KR102317964B1 - Experimental educational system and analysis methods, using a simple wind tunnel, glider, webcam and computer - Google Patents

Abstract

Disclosed are a glider, a simple wind tunnel, a webcam, and an experimental system for educating aircraft stability using a computer and a method therefor. Aircraft stability analysis system according to an embodiment of the present invention is a wind tunnel device for generating wind; an aircraft connected to the wind tunnel device by a connecting means and whose motion is changed by the wind generated by the wind tunnel device; a first photographing means for photographing an image for analyzing a pitch motion of the aircraft; a second photographing means for photographing an image for analyzing a roll motion and a yaw motion of the aircraft; And by analyzing the image taken by the first shooting means and the second shooting means to analyze the change in pitch motion, roll motion and yaw motion with respect to the vehicle, the analyzed pitch motion, roll motion with respect to the vehicle And control means for analyzing the stability of the vehicle based on the change in the yaw motion, wherein the vehicle is the head of the vehicle through the connecting means to limit the translational motion of the vehicle and leave only the rotational motion component The part and the wind tunnel device are connected.

Description

Experimental educational system and analysis methods, using a simple wind tunnel, glider, webcam and computer}

The present invention relates to an experimental technique for teaching aircraft stability using a glider, a simple wind tunnel, a webcam, and a computer. It relates to an aircraft stability analysis system and method for easily analyzing stability.

The activity of making model gliders or airplanes is a topic that is frequently dealt with in the field of gifted education and free exploration, and the basic principles are also covered in the high school curriculum. It is desirable to design a glider considering stability, but it is not easy for students to understand how to design a glider to have stability at the level of the secondary school curriculum. Stability of a glider is that it has the property of returning to its original equilibrium state in response to changes in rotation about the pitch, roll, and yaw axes of the glider in flight from its equilibrium position. It is difficult to find activities or data that can directly confirm the resilience of

In order to produce educational materials that can educate gifted students about the stability of an airplane, the existing technologies that can show the stability of an airplane are mainly about stability-related concepts showing how a glider glides when stability is broken or theoretical Most of them are presented in the direction of educating the concept. Although the currently proposed methods can explain the stability of the glider, it will help students to understand the concept of stability more easily and directly if it is possible to directly experimentally show that the glider returns to the equilibrium state when the three axes of the glider are changed. this could be In addition, rather than simply flying a glider or vehicle in an uncontrolled environment, showing experiments in a controlled environment would be appropriate to more systematically educate safety. A wind tunnel experiment is an ideal way to study and verify flight conditions in a small space in a controlled environment.

However, the wind tunnel test apparatus used in actual universities and industrial sites takes up a lot of volume and is expensive to use in the field of secondary and high schools.

Embodiments of the present invention provide a vehicle stability analysis system and method capable of easily analyzing the stability of the pitch axis, the roll axis and the yaw axis of the vehicle using a simple wind tunnel device and a photographing means having a simple structure.

Aircraft stability analysis system according to an embodiment of the present invention is a wind tunnel device for generating wind; an aircraft connected to the wind tunnel device by a connecting means and whose motion is changed by the wind generated by the wind tunnel device; a first photographing means for photographing an image for analyzing a pitch motion of the aircraft; a second photographing means for photographing an image for analyzing a roll motion and a yaw motion of the aircraft; And by analyzing the image taken by the first shooting means and the second shooting means to analyze the change in pitch motion, roll motion and yaw motion with respect to the vehicle, the analyzed pitch motion, roll motion with respect to the vehicle And control means for analyzing the stability of the vehicle based on the change in the yaw motion, wherein the vehicle is the head of the vehicle through the connecting means in order to limit the translational motion of the vehicle and leave only the rotational motion component The part and the wind tunnel device are connected.

The wind tunnel device may include a wind generator and a rectification grid, and the rectification grid may be disposed between the wind generator and the aircraft.

The aircraft may be changeable in position with respect to the main wing, and the angle may be changed with respect to the chord line of the main wing.

The control means may analyze the stability of the vehicle by approximating the angular change with respect to the equilibrium position of the vehicle with at least one of a slight attenuation function model and a critical attenuation function model.

Vehicle stability analysis system according to another embodiment of the present invention is a simple wind tunnel device including a wind generating device and a rectification grid for generating wind; a model aircraft connected to the simple wind tunnel device by a connection means, and whose motion is changed by the wind generated by the simple wind tunnel device; a first photographing means for photographing a side video of the model vehicle; a second photographing means for photographing a rear video of the model aircraft; And by analyzing the moving picture taken by the first shooting means and the second shooting means to analyze the changes in the pitch motion, roll motion and yaw motion for the model vehicle, the analyzed pitch motion for the model vehicle, and control means for analyzing the stability of the model vehicle based on changes in roll motion and yaw motion, wherein the model vehicle uses the connecting means to limit the translational motion of the model vehicle while leaving only the rotational motion component. The head of the model aircraft is connected to the simple wind tunnel device through the

The vehicle stability analysis method according to an embodiment of the present invention comprises the steps of: receiving a first image for analyzing a pitch motion of a vehicle connected to a simple wind tunnel device and a first image for analyzing a roll motion and a yaw motion of the vehicle; analyzing changes in pitch motion, roll motion and yaw motion with respect to the vehicle through the analysis of the received first and second images; and analyzing the stability of the vehicle based on changes to the analyzed pitch motion, roll motion and yaw motion with respect to the vehicle, wherein the vehicle restricts the translational motion of the vehicle while leaving only the rotational motion component For this, the head of the aircraft and the wind tunnel device are connected.

The simple wind tunnel device may include a wind generator generating wind and a rectification grid, and the rectification grid may be disposed between the wind generator and the aircraft.

Furthermore, the vehicle stability analysis method according to an embodiment of the present invention further comprises the step of changing the position with respect to the main wing of the vehicle or the angle with respect to the chord line of the main wing, and analyzing the change The step of changing the position of the main wing or the angle change with respect to the chord line through the analysis of the received first image and the second image in the state of change of position with respect to the main wing or the change of angle with respect to the chord line It is possible to analyze changes in pitch motion, roll motion and yaw motion with respect to the flying vehicle.

In the step of analyzing the stability, the stability of the vehicle can be analyzed by approximating the angular change with respect to the equilibrium position of the vehicle with at least one of a slight attenuation function model and a critical attenuation function model.

According to embodiments of the present invention, it is possible to easily analyze the stability of the pitch axis, the roll axis and the yaw axis of the aircraft by using a simple wind tunnel device and a photographing means having a simple structure.

According to embodiments of the present invention, education on various concepts such as aircraft stability, damped harmonic vibration, and three-dimensional multi-rigid motion at elementary, middle, and high school education and university lower grade levels can be shown through intuitive experiments, and various It can be easily applied in the educational field. In particular, in the modern educational environment where science and technology education is emphasized, it is possible to provide intuitive education on concepts using experimental tools for aircraft stability with simple devices as well as elementary and secondary courses.

According to the embodiments of the present invention, it is possible to directly understand various physical and mathematical concepts such as damped harmonic vibration, principal axis decomposition, etc. can help with

1 shows an exemplary view for explaining the three axes of the glider.
Figure 2 shows an exemplary view of a glider manufactured to explain the present invention.
3 shows an exemplary view of a simple wind tunnel device for explaining the present invention.
FIG. 4 shows an exemplary view for explaining the commutation grid shown in FIG. 3 .
5 shows the configuration of a system according to an embodiment of the present invention.
6 and 7 show exemplary views for explaining pitch motion analysis.
8 and 9 show exemplary views for explaining the analysis of roll motion.
10 and 11 show exemplary views for explaining yaw motion analysis.
12 shows an exemplary view for explaining the pitch angle change according to the position of the main wing.
13 shows an exemplary view for explaining the equilibrium state change according to the angle of the chord line of the main wings.
14 shows the angle change from the equilibrium point with time in the pitch motion and the results of fitting it with the critical damping function and the slight damping vibration function.
15 shows the change in angle from the equilibrium point with time in the roll motion and the results of fitting it with the critical damping function and the slight damping vibration function.
16 shows the angular change from the equilibrium point over time in the yaw motion and the results of fitting it with the critical damping function and the slightly damped vibration function.

Advantages and features of the present invention and methods of achieving them will become apparent with reference to the embodiments described below in detail in conjunction with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but will be embodied in various different forms, and only these embodiments allow the disclosure of the present invention to be complete, and common knowledge in the art to which the present invention pertains It is provided to fully inform those who have the scope of the invention, and the present invention is only defined by the scope of the claims.

The terminology used herein is for the purpose of describing the embodiments, and is not intended to limit the present invention. As used herein, the singular also includes the plural unless specifically stated otherwise in the phrase. As used herein, "comprises" and/or "comprising" refers to the presence of one or more other components, steps, operations and/or elements mentioned. or addition is not excluded.

Unless otherwise defined, all terms (including technical and scientific terms) used herein may be used with the meaning commonly understood by those of ordinary skill in the art to which the present invention belongs. In addition, terms defined in a commonly used dictionary are not to be interpreted ideally or excessively unless specifically defined explicitly.

Hereinafter, preferred embodiments of the present invention will be described in more detail with reference to the accompanying drawings. The same reference numerals are used for the same components in the drawings, and repeated descriptions of the same components are omitted.

Embodiments of the present invention have a gist of it to provide a system that can easily analyze the stability of the pitch axis, the roll axis and the yaw axis of the aircraft using a simple wind tunnel device and a photographing means having a simple structure.

Here, the wind tunnel device may consist only of a fan (or an air circulator) and a commutation grid, and although the wind tunnel device in the present invention has a simple structure, it is sufficient to float an aircraft made of a light material, for example, a glider, and analyze the motion. It can provide air volume and control function.

The present invention floats an aircraft such as a glider in a simple wind tunnel device consisting only of a wind generating device such as an air circulator and a commutation grid, so that the three axes of the glider, that is, the pitch axis, the roll axis, and the yaw axis axis))) can be analyzed. The glider to be floated on the wind tunnel device can be manufactured so that the status change of the glider can be seen according to the change in the position of the main wing or the angle of the chord line. The motion of the vehicle can be observed through image analysis using the means.

At this time, the present invention approximates the angular change with respect to the equilibrium position with a gradual decay function model and a critical decimation function model (GR Fowls, GL Cassiday, Analytical Mecanics (Cengage Learning, Canada, 2005)) through a video analysis method to determine the glider three The stability of the axis can be analyzed. Since the motion approximated by the slight damping function model or the critical damping function model has the property of returning to the equilibrium position with respect to the equilibrium displacement, the explanation of stability becomes possible at a certain level, for example, at the high school level.

A system is said to be in stable equilibrium if it has the property of returning to its original state when there is a change. A system with damped oscillations with respect to displacement is in a stable equilibrium state.

The function of the slight attenuation model with respect to the time (t) of the angle change can be expressed as in <Equation 1> below, and the function of the critical attenuation model with respect to the time (t) of the angle change is as shown in <Equation 2> below can indicate

[Equation 1]

[Equation 2]

는 속력에 비례하는 감쇠항의 비례상수 c와 물체의 질량 또는 관성모멘트에 해당하는 물리량 m에 대해

로 정의되는 감쇠인자(damping factor)를 의미하는데, 감쇠인자는 곡선맞춤 등으로 구할 수 있다.Here, A, B and C mean constants obtained by nonlinear curve fitting using the least squares method,

is for the proportional constant c of the damping term proportional to the speed and the physical quantity m corresponding to the mass or moment of inertia of the body.

It means a damping factor defined by . The damping factor can be obtained by curve fitting.

1 shows an exemplary view for explaining the three axes of the glider, as shown in FIG. 1 , the glider has three vertical axes, each of which is called a horizontal axis, a vertical axis, a vertical axis or a pitch axis, a roll axis, and a yaw axis. . The rotational motions about each axis are called pitch motion, roll motion, and yaw motion. If there is a property to return to the original state for each motion, the glider can be said to be stable.

2 shows an exemplary view of a glider manufactured to explain the present invention, and as shown in FIG. 2, the body of the glider is made of a specific material, for example, millet keg, with a specific paper, for example, A4 paper. It can be made by packaging, and if only millet cans are used, it is easily broken when it collides with the wall. The main wing and tail wing can be made of wood lock, and the angle of the wing can be adjusted by fixing the clip on the lower surface of the main wing. In addition, in the present invention, the glider in the present invention, in order to be able to move the main wing and the tail wing back and forth, a cradle in the shape of a square column for coupling the wing and the body may be separately manufactured using a wood lock. In order to adjust the center of gravity, a weight, for example, tongs for documents may be used, and through which the position may be adjusted back and forth. The glider manufactured in this way is connected to the wind tunnel device, so that the change in pitch motion according to the position of the wing and the change in roll motion according to the angle of the wing can be compared through shooting by means of a photographing means.

Figure 3 shows an exemplary view of a simple wind tunnel device for explaining the present invention, Figure 4 is a view showing an exemplary view for explaining the commutation grid shown in FIG.

Referring to FIGS. 3 and 4 , the simple wind tunnel device may be composed of only a wind generating device, for example, a fan or an air circulator and a commulator lattice, and the commutation lattice is dependent on the performance and performance of the 3D printer. In order to solve problems such as the rigidity of the grid, it can be manufactured in the same standard as in FIG. 4, and by combining a certain number of rectification grids in consideration of the size of the air circulator and the size of the rectification grid, rectification constituting a simple wind tunnel device A grid can be constructed. Here, the air circulator may use a product of Bonaido 633, and the rectifier grid may follow the standards presented in the Korean Industrial Standards.

5 shows the configuration of a system according to an embodiment of the present invention.

Referring to FIG. 5 , the system of the present invention includes a wind tunnel device, a glider, a first photographing means (webcam1), a second photographing means (webcam2), and a control means (note book).

The wind tunnel device includes a wind generating device and a rectifying grid as shown in FIGS. 3 and 4 , and the rectifying grid is disposed between the wind generating device and the aircraft.

Here, the wind tunnel device may connect the wind tunnel device and the aircraft through the connecting means, for example, by connecting the rectification grid and the aircraft with a thread so that the aircraft floats by the wind generated by the wind generator.

Furthermore, the wind tunnel device and the vehicle may connect the head of the vehicle and the wind tunnel device through the connecting means in order to limit the translational motion of the vehicle while leaving only the rotational motion component in the process of coupling the wind tunnel device and the vehicle by the connecting means. .

The first photographing means and the second photographing means are means for photographing the motion of the vehicle, that is, the glider as a video, the first photographing means photographing a video from the side of the vehicle, and the second photographing means By shooting a video, it is possible to shoot a video about the change in pitch motion of the vehicle and a video about the roll motion and yaw motion of the vehicle.

The control means analyzes the video taken by the first and second photographing means to acquire three-dimensional position change information of the vehicle, and then analyzes it in the necessary coordinate system, thereby analyzing the stability of the vehicle.

Here, the control means analyzes the images taken by the first and second photographing means by analyzing the pitch motion, the roll motion, and the change in the yaw motion with respect to the vehicle, and the analyzed pitch motion with respect to the vehicle , the stability of the vehicle may be analyzed based on changes to the roll motion and the yaw motion.

At this time, the control means can analyze the stability of the vehicle by approximating the angular change with respect to the equilibrium position of the vehicle with the slight attenuation function model and the critical attenuation function model.

As the control means, the analysis program can be configured using Logger Pro 3.14 and Microsoft's Excel. Data can be extracted by ignoring motion as well.

Further, the control means sets the part where the thread is fixed as the origin and the rotation axis as shown in FIG. 6 in order to check the degree of attenuation for the change of the pitch axis, and gives a change in the equilibrium position as shown in FIG. You can measure an angle to a position.

At this time, when using Logger Pro 3.14 as the control means, since there is no function to measure the angle in Logger Pro 3.14, extract the (z,y) coordinates for the origin and apply the inverse tangent to determine the angle to the y-axis and the equilibrium position. It is possible to measure the angle changed from the equilibrium position by the difference of the angle value with respect to the y-axis. The inverse tangent value can be calculated using Excel by using the value extracted from Logger Pro, and the calculated value can be received from Logger Pro and fitted with the critical attenuation function and the weak attenuation function.

In addition, in order to check the degree of attenuation for the roll motion, the control means takes the part where the thread is fixed in the xz plane as the origin as shown in FIG. 8, and the line connecting the center of gravity and the wing passes through the center of gravity, You can measure the angle it makes with a line that is in equilibrium with . Here, the position of the center of gravity may be located in the front part of the main wing, and the position of the untitled center may be adjusted by adjusting the position of the main wing.

In addition, since the control means also changes the position of the center of gravity when one wing is pressed down and released, the roll motion can be observed by extracting both the position change of the center of gravity and the position information of a preset specific part of the main wing. By finding the difference between the coordinates of a specific part and the coordinates of the center of gravity according to Since the subsequent process is the same as when analyzing the pitch motion, a description thereof will be omitted.

In addition, the control means extracts the x-coordinate and y-coordinate of the origin from the captured data of the two photographing means through analysis of the captured image, as shown in FIGS. 10 and 11 in order to check the degree of attenuation for the yaw axis change. can be analyzed. In addition, since the tail portion of the aircraft is lower than the head portion, the angle shown in FIG. 11 may be the angle of the line segment orthographically projected on the xy plane. In the equilibrium state, the body of the glider almost coincided with the y-axis, and when the yaw motion was generated by pushing the body and tail wing of the aircraft in the equilibrium position to the right as shown in FIG. 11, in order to extract the angle between the bodies, x,y Coordinates are extracted from each of the two moving images, and the subsequent process is the same as when analyzing the pitch motion, so a description thereof will be omitted.

12 shows an exemplary view for explaining the change in pitch angle according to the position of the main wing, by shooting and comparing how the angle between the glider and the z-axis changes while the glider is floated on the wind tunnel device and the position of the main wing is changed. did it

12, it can be seen that the angle increases as the position of the wing moves toward the tail, and it can be seen that the pitch motion of the glider is related to the positional relationship between the aerodynamic center and the center of gravity. When the main wing moves in the direction of the head, the position of the aerodynamic center is gradually moved forward with respect to the center of gravity, and the head is lifted. will go down As such, the present invention can educate students about the change in pitch motion according to the positional relationship between the aerodynamic center and the center of gravity through the pitch angle change according to the position of the main wing as shown in FIG. 12 .

13 shows an exemplary view for explaining the change in equilibrium state according to the angle of the chord line of the main wing, and what changes occur when the glider is floated on the wind tunnel device and the chord line of the right main wing is bent.

As can be seen from Figure 13, when the right main wing of the glider is bent, it can be seen that equilibrium is achieved while rotating in a clockwise direction with respect to the roll axis, and the roll motion is determined by the pressure difference by air acting on both wings However, when the chord line is bent, the area on which the corresponding wing receives air pressure changes. Accordingly, when the area to which the air pressure is applied is reduced, relatively less force is received compared to the wing whose area is not reduced, so that the roll motion is performed in the direction of the bent wing. Using these results, you can explain to students how roll motion occurs.

14 to 16 show the angular change from the equilibrium point with time in each of the pitch motion, roll motion, and yaw motion and the results of fitting them with the critical damping function and the slight damping vibration function, Tables 1 and 2 below are The values of the constants obtained through fitting in the critical damped vibration model for each slight damped vibration are shown.

As can be seen from the fitting results of FIGS. 14 to 16 and Tables 1 and 2, the measured values of angular changes for pitch rotation, roll rotation, and yaw rotation have smaller RMSE values in the slight attenuation model than in the critical attenuation model. It can be seen that, rather than the critical damping model, it can be seen that the slight damping model is an approximate model more suitable for analyzing the motion of a glider floating in a simple wind tunnel device. However, in the case of pitch and yaw motion, there may not be much difference from the critical damping model because the equilibrium position is reached after 1 or 2 vibrations. It can be explained that a glider floating on a wind tunnel device has a slight damping vibration close to the critical damping with respect to the angle changes with respect to the pitch axis, roll axis, and yaw axis. The high school curriculum explains that the state is stable when it has the property of returning to an equilibrium state with respect to change, so this result can be used to educate the stability of the three axes of the glider.

As such, the system according to the embodiment of the present invention uses a simple wind tunnel device composed of an air circulator and a commutation grid to float an aircraft, for example a glider, and to change the pitch angle according to the position of the main wing and the chord line of the right wing. When an angle is given, the change in roll equilibrium state can be checked and analyzed. That is, as the main wing moves in the tail direction, it can be seen that the tail part rises, and it can be seen that the chord line is rotated in the direction of the wing bent to achieve equilibrium.

In addition, the system of the present invention can also check the stability of pitch, roll, and yaw motion, and as a result of extracting the angle change data for each by a video analysis method and fitting it with the critical damping function and the slight damping function model, the critical damping It can be seen that approximation is possible with a slight damping motion close to . Using this, it was possible to demonstrate and explain the stability of a flying glider through an experiment with the concept of stability presented in the high school curriculum.

The system of the present invention is suitable for use in educational fields because it is simple to manufacture a wind tunnel device and does not occupy a lot of volume compared to an industrial wind tunnel or a university experiment wind tunnel. It is possible to develop various educational materials and educational contents that can teach the stability of the airplane in a controlled situation without flying it.

Specifically, the system of the present invention constitutes a wind tunnel with an air circulator and a commutation grating, and floats a glider made of wood lock in this wind tunnel device with a thread, and the pitch angle change according to the position of the main wing and the roll equilibrium position according to the change in the chord curve change can be directly demonstrated. As a result of the experiment, as the main wing moved in the tail direction, the tail part rose, and when the chord line was bent, the glider rotated in the direction of the bent wing and achieved a new equilibrium. In addition, the motion process that restores the equilibrium state when the angle for pitch, roll, and yaw rotation is changed in the equilibrium state is photographed using a recording means, for example, a webcam, and the Motion dynamics of wings and body can be analyzed. This restoration motion process can be analyzed by approximating it with the critical damping function and the slight damping function model. This result means that the glider floating in the simple wind tunnel has sufficient stability, and using it, not only stability for pitch, roll, and yaw rotation, but also fine damping motion, critical damping motion, damping The concept of harmonic oscillators can be shown directly to students. Moreover, the mathematical concept that rotation about three axes can be explained by separating the coupled motion into motion about each axis through principal axis decomposition can also be intuitively taught in an experimental way. . Lastly, the wind tunnel device used in the experiment is simple to manufacture and does not occupy much volume compared to an industrial wind tunnel or a university research wind tunnel, so it is suitable for experimentally demonstrating the stability of basic airplanes at the level of middle and high school.

In High School Physics I of the 2009 revised curriculum and Physics II of the 2015 revised curriculum, when the equilibrium is broken, the restoring force to return to the original position acts and returns to the original equilibrium state after a period of time is taught as stable. If the angular change of the glider can be approximated by the slight damping function and the critical damping function through the system of the present invention, it is to the high school students that the system has stability against the angular change because it has the property of returning to the equilibrium position with respect to the change. can do.

In addition, the part that can be presented as a concept in the curriculum can be taught to gifted students, and above all, it is meaningful for stability education to be able to show that the original equilibrium state is returned by directly changing the rotation of the glider floating on the wind tunnel device. there is In particular, by visually realizing the stability of the aviation field through the present invention, it can also be used as a good material that can expand the application field of the stability concept.

In addition, since the system of the present invention can be implemented with only an air circulator, a commutation grid, a glider, and a thread, it can be sufficiently used in front-line schools, and in the case of a commutation grid, it can also be produced with a straw if there is no 3D printer.

The process of analyzing the stability of the vehicle may be performed using the system of the present invention described above. That is, it is possible to implement the vehicle stability analysis method using the system of the present invention. The vehicle stability analysis method according to an embodiment of the present invention is a process of photographing an image for analyzing the pitch motion of the vehicle connected to the above-described simple wind tunnel device and an image for analyzing the roll motion and yaw motion of the vehicle, the captured image The process of analyzing changes in pitch motion, roll motion, and yaw motion of the vehicle through the analysis of may include

At this time, the method of the present invention can analyze the stability of the vehicle by approximating the angular change with respect to the equilibrium position of the vehicle with the slight attenuation function model and the critical attenuation function model.

Of course, the method according to the embodiment of the present invention may include all the contents described in the system of FIGS. 1 to 16, which is apparent to those skilled in the art.

The device described above may be implemented as a hardware component, a software component, and/or a combination of the hardware component and the software component. For example, the devices and components described in the embodiments may include a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, a microcomputer, a field programmable gate array (FPGA), and a programmable logic unit (PLU). It may be implemented using one or more general purpose or special purpose computers, such as a logic unit, microprocessor, or any other device capable of executing and responding to instructions. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For convenience of understanding, although one processing device is sometimes described as being used, one of ordinary skill in the art will recognize that the processing device includes a plurality of processing elements and/or a plurality of types of processing elements. It can be seen that can include For example, the processing device may include a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as parallel processors.

The software may comprise a computer program, code, instructions, or a combination of one or more thereof, which configures a processing device to operate as desired or is independently or collectively processed You can command the device. The software and/or data may be any kind of machine, component, physical device, virtual equipment, computer storage medium or device, to be interpreted by or to provide instructions or data to the processing device. can be embodied in The software may be distributed over networked computer systems, and stored or executed in a distributed manner. Software and data may be stored in one or more computer-readable recording media.

The method according to the embodiment may be implemented in the form of program instructions that can be executed through various computer means and recorded in a computer-readable medium. In this case, the medium may be to continuously store the program executable by the computer, or to temporarily store the program for execution or download. In addition, the medium may be various recording means or storage means in the form of a single or several hardware combined, it is not limited to a medium directly connected to any computer system, and may exist distributed on a network. Examples of the medium include a hard disk, a magnetic medium such as a floppy disk and a magnetic tape, an optical recording medium such as CD-ROM and DVD, a magneto-optical medium such as a floppy disk, and those configured to store program instructions, including ROM, RAM, flash memory, and the like. In addition, examples of other media may include recording media or storage media managed by an app store that distributes applications, sites that supply or distribute other various software, and servers.

As described above, although the embodiments have been described with reference to the limited embodiments and drawings, various modifications and variations are possible from the above description by those skilled in the art. For example, the described techniques are performed in a different order than the described method, and/or the described components of the system, structure, apparatus, circuit, etc. are combined or combined in a different form than the described method, or other components Or substituted or substituted by equivalents may achieve an appropriate result.

Therefore, other implementations, other embodiments, and equivalents to the claims are also within the scope of the following claims.

Claims (9)

wind tunnel device for generating wind;
an aircraft connected to the wind tunnel device by a connecting means and whose motion is changed by the wind generated by the wind tunnel device;
a first photographing means for photographing a side image for analyzing a pitch motion of the vehicle while being disposed on the side of the vehicle;
a second photographing means for photographing a rear image for analyzing a roll motion and a yaw motion of the vehicle while being disposed on the rear side of the vehicle; and
By analyzing the images captured by the first and second photographing means, the change in pitch motion, roll motion and yaw motion with respect to the aircraft is analyzed while ignoring the motion of the connecting means, which is an axis with no change in position. and a control means for analyzing the stability of the vehicle based on changes in pitch motion, roll motion and yaw motion analyzed with respect to the vehicle
includes,
the aircraft is
Aircraft stability analysis system, characterized in that the head of the aircraft and the wind tunnel device are connected through the connecting means in order to limit the translational motion of the aircraft while leaving only the rotational motion component.
According to claim 1,
The wind tunnel device
including a wind generator and a commutation grid,
The rectification grid is
Vehicle stability analysis system, characterized in that disposed between the wind generating device and the vehicle.
According to claim 1,
the aircraft is
A vehicle stability analysis system, characterized in that a change in position with respect to the main wing is possible, and an angle change with respect to the chord line of the main wing is possible.
According to claim 1,
the control means
Vehicle stability analysis system, characterized in that by analyzing the angular change with respect to the equilibrium position of the vehicle by approximating it with at least one of a slight attenuation function model and a critical attenuation function model, to analyze the stability of the vehicle.
delete A side image for analyzing the pitch motion of the vehicle connected to the simple wind tunnel device - the side image is taken by the first photographing means disposed on the side of the vehicle - and the rear side for analyzing the roll motion and yaw motion of the vehicle receiving an image, wherein the rear image is photographed by a second photographing means disposed on the rear of the vehicle;
analyzing the changes in pitch motion, roll motion and yaw motion with respect to the vehicle while ignoring the motion of the connecting means, which is an axis with no position change, through analysis of the received side image and rear image; and
Analyzing the stability of the vehicle based on changes to the analyzed pitch motion, roll motion and yaw motion with respect to the vehicle
includes,
the aircraft is
Aircraft stability analysis method, characterized in that the head of the aircraft and the wind tunnel device are connected in order to limit the translational motion of the aircraft while leaving only the rotational motion component.
7. The method of claim 6,
The simple wind tunnel device
It includes a wind generating device for generating wind and a rectifying grid,
The rectification grid is
Vehicle stability analysis method, characterized in that disposed between the wind generating device and the vehicle.
7. The method of claim 6,
Changing the position of the vehicle with respect to the main wing or the angle with respect to the chord line of the main wing
further comprising,
Analyze the change
Through the analysis of the received side image and rear image in the state of change of position with respect to the main wing or change of angle with respect to the chord line, An aircraft stability analysis method, characterized in that it analyzes changes in pitch motion, roll motion and yaw motion.
7. The method of claim 6,
The step of analyzing the stability is
Air vehicle stability analysis method, characterized in that by analyzing the angular change with respect to the equilibrium position of the vehicle by approximating it with at least one of a slight attenuation function model and a critical attenuation function model, to analyze the stability of the vehicle.

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