KR20200068264A - The Droplet Combustion Experiment System for parabolic flight - Google Patents

Abstract

The present invention relates to a droplet combustion test system for a gravity-free aircraft for studying characteristics of combustion phenomenon by simulating a micro-gravity environment of the universe using a weightless airplane on the ground. More specifically, the present invention relates to the droplet combustion test system for the gravity-free aircraft, capable of performing a droplet combustion test in a limited weightless section of the gravity-free aircraft by controlling each of experimental equipment according to a change in gravity of the gravity-free aircraft. The droplet combustion test system for the gravity-free aircraft includes: a chamber; a droplet combustion module; an optical equipment; and a switch unit.

Description

The Droplet Combustion Experiment System for parabolic flight

The present invention relates to a droplet combustion test system for a gravity-free aircraft for studying the characteristics of the combustion phenomenon by simulating the micro-gravity environment of the universe with a weightless airplane on the ground.

Liquid fuel production and consumption are steadily increasing around the world, and most liquid fuel is consumed through combustion in various fields such as power generation, heating, and transportation, where liquid fuel is mostly spray. It is supplied in the form of droplets through and is a combustor when understanding the phenomenon related to droplet combustion, such as evaporation of liquid fuel, heat transfer, mass transfer, preservation of chemical species, and chemical reaction rate. B. It is possible to develop technologies that can contribute to improving the combustion efficiency of engines or reducing pollutants (Nox, soot, etc.).

Research on engines to date has been carried out by researchers using a variety of experimental equipment, and especially in experiments with spray injection of liquid fuel, it is difficult to accurately understand the behavior of a single droplet inside the engine due to the influence of ambient droplets. Has been caused. Accordingly, it is necessary to prevent interference between surrounding droplets through a combustion experiment in a single droplet state having a diameter of 1 mm to 4 mm. In addition, since experiments on the ground are interfered by the self-weight acting on a single droplet fuel, in order to test a more precise combustion phenomenon, an experiment in a gravity-free environment having a micro-scale gravity is required. A droplet combustion experiment using a gravity-free environment in space has been performed through a combustion test equipment mounted on the International Space Station (ISS), a representative experimental space in a micro-gravity 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 is required before launch into space, and a free fall tower is required to simulate the microgravity environment on the ground. , A microgravity environment on the ground can be simulated using a parabolic flight and a 3D clinostat. Japanese Laid-Open Patent Publication No. 2010-069952 (How to Create a Low Gravity Environment by Aircraft, 2010.04.02.) discloses a technique for forming a micro-gravity environment of the parabolic flight, and thus a zero gravity plane In the case of forming a micro-gravity environment by using, the limitation of creating a micro-gravity environment for a limited time was caused by forming a micro-gravity environment through parabolic flight at a high altitude.

Japanese Laid-Open Patent Publication No. 2010-069952 (How to create a low-gravity environment by aircraft, 2010.04.02.)

The present invention has been devised to solve the above problems, and the droplet combustion test system for a zero gravity airplane of the present invention controls each of the experimental equipment according to the gravity change of the zero gravity airplane, thereby causing droplets in the microgravity state created through the zero gravity airplane. We want to conduct a combustion experiment.

In order to solve the above problems, the present invention relates to a droplet combustion test system for a gravityless airplane in a microgravity environment simulated using a gravityless aircraft, and more specifically, a chamber mounted in a gravityless aircraft and provided inside the chamber The droplet combustion module for injecting and igniting the droplet fuel in a single particle state, the optical equipment for observing the combustion of the droplet fuel in a single particle state formed by the experimental module, and the chamber according to the gravity change according to the operation of the zero gravity aircraft , A switch unit for controlling at least one operation of the experiment module and the optical equipment.

At this time, the droplet combustion module is disposed on the same plane as the at least one fiber and the fiber disposed on one plane inside the chamber, and receiving fuel having a predetermined flow rate from the fuel pump to inject fuel to the fiber A pair of droplet injectors, a pair of igniters disposed on a plane spaced a predetermined height from the fiber and the droplet injectors, and igniting the droplet fuel in the form of single particles formed on the fibers, rotating the droplet injectors It may include a rotary motor and a linear motor for linear movement of the igniter.

In addition, the switch unit may further include a first switch for operating the rotary motor and the linear motor to enter the droplet injector and the igniter respectively at the operating point.

In addition, the switch unit may further include a second switch for operating the droplet injector to inject fuel at a predetermined flow rate.

In addition, the switch unit may further include a third switch for operating the igniter to ignite the droplet fuel in the single particle state formed on the fiber.

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

At this time, the switch control unit includes a gravity sensor for detecting the gravity caused by the flight of the weightless aircraft, characterized in that to control the operation of the switch according to the gravity acting on the weightless aircraft measured by the gravity sensor do.

In addition, the switch control unit further comprises a timer for measuring the flight time of the weightless aircraft, it characterized in that it controls the operation of the switch portion over time according to the flight schedule of the weightless aircraft.

In addition, the droplet combustion module is characterized in that it further comprises a fiber exchanger for replacing the broken fiber when the fiber is broken by ignition of fuel.

The present invention according to the above-described configuration, by controlling the fuel supply, ignition and observation according to the gravity change of the zero gravity airplane on the ground to control the droplet combustion experiment for a limited time, the scientific basis of liquid fuel in a micro-gravity environment It is expected to build a database to derive scientific results based on the improvement of understanding of combustion phenomena (combustion rate by combustion environment, flame temperature, radiant heat flow rate, etc.), and it is expected to be used for prevention of flame explosion and fire safety accident. .

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

1 is a graph showing the change in gravity due to the operation of a 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 for explaining the relationship between the chamber, the droplet combustion module and the optical equipment 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 a droplet combustion module according to FIG. 5.
7 is a flow chart showing a method for burning droplets 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.

The present invention can be applied to various changes and can have various embodiments, and specific embodiments will be illustrated in the drawings and described in detail. However, this is not intended to limit the present invention to specific embodiments, and should be understood to include all modifications, equivalents, and substitutes included in the spirit and scope of the present invention.

When an element is said to be "connected" to or "connected" to another component, it is understood that other components may be directly connected to or connected to the other component, but may exist in the middle. It should be.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by a person skilled in the art to which the present invention pertains.

Terms such as those defined in a commonly used dictionary should be interpreted as having meanings consistent with meanings in the context of related technologies, and should not be interpreted as ideal or excessively formal meanings unless explicitly defined in the present application. Does not.

Hereinafter, the technical spirit of the present invention will be described in more detail with reference to the accompanying drawings.

The accompanying drawings are only examples shown in order to explain the technical spirit of the present invention in more detail, so the technical spirit of the present invention is not limited to the form of the accompanying drawings.

1 is a graph showing the change in gravity due to the operation of a weightless airplane, referring to FIG. 1, when the gravity change according to the operation of the weightless airplane 10 is described in detail, the weightless airplane 10 is 21,000feet or more By gliding so as to draw a parabola in the air having an altitude, it is possible to create an environment in which the gravity applied to the non-gravity airplane 10 has a fine value in micro units. In more detail, the inertia of the gravityless aircraft 10, which was raised by turning the engine off and free-falling, after the weightless aircraft 10 was raised to receive a pressure (2G) that is twice the gravity (G). The gravity acting on the zero gravity plane 10 is canceled by, so that for a period of time, the zero gravity plane 10 creates a microgravity (hereinafter referred to as zero gravity) environment (C-D section).

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

At this time, the droplet combustion test system 1000 of the present invention controls the respective devices to perform the droplet combustion experiment for a limited weightless period (T+b) to perform an experiment in a zero gravity environment using the weightless aircraft 10 It aims to do.

2 is a block diagram illustrating a droplet combustion experiment system 1000 according to an embodiment of the present invention, and FIG. 3 is for explaining a relationship between a chamber, a droplet combustion module, and optical equipment according to an embodiment of the present invention. 2 and 3, the droplet combustion test system 1000 of the present invention includes a chamber 100, a droplet combustion module 200, an optical device 300, a switch unit 400, and a switch control unit ( 500) and the storage unit 600.

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 micro-gravity state, As shown in Figure 4, the chamber 100 accommodates the droplet combustion module 200 therein, is mounted inside the weightless aircraft 10, the droplet combustion according to the operation of the weightless aircraft 10 As 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 light inside the chamber 100 and a vacuum pump (not shown) for adjusting the pressure inside the chamber 100 may be included, wherein the chamber 100 includes the droplet combustion module ( In order to create an optimized combustion environment of droplet fuel in a single particle state according to 200), it is formed so that airtightness can be maintained. It is preferable to suppress the reflection of light due to combustion of droplet fuels by applying matte paint and electropolishing (EP) to minimize light reflection. 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 weightless aircraft 10 on which the chamber 100 is mounted. It is desirable to be manufactured to satisfy 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 a droplet combustion module according to FIG. 5, referring to FIGS. 5 and 6, the droplet combustion module ( 200) is provided inside the chamber 100, and is configured to perform a droplet combustion experiment that injects and ignites droplet fuel in a single particle state, and the droplet combustion module 200 is installed inside the chamber 100 Equipment including a fiber 210, a droplet injector 220, a rotating motor 230, an igniter 240, and a linear motor 250 for the combustion test of droplet fuel is disposed on one surface of the cradle 150 It is preferably formed.

At this time, the fiber 210 is a linear fiber (Fiber) disposed on a plane inside the chamber 100 so that the fuel injected from the droplet injector 220 can be formed in a single particle state, the liquid The fuel injected from the integrator 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 leave the observation area during combustion of the droplet fuel.

The droplet injector 220 transports the microtube 221 and the microtube 221 and the fuel pump 223 for injecting the fuel supplied from the fuel pump 223 into the fiber 210. It may be made of a tube 222, wherein the control unit 400 controls the flow rate and the amount of fuel injected according to the inner diameter of the fine tube 221, the single particle of the fiber 210 The size of the droplet fuel can be adjusted. That is, the control unit 400 forms the size of the droplet fuel in the single-particle state designed in consideration of the combustion time of the droplet fuel in the single-particle state for a period of time (b) in which the single weightless section of the weightless aircraft 10 lasts. In order to be able to do so, the discharge amount of the fuel pump 223 must be controlled so that the fuel discharged from the fuel pump 223 has a predetermined flow rate. At this time, the fuel pump 223 controls the flow rate and flow rate of the fine fuel, and the pump It is preferable to use a syringe pump (syringe pump) to prevent errors due to the pulsation of.

In addition, the droplet injector 220 is preferably formed in a pair disposed on the same plane as the fiber 210, the pair of droplet injectors 220 is based on the fiber 210 It includes a pair of microtubes 221 arranged to face each other facing each other, and the pair of microtubes 221 are connected to one side of the transport pipe 222 extending in the vertical direction, respectively. The other side of 222 is connected to the rotating motor 230 so that a pair of droplet sprayers 220 perform rotational movements having a constant radius based on each rotating motor 230 in opposite directions. It works. At this time, the pair of microtubes 221 is rotated by a certain radius starting from a point of the fiber 210, and the droplet sprayer 220 has the pair of microtubes 221 having the fiber 210 ) Is operated to inject fuel at a point that is disposed to face each other in close proximity to any one point, and the distance between the pair of microtubes 221 and the fibers 221 is the size of the droplet fuel in a single particle state. It is preferable to have, but is operated to gradually move away when the fuel is injected so that the fuel can be driven to enter the fiber 210 in a single particle state.

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

The optical device 300 is a configuration for observing the combustion of the droplet fuel in the form of a single particle formed by the droplet combustion module 200, a plurality of optics for measuring the observation area in which the droplet fuel in the form of single particles is formed It comprises a camera, the plurality of optical cameras should be arranged to have a position and angle that does not interfere with the viewing field of view by the respective devices of the droplet combustion module (200).

In addition, the optical device 300 measures a flame temperature by measuring a radiation meter (310, radiometer) for measuring the energy of electromagnetic waves generated during combustion of the droplet fuel and a radiation light generated during combustion of the droplet fuel. Includes two types of CCD cameras 320 combined with an optical filter to do so, and the color for observing the image of droplet fuel combustion in the radiation meter 310, CCD camera 320 and microgravity environment A plurality of cameras 330 may be provided, respectively, and may be disposed inside or outside the chamber 100.

The radiation meter 310 is composed of three, each of which can measure the radiation energy of different wavelengths. In general, the wavelength of the flame generated during combustion varies from the visible light to the infrared region. One radiation system (310b) is a radiation system that covers all the wavelength bands in this region. The radiation meters 310a and 310c monitor the radiant energy in the range of 5.5um to 7.5um, which is one of the wavelength bands of water. It is possible to confirm the creation/decay of flame and other physical phenomena by measuring the radiant energy of water (H2O), one of the products of combustion.

In addition, the CCD camera 320 performs non-contact temperature measurement capable of predicting the temperature of the flame in an independent manner of emissivity by simultaneously measuring radiant light of soot particles emitted at different wavelengths and applying it to Planck's law, 700 nm The spatial temperature distribution of the diffusion flame can be predicted by using the optical filter of and 900 nm band filter, and the error caused by reducing the interval of dividing the visual line can be minimized. At this time, if it is applied to measure the flame temperature, the radiant intensity of the soot particles formed inside the flame is an important variable, and in the region where the temperature is relatively low, such as the central portion of the flame, errors in flame temperature prediction may occur due to the weak radiative strength. 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 in gravity in the zero gravity plane according to the operation of the zero gravity plane 10 As a configuration for controlling at least one operation, the switch unit 400 is a driving pattern of the zero gravity aircraft 10 that simulates a zero gravity environment through a parabolic flight in the sky, that is, the gravity of the gravity according to the operation of the zero gravity aircraft 10 It is configured to control the chamber 100, the droplet combustion module 200, and the optical equipment 300 according to changes. In this case, the storage unit 600 collects and stores information measured and observed in the chamber 100, the droplet combustion module 200, and the optical device 300 and data accompanying the droplet combustion experiment to be databased. Can be.

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 that lights up an experimental state according to the operation of the switches. ), wherein, Figure 7 is a flow chart of a droplet combustion experiment according to an embodiment of the present invention, using the droplet combustion test system 1000 for gravity-free aircraft below with reference to Figures 2 and 7 The droplet combustion experiment in a non-gravity aircraft will be described in detail.

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

More specifically, the first switch 410 may be operated before the zero gravity plane 10 takes off and enters the zero gravity section (section C of FIG. 1), preferably after the zero gravity plane 10 takes off. It is operated before the section in which the second switch operates (section A in FIG. 1). At this time, the control unit 400 receives the operation signal of the first switch 510, creates an experiment environment inside the chamber 100, and the droplet ejector 220 and the igniter (of the droplet combustion module 200) The operation of the rotating 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 by the weightless aircraft before entering the weightless section, and preparing the droplet fuel before entering the weightless section, and thereafter, the weightless airplane 10 Immediately after entering the zero gravity section, the third switch 530 may be operated to perform a measurement step (S300) of igniting and observing the droplet fuel formed in the fiber 210.

At this time, the above-described series of steps is preferably performed according to the change in gravity acting on the weightless aircraft, and at this time, precisely designed experiments by controlling the operation of the switch unit over time according to the flight schedule of the weightless aircraft It can be done.

8 is a flow chart for explaining the overall operation of the combustion experiment system 1000 according to an embodiment of the present invention, the sequence in which the combustion experiment system 1000 operates according to the change of gravity is further time-series from below It will be explained in detail.

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

[t <T-a]

Before the zero gravity plane 10 enters the zero gravity section, a pair of rotating motors 230 and a linear motor 250 are operated, and the droplet jet 220 and the igniter 240 are respectively operated. The preparation step (S100) for entering is performed, wherein the preparation step (S100) may be operated by the first switch 510.

[T-a ≤ t <T]

Subsequently, before the predetermined time (a) before the zero gravity plane 10 enters the zero gravity section, a fuel pump is operated to supply fuel to the droplet injector 220, thereby dropping droplets in the form of single particles on the fiber 210 The fuel supply step (S210) for forming fuel is performed, and the control unit 400 operates the pressure sensor 120 and the oxygen sensor 110 provided in the chamber 100 to operate the environment inside the chamber 100. It comprises a sensor measuring step (S220) for measuring and the observation step (S230) for operating the optical device 300 to observe the formed droplet fuel, wherein the series of steps described above is the second switch ( 420) is performed uniformly by the operation signal received from. At this time, in the observation step (S230), it is possible to control the observation to be performed after the input delay time by delaying the operation time of the plurality of cameras and illuminators of the optical equipment 300 as necessary.

[T ≤ t <T+b]

Subsequently, 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 single-particle droplet fuel, and then the rotary motor 230 And measurement in the sensors of the chamber 100 after being delayed by a predetermined time (b) set immediately after entering the ignition step (S310) and the weightless section in which the linear motor 250 is retracted to be separated from the fiber 210. And an end step 320 of stopping observation of the optical equipment 300. At this time, the predetermined time (b) in which the termination step (S320) is operated is preferably a time point (T+b) in which the weightless aircraft 10 deviates from the weightless area, but in some cases is a time point when the combustion of a single droplet fuel ends. Will be able to.

[t ≥ T+b]

In addition, after the weightless aircraft 10 leaves the weightless section, the number of experiments N set according to the flight schedule of the weightless aircraft 10 is counted, and the process returns to the preparation step (S100) for the experiment of the next order. It may be performed by further comprising a repeating experiment step (S400).

In this case, when the fiber 210 is damaged by the ignition of fuel, the droplet combustion module 200 operates the fiber exchanger 260 to replace the broken fiber 210, thereby breaking the broken fiber 210. Can be replaced to prepare for the next order of experiments. In the related art, when the fiber is damaged, the inconvenience of the operator having to replace the fiber directly occurs, while the present invention uses the fiber exchanger 260 to replace the broken fiber, thereby operating the gravityless aircraft 10 There is an advantage that it is possible to perform the experiment of the next order faster because the operator does not perform the fiber replacement work for a limited time.

9 is a view for explaining the switch unit 400, a view showing a control panel composed of a plurality of switches and LEDs. Referring to FIG. 9, the switch unit 400 has a total of four LED ( LG, LR), one selector switch (SSL), and 15 push switches (PB), while the experiment is in progress in a zero-gravity aircraft, grasp the operation status inside the combustion tester by LED, and The combustion test module can be controlled for each step and for each part (each motor) by a push switch.

At this time, the lamp unit 440 is a first lamp (441, Ready) indicating a ready state to start the combustion experiment, a pair of rotary motors of the droplet injector and a pair of linear motors to ignite the droplet fuel The second lamp (442, 1st ing) indicating the operating state, the third lamp (443, Rdy for Ign) indicating that the supply of the droplet fuel is completed and the ignition for the combustion experiment is ready, and the combustion state of the droplet fuel It includes a fourth lamp (444, Igniting), the first switch 410 transmits a signal to the motor and limit switches that are operated to perform the preparation step (S100), a pair of linear motors ( 250) and a motor including a pair of rotating motors 230 are spaced apart from the fiber 210 and fixed by a limit switch, each of which is an initial switch 410a which is operated to prevent parts from deviating from the rotating radius, and It may be formed by including a 1st switch (410b) that is operated to rotate the motor including a pair of linear motor 250 and a pair of rotating motors 230 adjacent to the fiber 210, wherein the combustion experiment In the preparation step (S100), the control is performed through the 1st switch 410b, and the control is performed through the initial switch 410a in the repetition test step (S400), in which the experiment of the next order is returned to the preparation step S100. 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 continuously lighting to stop flashing, the motor is displayed to the user. In addition, by operating the second switch (420, Pump X), and controls to perform the fuel supply step (S200), the droplet injector 220 is preset by the user by the second switch (420) By supplying fuel as much as the fuel amount X, at this time, the second switch 420 is repeatedly operated to supply fuel so as to form a desired droplet size during the experiment. Thereafter, when the supply of the droplet fuel is completed, the third lamp 443 lights up 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 droplet fuel is operated and the fourth After the lamp 444 is turned on, and the pair of rotating motors and the pair of linear motors retreat to their initial positions, the first lamp 441 is turned on again to display the combustion state of droplet fuel.

At this time, the switch unit 400 is provided with a linear X switch (411a), a linear Y switch (441b), Rotated to control the pair of rotary motor 230 and a pair of linear motor 250 respectively It may include an X switch (412a) and a rotated Y switch (412b), through the linear X switch (411a), the linear Y switch (441b), the igniter (240) to each forward or backward control by a certain displacement value It is possible to rotate the droplet injector 220 by a certain radius value through the Rotated X switch 412a and the Rotated Y switch 412b, so that it can be fine-tuned, thereby controlling an error value due to self-weight or external force. It has the advantage of being able to compensate. At this time, the switch unit 400 may further include a selection switch 413 provided to select the 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) paired with one rotating motor (230, A in FIG. 3) or another linear motor (250, B in FIG. 3) paired with another rotating motor (230, B in Fig. 3) is operated to control separately.

Also, the switch unit 400 sets a pump initialization switch 421 for controlling the fuel pump 223, a reset switch 440 for initializing the set control value, and a reference point for controlling the motor. Zero point switch (450, zero), emergency switch 460, which is operated to stop all control in case of emergency to prevent safety accidents, and mode switching switch to perform manual/automatic mode switching of the switch unit 400 (470, mode chg), the fiber switch 260 to rotate the motor of the fiber exchanger to the initial position switch (280a, FM0) and the motor of the fiber exchanger 260 by rotating a certain angle to the part where droplets can be supplied It may be configured to further include a fiber exchange switch 280b, FM90 to operate to position.

At this time, the following Table 1 is the gravity value (G State) acting on the gravity-flight aircraft operating sequence of the droplet fuel test system 1000 when performing a droplet fuel test in a zero gravity airplane according to an embodiment of the present invention and As shown in accordance with the control time value (Time Required), referring to Table 1 and FIG. 1 below, the weightless section simulated by the weightless aircraft 10 is constructed for a limited time (b), thereby limiting the weightlessness The target droplet combustion experiment should be performed for time (b). 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 ejector 220 of the droplet combustion module 200 and The rotating motor 230 and the linear motor 250 are controlled to move the igniter 240 to a position proximate to the fiber 210, and must be prepared in advance until fuel is injected, and then the zero gravity airplane 10 is weightless The technical idea of the present invention is required to operate the droplet injector 220 before a predetermined time (a) to enter a section to form a target single-particle droplet fuel during the predetermined time (a).

State of Aircraft G State Work Item Time Required Loading 1G System setting (Stop → Reset → Initial → Zero → Pump initial)
Pre-filled fuel piping in the combustion test equipment
Check the fuel supply line change during altitude rise Continues "2 minutes before starting 1st PF"
↓ 1G Chamber pressure setting (xbar),
System zero setting and experiment 1st stage positioning
(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 minutes "1 minute"
↓ 0.5 ~ 1.2G Experiment standby after fuel supply (diameter 2.5mm) (Pump X) 1 minutes "30 seconds"
↓ 2G Waiting for the experiment 30 seconds "NOW" micro-G After ignition of droplet fuel (Igniter)
Automatic recording of experimental data 6 seconds End of 0G
Normal flight
↓ 1.5G Check the test results (whether or not to ignite/drop fuel) 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 setting and experiment 1st stage positioning
(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 the experiment 1 minute "1 minute"
↓ 0.5 ~ 1.2G Experiment standby after fuel supply (diameter 2.5mm) (Pump X) 1 minutes "30 seconds"
↓ 2G Waiting for the experiment 30 seconds "NOW" micro-G After ignition of droplet fuel (Igniter)
Automatic recording of experimental data 6~8 seconds end of 0G
Normal flight
↓ 1.5G Check the test results (whether or not to ignite/drop fuel) 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 weightless airplane of the present invention receives the signal according to the operation of the switch unit 400 according to the gravity (G State) acting on the weightless airplane and described above. Performing a series of processes, at this time, the droplet combustion test system 1000 of the present invention is a switch control unit 500 for controlling the operation of the switch unit 400 according to the gravity change according to the operation of the weightless aircraft 10 In addition, the switch unit 400 may be automatically operated according to a series of experimental procedures.

At this time, the switch control unit 500 is a gravity detection sensor 520 for measuring the gravity due to the flight of the weightless aircraft 10, the switch control unit is a gravity detection sensor 520 for detecting the gravity due to the flight of the weightless aircraft Further comprising, it is possible to automatically control the operation of the switch unit 400 according to the gravity (G State) acting on the weightless aircraft 10 measured by the gravity sensor 520.

Referring to this in more detail with reference to Table 1, the first switch 410 operates when the gravity acting on the weightless aircraft 10 is 1G, and the second switch 420 is the weightless aircraft 10 ) Acts when the gravity acting from 0.5G to 1.2G, and the third switch 430 can operate when the gravity acting on the zero gravity plane 10 is micro-G, wherein the gravity The sensing sensor 520 detects the acceleration of the zero gravity airplane 10 and senses a gravity acceleration sensor such as a gyro sensor that calculates the gravity acting on the zero gravity airplane, or an applied load, and inductance, capacity, and resistance according to the applied load. It can be composed of a load cell (load cell) to detect the gravity acting on the weightless aircraft 10 by converting the change value of the back, the gravity sensor 520 is a gravity-free aircraft without departing from the subject matter of the present invention ( 10) It will be possible to perform deformation by various means for detecting the gravity due to the operation.

In addition, the switch control unit 500 further includes a timer 510 for measuring the flight time of the zero gravity plane 10, the switch unit 400 according to the passage of time according to the flight schedule of the zero gravity plane 10 ) Can be controlled automatically. The timer 510 is configured to determine the operating point of each of the switches 510, 520, and 530, and the zero gravity plane 10 that detects and changes the gravity according to the planned flight of the zero gravity plane 10 You can judge the section you are entering. At this time, the first switch 410 operates before the zero gravity plane enters the zero gravity section, and the second switch 420 operates before a predetermined time (a) before the zero gravity plane enters the zero gravity section, The third switch 430 is preferably operated immediately after the zero gravity plane enters the zero gravity section, wherein the predetermined time (a) depends on the change in gravity according to the driving pattern of the zero gravity plane 10 At this time, when the weightless airplane 10 performs the operation of the predetermined pattern from the time of take-off to landing, the predetermined time (a) may be pre-calculated according to the driving pattern of the weightless airplane 10, and the weightlessness Of the times measured from the time of take-off of the airplane 10 to the time of landing, the predetermined time (a) from immediately before entering the weightless section based on the time (T) for entering the predetermined weightless section is the droplet combustion module ( At 200), it may be a time from when fuel injection is started to immediately before entering the weightless section. At this time, the droplet fuel in the form of a single particle formed during the predetermined time (a) is determined according to a predetermined flow rate and a supply amount injected from the droplet injector 220, and the gravity state value measured from the gravity sensing sensor 520 ( G state) and the time value (Time Required) are values according to an embodiment of the present invention, without departing from the gist of the present invention, the operation state of the zero gravity aircraft 10 on which the droplet combustion experiment 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 value by the operator performing the experiment.

The present invention is not limited to the above-described embodiment, the scope of application is, of course, various modifications are possible without departing from the gist of the invention as claimed in the claims.

10: weightless airplane
1000: Droplet combustion test system
100: chamber 110: oxygen sensor
120: pressure sensor 130: light source
140: optical window 150: holder
160: fuel tank
200: droplet combustion module
210: fiber 220: droplet injector
221: microtube 222: transport pipe
223: fuel pump
230: rotating motor 240: igniter
241: ignition circuit 242: linear rail
250: linear motor
300: optical equipment 310: radiation meter
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 unit

Claims (9)

In the droplet combustion test system for a gravityless airplane in a microgravity environment simulated using a gravityless aircraft,
A chamber mounted on a zero gravity plane;
A droplet combustion module provided inside the chamber to inject and ignite droplet fuel in a single particle state;
Optical equipment for observing the combustion of droplet fuel in a single particle state formed by the experiment module; And
A switch unit for controlling at least one operation of the chamber, the experimental module, and the optical equipment according to a change in gravity according to the operation of the zero gravity plane;
It characterized in that it comprises a droplet combustion experiment system for weightless aircraft.
According to claim 1,
The droplet combustion module,
At least one fiber disposed on one plane inside the chamber,
A pair of droplet injectors arranged on the same plane as the fiber and receiving fuel having a predetermined flow rate from a fuel pump to inject fuel into the fiber,
A pair of igniters arranged on a plane spaced a predetermined height from the fiber and the droplet injector to ignite the droplet fuel in the form of single particles in the fiber,
A rotary motor for rotating the droplet injector, and
Linear motor for linear movement of the igniter,
Droplet combustion test system for zero gravity airplane, characterized in that it comprises a.
According to claim 2,
The switch unit is a first switch for operating the rotary motor and the linear motor to enter the droplet injector and the igniter respectively to the operating point,
Droplet combustion experiment system for weightless aircraft, characterized in that it further comprises.
According to claim 3,
The switch unit is a second switch for operating the droplet injector to inject fuel at a predetermined flow rate,
Droplet combustion experiment system for weightless aircraft, characterized in that it further comprises.
The method of claim 4,
The switch unit is a third switch for operating the igniter to ignite the droplet fuel in a single particle state formed on the fiber,
Droplet combustion experiment system for weightless aircraft, characterized in that it further comprises.
The method of claim 5,
The droplet combustion test system includes a switch control unit that automatically controls the operation of the switch unit according to a change in gravity according to the operation of the zero gravity plane;
Droplet combustion experiment system for weightless aircraft, characterized in that it further comprises.
The method of claim 6,
The switch control unit is a gravity detection sensor for detecting the gravity due to the flight of the weightless aircraft,
Including,
Droplet combustion test system for a zero gravity airplane, characterized in that to control the operation of the switch according to the gravity acting on the zero gravity plane measured by the gravity sensor.
The method of claim 7,
The switch control unit is a timer for measuring the flight time of the weightless aircraft,
Including,
Droplet combustion test system for a zero gravity airplane, characterized in that to control the operation of the switch unit over time according to the flight schedule of the zero gravity aircraft.
According to claim 2,
The droplet combustion module is a fiber exchanger for replacing the broken fiber when the fiber is broken by ignition of fuel,
Droplet combustion experiment system for weightless aircraft, characterized in that it further comprises.

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