KR102156070B1 - The Droplet Combustion Experiment System for parabolic flight - Google Patents

Abstract

The present invention relates to a droplet combustion test system for a zero-gravity plane to study the characteristics of a combustion phenomenon by simulating the micro-gravity environment of the universe with a zero-gravity plane on the ground. The present invention relates to a droplet combustion test system for zero-gravity planes that can be controlled and performed in a limited zero-gravity section of zero-gravity planes.

Description

The Droplet Combustion Experiment System for parabolic flight}

The present invention relates to a droplet combustion test system for a zero-gravity aircraft to study the characteristics of the combustion phenomenon by simulating the microgravity environment of the universe as a zero-gravity plane on the ground.

The world's liquid fuel production and consumption is steadily increasing, and most of the liquid fuel is consumed through combustion in various fields such as power generation, heating, and transportation. At this time, most of the liquid fuel is sprayed. It is supplied in the form of droplets through a combustor when an understanding of phenomena related to droplet combustion such as evaporation of liquid fuel, heat transfer, mass transfer, preservation of chemical species, and chemical reaction rates are involved. B. It is possible to develop technologies that can contribute to improving engine combustion efficiency or reducing pollutants (Nox, soot, etc.).

Until now, engine research has been carried out by researchers using various experimental devices. In particular, in experiments through spray injection of liquid fuel, it is difficult to accurately grasp the behavior of a single droplet inside the engine due to the influence of the surrounding droplets. Has been caused. Accordingly, interference between surrounding droplets should be prevented through a combustion experiment in the state of a spherical single droplet having a diameter of 1 mm to 4 mm. In addition, since experiments on the ground are subject to interference by the self-weight acting on a single droplet fuel, experiments in a zero-gravity state with micro-level gravity are required to test more precise combustion phenomena. A droplet combustion experiment using a zero gravity environment in space has been performed through a combustion test equipment mounted on the International Space Station (ISS), a representative experimental space in a microgravity environment.

At this time, in order to verify the performance of the combustion test equipment mounted on the International Space Station (ISS), a performance verification experiment on the ground before launching into space is required. To simulate the microgravity environment on the ground, a free fall tower , Parabolic flight, and 3D clinostat can be used to simulate the microgravity environment on the ground. Japanese Laid-Open Patent Publication No. 2010-069952 (Method for creating a low-gravity environment by an aircraft, 2010.04.02.) discloses a technology for forming a micro-gravity environment for the parabolic flight, and thus a zero-gravity plane. In the case of forming a micro-gravity environment by using, there is a limitation in creating a micro-gravity environment for a limited time as the micro-gravity environment is formed through parabolic flight at a high altitude.

Japanese Laid-Open Patent Publication No. 2010-069952 (Method of creating a low-gravity environment by an aircraft, 2010.04.02.)

The present invention was conceived to solve the above problems, and the droplet combustion experiment system for a zero-gravity plane of the present invention controls each of the experimental equipment according to the change in gravity of the zero-gravity plane, so that droplets in the microgravity state formed through the zero-gravity plane I want to conduct a combustion experiment.

In order to solve the above problems, the present invention provides a droplet combustion experiment system for a zero gravity airplane in a microgravity environment simulated using a zero gravity airplane, comprising: a chamber mounted on a zero gravity airplane; A droplet combustion module provided inside the chamber and injecting and igniting droplet fuel in a single particle state; Optical equipment for observing the combustion of the droplet fuel in a single particle state formed by the droplet combustion module; According to the change in gravity according to the operation of the zero-gravity plane, including after take-off of the zero-gravity plane, before a predetermined time (a) before the zero-gravity plane enters the micro-gravity section, and immediately after the zero-gravity plane enters the micro-gravity section. A switch unit for controlling an operation of at least one of a chamber, a droplet combustion module, and an optical device; And a switch control unit configured to include a gravity sensor for sensing gravity according to the flight of the zero-gravity plane, and automatically control the operation of the switch unit according to the change in gravity according to the operation of the zero-gravity plane, including,
The droplet combustion module,
At least one fiber disposed on a plane inside the chamber,
A pair of droplet injectors disposed on the same plane as the fibers and receiving fuel having a predetermined flow rate from a fuel pump and injecting fuel into the fibers,
A pair of igniters disposed on a plane spaced apart from the fiber and the droplet injector at a predetermined height to ignite droplet fuel in a single particle state formed on the fiber,
A rotary motor for rotating the droplet injector, and
A linear motor for linearly moving the igniter,
It characterized in that it comprises a.

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In addition, the switch unit may further include a first switch for operating the rotary motor and the linear motor to enter the droplet ejector and the igniter at respective operating points after take-off of the zero gravity aircraft.

In addition, the switch unit may further include a second switch for operating the droplet sprayer so that fuel is injected at a predetermined flow rate before a predetermined time (a) before the zero gravity aircraft enters the microgravity section.

In addition, the switch unit may further include a third switch for operating the igniter to ignite droplet fuel in a single particle state formed on the fiber immediately after the zero gravity plane enters the microgravity section.

In addition, the droplet combustion test system may further include a switch control unit for automatically controlling the operation of the switch unit according to the change in gravity according to the operation of the zero gravity aircraft.

At this time, the switch control unit comprises a gravity sensor for sensing the gravity according to the flight of the zero gravity aircraft, characterized in that to control the operation of the switch unit according to the gravity acting on the zero gravity airplane measured by the gravity sensor do.

In addition, the switch control unit further comprises a timer for measuring the flight time of the zero-gravity airplane, characterized in that to control the operation of the switch unit according to the passage of time according to the flight schedule of the zero-gravity airplane.

In addition, the droplet combustion module may further include a fiber exchanger for replacing the broken fiber when the fiber is broken by ignition of fuel.

The present invention according to the above configuration controls fuel supply, ignition, and observation according to the change in gravity of a zero-gravity airplane on the ground to perform droplet combustion experiments for a limited time, so that the scientific basis of liquid fuel in a microgravity environment A database is established to derive scientific achievements based on improved understanding of combustion phenomena (combustion rate by combustion environment, flame temperature, radiant heat flow rate, etc.), and it is expected that it can be used for prevention of flame explosion accidents and fire safety accidents. .

In addition, by using the droplet combustion test system for a zero gravity airplane of the present invention, it is possible to secure high reliability through verification of the performance of the droplet combustion test equipment mounted on the International Space Station (ISS) on the ground.

1 is a graph showing the change in gravity according to the operation of the zero-gravity airplane.
2 is a block diagram showing a droplet combustion experiment system according to an embodiment of the present invention.
3 is a configuration diagram illustrating a relationship between a chamber, a droplet combustion module, and an optical device according to an embodiment of the present invention.
4 is a perspective view showing a chamber according to an embodiment of the present invention.
5 is a perspective view showing a droplet combustion module according to an embodiment of the present invention.
6 is a plan view showing the droplet combustion module according to FIG. 5.
7 is a flow chart showing a droplet combustion test method according to the weightless state determination unit of the present invention.
8 is a flow chart for explaining the overall operation of the combustion test system according to the droplet combustion test method of the present invention.
9 is a view for explaining a switch unit according to an embodiment of the present invention.

In the present invention, various modifications may be made and various embodiments may be provided, and specific embodiments will be illustrated in the drawings and described in detail. However, this is not intended to limit the present invention to a specific embodiment, it is to be understood to include all changes, equivalents, and substitutes included in the spirit and scope of the present invention.

When a component is referred to as being "connected" or "connected" to another component, it is understood that it may be directly connected or connected to the other component, but other components may exist in the middle. Should be.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which the present invention belongs.

Terms such as those defined in commonly used dictionaries should be interpreted as having a meaning consistent with the meaning in the context of the related technology, and should not be interpreted as an ideal or excessively formal meaning unless explicitly defined in this application. Does not.

Hereinafter, the technical idea of the present invention will be described in more detail using the accompanying drawings.

The accompanying drawings are only an example shown to describe the technical idea of the present invention in more detail, so the technical idea of the present invention is not limited to the form of the accompanying drawings.

FIG. 1 is a graph showing the change in gravity according to the operation of the zero-gravity plane, and referring to FIG. 1, when the change in gravity according to the operation of the zero-gravity plane 10 is described in detail, the zero-gravity plane 10 is 21,000 feet or more. By glide so as to draw a parabola in the altitude, it is possible to create an environment in which the gravity applied to the zero gravity aircraft 10 has a microscopic value. In more detail, the inertia of the zero-gravity plane 10, which was ascended by turning off the engine and falling freely after rising to receive a pressure (2G) that is twice the gravity (G) (section B-C). The gravity acting on the zero-gravity plane 10 is canceled by this, and for a certain period of time, the zero-gravity plane 10 creates a microgravity (hereinafter referred to as zero-gravity) environment (section C-D).

As described above, the zero-gravity plane 10 repeats a series of processes to create a zero-gravity environment several times and then lands on the ground. At this time, as the zero-gravity section in the above-described C-D section lasts for a limited time (b) of tens of seconds to several minutes, droplets within the time (T+b) before the zero-gravity plane 10 enters and leaves the zero-gravity section. Combustion tests should be carried out.

At this time, the droplet combustion experiment system 1000 of the present invention controls each equipment so that droplet combustion experiments can be performed for a limited period of zero gravity (T+b) to perform an experiment in a zero gravity environment using the zero gravity airplane 10 It aims to do.

Figure 2 is a configuration diagram showing a droplet combustion experiment system 1000 according to an embodiment of the present invention, Figure 3 is for explaining the relationship between the chamber, the droplet combustion module and optical equipment according to an embodiment of the present invention As a configuration diagram, referring to FIGS. 2 and 3, the droplet combustion experiment system 1000 of the present invention includes a chamber 100, a droplet combustion module 200, an optical equipment 300, a switch unit 400, a switch control unit ( 500) and a storage unit 600 may be included.

The droplet combustion module 200 and the optical equipment 300 are installed inside and outside the chamber 100 to test and observe the combustion phenomenon of droplet fuel formed in a single particle state in a microgravity state, As shown in Figure 4, the chamber 100 accommodates the droplet combustion module 200 therein, and is mounted inside the zero gravity airplane 10 to burn the droplet according to the operation of the zero gravity airplane 10. A configuration for creating an experimental environment of the module 200, an oxygen sensor 110 for measuring the amount of oxygen inside the chamber 100, a pressure sensor 120 for measuring the pressure inside the chamber 100, A light source 130 for illuminating the interior of the chamber 100 and a vacuum pump (not shown) for adjusting the pressure inside the chamber 100 may be included, and the chamber 100 may include the droplet combustion module ( In order to create an optimized combustion environment for single particle fuel droplets according to 200), it is formed so that airtightness can be maintained. The inner surface is preferably coated with matte paint and electropolished (EP) to minimize light reflection to suppress reflection of light due to combustion of the droplet fuel. In addition, the chamber 100 may further include an optical window 150 formed to perform observation through an external camera, and preferably, the design of the zero gravity plane 10 in which the chamber 100 is mounted It is desirable to be manufactured to meet the requirements.

5 is a perspective view showing a droplet combustion module according to an embodiment of the present invention, and FIG. 6 is a plan view showing the droplet combustion module according to FIG. 5. Referring to FIGS. 5 and 6, the droplet combustion module ( 200) is provided in the chamber 100 to perform a droplet combustion experiment in which droplet fuel in a single particle state is injected and ignited, and the droplet combustion module 200 is installed inside the chamber 100 Equipment including a fiber 210, a droplet sprayer 220, a rotary motor 230, an igniter 240, and a linear motor 250 for a combustion experiment of droplet fuel are arranged on one surface of the cradle 150 that is It is preferably formed.

In this case, the fiber 210 is a linear fiber disposed on one plane inside the chamber 100 so that the fuel injected from the droplet injector 220 can be formed in a single particle state, and the liquid The fuel injected from the injector 220 is prevented from falling due to its own weight or external force, and in a zero gravity environment, the droplet fuel is fixed so that it does not deviate from the observation area during combustion of the droplet fuel.

The droplet injector 220 is a microtube 221 for injecting fuel supplied from the fuel pump 223 into the fiber 210, and a transport connecting the microtube 221 and the fuel pump 223 It may include a tube 222, wherein the switch unit 400 controls the flow rate and supply amount of the injected fuel according to the inner diameter of the microtube 221, and the state of a single particle formed on the fiber 210 The size of the droplet fuel can be adjusted. That is, the switch unit 400 considers the combustion time of the droplet fuel in the single particle state during the duration (b) of the single zero gravity section of the zero gravity aircraft 10, and determines the size of the droplet fuel in the single particle state. In order to form the fuel discharged from the fuel pump 223 to have a predetermined flow rate, the discharge amount of the fuel pump 223 must be controlled. At this time, the fuel pump 223 controls the flow rate and flow rate of the fine fuel, It is preferable to use a syringe pump to prevent errors due to the pulsation of the pump.

In addition, the droplet ejector 220 is preferably formed in a pair disposed on the same plane as the fiber 210, the pair of droplet ejector 220 is based on the fiber 210 It includes a pair of microtubes 221 arranged to face each other, and the pair of microtubes 221 are connected to one side of a transfer tube 222 extending in a vertical direction, respectively, and the transfer tube The other side of 222 is connected to the rotation motor 230 so that a pair of droplet sprayers 220 perform a rotational motion having a predetermined radius with respect to each rotation motor 230 in a direction opposite to each other. It works. At this time, the pair of microtubes 221 are rotated by a predetermined radius from a point of the fiber 210, so that the droplet ejector 220 includes the pair of microtubes 221 ) Is operated to inject fuel at a point arranged to face each other in proximity to a point, and the distance between the pair of microtubes 221 and the fiber 221 is the size of the designed single particle droplet fuel Although it is preferable to have a, it is operated to gradually move away from the fuel when the fuel is injected, so that the fuel may be driven to form a single particle on the fiber 210.

The igniter 240 is a configuration for heating and igniting the fuel injected by the droplet injector 220 in a single particle state on the fiber 210, and is an ignition circuit for dissipating heat by receiving power. 241, the ignition circuit 241 from the fiber 210 and the droplet ejector 220 so as not to interfere with the fiber 210 and a pair of droplet ejector 220 It is preferable to be disposed on a plane spaced apart from a predetermined height, and after ignition of the droplet fuel in a single particle state formed on the fiber 210, the linear rail 242 retracting so as not to interfere with the observation area of the optical device 300 ) And a linear motor 250 may be included. At this time, the igniter 240 is made of a pair of ignition circuits 241 of the pair of igniters 240 are arranged on the same line in a direction facing each other on one surface of the cradle 150 It is preferably disposed on a plane spaced apart from the fiber 210 by a predetermined height, and disposed in a direction that does not interfere with the fiber 210 and the droplet sprayer 220.

The optical equipment 300 is a configuration for observing the combustion of the droplet fuel in a single particle state formed by the droplet combustion module 200, and a plurality of optics measuring an observation area in which the droplet fuel in the single particle state is formed. Cameras are included, and the plurality of optical cameras should be arranged so as to have a position and angle that does not interfere with the observation field of view by the respective devices of the droplet combustion module 200.

In addition, the optical device 300 measures the flame temperature by measuring the radiometer 310 for measuring the energy of the electromagnetic wave generated during the combustion of the droplet fuel and the radiant light generated during the combustion of the droplet fuel. Includes two types of CCD camera 320 combined with an optical filter for performing the radiometer 310, the CCD camera 320, and a color for observing the image of the droplet fuel burning in the microgravity environment Each of the cameras 330 may be provided in plural and may be disposed inside or outside the chamber 100.

The radiometer 310 is composed of three, each of which can measure the radiant energy of a different wavelength band. In general, the wavelength of the flame generated during combustion varies from visible light to the infrared range, and one radiometer (310b) is a radiometer that covers all of the wavelength bands in this range, and is used to determine the generation and extinction time of the flame. And, the radiometers 310a and 310c observe radiant energy in a range of 5.5um to 7.5um, one of the wavelength bands of water. This is by measuring the radiant energy of water (H2O), which is one of the products of combustion, and it is possible to confirm the generation/extinguishment of flames and other physical phenomena.

In addition, the CCD camera 320 simultaneously measures the radiant light of soot particles radiated at different wavelengths and applies it to Planck's law to perform non-contact temperature measurement capable of predicting the temperature of the flame in a manner independent of emissivity, and 700 nm The spatial temperature distribution of the diffusion flame can be predicted by using the optical filter of the 900 nm band filter and the error generated by reducing the interval for dividing the line of sight can be minimized. In this case, when this is applied to measure the flame temperature, the radiation intensity of the soot particles formed inside the flame is an important variable, and in the relatively low temperature region such as the center of the flame, an error may occur in the prediction of the flame temperature due to weak radiation intensity. have.

The switch unit 400 is one of the respective devices of the chamber 100, the droplet combustion module 200, and the optical equipment 300 according to the change of gravity in the zero-gravity plane according to the operation of the zero-gravity plane 10. With a configuration for controlling at least one or more operations, the switch unit 400 is a driving pattern of the zero-gravity plane 10 that simulates a zero-gravity environment through parabolic flight in the sky, that is, the gravitational force according to the operation of the zero-gravity plane 10. It is configured to control the chamber 100, the droplet combustion module 200, and the optical equipment 300 respectively according to the change. At this time, the storage unit 600 collects and stores the information measured and observed in the chamber 100, the droplet combustion module 200, and the optical equipment 300, and data associated with the droplet combustion experiment to be converted into a database. I can.

As shown in FIG. 2, the switch unit 400 includes a first switch 410, a second switch 420, a third switch 430, and a lamp 440 for lighting the experimental state according to the operation of the switches. ) May be included, and at this time, FIG. 7 is a flow chart of a droplet combustion experiment according to an embodiment of the present invention, using a droplet combustion experiment system 1000 for a zero gravity aircraft in the following with reference to FIGS. 2 and 7 The droplet combustion experiment in zero gravity plane will be described in detail.

The droplet combustion experiment using the droplet combustion experiment system 1000 for a zero gravity aircraft of the present invention is performed including a preparation step (S100), a droplet formation step (S200), a measurement step (S300) and a repeat experiment step (S400), At this time, in the preparation step (S100), before the zero-gravity plane 10 enters the zero-gravity section, the rotary motor 230 and the linear motor 250 are driven, and the fine tube 221 of the droplet sprayer 220 is ) And the ends of the ignition circuit 241 of the igniter 240 are positioned so as to be close to any one point (where the droplet is formed) of the fiber 210, and then the prepared droplet sprayer 220 ) To form droplet fuel in a single particle state on the fiber 210 by injecting fuel at a predetermined flow rate (S200) and immediately after the zero gravity plane 10 enters the zero gravity section, the prepared igniter After heating and igniting the droplet fuel formed by operating (240), the droplet sprayer 220 and the igniter 240 are retracted so as not to interfere with the observation from the optical device 300 The measurement step (S300) is performed, wherein the preparation step (S100) is performed according to an operation signal of the first switch 410, and the droplet forming step (S200) is an operation of the second switch 420 It is performed according to a signal, and the measuring step (S300) is performed according to an operation signal of the third switch 430.

In more detail, the first switch 410 may be operated before the zero-gravity plane 10 takes off and enters the zero-gravity section (section C in FIG. 1), and preferably, after the take-off of the zero-gravity plane 10 To the second switch is operated before the operating section (section A in FIG. 1). At this time, the switch unit 400 receives the operation signal of the first switch 510 to create an experimental environment inside the chamber 100, and the droplet injector 220 and the igniter of the droplet combustion module 200 The operation of the rotary motor 230 and the linear motor 250 is controlled to move the 240 to a position close to the fiber 210.

In addition, the second switch 420 is preferably operated before the zero-gravity plane enters the zero-gravity section, and forms and prepares droplet fuel in advance before entering the zero-gravity section, and thereafter, the zero-gravity plane 10 Immediately after entering the zero-gravity section, the third switch 530 may be operated to perform a measurement step S300 of ignition and observation of the droplet fuel formed on the fiber 210.

At this time, the above-described series of steps is preferably performed according to the change of gravity acting on the zero-gravity plane, and at this time, a precisely designed experiment is conducted by controlling the operation of the switch unit according to the time lapse of the flight schedule of the zero-gravity plane. Can be done.

8 is a flow chart for explaining the overall operation of the combustion test system 1000 according to an embodiment of the present invention. The sequence of operating the combustion test system 1000 according to a change in gravity is further time-sequentially described below. I will explain in detail.

Referring to FIG. 8, in the droplet combustion experiment using the combustion experiment system 1000 of the present invention, an optical device consisting of a chamber 100 equipped with sensors measuring the combustion experiment environment and cameras for observing the combustion of droplet fuel ( 300) and a droplet combustion module 200 that forms droplet fuel in a single particle state and ignites the formed droplet fuel, and the switch unit 400 includes the chamber 100 and the droplet combustion module 200 described above. And each of the optical equipment 300 is independently controlled according to the change of gravity. At this time, the droplet combustion test system 1000 for a zero-gravity aircraft controls the chamber 100 and the droplet combustion module 200, and independently controls the optical equipment 300 and an independent first server that converts the measured values into a database. And, further comprising a second server for converting the observed values into a database, the chamber 100 and the droplet combustion module 200 or the optical equipment 300 is independent by receiving the operation signal from the switch 400 You can run it.

[t <T-a]

Before the zero-gravity plane 10 enters the zero-gravity section, by operating a pair of rotary motors 230 and linear motors 250, the droplet sprayer 220 and the igniter 240 are respectively operated at the point where they are operated. A preparatory step (S100) of entering is performed, and in this case, the preparatory step (S100) may be operated by the first switch 510.

[T-a ≤ t <T]

Thereafter, before the predetermined time (a) before the zero-gravity plane 10 enters the zero-gravity section, the fuel pump is operated to supply fuel to the droplet injector 220, thereby forming droplets of a single particle on the fiber 210. A fuel supply step (S210) of forming fuel is performed, and at this time, the switch unit 400 operates the pressure sensor 120 and the oxygen sensor 110 provided in the chamber 100 to A sensor measurement step (S220) of measuring the environment and an observation step (S230) of operating the optical equipment 300 to observe the formed droplet fuel, wherein the series of steps described above are performed by the second switch It is uniformly performed by the operation signal applied from (420). In this case, in the observing step (S230), if necessary, by delaying the operation time of the plurality of cameras and illuminators of the optical equipment 300, the observation may be performed after the input delay time.

[T ≤ t <T+b]

Thereafter, immediately after the zero-gravity plane 10 enters the zero-gravity section, the ignition circuit 241 of the igniter 240 is heated to ignite the formed droplet fuel in the single particle state, and then the rotary motor 230 And the ignition step (S310) of retreating the linear motor 250 so as to be separated from the fiber 210 and measurement by the sensors of the chamber 100 after a delay for a predetermined time (b) set immediately after entering the zero-gravity section. And a termination step 320 of stopping observation of the optical equipment 300. At this time, the predetermined time (b) at which the end step (S320) is operated is preferably the point at which the zero-gravity plane 10 leaves the zero-gravity section (T+b), but in some cases, it is the point at which the combustion of a single droplet fuel ends. I will be able to.

[t ≥ T+b]

In addition, after the zero-gravity plane 10 is out of the zero-gravity section, the number of experiments (N) set according to the flight schedule of the zero-gravity plane 10 is counted and returns to the preparation step (S100) for the next order of experiment. It may be performed by further including a repeat experiment step (S400).

At this time, the droplet combustion module 200 operates the fiber exchanger 260 for replacing the broken fiber 210 when the fiber 210 is damaged by the ignition of fuel, and the broken fiber 210 You can prepare for the next order of experiment by replacing. Conventionally, when the fiber is damaged, the operator has to change the fiber directly, whereas the present invention uses the fiber exchanger 260 to exchange the damaged fiber, when operating the zero gravity aircraft 10 There is an advantage that a faster next-order experiment is possible because the operator does not perform the fiber replacement work for a limited time occurring in the system.

9 is a view for explaining the switch unit 400, a view showing a control panel consisting of a plurality of switches and LEDs. Referring to FIG. 9, the switch unit 400 includes a total of 4 LEDs ( LG, LR), 1 selection switch (SSL), and 15 push switches (PB). During the experiment in a zero-gravity plane, the operation status of the combustion test apparatus is checked by LEDs, and the selection switch and It is possible to control the combustion experiment module for each step and each part (each motor) by a push switch.

At this time, the lamp unit 440 includes a first lamp 441 (Ready) indicating a ready state for starting a combustion experiment, a pair of rotating motors of the droplet injector and a pair of linear motors igniting droplet fuel. A second lamp (442, 1st ing) indicating the operation status, a third lamp (443, Rdy for Ign) indicating that the supply of the droplet fuel is complete and the ignition is ready for the combustion experiment, and the combustion state of the droplet fuel are displayed. It includes a fourth lamp 444 (Igniting), and the first switch 410 transmits signals to a motor and limit switches operated to perform the preparation step S100, and a pair of linear motors ( 250) and the motors including a pair of rotating motors 230 are separated from the fiber 210 and fixed by a limit switch, which is operated to prevent the parts from deviating from the rotation radius, and the initial switch 410a and the above It may be formed to include a 1st switch 410b operated to rotate motors including a pair of linear motors 250 and a pair of rotary motors 230 to be adjacent to the fiber 210, and at this time, combustion experiment In the preparation step (S100) for, it is controlled through the 1st switch (410b), and in the iterative experiment step (S400) of returning the next-order experiment to the preparation step (S100), it is controlled through the initial switch (410a). Can be. At this time, the second lamp 442 blinks repeatedly while the motor is operating so that the operation state of the motor can be monitored by the 1st switch 410b, and when the control command by the 1st switch 410b is completed. By continuing to light up to stop flashing, it indicates the motor's operating status to the user. In addition, the second switch 420 (Pump X) is operated to control to perform the fuel supply step (S200), and the droplet injector 220 is preset by the user by the second switch 420. Fuel is supplied as much as the amount of fuel X, and at this time, by repeatedly operating the second switch 420, fuel can be supplied to form a desired droplet size during the experiment. Thereafter, when the supply of the droplet fuel is completed, the third lamp 443 is turned on to indicate that ignition is ready.

Thereafter, the ignition step (S300) is operated by the third switch 430, and when the third switch 430 is operated, a pair of igniters 240 for burning the droplet fuel are operated, and the fourth After the lamp 444 is turned on, after the pair of rotary motors and the pair of linear motors retreat to their initial positions, the first lamp 441 is turned on again to indicate the combustion state of the droplet fuel.

At this time, the switch unit 400 is a linear X switch (411a), a linear Y switch (441b) provided to control each of the pair of rotary motors 230 and the pair of linear motors 250, Rotated It may include an X switch (412a) and a rotated Y switch (412b), and through the linear X switch (411a) and linear Y switch (441b), the igniter 240 is respectively controlled forward or backward by a constant displacement value. The droplet sprayer 220 is rotated by a constant radius value through the Rotated X switch 412a and the Rotated Y switch 412b to allow fine adjustment, so that an error value according to its own weight or an external force can be adjusted. It has the advantage of being able to correct it. At this time, the switch unit 400 may further include a selection switch 413 provided to select control of the rotary motor 230 and the linear motor 250, and the selection switch 413 is a single linear motor. (250, A in FIG. 3) and a pair of one rotary motor 230 (A in FIG. 3) or another linear motor 250 (B in FIG. 3) and a pair of another rotary motor (230, B in FIG. 3) is operated to control separately.

In addition, the switch unit 400 sets a pump initialization switch 421 (pump init) for controlling the fuel pump 223, a reset switch 440 (reset) for initializing a set control value, and a reference point for controlling the motor. Zero switch (450, zero), an emergency switch 460 that is operated to prevent safety accidents by stopping all controls in an emergency situation, and a mode switching switch that performs manual/automatic mode switching of the switch unit 400 (470, mode chg), the fiber exchanger recovery switch (280a, FM0) that rotates the motor of the fiber exchanger 260 to the initial position and the motor of the fiber exchanger 260 is rotated at a certain angle to the part where droplets can be supplied. It may be configured to further include a fiber exchange switch (280b, FM90) operative to position.

At this time, Table 1 below shows the order of operation of the droplet fuel experiment system 1000 when performing the droplet fuel experiment in a zero gravity airplane according to an embodiment of the present invention, and a gravity value (G State) acting on the zero gravity airplane and As shown according to the control time value (Time Required), referring to Table 1 and FIG. 1 below, the zero-gravity section simulated by the zero-gravity plane 10 is formed for a limited time (b). During time (b), the target droplet combustion experiment should be performed. Therefore, before the zero-gravity plane 10 takes off and enters the zero-gravity section (before section C), an experimental environment inside the chamber 100 is created, and the droplet sprayer 220 and the droplet injector 220 of the droplet combustion module 200 By controlling the rotary motor 230 and the linear motor 250 to move the igniter 240 to a position close to the fiber 210, it must be prepared in advance before injecting fuel, and then the zero-gravity plane 10 The technical idea of the present invention is that the droplet injector 220 must be operated before the predetermined time (a) before entering the section to form the target single-particle state droplet fuel for the predetermined time (a).

State of Aircraft G State Work Item Time Required Loading 1G System setting (Stop → Reset → Initial → Zero → Pump initial)
Filling the fuel pipe in the combustion test equipment in advance
Checking the change in fuel quantity in the fuel supply line during altitude rise Continues "2 minutes before starting 1st PF"
↓ 1G Chamber pressure setting (xbar),
System zero point setting and experiment stage 1 position setting
(Initial → Zero → 1st)

At this time, fine adjustment is possible for various motors (Linear X, Linear Y, Rotated X, Rotated Y, using selection switch) 1 minute "1 minute"
↓ 0.5~1.2G Wait for experiment (Pump X) after supplying fuel (diameter 2.5mm) 1 minute "30 seconds"
↓ 2G Waiting for experiment 30 seconds "NOW" micro-G After drop fuel ignition (Igniter)
Automatic recording of experimental data 6 seconds End of 0G
Normal flight
↓ 1.5G Checking the test results (whether ignition/dropped fuel, etc.) 20 seconds The following experiment preparation ↓(Returns to "2 minutes before 2nd PF" call. And repeat PF till predefined times.)
↓ 1G After opening the chamber, clean the optical window
Chamber pressure setting (xbar),
System zero point setting and experiment stage 1 position setting
(Initial → Zero → 1st) Fill in reauied time to prepare experiment for nest PF
3 minutes "2 minutes bbefore starting 2nd ~ the final PF"
↓ 1G Waiting for experiment 1 minute "1 minute"
↓ 0.5~1.2G Wait for experiment after supplying fuel (diameter 2.5mm) (Pump X) 1 minute "30 seconds"
↓ 2G Waiting for experiment 30 seconds "NOW" micro-G After drop fuel ignition (Igniter)
Automatic recording of experimental data 6~8 seconds end of 0G
Normal flight
↓ 1.5G Checking the test results (whether ignition/dropped fuel, etc.) 20 seconds n ^th repeat
↓ (~) G Repeat experiment Departure from experiment airspace
Landing 1G Data storage and verification
End of experiment 20 minutes

As described in Table 1, the droplet combustion test system 1000 for a zero-gravity plane of the present invention receives a signal according to the operation of the switch unit 400 according to the gravitational force (G State) acting on the zero-gravity plane, as described above. A series of processes are performed, and at this time, the droplet combustion experiment system 1000 of the present invention includes a switch control unit 500 that controls the operation of the switch unit 400 according to the change in gravity according to the operation of the zero gravity aircraft 10. Including further, the switch unit 400 may be automatically operated according to a series of experimental processes.

At this time, the switch control unit 500 is a gravity detection sensor 520 that measures the gravity according to the flight of the zero-gravity airplane 10, the switch control unit gravity detection sensor 520 that senses the gravity according to the flight of the zero-gravity airplane Including, it is possible to automatically control the operation of the switch unit 400 according to the gravity (G State) acting on the zero gravity aircraft 10 measured by the gravity sensing sensor 520.

When this is described in more detail with reference to Table 1, the first switch 410 operates when the gravity acting on the zero-gravity plane 10 is 1G, and the second switch 420 is the zero-gravity plane 10 ) Is operated when the gravity acting on is 0.5G ~ 1.2G, and the third switch 430 can operate when the gravity acting on the zero-gravity airplane 10 is micro-G, and at this time, the gravity The detection sensor 520 detects a gravity acceleration sensor such as a gyro sensor or an applied load that detects the acceleration of the zero-gravity plane 10 and calculates gravity acting on the zero-gravity plane, and detects the applied load, and the inductance, capacity, and resistance according to the applied load It may be composed of a load cell (load cell) that detects the gravity acting on the zero-gravity airplane 10 by converting the change value such as, the gravity sensing sensor 520 without departing from the gist of the present invention. 10) It will be possible to implement the transformation by various means for detecting the gravity according to the operation.

In addition, the switch control unit 500 further includes a timer 510 for measuring the flight time of the zero-gravity airplane 10, the switch unit 400 according to the passage of time according to the flight schedule of the zero-gravity airplane 10. ) Operation can be controlled automatically. The timer 510 is a configuration for determining the operation point of each of the switches 510, 520, 530, and the zero gravity plane 10 flying by detecting the change in gravity according to the planned flight of the zero gravity plane 10 You can determine the section you are entering. At this time, the first switch 410 is operated before the zero-gravity plane enters the zero-gravity section, and the second switch 420 is operated before a predetermined time (a) for the zero-gravity plane to enter the zero-gravity section, The third switch 430 is preferably operated immediately after the zero-gravity plane enters the zero-gravity section, and at this time, the predetermined time (a) is according to the change of gravity according to the driving pattern of the zero-gravity plane 10 At this time, when the zero-gravity plane 10 performs the operation of a predetermined pattern from take-off to landing, a predetermined time (a) may be calculated in advance according to the driving pattern of the zero-gravity plane 10, and the zero gravity Among the times measured from the take-off of the airplane 10 to the time of landing, the predetermined time (a) until immediately before entering the zero-gravity section based on the time (T) to enter the specified zero-gravity section is the droplet combustion module ( In 200), it may be a time from the start of fuel injection to just before entering the zero gravity section. At this time, the droplet fuel in the single particle state formed during the predetermined time (a) is determined according to the predetermined flow velocity and supply amount injected from the droplet injector 220, and the gravity state value measured by the gravity sensing sensor 520 ( G state) and time value (Time Required) are values according to an embodiment of the present invention, without departing from the gist of the present invention, the operating state of the zero gravity aircraft 10 in which the droplet combustion test system 1000 of the present invention is mounted And according to the flight schedule, it is preferable to be set to have an appropriate threshold by the operator performing the experiment.

The present invention is not limited to the above-described embodiments, and of course, various modifications can be made without departing from the gist of the present invention as claimed in the claims.

10: zero gravity plane
1000: droplet combustion test system
100: chamber 110: oxygen sensor
120: pressure sensor 130: light source
140: optical window 150: cradle
160: fuel tank
200: droplet combustion module
210: fiber 220: droplet sprayer
221: microtube 222: transport pipe
223: fuel pump
230: rotary motor 240: igniter
241: ignition circuit 242: linear rail
250: linear motor
300: optical equipment 310: radiometer
320: wave camera 330: CCD camera
400: switch unit 410: first switch
420: second switch 430: third switch
440: LED lamp
500: switch control unit 510: timer
520: Gravity sensor
600: storage

Claims (9)

In the droplet combustion experiment system for a zero gravity airplane in a microgravity environment simulated using a zero gravity airplane,
A chamber mounted on a zero gravity plane;
A droplet combustion module provided inside the chamber and injecting and igniting droplet fuel in a single particle state;
Optical equipment for observing the combustion of the droplet fuel in a single particle state formed by the droplet combustion module;
According to the change in gravity according to the operation of the zero-gravity plane, including after take-off of the zero-gravity plane, before a predetermined time (a) before the zero-gravity plane enters the micro-gravity section, and immediately after the zero-gravity plane enters the micro-gravity section. A switch unit for controlling an operation of at least one of a chamber, a droplet combustion module, and an optical device; And
A switch control unit configured to include a gravity sensor for sensing gravity according to the flight of the zero-gravity plane, and automatically control the operation of the switch part according to the change in gravity according to the operation of the zero-gravity plane;
Including,
The droplet combustion module,
At least one fiber disposed on a plane inside the chamber,
A pair of droplet injectors disposed on the same plane as the fibers and receiving fuel having a predetermined flow rate from a fuel pump and injecting fuel into the fibers,
A pair of igniters disposed on a plane spaced apart from the fiber and the droplet injector at a predetermined height to ignite droplet fuel in a single particle state formed on the fiber,
A rotary motor for rotating the droplet injector, and
A linear motor for linearly moving the igniter,
Droplet combustion test system for a zero gravity airplane, characterized in that it comprises a.
delete The method of claim 1,
The switch unit
After the take-off of the zero gravity aircraft, a first switch for operating the rotary motor and the linear motor to enter the droplet injector and the igniter respectively operating points,
Droplet combustion test system for a zero gravity airplane, characterized in that it further comprises.
The method of claim 3,
The switch unit
A second switch for operating the droplet ejector so that fuel is injected at a predetermined flow rate before a predetermined time (a) before the zero gravity airplane enters the microgravity section,
Droplet combustion test system for a zero gravity airplane, characterized in that it further comprises.
The method of claim 4,
The switch unit
A third switch for operating the igniter to ignite droplet fuel in a single particle state formed on the fiber immediately after the zero gravity plane enters the microgravity section,
Droplet combustion test system for a zero gravity airplane, characterized in that it further comprises.
delete delete The method of claim 1,
The switch control unit timer for measuring the flight time of the zero gravity aircraft,
Including,
A droplet combustion test system for a zero gravity airplane, characterized in that for controlling the operation of the switch unit according to the passage of time according to the flight schedule of the zero gravity airplane.
The method of claim 1,
The droplet combustion module is a fiber exchanger for replacing the broken fiber when the fiber is broken by ignition of fuel,
Droplet combustion test system for a zero gravity airplane, characterized in that it further comprises.

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