the turbine drive device 120 and the ram drive device 130 by means of the working fluid circulation, reduces the temperature of the first driving airflow and the second driving airflow, is beneficial to the normal operation of the turbine drive device 120 and the ram drive device 130, prevents them from being damaged by high temperature due to excessive temperature, and improves the working efficiency; secondly, the heat energy conversion device can convert the absorbed heat energy into electrical energy, and the electrical energy can be used to maintain the operation of various subsystems of the aircraft, reduce the weight of the battery, and improve the energy utilization efficiency; thirdly, the setting that the first driving oil through the first branch 222 can flow to the outlet of the second branch 223 after heat exchange with the first driving airflow, can use the fuel itself to cool down the temperature of the first driving airflow, and on the basis of allowing the circulating cooling loop 300 to convert part of the heat energy into electrical energy, reduce the heat load of the circulating cooling loop 300, and further improve the cooling effect of the power system.

[0060] Optionally, the heat energy conversion assembly 310 includes a converter 311, a cooler 312, and a regenerator 313. The converter 311 can be a turbine device, a turbine device, etc. The cooler 312 is used to exchange heat between the working fluid in the circulation pipeline 330 and the first driving oil and the second driving oil. The driving member 320 includes a compressor. The working fluid that absorbs heat enters the turbine device for work and then enters the regenerator 313 to recover part of the heat. After that, the working fluid enters the cooler 312, and the heat of the working fluid is cooled by the cooler 312. The cooled working fluid enters the compressor and is compressed to a high pressure state again. The working fluid enters the turbine drive device 120 and / or the ram drive device 130 from the compressor outlet for precooling.

[0061] Please refer to Figure 3 to Figure 4 , Figure 3 is a plan view of an embodiment of a turbine precooling assembly in a power system of an embodiment of the present application, Figure 4 It is a plan schematic diagram of another embodiment of a turbine precooling assembly in the power system of an embodiment of the present application.

[0062] In some embodiments, the turbine drive device 120 includes a turbine precooling assembly 121 and a turbine drive assembly 122. The turbine precooling assembly 121 is located upstream of the turbine drive assembly 122 and downstream of the air inlet 110. The first driving airflow provided by the air inlet 110 enters the turbine drive assembly 122 after passing through the turbine precooling assembly 121. The circulation pipeline 330 passes through the turbine precooling assembly 121 so that the working medium and the first driving airflow are heat exchanged. The first branch 222 passes through the turbine precooling assembly 121 so that the first driving oil and the first driving airflow are heat exchanged.

[0063] The arrangement of the circulation pipeline 330 through the turbine precooling component 121 and the first branch 222 includes but is not limited to the circulation pipeline 330 through the turbine precooling component 121 being located upstream of the first branch 222, the circulation pipeline 330 through the turbine precooling component 121 being located upstream of the first branch 222, and the circulation pipeline 330 through the turbine precooling component 121 and the first branch 222 being arranged to intersect in the flow direction of the first driving airflow.

[0064] The turbine drive assembly 122 includes a compressor, a turbine gas chamber, and a turbine. The compressor is located upstream of the turbine gas chamber and downstream of the turbine precooling assembly 121. The turbine gas chamber is located downstream of the compressor, and the turbine is located downstream of the turbine gas chamber. The first driving airflow works in sequence through the turbine precooling assembly 121, the compressor, the turbine gas chamber, and the turbine. The outlet of the second branch 223 is the turbine gas chamber.

[0065] The power system provided in the embodiment of the present application provides cooling space for the first driving airflow that is about to enter the turbine driving assembly 122 through the setting of the turbine precooling assembly 121, which is beneficial to the uniform cooling of the first driving airflow and facilitates the setting of the circulation pipeline 330 and the first branch 222.

[0066] In some embodiments, the turbine precooling assembly 121 includes a first portion 1211 and a second portion 1212, the circulation pipeline 330 passes through the first portion 1211, and the first branch 222 passes through the second portion 1212. One of the first portion 1211 and the second portion 1212 is located upstream of the other; or, the first portion 1211 and the second portion 1212 are arranged along a first direction, and the first direction intersects with the flow direction of the first driving airflow passing through the turbine precooling assembly 121.

[0067] The first direction and the flow direction of the first driving airflow through the turbine precooling assembly 121 may be 80 degrees, 90 degrees, 100 degrees, etc. Optionally, the angle between the two is 90 degrees.

[0068] The power system provided in the embodiment of the present application facilitates the arrangement of the circulation pipeline 330 and the first branch 222 through the turbine precooling component 121 through the arrangement of the first part 1211 and the second part 1212, and can conveniently adjust the positions of the circulation pipeline 330 and the first branch 222 through the turbine precooling component 121 according to actual needs, thereby facilitating the realization of personalized precooling needs.

[0069] In some embodiments, the ram drive device 130 includes a ram drive assembly 131 and a ram engine cooling assembly 132. The air inlet 110 is configured to provide a second driving airflow to the ram drive assembly 131, the second oil circuit 230 is connected between the ram drive assembly 131 and the oil supply device 210, and the oil supply device 210 is configured to provide a second driving oil to the ram drive assembly 131 via the second oil circuit 230, the ram drive assembly 131 includes a ram wall 1311 and a ram chamber 1312, and the ram wall 1311 encloses the ram chamber 1312; the ram engine cooling assembly 132 is connected to the side of the ram wall 1311 facing the ram chamber 1312, and the circulation pipeline 330 passes through the ram engine cooling assembly 132 so that the working medium absorbs the heat energy of the second driving airflow passing through the ram drive assembly 131.

[0070] The ramjet engine cooling assembly 132 is located in the ramjet chamber 1312. The structure of the ramjet engine cooling assembly 132 includes but is not limited to a structure having multiple channels. Along the radial direction of the ramjet drive assembly 131, the thickness of the ramjet engine cooling assembly 132 can be adjusted according to actual conditions.

[0071] The power system provided in the embodiment of the present application can, through the setting of the ramjet engine cooling assembly 132, firstly, reduce the heat dissipated by the ramjet drive assembly 131 during the working stage to reduce the heat load of the ramjet drive assembly 131; secondly, the setting of the ramjet engine cooling assembly 132 on the surface of the ramjet chamber 1312 can facilitate sufficient heat exchange between the working fluid in the circulation pipeline 330 and the second driving airflow, thereby improving the heat dissipation efficiency, further increasing the working efficiency of the ramjet drive assembly 131, and extending the life of the ramjet drive assembly 131.

[0072] In some embodiments, the ramjet engine cooling assembly 132 includes a third portion 1321 and a fourth portion 1322. The third portion 1321 is located in the ram chamber 1312, and the third portion 1321 is connected to a portion of the ram wall 1311. The circulation pipeline 330 passes through the third portion 1321 so that the working medium absorbs the heat energy of the second driving airflow passing through the ram drive assembly 131. The fourth portion 1322 is located in the ram chamber 1312, and the fourth portion 1322 is connected to another portion of the ram wall 1311. The second oil circuit 230 passes through the fourth portion 1322 so that the second driving oil enters the ram drive assembly 131 after heat exchange with the second driving airflow passing through the ram drive assembly 131.

[0073] The third part 1321 and the fourth part 1322 can be a symmetrical structure or an asymmetrical structure on the stamping wall 1311 , and the structures of the third part 1321 and the fourth part 1322 can be adjusted according to actual conditions.

[0074] The power system provided in the embodiment of the present application can provide a variety of cooling methods for the stamping drive assembly 131 through the arrangement of the third part 1321 and the fourth part 1322. Further, the combined drive assembly 100 has a variety of cooling methods to prevent a single cooling method from being too heavy. In addition, by cooling the combined drive assembly 100 with the first drive oil and the second drive oil, the power system is lightweight and the burden on the aircraft is reduced.

[0075] In some embodiments, the heat energy conversion component 310 includes a converter 311 and a cooler 312. The converter 311 is configured to convert a portion of the heat energy into electrical energy. The oil supply component 200 also includes a converging oil circuit 260. One end of the converging oil circuit 260 is connected to the oil outlet circuit 221 and the second oil circuit 230. The other end of the converging oil circuit 260 is connected to the oil supply device 210. The first drive oil and the second drive oil are diverted to the oil outlet circuit 221 and the second oil circuit 230 after passing through the converging oil circuit 260. The converging oil circuit 260 and the circulating pipeline 330 pass through the cooler 312. The cooler 312 is configured to allow the first drive oil and the second drive oil passing through the converging oil circuit 260 to exchange heat with the heat energy absorbed by the working fluid in the circulating pipeline 330.

[0076] Converter 311 may be a turbine device that converts thermal energy into mechanical energy and then into electrical energy. The electrical energy converted by converter 311 is supplied to other subsystems of the aircraft. A small portion of the thermal energy of the working fluid in the circulation pipeline 330 is converted into electrical energy by converter 311.

[0077] The power system provided in the embodiment of the present application, firstly, realizes the conversion of thermal energy and electrical energy through the setting of the converter 311, improves the energy utilization rate, and can supply electrical energy to other subsystems of the aircraft. Secondly, the setting of the cooler 312 transfers the other thermal energy of the working fluid in the circulation pipeline 330 to the convergent oil circuit 260, which can reduce the thermal load of the converter 311.

[0078] In some embodiments, the oil supply assembly 200 further includes an oil return oil circuit 240 and an oil replenishment oil circuit 250. The oil return oil circuit 240 is connected between the oil supply device 210 and the converging oil circuit 260 and / or the second branch 223; the oil replenishment oil circuit 250 is connected between the oil supply device 210 and the converging oil circuit 260.

[0079] The oil return circuit 240 is connected between the oil supply device 210 and the converging oil circuit 260, or between the oil supply device 210 and the second branch 223, or between the oil supply device 210 and the converging oil circuit 260 and between the oil supply device 210 and the second branch 223. When the oil return circuit 240 is connected between the oil supply device 210 and the converging oil circuit 260, when the amount of fuel passing through the cooler 312 is greater than the fuel consumption of the running stamping drive assembly 131 and / or turbine drive assembly 122, the fuel of the converging oil circuit 260 can be returned; when the oil return circuit 240 is connected between the oil supply device 210 and the second branch 223, when the amount of fuel flowing to the second branch 223 is greater than the fuel consumption of the running turbine drive assembly 122, the fuel of the second branch 223 can be returned.

[0080] The power system provided in the embodiment of the present application can, firstly, meet the demand for conversion of heat energy of the precooler by setting up the return oil circuit 240 and the outlet oil circuit 221; secondly, it can also meet the balance between the oil consumption and the oil supply of the turbine drive assembly 122, making the oil circuit setting more reasonable and controllable.

[0081] Optionally, the number of combined drive assemblies 100 may be one group, and the specific connection method may be that one group of combined drive assemblies 100 is connected to one group of oil supply assemblies 200 and one group of circulating cooling circuits 300 .

[0082] It is understandable that the above embodiments are all illustrated by taking the number of combined drive components 100 as one group, which is an optional embodiment. In some embodiments, the combined drive components 100 can also include more than two groups, and each group of combined drive components 100 is respectively connected to the oil supply component 200 and the circulating cooling circuit 300.

[0083] Please refer to Figure 5 As shown, Figure 5 It is a plan view of another embodiment of the power system of the embodiment of the present application. Exemplarily, two groups are used as an example for explanation, the two groups of combined drive components 100 are symmetrically arranged, the two groups of combined drive components 100 share the same group of oil supply components 200 and a group of circulating cooling circuits 300, one group of oil supply components 200 has two groups of first oil circuits 220 and two groups of second oil circuits 230, one group of first oil circuits 220 and second oil circuits 230 are connected to one group of combined drive components 100, another group of first oil circuits 220 and second oil circuits 230 are connected to another group of combined drive components 100, the two groups of combined drive components 100 share a group of oil supply devices 210, and a group of circulating cooling circuits 300 passes through the two groups of combined drive components 100.

[0084] An embodiment of the present application provides an aircraft, comprising any of the power systems described above.

[0085] The aircraft provided in the embodiment of the present application includes a power system, and the power system includes a combined drive assembly 100, an oil supply assembly 200, and a circulating cooling circuit 300. The combined drive assembly 100 includes a turbine drive device 120 and a ram drive device 130, and the circulating cooling circuit 300 and the first branch 222, the oil outlet branch, and the second oil circuit 230 of the oil supply assembly 200 simultaneously realize cooling of the first driving airflow and the second driving airflow of the turbine drive device 120 and the ram drive device 130. Firstly, the cooling effect of the aircraft can be improved; secondly, the aircraft can be provided with electrical energy; thirdly, the cooling of the combined drive assembly 100 can be realized by using a variety of methods such as working fluid cooling and fuel cooling, which can reduce the weight of the circulating cooling circuit 300 and realize the lightweight of the entire flight system.

[0086] Please refer to Figure 6 As shown, Figure 6 It is a flowchart of an embodiment of the aircraft control method of the present application.

[0087] The present application provides an aircraft control method, the aircraft control method comprising:

[0088] S110, providing an aircraft, wherein the aircraft includes the power system of the above embodiment;

[0089] S120, setting the aircraft operating speed to a first preset speed;

[0090] S130 , controlling the oil supply device 210 to provide the first driving oil to the turbine driving device 120 through the oil outlet passage 221 and the second branch passage 223 , and controlling the air intake passage 110 to provide the first driving air flow to the turbine driving device 120 .

[0091] In step S130 , the oil supply device 210 and the air inlet 110 are controlled to provide the turbine drive device 120 with the first drive oil and the first drive air flow so as to operate the aircraft.

[0092] The aircraft control method provided in the embodiment of the present application provides energy to the turbine drive device 120 through the fuel supply device 210 and the air inlet 110, so that the aircraft enters a first preset speed.

[0093] In some embodiments, the turbine drive device 120 includes a turbine precooling assembly 121 and a turbine drive assembly 122. The turbine precooling assembly 121 is located upstream of the turbine drive assembly 122 and downstream of the air inlet 110. The first driving airflow provided by the air inlet 110 enters the turbine drive assembly 122 after passing through the turbine precooling assembly 121. The oil supply device 210 is controlled to provide fuel to the turbine drive device 120 through the oil outlet oil path 221 and the second branch 223. After the air inlet 110 is controlled to provide the first driving airflow to the turbine drive device 120, the method further includes:

[0094] S140, setting the aircraft running speed to a second preset speed, where the second preset speed is greater than the first preset speed;

[0095] S150, controlling the oil supply device 210 to sequentially supply the first driving oil to the turbine driving assembly 122 via the oil outlet passage 221 and the first branch passage 222 so as to allow the first driving oil to exchange heat with the first driving air flow;

[0096] S160, controlling the driving member 320 to drive the working medium in the circulation pipeline 330 to pass through the turbine precooling assembly 121 so that the working medium absorbs the heat energy of the first driving airflow;

[0097] S170, controlling the oil supply device 210 to provide the second driving oil to the stamping drive device 130 through the second oil passage 230, and controlling the air inlet 110 to provide the second driving air flow to the stamping drive device 130;

[0098] S180, controlling the driving member 320 to drive the working medium in the circulation pipeline 330 to pass through the stamping driving device 130 so that the working medium absorbs the heat energy of the second driving airflow.

[0099] In step S150, the amount of fuel controlled by the fuel supply device 210 through the first branch 222 and the second branch 223 can be adjusted according to actual conditions. The fuel in the oil outlet branch can reach the first branch 222 and the second branch 223 at the same time, or it can only reach one of the first branch 222 or the second branch 223.

[0100] The aircraft control method provided in the embodiment of the present application starts the turbine drive device 120 and the ram drive device 130 to meet the operation of the aircraft reaching a second preset speed, and cools the first driving airflow simultaneously through working fluid cooling and fuel cooling, thereby improving the cooling efficiency of the turbine device, reducing the heat load of the circulating cooling pipeline, and improving the stability and safety of the aircraft operation.

[0101] In some embodiments, the ram drive device 130 includes a ram drive assembly 131 and a ram engine cooling assembly 132. The air inlet 110 is configured to provide a second driving airflow to the ram drive assembly 131. The second oil circuit 230 is connected between the ram drive assembly 131 and the oil supply device 210. The oil supply device 210 is configured to provide a second driving oil to the ram drive assembly 131 via the second oil circuit 230. The ram engine cooling assembly 132 is located on at least a wall surface of the ram drive assembly 131. The circulating pipeline 330 passes through the ram engine cooling assembly 132 to control the oil supply device 210 to provide the second driving oil to the ram drive device 130 via the second oil circuit 230. The second driving oil, the step of controlling the air intake 110 to provide the second driving airflow to the ram drive device 130 includes: controlling the air intake 110 to provide the second driving airflow to the ram drive assembly 131; controlling the oil supply device 210 to provide the second driving oil to the ram drive assembly 131 through the second oil circuit 230 and the ram engine cooling assembly 132; controlling the driving member 320 to drive the working fluid in the circulation pipeline 330 through the ram drive device 130 so that the working fluid absorbs the heat energy of the second driving airflow, including: controlling the driving member 320 to drive the working fluid in the circulation pipeline 330 through the ram engine cooling assembly 132 so that the working fluid absorbs the heat energy of the second driving airflow.

[0102] The aircraft control method provided in the embodiment of the present application controls the oil supply device 210 to provide the second drive oil to the ram drive assembly 131 through the second oil circuit 230 and the ramjet engine cooling assembly 132. Firstly, the ram drive assembly 131 is cooled by multiple cooling methods such as working fluid cooling and fuel cooling in the second oil circuit 230, thereby improving the cooling efficiency of the ram drive assembly 131. Secondly, the turbine drive assembly 122 and the ram drive assembly 131 are cooled by multiple cooling methods. The cooling method can be adjusted according to actual needs, which can be more suitable for the absorption and utilization of various thermal energies. Thirdly, it can also reduce the burden of working fluid cooling, thereby achieving lightweight of the aircraft.

[0103] In some embodiments, the heat energy conversion component 310 includes a converter 311 and a cooler 312. The converter 311 is configured to convert a portion of the heat energy into electrical energy. The oil supply component 200 also includes a converging oil circuit 260. One end of the converging oil circuit 260 is connected to the oil outlet oil circuit 221 and the second oil circuit 230. The converging oil circuit 260 and the circulating pipeline 330 are connected via the cooler 312. The cooler 312 is configured to allow the first driving oil, the second driving oil and the heat energy absorbed by the circulating working medium to perform heat exchange. The oil supply component 200 also includes a return oil circuit 240 and an oil replenishment circuit 250. The oil outlet oil circuit 221, the second oil circuit 230, the circulating pipeline 330, the return oil circuit 240, and the oil replenishment circuit 250. The return oil circuit 240, the oil supply device 210, the replenishing oil circuit 250, the oil outlet oil circuit 221, the oil supply device 210, the return oil circuit 240 is connected between the oil supply device 210 and the converging oil circuit 260 and / or the second branch 223, the replenishing oil circuit 250 is connected between the oil supply device 210 and the converging oil circuit 260, and the driving member 320 is controlled to drive the working fluid in the circulation pipeline 330 through the stamping driving device so that the working fluid absorbs the heat energy of the second driving air flow. The control method also includes: the heat energy includes the first heat energy and the second heat energy, and the converter 311 is controlled to convert the first heat energy into electrical energy; the cooler 312 is controlled to heat exchange the second heat energy with the first driving oil and the second driving oil of the converging oil circuit 260.

[0104] The cooler 312 and the converter 311 jointly absorb or convert the heat energy of the working fluid in the circulation pipeline 330 , and the amount of heat energy cooled by the cooler 312 and the amount of heat energy converted by the converter 311 can be adjusted according to actual conditions.

[0105] The aircraft control method provided in the embodiment of the present application absorbs the first thermal energy through the converter 311 and absorbs the second thermal energy through the cooler 312. The converter 311 converts the first thermal energy into electrical energy for use by the subsystems of the aircraft, and the remaining second thermal energy is absorbed by the first driving oil and the second driving oil. The heat is absorbed by the first driving oil and the second driving oil, which can reduce the thermal load of the converter 311.

[0106] In some embodiments, after controlling the cooler 312 to heat-exchange the second heat energy with the first drive oil and the second drive oil of the converging oil circuit 260, the control method includes: judging the total amount of the first drive oil and the second drive oil passing through the cooler 312 and the oil consumption of the stamping drive assembly 131 and / or the turbine drive assembly 122; if the total amount is greater than the oil consumption, controlling the return oil circuit 240 to open; if the total amount is less than the oil consumption, controlling the oil replenishment circuit 250 to open.

[0107] The amount of oil returned in the oil return circuit 240 and the amount of oil replenished in the oil replenishment circuit 250 can be adjusted according to actual conditions.

[0108] The aircraft control method provided in the embodiment of the present application can ensure that the amount of oil flowing into the turbine drive assembly 122 is the same as the actual fuel consumption through the setting of the return oil circuit 240 and the replenishing oil circuit 250, thereby preventing an imbalance between the fuel supply level and the fuel consumption.

[0109] In some embodiments, controlling the drive member 320 to drive the working fluid in the circulation pipeline 330 through the ram drive device 130 so that the working fluid absorbs the heat energy of the second driving airflow includes: setting the aircraft operating speed to a third preset speed, the third preset speed is greater than the second preset speed; closing the first oil circuit 220; closing the circulation pipeline 330 flowing through the turbine precooling assembly 121.

[0110] The first preset speed, the second preset speed, and the third preset speed may be range values ​​or specific values, and are not specifically limited.

[0111] The aircraft control method provided in the embodiment of the present application adjusts the aircraft's operating speed so that all the working fluid in the circulation pipeline 330 is used for cooling the stamping drive assembly 131, and all the oil in the oil supply assembly 200 is supplied to the stamping drive assembly 131, so that the stamping drive assembly 131 provides sufficient power for the aircraft, thereby maximizing the cooling effect of the stamping drive assembly 131.

[0112] Although the present application has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced with equivalents without departing from the scope of the present application. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A power system, It is characterized in that include: A combined drive assembly, comprising an air inlet, a turbine drive device and a ram drive device, wherein the air inlet is configured to provide a first drive airflow to the turbine drive device and a second drive airflow to the ram drive device; An oil supply assembly, comprising an oil supply device, a first oil circuit and a second oil circuit, wherein the first oil circuit is connected between the oil supply device and the turbine drive device, and the second oil circuit is connected between the oil supply device and the stamping drive device, and the oil supply device is configured to provide a first driving oil to the turbine drive device and a second driving oil to the stamping drive device; A circulating cooling circuit comprises a heat energy conversion component, a driving member and a circulating pipeline, wherein the heat energy conversion component is connected to the turbine driving device and the ram driving device through the circulating pipeline, the driving member is configured to drive the working medium in the circulating pipeline to make the working medium absorb the heat energy of the first driving airflow and the second driving airflow, and at least a part of the heat energy conversion component is configured to convert the heat energy into electrical energy. Among them, the first oil circuit includes an oil outlet circuit, a first branch and a second branch, the outlet of the oil outlet circuit is connected to the inlet of the first branch and the inlet of the second branch, the outlet of the first branch is located upstream of the outlet of the second branch, and the first driving oil through the first branch can flow to the outlet of the second branch after heat exchange with the first driving airflow.

2. The power system according to claim 1, It is characterized in that The turbine drive device includes a turbine precooling assembly and a turbine drive assembly, wherein the turbine precooling assembly is located upstream of the turbine drive assembly and downstream of the air inlet, and the first driving airflow provided by the air inlet enters the turbine drive assembly after passing through the turbine precooling assembly. The circulation pipeline passes through the turbine precooling component so that the working medium exchanges heat with the first driving air flow, and the first branch passes through the turbine precooling component so that the first driving oil exchanges heat with the first driving air flow.

3. The power system according to claim 2, It is characterized in that The turbine precooling assembly comprises: A first part and a second part, the circulation pipeline passes through the first part, and the first branch passes through the second part; Wherein, one of the first part and the second part is located upstream of the other; or, the first part and the second part are arranged along a first direction, and the first direction intersects with a flow direction of the first driving airflow passing through the turbine precooling assembly.

4. The power system according to claim 2, It is characterized in that The punching drive device comprises: A stamping drive assembly, wherein the air inlet is configured to provide the second driving airflow to the stamping drive assembly, the second oil circuit is connected between the stamping drive assembly and the oil supply device, the oil supply device is configured to provide the second driving oil to the stamping drive assembly via the second oil circuit, the stamping drive assembly comprises a stamping wall and a stamping chamber, and the stamping wall encloses the stamping chamber; A ramjet cooling assembly is connected to a side of the ramjet wall facing the ramjet chamber, and the circulation pipeline passes through the ramjet cooling assembly so that the working medium absorbs the heat energy of the second driving airflow passing through the ramjet driving assembly.

5. The power system according to claim 4, It is characterized in that The ramjet cooling assembly comprises: A third portion, located in the stamping chamber, the third portion is connected to a portion of the stamping wall, the circulation pipeline passes through the third portion so that the working medium absorbs heat energy of the second driving air flow passing through the stamping driving assembly; The fourth part is located in the stamping chamber, the fourth part is connected to another part of the stamping wall, and the second oil circuit passes through the fourth part so that the second driving oil enters the stamping drive component after heat exchange with the second driving air flow passing through the stamping drive component.

6. The power system according to claim 4, It is characterized in that The heat energy conversion component includes a converter and a cooler, and the converter is configured to convert a part of the heat energy into the electrical energy. The oil supply component also includes a converging oil circuit, one end of which is connected to the oil outlet oil circuit and the second oil circuit, and the other end of which is connected to the oil supply device. The first driving oil and the second driving oil are divided into the oil outlet oil circuit and the second oil circuit after passing through the converging oil circuit. The converging oil circuit and the circulating pipeline pass through the cooler, and the cooler is configured to allow the first driving oil and the second driving oil passing through the converging oil circuit to perform heat exchange with heat energy absorbed by the working medium in the circulating pipeline.

7. The power system according to claim 6, It is characterized in that The oil supply assembly also includes: An oil return oil circuit connected between the oil supply device and the converging oil circuit and / or the second branch circuit; The oil replenishment circuit is connected between the oil supply device and the converging oil circuit.

8. The power system according to any one of claims 1 to 7, It is characterized in that The number of the combined drive components is more than two, and each of the combined drive components is connected to the oil supply component and the circulating cooling circuit respectively.

9. An aircraft, It is characterized in that Comprising a power system as claimed in any one of claims 1 to 8.

10. A method for controlling an aircraft, It is characterized in that The aircraft control method comprises: Providing an aircraft, the aircraft comprising the power system according to claim 1; Setting the operating speed of the aircraft to a first preset speed; The oil supply device is controlled to provide the first driving oil to the turbine driving device through the oil outlet passage and the second branch passage, and the air intake passage is controlled to provide the first driving air flow to the turbine driving device.

11. The aircraft control method according to claim 10, It is characterized in that The turbine drive device includes a turbine precooling assembly and a turbine drive assembly, wherein the turbine precooling assembly is located upstream of the turbine drive assembly and downstream of the air inlet, and the first driving airflow provided by the air inlet enters the turbine drive assembly after passing through the turbine precooling assembly. After the oil supply device is controlled to supply fuel to the turbine drive device through the oil outlet passage and the second branch passage, and the air intake passage is controlled to provide the first driving airflow to the turbine drive device, the control method further includes: Setting the aircraft running speed to a second preset speed, wherein the second preset speed is greater than the first preset speed; Controlling the oil supply device to sequentially supply the first driving oil to the turbine driving assembly via the oil outlet passage and the first branch passage so as to allow the first driving oil to exchange heat with the first driving air flow; Controlling the driving member to drive the working medium in the circulation pipeline to pass through the turbine precooling assembly so that the working medium absorbs the heat energy of the first driving airflow; Controlling the oil supply device to provide the second driving oil to the stamping drive device through the second oil circuit, and controlling the air inlet to provide the second driving air flow to the stamping drive device; The control driving member drives the working medium in the circulation pipeline to pass through the stamping driving device so that the working medium absorbs the heat energy of the second driving air flow.

12. The aircraft control method according to claim 11, It is characterized in that The ram drive device comprises a ram drive assembly and a ram engine cooling assembly, the air inlet is configured to provide the second drive airflow to the ram drive assembly, the second oil circuit is connected between the ram drive assembly and the oil supply device, the oil supply device is configured to provide the second drive oil to the ram drive assembly via the second oil circuit, the ram engine cooling assembly is located at least on the wall surface of the ram drive assembly, the circulation pipeline passes through the ram engine cooling assembly, The steps of controlling the oil supply device to provide the second driving oil to the stamping drive device through the second oil circuit, and controlling the air inlet to provide the second driving air flow to the stamping drive device include: Controlling the air inlet to provide a second driving airflow to the ram drive assembly; Controlling the oil supply device to supply the second driving oil to the ramjet drive assembly through the second oil circuit and the ramjet engine cooling assembly; The step of controlling the driving member to drive the working medium in the circulation pipeline to pass through the stamping driving device so that the working medium absorbs the heat energy of the second driving air flow includes: The driving member is controlled to drive the working medium in the circulation pipeline to pass through the ramjet engine cooling assembly so that the working medium absorbs the heat energy of the second driving air flow.

13. The aircraft control method according to claim 11, It is characterized in that The heat energy conversion component includes a converter and a cooler, wherein the converter is configured to convert a part of the heat energy into electrical energy, the oil supply component also includes a converging oil circuit, one end of which is connected to the oil outlet oil circuit and the second oil circuit, the converging oil circuit and the circulation pipeline pass through the cooler, and the cooler is configured to allow the first driving oil, the second driving oil and the heat energy absorbed by the circulating working medium to perform heat exchange, the oil supply component also includes a return oil circuit and an oil replenishment circuit, the return oil circuit is connected between the oil supply device and the converging oil circuit and / or the second branch, and the replenishment oil circuit is connected between the oil supply device and the converging oil circuit, After controlling the driving member to drive the working medium in the circulation pipeline to pass through the stamping driving device so that the working medium absorbs the heat energy of the second driving airflow, the control method further includes: The thermal energy includes first thermal energy and second thermal energy, and the converter is controlled to convert the first thermal energy into electrical energy; The cooler is controlled to heat-exchange the second heat energy with the first driving oil and the second driving oil in the merging oil passage.

14. The aircraft control method according to claim 13, It is characterized in that After controlling the cooler to heat-exchange the second heat energy with the first driving oil and the second driving oil in the converging oil circuit, the control method includes: Determine the total amount of the first driving oil and the second driving oil passing through the cooler and the oil consumption of the stamping drive assembly and / or the turbine drive assembly; If the total amount is greater than the oil consumption, the oil return circuit is controlled to open; If the total amount is less than the fuel consumption, the fuel replenishment circuit is controlled to open.

15. The aircraft control method according to claim 11, It is characterized in that After the control driving member drives the working medium in the circulation pipeline to pass through the stamping driving device so that the working medium absorbs the heat energy of the second driving airflow, the control method further includes: Setting the aircraft running speed to a third preset speed, wherein the third preset speed is greater than the second preset speed; Close the first oil circuit; The circulation line flowing through the turbine precooling assembly is closed.

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