阅读说明：本技术 一种冲压式红外增强器 (Infrared reinforcing ware of punching press formula ) 是由 王磊 于 2020-06-05 设计创作，主要内容包括：本发明公开了一种冲压式红外增强器,涉及航空技术领域。本发明的冲压式红外增强器,包括进气装置、燃料供给装置、燃烧室和控制装置,其中,控制装置与进气装置和燃料供给装置连接,并且进气装置和燃料供给装置还与燃烧室连通,使得进气装置能够在控制装置的作用下为燃烧室提供助燃气体,燃料供给装置能够在控制装置的作用下为燃烧室提供液体燃料和/或气体燃料；控制装置还与燃烧室连接,以通过控制装置控制燃烧室内液体燃料和/或气体燃料的燃烧。本发明的冲压式红外增强器使用液体燃料和/或气体燃料,使得燃烧速度可控,而且燃烧时间较长,将其用于无人机的迎头和/或尾后,工作时间长,可满足无人机所需的飞行速度域和高度域。(The invention discloses a stamping type infrared enhancer and relates to the technical field of aviation. The ram-type infrared enhancer comprises an air inlet device, a fuel supply device, a combustion chamber and a control device, wherein the control device is connected with the air inlet device and the fuel supply device, the air inlet device and the fuel supply device are also communicated with the combustion chamber, so that the air inlet device can provide combustion-supporting gas for the combustion chamber under the action of the control device, and the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber under the action of the control device; the control device is also connected to the combustion chamber for controlling the combustion of the liquid fuel and/or the gaseous fuel in the combustion chamber by means of the control device. The ram-type infrared enhancer disclosed by the invention uses liquid fuel and/or gas fuel, so that the combustion speed is controllable, the combustion time is long, the ram-type infrared enhancer is long in working time after being used for the head and/or tail of an unmanned aerial vehicle, and the required flight speed domain and the required altitude domain of the unmanned aerial vehicle can be met.)

1. A ram-type infrared enhancer, characterized by comprising an air intake device, a fuel supply device, a combustion chamber (1) and a control device (2), wherein,

the control device (2) is connected with the air inlet device and the fuel supply device, and the air inlet device and the fuel supply device are also communicated with the combustion chamber (1), so that the air inlet device can provide combustion-supporting gas for the combustion chamber (1) under the action of the control device (2), and the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber (1) under the action of the control device (2);

the control device (2) is also connected with the combustion chamber (1) to control the combustion of liquid fuel and/or gaseous fuel in the combustion chamber (1) by means of the control device (2).

2. The stamped infrared enhancer of claim 1, wherein the air inlet means comprises an air inlet channel (3) and an air inlet tube (4), wherein,

the air inlet (3) is a fixed punching air inlet, the outer surface of the air inlet is of a conical structure,

intake pipe (4) set up in the afterbody of intake duct (3), and intake pipe (4) with combustion chamber (1) intercommunication, in order to pass through intake duct (3) with intake pipe (4) to combustion chamber (1) provides combustion-supporting gas.

3. The impact infrared enhancer of claim 1, characterized in that the fuel supply means comprise a fuel tank (5), the fuel tank (5) being intended to store propane fuel, and the fuel tank (5) communicating with the combustion chamber (1) through a first delivery duct (6).

4. The impact infrared enhancer of claim 3, characterized in that the fuel supply device further comprises a second delivery duct (7), one end of the second delivery duct (7) being in communication with the tank of the drone and the other end being in communication with the fuel tank (5) via a solenoid valve (8) and an oil pump (9), so that the drone can deliver jet fuel to the combustion chamber (1) through the second delivery duct (7).

5. The impact infrared enhancer of claim 1, further comprising an ignition device connected to the combustion chamber (1) and the control device (2) such that the ignition device can ignite and burn fuel in the combustion chamber (1) under the action of the control device (2).

6. The stamped infrared enhancer of claim 5, characterized in that the ignition device comprises an ignition box (10) and an ignition mouth (11), wherein the ignition box (10) is connected to the control device (2); the ignition nozzle (11) is arranged on the combustion chamber (1), and the ignition nozzle (11) is also connected with the ignition box (10).

7. The ram-type infrared enhancer as recited in claim 1, further comprising a nozzle (12), wherein the nozzle (12) is disposed at the rear of the combustion chamber (1), and the nozzle (12) is further connected to the control device (2) so that the nozzle (12) can eject the combusted gas in the combustion chamber (1) under the action of the control device (2).

8. The stamped infrared enhancer of claim 1, further comprising a power supply device, wherein the power supply device is a battery (13) or an unmanned aerial vehicle power supply, and the power supply device is connected with the control device (2) to supply power to the control device (2) through the power supply device.

9. The impact infrared enhancer of claim 1, characterized in that it further comprises a housing (14), said housing (14) being located at the end of the air intake duct (3), and said fuel supply means, said combustion chamber (1), said control means (2), ignition means and nozzle (12) being located inside said housing (14).

10. The stamped infrared enhancer of claim 9, wherein the housing (14) is provided with a pitot tube (15) and at least one mounting seat (16), wherein,

the airspeed head (15) is arranged on the upper end face of the shell (14), and the airspeed head (15) is used for detecting the flight speed of the unmanned aerial vehicle;

at least one mount pad (16) set up in the lower terminal surface of casing (14) to through at least one mount pad (16) will punching press formula infrared reinforcement install on unmanned aerial vehicle.

Technical Field

The invention relates to the technical field of aviation, in particular to a stamping type infrared enhancer.

Background

The target drone is used as a dynamic simulator for replacing a real aircraft, is mainly used for simulating a real flying target, and provides a dynamic simulation target with certain fidelity for evaluating detection, tracking and guidance of various air defense weapons. However, except for individual large targets, the size and mass of most targets are generally smaller than those of real flying targets, and the infrared characteristics of the targets are far from those of the real targets. In order to effectively simulate the infrared radiation characteristics of a real flying target, it is necessary to mount enough infrared enhancement equipment on the target drone.

The infrared enhancement equipment is researched by military strong countries in the world since the 60 th century. At present, the infrared enhancement equipment widely applied to the target drone mainly comprises two types, one type is an infrared mop, and the other type is an infrared wingtip pod. The infrared enhancement equipment carried on the target drone generally enhances the infrared characteristic of the target drone by adjusting the infrared radiation intensity of the infrared enhancement equipment through burning fuel at present in China, and approaches the real simulated target characteristic so as to accurately identify the comprehensive performance of various weapon systems.

The existing commonly used infrared intensifier takes high-temperature flame generated by burning of internal gunpowder and a metal shell heated by the flame as an infrared intensifying source, the gunpowder is burnt violently but has short duration, the infrared intensifying is carried out in the fuel burning mode, the infrared intensifying effect is limited by the burning radiation characteristic of the fuel, and the controllability and the adjustability are difficult to realize. Make present unmanned aerial vehicle's infrared intensifier be used for the head-on, operating time is shorter, can not satisfy required airspeed field of unmanned aerial vehicle and high field. Therefore, it is urgently needed to provide a universal infrared enhancer, so that the target drone can simulate a real combat airplane and is suitable for a larger flight speed domain and a larger altitude domain.

Disclosure of Invention

One of the purposes of the invention is to provide a stamping type infrared enhancer, which solves the technical problems that the infrared enhancer in the prior art takes gunpowder as fuel, the combustion duration is short, the infrared enhancer is used for head-on, the working time is short, and the required flight speed domain and the required altitude domain of an unmanned aerial vehicle cannot be met. The various technical effects that can be produced by the preferred technical solution of the present invention are described in detail below.

In order to achieve the purpose, the invention provides the following technical scheme:

the ram-type infrared enhancer comprises an air inlet device, a fuel supply device, a combustion chamber and a control device, wherein the control device is connected with the air inlet device and the fuel supply device, the air inlet device and the fuel supply device are also communicated with the combustion chamber, so that the air inlet device can provide combustion-supporting gas for the combustion chamber under the action of the control device, and the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber under the action of the control device; the control device is also connected with the combustion chamber so as to control the combustion of liquid fuel and/or gas fuel in the combustion chamber through the control device.

According to a preferred embodiment, air inlet unit includes intake duct and intake pipe, wherein, the intake duct is fixed punching press intake duct, and its surface is the toper structure, the intake pipe set up in the afterbody of intake duct, and the intake pipe with the combustion chamber intercommunication, in order to pass through the intake duct with the intake pipe to the combustion chamber provides combustion-supporting gas.

According to a preferred embodiment, the fuel supply means comprise a fuel tank for storing propane fuel and communicating with the combustion chamber through a first delivery duct.

According to a preferred embodiment, the fuel supply device further comprises a second delivery pipe, one end of the second delivery pipe is communicated with an oil tank of the unmanned aerial vehicle, and the other end of the second delivery pipe is communicated with the fuel tank through an electromagnetic valve and an oil pump, so that the unmanned aerial vehicle can deliver the aviation kerosene to the combustion chamber through the second delivery pipe.

According to a preferred embodiment, the ram-type infrared enhancer further comprises an ignition device, and the ignition device is connected with the combustion chamber and the control device, so that the ignition device can ignite and burn fuel in the combustion chamber under the action of the control device.

According to a preferred embodiment, the ignition device comprises an ignition box and an ignition nozzle, wherein the ignition box is connected with the control device; the ignition nozzle is arranged on the combustion chamber and is also connected with the ignition box.

According to a preferred embodiment, the ram-type infrared enhancer further comprises a nozzle which is arranged at the tail part of the combustion chamber and is also connected with the control device, so that the nozzle can eject the gas combusted in the combustion chamber under the action of the control device.

According to a preferred embodiment, the ram-type infrared enhancer further comprises a power supply device, the power supply device is a storage battery or an unmanned aerial vehicle power supply, and the power supply device is connected with the control device so as to supply power to the control device through the power supply device.

According to a preferred embodiment, the ram-type infrared enhancer further comprises a housing located at an end of the intake duct, and the fuel supply device, the combustion chamber, the control device, the ignition device and the nozzle are located inside the housing.

According to a preferred embodiment, the shell is provided with a pitot tube and at least one mounting seat, wherein the pitot tube is arranged on the upper end surface of the shell, and the flying speed of the unmanned aerial vehicle is detected through the pitot tube; at least one the mount pad set up in the lower terminal surface of casing to through at least one the mount pad will infrared intensifier of punching press formula install on unmanned aerial vehicle.

The stamping type infrared enhancer provided by the invention at least has the following beneficial technical effects:

the ram-type infrared enhancer comprises an air inlet device, a fuel supply device, a combustion chamber and a control device, wherein the air inlet device can provide combustion-supporting gas for the combustion chamber under the action of the control device, the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber under the action of the control device, and the control device is also used for controlling the combustion of the liquid fuel and/or the gas fuel in the combustion chamber. The working time is short, and the technical problems of the required flight speed domain and the required altitude domain of the unmanned aerial vehicle cannot be met.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic block diagram of a preferred embodiment of a stamped infrared enhancer of the present invention;

FIG. 2 is a schematic structural view of a preferred embodiment of the stamped infrared enhancer of the present invention;

FIG. 3 is a schematic view of the internal structure of a preferred embodiment of the stamped infrared enhancer of the invention.

In the figure: 1. a combustion chamber; 2. a control device; 3. an air inlet channel; 4. an air inlet pipe; 5. a fuel tank; 6. a first delivery conduit; 7. a second delivery conduit; 8. an electromagnetic valve; 9. an oil pump; 10. an ignition box; 11. an ignition nozzle; 12. a nozzle; 13. a battery cell; 14. a housing; 15. a pitot tube; 16. and (7) mounting a seat.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the examples given herein without any inventive step, are within the scope of the present invention.

The following describes the stamped infrared enhancer of the present embodiment in detail with reference to the accompanying drawings 1-3 of the specification.

The ram-type infrared enhancer of the present embodiment includes an air intake device, a fuel supply device, a combustion chamber 1, and a control device 2, as shown in fig. 1. Wherein, the control device 2 is connected with the air inlet device and the fuel supply device, and the air inlet device and the fuel supply device are also communicated with the combustion chamber 1, so that the air inlet device can provide combustion-supporting gas for the combustion chamber 1 under the action of the control device 2, and the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber 1 under the action of the control device 2. The control device 2 is also connected to the combustion chamber 1 for controlling the combustion of the liquid fuel and/or the gaseous fuel in the combustion chamber 1 by means of the control device 2. Preferably, the combustion chamber 1 comprises a premixing section for mixing combustion-supporting gas with liquid fuel and/or gaseous fuel and a combustion section; the combustion section is used for combustion of fuel.

Preferably, the control means 2 comprise a combustion control assembly and an integrated control assembly. Wherein, the combustion control assembly comprises an inflow sensor (comprising an air temperature sensor and/or an air pressure sensor), an exhaust temperature sensor, a flow valve and the like, and is used for controlling the combustion of the fuel in the combustion chamber 1. The integrated control assembly is used for self-checking of the infrared intensifier, normal operation control (including starting, automatic air and fuel mixing ratio adjustment according to air flow and closing), emergency closing, alarming, and exchanging operation information through an interface.

The ram-type infrared enhancer of the embodiment comprises an air inlet device, a fuel supply device, a combustion chamber 1 and a control device 2, wherein the air inlet device can provide combustion-supporting gas for the combustion chamber 1 under the action of the control device 2, the fuel supply device can provide liquid fuel and/or gas fuel for the combustion chamber 1 under the action of the control device 2, and the control device 2 is also used for controlling the combustion of the liquid fuel and/or the gas fuel in the combustion chamber 1. the ram-type infrared enhancer of the embodiment uses the liquid fuel and/or the gas fuel, so that the combustion speed is controllable, the combustion time is long, the ram-type infrared enhancer is used for the head and/or tail of an unmanned aerial vehicle, the working time is long, the flight speed domain and the height domain required by the unmanned aerial vehicle can be met, the problem that the infrared enhancer in the prior art uses gunpowder as fuel, the combustion duration is short, make it be used for meeting, operating time is shorter, can not satisfy the required flight speed of unmanned aerial vehicle territory and the technical problem in high territory.

According to a preferred embodiment, the air intake means comprises an intake duct 3 and an intake pipe 4. Wherein, the air inlet 3 is a fixed type punching air inlet, and the outer surface thereof is a conical structure, as shown in fig. 2 or 3. The intake pipe 4 is disposed at the tail of the intake passage 3, and the intake pipe 4 is communicated with the combustion chamber 1 to supply combustion-supporting gas to the combustion chamber 1 through the intake passage 3 and the intake pipe 4, as shown in fig. 3. Preferably, the combustion-supporting gas supplied to the combustion chamber 1 by the air intake device is air. The air intake device of the preferred technical scheme of the embodiment comprises an air inlet passage 3 and an air inlet pipe 4, wherein the air inlet passage 3 adopts a fixed and non-adjustable ram-type air inlet passage, provides required air flow and pressure for the combustion chamber 1, and is applicable to a larger flight speed domain and a higher altitude domain. Preferably, the air flow and pressure required for the combustion chamber 1 may be determined based on the flow of fuel in the combustion chamber 1, the required temperature, the altitude field and/or the speed field of the drone flight.

According to a preferred embodiment, the fuel supply means comprises a fuel tank 5, the fuel tank 5 being intended to store propane fuel, and the fuel tank 5 being in communication with the combustion chamber 1 through a first delivery duct 6, as shown in fig. 3. Preferably, the fuel tank 5 has a cylindrical or cylindrical ring structure, and the middle or lower end surface of the fuel tank 5 has an arc-shaped groove matched with the outer surface of the air inlet pipe 4, so that the fuel tank 5 is clamped on the outer surface of the air inlet pipe 4. The preferred technical scheme's of this embodiment fuel tank 5 joint sets up in the surface of intake pipe 4, not only can be that fuel tank 5 has sufficient space to be used for saving gaseous fuel, still can make infrared intensifier's compact structure, can not cause the influence to unmanned aerial vehicle's flight, also can guarantee the steadiness of fuel tank 5 installation, can make the stable burning of fuel.

Preferably, the fuel supply device further comprises a second delivery pipe 7, one end of the second delivery pipe 7 is communicated with the oil tank of the unmanned aerial vehicle, and the other end is communicated with the fuel tank 5 through an electromagnetic valve 8 and an oil pump 9, so that the unmanned aerial vehicle can deliver the aviation kerosene to the combustion chamber 1 through the second delivery pipe 7, as shown in fig. 3. More preferably, the oil pump 9 is used for pumping the jet fuel from the unmanned engine oil tank into the fuel tank 5, and the electromagnetic valve 8 is used for controlling parameters such as the speed and the flow rate of the jet fuel pumped by the oil pump 9. The solenoid valve 8 and the oil pump 9 are of a prior art construction and will not be described in detail. Specifically, the aviation kerosene enters the fuel tank 5 through the second delivery pipe 7, and then enters the combustion chamber 1 through the first delivery pipe 6.

Preferably, the fuel supply device further comprises a pressure regulator, a safety controller (including a safety valve and/or an anti-backfire device), a warmer and the like. Specifically, the structures of the pressure regulator, the safety controller, the heater and the like are the structures in the prior art, and are not described herein again. The preferable technical scheme of the embodiment is that through a fuel supply device, the fuel which meets the requirements such as flow, pressure and temperature can be provided for the combustion chamber 1 based on the requirements of radiation power and radiation temperature on combustion; according to the time of the flight mission, the fuel supply device can also supply fuel to the fuel tank 5 by the unmanned aerial vehicle, and the operation of the infrared intensifier is ensured.

The fuel supply apparatus of the present embodiment may supply the combustion chamber 1 with a gaseous fuel and a liquid fuel, preferably, the gaseous fuel is propane and the liquid fuel is aviation kerosene, but is not limited thereto, and the remaining gaseous fuel and liquid fuel may be used. The fuel supply device of the preferred technical scheme of the embodiment comprises a fuel tank 5, and a certain amount of propane fuel is stored in the fuel tank 5 in advance, so that the infrared enhancer can work for a period of time. If the flight mission time is long, after the propane fuel pre-stored in the fuel tank 5 is burnt, part of aviation kerosene in the unmanned engine oil tank can be supplied to the combustion chamber 1 through the second conveying pipeline 7 and the oil pump 9, so that the normal work of the infrared intensifier is ensured, and the requirement of the flight mission time is met.

According to a preferred embodiment, the stamped infrared enhancer further comprises an ignition device connected to the combustion chamber 1 and to the control device 2, so that the ignition device can ignite and burn the fuel in the combustion chamber 1 under the action of the control device 2. Preferably, the ignition device comprises an ignition box 10 and an ignition nozzle 11, wherein the ignition box 10 is connected with the control device 2; a burner 11 is provided on the combustion chamber 1, and the burner 11 is also connected to the ignition box 10, as shown in fig. 3. The preferred technical scheme of the embodiment can control the ignition time of the ignition device through the control device 2.

According to a preferred embodiment, the stamped infrared enhancer further comprises a spout 12. Preferably, a nozzle 12 is arranged at the rear of the combustion chamber 1, and the nozzle 12 is also connected to the control device 2, so that the nozzle 12 can eject the gas combusted in the combustion chamber 1 under the action of the control device 2, as shown in fig. 3. The nozzle 12 is a structure in the prior art, specifically, the nozzle 12 includes a rectifying device, a stabilizing screen, a nozzle and the like, and the gas combusted in the combustion chamber 1 can be ejected at a certain temperature and speed by the action of the nozzle 12.

According to a preferred embodiment, the stamped infrared enhancer further comprises power supply means. Preferably, power supply unit is storage battery 13 or unmanned aerial vehicle power to power supply unit is connected with controlling means 2, and as shown in fig. 3 for controlling means 2 power supply through power supply unit. The power supply unit of the preferred technical scheme of this embodiment is infrared intensifier from taking storage battery 13 or unmanned aerial vehicle power, and through power supply unit's effect, can guarantee infrared intensifier's normal work for the part power supply of the required power consumption of infrared intensifier.

According to a preferred embodiment, the stamped infrared enhancer further comprises a housing 14. Preferably, the housing 14 is located at the end of the intake duct and the fuel supply, the combustion chamber 1, the control device 2, the ignition device and the nozzle 12 are located inside the housing 14, as shown in fig. 2. As can be seen from fig. 2 and 3, the control device 2, the ignition box 10, the electromagnetic valve 8, the oil pump 9 and the battery 13 are positioned at two sides of the air inlet pipe 4, and the parts can be integrated through the shell 14. Preferably, the housing 14 has space for mounting other devices and interfaces for mechanical, electrical, information, etc.

According to a preferred embodiment, housing 14 is provided with a pitot tube 15 and at least one mounting seat 16, as shown in FIG. 2. Wherein, airspeed tube 15 sets up in the up end of casing 14 to detect unmanned aerial vehicle's airspeed tube 15 flying speed. At least one mount 16 sets up in the lower terminal surface of casing 14 to install the punching press formula infrared enhancer that will through at least one mount 16 on the unmanned aerial vehicle. The preferred technical scheme of this embodiment is through setting up airspeed head 15 on casing 14, can detect unmanned aerial vehicle's airspeed. Preferably, the pitot tube 15 is connected to the control device 2 so that the control device 2 can control the operating conditions of the remaining components based on the flight speed of the drone. As shown in fig. 2, the lower end surface of the housing 14 is provided with two mounting seats 16, and the infrared enhancer can be hung on the unmanned aerial vehicle through the mounting seats 16.

The infrared enhancer of the embodiment can simulate far-field infrared point source characteristics of an jet nozzle of an aircraft jet engine, such as wavelength, radiation power, temperature, flame length and the like; the device can be used for the head and tail of the unmanned aerial vehicle; due to the use of liquid fuel (jet fuel) and/or gaseous fuel (propane), the operation time is long, and the infrared enhancer is a universal infrared enhancer applicable to larger flight speed domains and altitude domains. The infrared intensifier of the embodiment also has the advantages of simple structure, safe use, convenience, reliability, convenient maintenance, capability of being hung on a multi-type carrier and the like. The infrared enhancer of this embodiment, whose code is "HZ 1", is also called HZ1 punch type infrared enhancer.

The infrared intensifier of the embodiment can realize intermittent or continuous work in the air and work in a program control or ground instruction control mode. Thrust is not generated in the flight process of the unmanned aerial vehicle; can be repeatedly used; through the control device 2, the functions of self-checking, safety control and the like can be realized, such as automatic alarm and shutdown caused by over-temperature, leakage and abnormal system operation, or the alarm is not allowed to start; the infrared enhancer of this embodiment may also be equipped with off-target indicators, telemetry motors, transponders, and the like.

It is understood that the same or similar parts in the present embodiment may be mutually referred to, and the same or similar contents in other embodiments may be referred to for the contents which are not described in detail in some embodiments.

It should be noted that, in the description of the present application, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Further, in the description of the present application, the meaning of "a plurality" means at least two unless otherwise specified.

The term "connection" as used herein may refer to one or more of a data connection, a communication connection, a wired connection, a wireless connection, a connection via a physical connection, and the like, as will be appreciated by those skilled in the art.

Any process or method descriptions in flow charts or otherwise described herein may be understood as representing modules, segments, or portions of code which include one or more executable instructions for implementing specific logical functions or steps of the process, and the scope of the preferred embodiments of the present application includes other implementations in which functions may be executed out of order from that shown or discussed, including substantially concurrently or in reverse order, depending on the functionality involved, as would be understood by those reasonably skilled in the art of the present application.

It should be understood that portions of the present application may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like. Such as the control device 2 in the present application.

It will be understood by those skilled in the art that all or part of the steps carried by the method for implementing the above embodiments may be implemented by hardware related to instructions of a program, which may be stored in a computer readable storage medium, and when the program is executed, the program includes one or a combination of the steps of the method embodiments.

In addition, functional units in the embodiments of the present application may be integrated into one processing module, or each unit may exist alone physically, or two or more units are integrated into one module. The integrated module can be realized in a hardware mode, and can also be realized in a software functional module mode. The integrated module, if implemented in the form of a software functional module and sold or used as a stand-alone product, may also be stored in a computer readable storage medium.

The storage medium mentioned above may be a read-only memory, a magnetic or optical disk, etc.

In the description herein, reference to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.