CN113353297A - Rapid and uniform static load heating device of high-speed aircraft and control method - Google Patents
Rapid and uniform static load heating device of high-speed aircraft and control method Download PDFInfo
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Abstract
The invention relates to a rapid and uniform static load heating device of a high-speed aircraft and a control method, wherein a loading device of the rapid and uniform static load heating device comprises a rapid and uniform static load heater, a temperature acquisition card, a silicon controlled transformer, a single chip microcomputer, a frequency converter, a fan, a computer, a signal transmission line and a gas transmission pipe; the invention can solve the problems of high experimental cost, low accuracy, long research period and the like in the prior art. Aiming at the target load with nonlinearity and high temperature rise rate in the quartz lamp radiation type pneumatic thermal environment simulation test technology, the traditional control method is improved, the neural network-deep learning strategy is adopted for power control, the common characteristics of the temperature control problems are extracted, the controller with higher universality is designed, and the development of the quartz lamp radiation type pneumatic thermal environment simulation test technology is promoted.
Description
Technical Field
The invention belongs to the technical field of energy, and particularly relates to a rapid and uniform static load heating device of a high-speed aircraft and a control method.
Background
With the rapid development of scientific technology, rocket technology plays an increasingly important role in the field of aerospace, and how to simulate the thermal environment of a rocket engine becomes a problem which cannot be ignored. In early aircraft engine design, most of them were analyzed by obtaining simulation data using simulation experiments, such as aerodynamic thermal simulation, including "convective method" represented by expensive wind tunnel experiment and "non-convective method" represented by quartz lamp radiative aerodynamic thermal environment simulation. However, in the traditional quartz lamp radiation type pneumatic thermal environment simulation test technology in a non-convection mode, the modes such as fuzzy control, fuzzy adaptive PID control and the like are adopted, the number of intermediate parameters to be controlled is large, the selection of membership function and quantization factor is based on experience, and a controller needs to be redesigned according to the requirement of a specific simulation experiment, so that the research period is long, the waste of manpower and material resources is caused, and the rapid and uniform heating cannot be realized.
Disclosure of Invention
The invention aims to provide a rapid and uniform static load heating device and a control method for a high-speed aircraft, and aims to solve the problems of high experiment cost, low accuracy, long research period, non-uniform heating and the like in the prior art. Aiming at the target load with nonlinearity and high temperature rise rate in the quartz lamp radiation type pneumatic thermal environment simulation test technology, the traditional control method is improved, the neural network-deep learning strategy is adopted for power control, the common characteristics of the temperature control problems are extracted, the controller with higher universality is designed, and the development of the quartz lamp radiation type pneumatic thermal environment simulation test technology is promoted.
In order to solve the technical problems, the invention is realized by the following technical scheme:
a rapid and uniform static load heating device of a high-speed aircraft comprises a rapid and uniform static load heater, a temperature acquisition card, a silicon controlled transformer, a singlechip, a frequency converter, a fan and a computer;
the rapid and uniform static load heater comprises an aluminum alloy bracket, a quartz lamp tube, an annular air distribution plate, a thermocouple, a heat shielding cover and an aircraft heating shell; the two annular air distribution plates are respectively arranged at two ends of the aircraft heating shell, and the quartz lamp tubes are arranged outside the aircraft heating shell along the length direction of the aircraft; the aluminum alloy bracket fixes and limits the quartz lamp tube and the annular air distribution plate, and adjusts the distance between the quartz lamp tube and the aircraft heating shell; the heat shield covers the periphery of the aluminum alloy bracket; the thermocouples are uniformly distributed on the aircraft heating shell;
the single chip microcomputer is electrically connected with the silicon controlled transformer, the temperature acquisition card, the frequency converter and the computer through signal transmission lines; the frequency converter is electrically connected with the fan; and the fan leads out two gas pipes which are respectively connected with the two annular air distribution plates of the rapid and uniform static load heater.
As a further improvement of the invention, the annular air distribution plate is provided with a connecting air port and an annular air distribution channel, and a through hole is arranged in the middle of the annular air distribution channel; the connecting air port is communicated with the annular air distribution channel.
As a further development of the invention, the thermocouple is attached to the surface of the aircraft heating shell.
As a further improvement of the invention, the heat shield material is aluminum foil.
As a further improvement of the invention, the aluminum alloy bracket is an annular bracket, and the annular bracket is radially provided with a plurality of mounting grooves pointing to the circle center; at least two the aluminum alloy support is a set of, and multiunit aluminum alloy support interval sets up outside aircraft heating casing and connects through the connecting rod, the quartz lamp tube is installed on the mounting groove.
As a further improvement of the invention, the quartz lamp tubes are arranged in a manner of being divided into a plurality of sections in the vertical direction and are arranged in a surrounding manner in the horizontal direction.
As a further improvement of the invention, one end of the aircraft heating shell is open, and the other end is provided with a fan; the fan is placed at the lower end of the rapid and uniform static load heater.
A control method of a rapid and uniform static load heating device of a high-speed aircraft comprises the following steps:
acquiring temperature data of each measuring point for measuring the temperature of the aircraft heating shell in real time by a thermocouple through a temperature acquisition card;
the computer carries out temperature control calculation according to the temperature data to obtain the heating power of the quartz lamp tube at the next moment;
in the singlechip for sending the heating power, the singlechip analyzes and processes the output power control signal to control the silicon controlled transformer to regulate the power of the quartz lamp tube; simultaneously controlling a frequency converter to adjust the frequency of the fan; the fan is controlled by frequency conversion and then changes the air output through the air delivery pipe; the fan is respectively connected with the upper annular air distribution plate and the lower annular air distribution plate, and the fan exchanges heat with the rapid and uniform static load heater after the regulation action of the frequency converter.
As a further improvement of the invention, the temperature control calculation is obtained by a deep reinforcement learning algorithm; the training model comprises the following steps:
creating an environment, creating an experience pool, constructing a heating process data simulation model, starting a deep reinforcement learning algorithm for training, if the number of training rounds is not exceeded, training according to the training model, and if the number of training rounds is exceeded, ending the training and storing the model.
As a further improvement of the invention, the specific steps of constructing the heating process data simulation model are as follows:
after environment initialization and temperature distribution input, selecting heating power according to the neural network to obtain the temperature distribution at the next moment, comparing the temperature distribution of the previous time and the temperature distribution of the next time to obtain a reward value, then judging whether the temperature distribution meets the final requirement, if not, updating the current temperature distribution and returning to retraining, and if so, updating the parameters of the neural network and ending one round of training.
Compared with the prior art, the invention has the beneficial effects that:
compared with the traditional simulation device adopting the modes of fuzzy control, fuzzy adaptive PID control and the like, the rapid and uniform static load heating device for the high-speed aircraft improves the traditional control method aiming at the target load with non-linearity and high heating rate in the quartz lamp radiation type pneumatic thermal environment simulation test technology, adopts the neural network-deep learning strategy to carry out power control, and can realize instantaneous control; by applying the deep reinforcement learning theory, the control strategy of the heater can be continuously corrected in the use process of the rapid and uniform static load heater, and the ideal control effect is approached. After the rocket engines with different diameters are replaced, the control strategy does not need to be trained from zero again, only the basic part of the neural network trained before is moved to a new rocket engine heating model, and the model can rapidly learn the control of the rocket through the mode of automatically adjusting the program learning rate. The invention can solve the problems of high experimental cost, low accuracy, long research period and the like in the prior art. Aiming at the target load with nonlinearity and high temperature rise rate in the quartz lamp radiation type pneumatic thermal environment simulation test technology, the traditional control method is improved, the neural network-deep learning strategy is adopted for power control, the common characteristics of the temperature control problems are extracted, the controller with higher universality is designed, and the development of the quartz lamp radiation type pneumatic thermal environment simulation test technology is promoted.
Furthermore, the invention adopts an innovative and effective heating device, and the rapid and uniform static load heater mainly has the following three characteristics: 1. multi-stage control; 2. the method is rapid and uniform; 3. circularly blowing air; 4. and energy is converged. The quartz lamp tubes are arranged in a multi-section manner in the vertical direction and are arranged in a surrounding manner in the horizontal direction, so that the circumferential uniform radiation in the horizontal direction can be achieved, a uniform temperature field is formed, and meanwhile, the rapid temperature rise of the heating shell of the aircraft is achieved; the upper end part and the lower end part of the rapid uniform static load heater are respectively provided with an annular air distribution plate, the upper end annular air distribution plate is used for absorbing hot air, and the lower end annular air distribution plate is used for uniformly spraying hot air in the circumferential direction, so that the circulating air supply effect of reducing convection temperature difference and reducing hot air loss is achieved. In addition, the energy convergence is realized by adopting a reflecting material, a coating on the surface of the quartz lamp tube and a heat shielding cover made of aluminum foil.
Furthermore, the invention adopts a three-layer control, transmission and execution system which consists of a rapid and uniform static load heater, a temperature acquisition card, a silicon controlled transformer, a singlechip and the like. The thermocouple for collecting the temperature of the heated member is adhered to the surface of the heated member and connected with the temperature collecting board, the temperature data of each measuring point is collected into a computer through a data collecting line, the program in the computer calculates through a temperature control program according to the collected temperature data to obtain the heating power which is required to be achieved by the lamp tube at the next moment, the heating power is transmitted into a single chip microcomputer through a port, the single chip microcomputer analyzes and processes a power control signal, the pulse signal is amplified through an amplifying circuit, and a thyristor transformer is controlled to regulate the power of the quartz lamp tube. The specific three-layer structure is shown in detail in fig. 3.
Furthermore, the invention adopts GUI interface design, and can display basic information, parameter setting and control buttons, such as temperature of each measuring point, control heating, operation of an air pump and the like.
Drawings
The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.
FIG. 1 is a schematic view of a rapid uniform static load heating device for a high-speed aircraft according to the present invention;
FIG. 2 is a diagram of an arrangement of a fast uniform deadload heater;
FIG. 3 is a conceptual diagram of a control method based on deep reinforcement learning;
FIG. 4 is a three-dimensional schematic view of an annular air distribution plate;
FIG. 5 is a flow chart of a deep reinforcement learning control method in the field of artificial intelligence;
FIG. 6 is a flow chart of a deep reinforcement learning training model construction method in the field of artificial intelligence;
FIG. 7 is a diagram of a neural network training algorithm;
FIG. 8 is a flow chart of a neural network training module.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the technical solution in the embodiment of the present invention will be clearly and completely described below with reference to the drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiment of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, shall fall within the scope of protection of the present invention.
The invention is further illustrated by way of example in the following figures.
Referring to fig. 1, the invention relates to a rapid and uniform static load heating device for a high-speed aircraft, which comprises a rapid and uniform static load heater a, a temperature acquisition card b, a thyristor transformer c, a single chip microcomputer d, a frequency converter e, a fan f, a computer g, a signal transmission line h and a gas transmission pipe i.
In which, as shown in FIG. 2,
the rapid and uniform static load heater a comprises an aluminum alloy support 1, a quartz lamp tube 2, an annular air distribution plate 3, a thermocouple 4, a heat shielding cover 5, a fan 6 and an aircraft heating shell 7. The aluminum alloy support 1 serves as a framework of the rapid and uniform static load heater system a and plays a role in fixing the quartz lamp tubes 2 and the annular air distribution plates 3, the quartz lamp tubes 2 are arranged in multiple sections in the vertical direction, the horizontal direction is arranged in a surrounding mode, and rapid and uniform heating of the aircraft heating shell can be achieved. In addition, the upper end part and the lower end part of the rapid uniform static load heater a are respectively provided with an annular protruding type annular air distribution plate 3, the upper end annular air distribution plate 3 is used for absorbing hot air, the lower end annular air distribution plate 3 is used for uniformly spraying the hot air in the circumferential direction, uniform heating of circulating air is realized, and the two annular air distribution plates 3 are connected through a small-sized air feeder;
the rapid and uniform static load heater a is connected with a temperature acquisition card b and a silicon controlled transformer c through a signal transmission line h and is connected with a fan f through a gas transmission pipe i.
Thermocouple 4 among the quick even quiet load heater device a pastes on the surface of aircraft heating casing 7, measures the temperature of aircraft heating casing 7 in real time and gives temperature collection card b with data transfer, and annular grid plate 3 places in the upper and lower both ends of quick even quiet load heater, and on it was fixed in the pole on the aluminum alloy support 1, upper end annular grid plate 3 was used for absorbing the hot-air, and lower extreme annular grid plate 3 is used for the even blowout hot-air of circumference, and two annular grid plates 3 link to each other through a fan f.
The aluminum alloy support 1 in the rapid and uniform static load heater a serves as a framework of the rapid and uniform static load heater system a, the quartz lamp tube 2 and the annular air distribution plate 3 are fixed, and meanwhile the sawtooth-shaped special structural design is adopted, so that the distance between the quartz lamp tube 2 and the aircraft heating shell 7 is adjusted, and the radiation heat exchange between the quartz lamp tube 2 and the aircraft heating shell 7 is flexible.
Wherein, the arrangement mode of quartz lamp tube 2 in quick even static load heater a is for dividing the multistage in vertical direction and arranging, and the horizontal direction is the type of encircleing and arranges, and this kind of arrangement mode can reach the even radiation of circumference of horizontal direction, and the effect of power is controlled respectively as required in the vertical direction, realizes the quick even heating of aircraft heating casing 7 simultaneously.
Wherein, annular air distribution plate 3 in the quick even static load heater a adopts annular outstanding structural design, and lower extreme annular air distribution plate 3 absorbs the hot-air that is carried over through gas-supply pipe i by fan f and spouts the hot-air, and upper end annular air distribution plate 3 absorbs the hot-air and carries the hot-air to fan f through gas-supply pipe i, and this structural design has realized the even heating of circulated air of aircraft heating casing 7. The specific structure of the annular air distribution plate is shown in detail in figure 4.
The heat shielding cover 5 is made of aluminum foil material, and the material has the characteristic of low absorption rate of the inner wall, so that the heat shielding cover 5 has excellent heat insulation performance, and heat loss of a system is reduced.
Wherein, the plurality of thermocouples 4 used for collecting the temperature of the aircraft heating shell 7 are adhered on the surface of the aircraft heating shell 7 and connected with the temperature collecting board card b, the temperature data of each measuring point is collected into the computer g through the data collecting line h, the program in the computer obtains the heating power of the quartz lamp tube 2 at the next moment through the calculation of the temperature control program according to the collected temperature data, the heating power is transmitted into the singlechip d through a port, the singlechip analyzes and processes the output power control signal, the pulse signal is amplified through the amplifying circuit, the thyristor transformer c is controlled to regulate the power of the quartz lamp tube 2, the frequency converter e is controlled to regulate the frequency of the fan f, the fan f changes the air supply amount through the air conveying pipe i after being controlled by frequency conversion, and then the convection heat exchange between the aircraft heating shell 7 and the air is regulated, the above steps are repeated in a circulating way;
two gas pipes i are led out of the fan f and are respectively connected with the upper annular air distribution plate 3 and the lower annular air distribution plate 3, and the fan f exchanges heat with the rapid and uniform static load heater after the regulation action of the frequency converter e. The frequency converter e is connected with the single chip microcomputer d, and the single chip microcomputer d transmits a control signal to the frequency converter e so as to control the frequency converter e.
Two pins are led out from the lower end of the rapid and uniform static load heater device a and are respectively connected with the temperature acquisition card b and the silicon controlled transformer c, and the silicon controlled transformer c is used as a power control unit of the whole rapid and uniform static load heater a, receives a power control signal transmitted by the singlechip d and controls the power of the quartz lamp tube 2 in the rapid and uniform static load heater device a. And after the thermocouple 4 in the rapid and uniform static load heater device a measures the temperature of the heating shell 7 of the aircraft, transmitting the temperature data to the temperature acquisition card b.
As a preferred embodiment, the singlechip d is connected with the thyristor transformer c, the temperature acquisition card b, the frequency converter e and the computer g through a signal transmission line h. The singlechip d transmits temperature data to the computer g and receives control information transmitted by the computer g so as to effectively control the frequency converter e and the silicon controlled transformer c.
As a preferred embodiment, the frequency converter e is connected with the fan f and the singlechip d through a signal transmission line h, and the frequency converter e performs frequency conversion control on the fan f.
As a preferred embodiment, the temperature acquisition card b is connected with the rapid and uniform static load heater a and the singlechip d through a signal transmission line h, and the temperature acquisition card b acquires temperature data transmitted by the thermocouple 4 in real time and transmits the temperature data to the singlechip d.
As a preferred embodiment, the thyristor transformer c is connected with the rapid and uniform static load heater a and the singlechip d through the signal transmission line h, and the power of the quartz lamp tube 2 in the rapid and uniform static load heater a is controlled according to requirements.
As a preferred embodiment, the computer g is connected with the singlechip d through a signal transmission line h, receives temperature data transmitted by the singlechip d, calculates through a depth reinforcement learning program, outputs a corresponding control signal and transmits the control signal to the singlechip d, and therefore relevant devices are effectively controlled.
Referring to fig. 3, a conceptual diagram of a control method of a fast and uniform static load heating device for a high-speed aircraft is shown. The system has three layers of structures: control layer, transport layer, executive layer.
According to the deep reinforcement learning control method in the field of artificial intelligence, the control layer 1, the transmission layer 2 and the execution layer 3 are adopted to perform controllable operation on the whole loading device, and the heating of the aircraft heating shell 7 is realized according to the user requirements. And meanwhile, the rapid and uniform static heat of the high-speed aircraft is effectively simulated.
The control layer includes virtual training, user interface, and gathering feedback. The user sets the control computer g according to the parameters of the user interface to perform the numerical simulation of the heating process, and simultaneously, the control computer g is matched with the deep reinforcement learning algorithm to train networks meeting the requirements, including a neural network, a migration network, a personalized network, a calling network and the like. After the network training is finished, the computer g transmits training data to the transmission layer, and the silicon controlled transformer c and the programmable frequency converter e are further controlled through the singlechip d.
The thyristor transformer c is provided with a voltage transformation circuit and a signal amplification circuit, and the programmable frequency converter e is provided with a frequency conversion circuit and a signal amplification circuit. The thyristor transformer c can perform voltage transformation control on the quartz lamp tube 2 in the rapid and uniform static load heater a, so that the radiation power of the quartz lamp tube 2 is changed. The programmable frequency converter e controls the frequency of the small fan f, and further controls the heat exchange between the small fan f and the heating shell 7 of the aircraft. The quartz lamp tube array 2 controls the radiation heat exchange with the heated shell 7 of the aircraft, and the small fan f controls the convection heat exchange with the heated shell 7 of the aircraft.
The thermocouple 4 in the execution layer measures the temperature value of each measuring point on the heating shell 7 of the aircraft, the temperature data is transmitted to the temperature acquisition card b of the transmission layer, the temperature acquisition card b feeds the data back to the singlechip d after collecting the data, the data is further fed back to the computer g, the network is retrained through a depth reinforcement learning algorithm, and the operation is repeated in such a circulating way to meet the heat exchange requirement of the heating shell of the aircraft.
As a preferred embodiment, the computer g is connected with the singlechip d through a signal transmission line h, receives temperature data transmitted by the singlechip d, calculates through a depth reinforcement learning program, outputs a corresponding control signal and transmits the control signal to the singlechip d, and therefore relevant devices are effectively controlled.
Please refer to fig. 4, which is a schematic view of an annular air distribution plate. The annular air distribution plate 3 is provided with a connecting air port and an annular air distribution channel, and a through hole is formed in the middle of the annular air distribution channel; the connecting air port is communicated with the annular air distribution channel.
As a preferred embodiment, the upper and lower annular air distribution plates are annular, which facilitates uniform flow of air and adequate heat exchange with the aircraft heating shell.
Please refer to fig. 5, which is a GUI interface control flow diagram.
The deep reinforcement learning control method in the artificial intelligence field is mainly characterized in that a main process is started from a main program to create an environment and an experience pool, then a model is further built, then training is started, if the number of training rounds is not exceeded, training is carried out according to the training model, and if the number of training rounds is exceeded, the training is ended and the model is saved.
Please refer to fig. 6, which is a schematic flowchart of the start training in fig. 6. The main process of the training model comprises the steps of initializing the environment, selecting actions (namely power values) according to the neural network after temperature distribution is input, obtaining the temperature distribution of the next moment by a specific training algorithm shown in figure 7, comparing the temperature distribution of the previous time and the temperature distribution of the next time to obtain a reward value, judging whether the temperature distribution meets the final requirement, updating the current temperature distribution and returning to retraining if the temperature distribution does not meet the final requirement, updating parameters of the neural network if the temperature distribution does not meet the final requirement, and finishing one round of training.
As shown in fig. 8, according to the temperature distribution, a three-layer fully-connected network is obtained through DQN neural network training, the distribution probability of the control voltage is output, and the voltage with the maximum corresponding probability is selected.
As a preferred embodiment, the user interface can effectively control the system according to the requirements of the user. The user can set parameters, such as: the outer diameter, wall thickness, material and heated target temperature of the heated shell 7 of the aircraft are used for computer training. Meanwhile, a temperature curve of each measuring point of the heated shell 7 of the aircraft can be drawn, and more intuitive feedback is provided for a user. The interface is also provided with a 'training start' button and an air pump switch button.
The invention relates to a rapid and uniform static load heating device of a high-speed aircraft, which comprises the following parts:
the system comprises a rapid and uniform static load heater a, a temperature acquisition card b, a silicon controlled transformer c, a single chip microcomputer d, a frequency converter e, a fan f, a computer g, a signal transmission line h, a gas transmission pipeline i and the like.
A plurality of thermocouples 4 used for collecting the temperature of a heated piece are pasted on the surface of an aircraft heating shell 7 and connected with a temperature collecting board card b, the temperature data of each measuring point is collected into a computer g through a data collecting line h, a program in the computer calculates through a temperature control program according to the collected temperature data to obtain the heating power required by the quartz lamp tube 2 at the next moment, the heating power is transmitted into a single chip microcomputer d through a port, a power control signal is output through analysis and processing of the single chip microcomputer, and after the pulse signal is amplified through an amplifying circuit, the power of the quartz lamp tube 2 is controlled to be regulated by a silicon controlled transformer c.
Compared with the traditional fuzzy control and fuzzy self-adaptive PID control, the method improves the traditional control method, adopts a neural network-deep learning strategy to carry out power control, extracts the common characteristics of the temperature control problems, designs the controller with higher universality as the energy collection system, and promotes the development of the quartz lamp radiation type pneumatic thermal environment simulation test technology.
According to the deep reinforcement learning control method in the field of artificial intelligence, a control layer, a transmission layer and an execution layer are adopted to perform controllable operation on the whole loading device, and heating of the shell is achieved according to user requirements. And meanwhile, the rapid and uniform static heat of the high-speed aircraft is effectively simulated.
The invention can solve the problems of high experimental cost, low accuracy, long research period and the like in the prior art. Aiming at the target load with nonlinearity and high temperature rise rate in the quartz lamp radiation type pneumatic thermal environment simulation test technology, the traditional control method is improved, the neural network-deep learning strategy is adopted for power control, the common characteristics of the temperature control problems are extracted, the controller with higher universality is designed, and the development of the quartz lamp radiation type pneumatic thermal environment simulation test technology is promoted.
It is clear to those skilled in the art that, for convenience and brevity of description, the specific working processes of the above-described systems, apparatuses and units may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again.
The terms "first," "second," "third," "fourth," and the like in the description of the application and the above-described figures, if any, are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are, for example, capable of operation in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed, but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
It should be understood that in the present application, "at least one" means one or more, "a plurality" means two or more. "and/or" for describing an association relationship of associated objects, indicating that there may be three relationships, e.g., "a and/or B" may indicate: only A, only B and both A and B are present, wherein A and B may be singular or plural. The character "/" generally indicates that the former and latter associated objects are in an "or" relationship. "at least one of the following" or similar expressions refer to any combination of these items, including any combination of single item(s) or plural items. For example, at least one (one) of a, B, or C, may represent: a, B, C, "A and B", "A and C", "B and C", or "A and B and C", wherein A, B, C may be single or plural.
In the several embodiments provided in the present application, it should be understood that the disclosed system, apparatus and method may be implemented in other manners. For example, the above-described apparatus embodiments are merely illustrative, and for example, the division of the units is only one logical division, and other divisions may be realized in practice, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions in the embodiments of the present application.
Claims (10)
1. A rapid and uniform static load heating device of a high-speed aircraft is characterized by comprising a rapid and uniform static load heater (a), a temperature acquisition card (b), a silicon controlled transformer (c), a singlechip (d), a frequency converter (e), a fan (f) and a computer (g);
the rapid and uniform static load heater (a) comprises an aluminum alloy bracket (1), a quartz lamp tube (2), an annular air distribution plate (3), a thermocouple (4), a heat shielding cover (5) and an aircraft heating shell (7); the two annular air distribution plates (3) are respectively arranged at two ends of an aircraft heating shell (7), and the quartz lamp tubes (2) are arranged outside the aircraft heating shell (7) along the length direction of the aircraft; the aluminum alloy bracket (1) fixes and limits the quartz lamp tube (2) and the annular air distribution plate (3), and adjusts the distance between the quartz lamp tube (2) and the aircraft heating shell (7); the heat shield (5) surrounds the periphery of the aluminum alloy bracket (1); the thermocouples (4) are uniformly distributed on the aircraft heating shell (7);
the single chip microcomputer (d) is electrically connected with the silicon controlled transformer (c), the temperature acquisition card (b), the frequency converter (e) and the computer (g) through a signal transmission line (h); the frequency converter (e) is electrically connected with the fan (f); and two gas transmission pipes (i) led out from the fan (f) are respectively connected with the two annular air distribution plates (3) of the rapid and uniform static load heater (a).
2. The rapid uniform static load heating device for the high-speed aircraft according to claim 1, wherein the annular air distribution plate (3) is provided with a connecting air port and an annular air distribution channel, and a through hole is formed in the middle of the annular air distribution channel; the connecting air port is communicated with the annular air distribution channel.
3. A rapid and uniform dead load heating device for a high-speed aircraft according to claim 1, characterized in that the thermocouple (4) is attached to the surface of the aircraft heating shell (7).
4. A rapid and uniform static load heating device for a high-speed aircraft according to claim 1, characterized in that the heat shield (5) is made of aluminum foil.
5. The rapid and uniform static load heating device for the high-speed aircraft according to claim 1, wherein the aluminum alloy support (1) is an annular support, and the annular support is provided with a plurality of mounting grooves pointing to the circle center along the radial direction; at least two aluminum alloy support (1) are a set of, and multiunit aluminum alloy support interval sets up in aircraft heating casing (7) outside and connects through the connecting rod, quartz lamp tube (2) are installed on the mounting groove.
6. The rapid and uniform static load heating device for the high-speed aircraft as claimed in claim 1, wherein the quartz lamp tubes (2) are arranged in a vertical direction in multiple sections and in a surrounding manner in a horizontal direction.
7. A high-speed aircraft rapid uniform static load heating device according to claim 1, characterized in that the aircraft heating shell (7) is open at one end and is provided with a fan (6) at the other end; the fan (6) is placed at the lower end of the rapid and uniform static load heater (a).
8. The control method of the rapid and uniform static load heating device of the high-speed aircraft as claimed in any one of claims 1 to 7, characterized by comprising the following steps:
temperature data of each measuring point for measuring the temperature of the aircraft heating shell (7) in real time by the thermocouple (4) are obtained through a temperature acquisition card (b);
the computer (g) carries out temperature control calculation according to the temperature data to obtain the heating power of the quartz lamp tube (2) at the next moment;
in the singlechip (d) for sending the heating power, the singlechip (d) analyzes and processes the output power control signal and controls the silicon controlled transformer (c) to adjust the power of the quartz lamp tube (2); simultaneously controlling a frequency converter (e) to adjust the frequency of the fan (f); the fan (f) is controlled by frequency conversion and then changes the air output through the air delivery pipe (i); are respectively connected with the upper annular air distribution plate and the lower annular air distribution plate (3), and the fan (f) exchanges heat with the rapid uniform static load heater after the regulation action of the frequency converter (e).
9. The control method of the rapid uniform static load heating device of the high-speed aircraft according to claim 8, wherein the temperature control calculation is obtained by a deep reinforcement learning algorithm; the training model comprises the following steps:
creating an environment, creating an experience pool, constructing a heating process data simulation model, starting a deep reinforcement learning algorithm for training, if the number of training rounds is not exceeded, training according to the training model, and if the number of training rounds is exceeded, ending the training and storing the model.
10. The control method of the rapid and uniform static load heating device of the high-speed aircraft according to claim 9, wherein the specific steps of constructing the heating process data simulation model are as follows:
after environment initialization and temperature distribution input, selecting heating power according to the neural network to obtain the temperature distribution at the next moment, comparing the temperature distribution of the previous time and the temperature distribution of the next time to obtain a reward value, then judging whether the temperature distribution meets the final requirement, if not, updating the current temperature distribution and returning to retraining, and if so, updating the parameters of the neural network and ending one round of training.
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