KR101649516B1 - Apparatus for estimating variable aerodynamic force of flight vehicle and method thereof - Google Patents

Apparatus for estimating variable aerodynamic force of flight vehicle and method thereof Download PDF

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KR101649516B1
KR101649516B1 KR1020150103256A KR20150103256A KR101649516B1 KR 101649516 B1 KR101649516 B1 KR 101649516B1 KR 1020150103256 A KR1020150103256 A KR 1020150103256A KR 20150103256 A KR20150103256 A KR 20150103256A KR 101649516 B1 KR101649516 B1 KR 101649516B1
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aerodynamic
change
predicting
amount
variables
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이은석
이진규
강경태
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국방과학연구소
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    • G06F17/00—Digital computing or data processing equipment or methods, specially adapted for specific functions
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Abstract

The present invention relates to an apparatus for predicting the aerodynamic variation of a flight vehicle and a method thereof, which can predict an aerodynamic variation due to a lateral jet over the entire operation range of a side jet thruster of a flight vehicle and reduce time and cost required for the prediction. The apparatus for predicting the aerodynamic variation of a flight vehicle comprises: a discretization module for discretizing variables, which determine the aerodynamic variation of the flight vehicle, to minimize temporal and material resources required for the prediction of the aerodynamic variation of the flight vehicle; a function calculation module for calculating correlation functions between the aerodynamic variation and the discretized variables; and a prediction module for predicting the aerodynamic variation of the entire operation range of the side jet thruster from the correlation functions.

Description

[0001] APPARATUS FOR ESTIMATING VARIABLE AERODYNAMIC FORCE OF FLIGHT VEHICLE AND METHOD THEREOF [0002]

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an apparatus and method for predicting aerodynamic variation of a flying body.

Conventionally, the method of predicting the aerodynamic change amount of a flying body is limited to a single nozzle, so that it is difficult to predict the aerodynamic amount of change when a plurality of nozzles arranged in the thrust system operate independently.

SUMMARY OF THE INVENTION It is an object of the present invention to provide an aerodynamic amount variation predicting device for a vehicle capable of predicting an aerodynamic amount of change due to a lateral jet over the entire operating range of a lateral thrust of a flight, And a method therefor.

An apparatus for predicting a change in aerodynamic force of a flying object according to an exemplary embodiment of the present invention includes a discretization module for discretizing parameters for determining an aerodynamic change amount of the flying body to minimize temporal and material resources required for predicting a change in aerodynamic force of the flying body; A function calculation module for obtaining an aerodynamic change amount-variable correlation function for the discretized variables; And a prediction module for predicting an aerodynamic change amount over the entire range of the side thrusters from the obtained correlation function.

In an embodiment of the present invention, the variables may include the flight speed, flight altitude, and the magnitude and direction of the angle of attack of the aircraft.

The method of predicting aerodynamic variation of a flying object according to an embodiment of the present invention includes the steps of: discretizing variables for determining an aerodynamic change amount of the airplane in order to minimize temporal and material resources required for predicting the aerodynamic variation of the airplane; Obtaining an aerodynamic change amount-variable correlation function for the discretized variables; And estimating an aerodynamic change amount over the entire range of the side thrusters from the obtained correlation function, wherein the variables may include the flight speed, flight altitude, and the magnitude and direction of the angle of attack of the air vehicle.

An apparatus and method for predicting aerodynamic variation of a flying body according to an embodiment of the present invention can estimate an aerodynamic amount of change due to a lateral jet over the entire operating range of a side impactor, Can be saved.

1 is a block diagram showing an apparatus for predicting a change in aerodynamic force of a vehicle according to an embodiment of the present invention.
FIG. 2 is a block diagram conceptually showing the operation principle of the side thrusters, and a case in which there are four side thrusters mounted on the body of the air vehicle (guidance).
Fig. 3 is an exemplary view showing a method of discretizing (simplifying) an output combination of each nozzle.
FIGS. 4A to 4D are diagrams showing a method of obtaining the aerodynamic change amount-correlation function between variables. FIG.
5 is an exemplary view showing a method of calculating an aerodynamic change amount for the entire range of the side thrusters from the discretized (simplified) variable.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein like or similar elements are denoted by the same reference numerals, and redundant description thereof will be omitted. The suffix "module" and " part "for the components used in the following description are given or mixed in consideration of ease of specification, and do not have their own meaning or role. In the following description of the embodiments of the present invention, a detailed description of related arts will be omitted when it is determined that the gist of the embodiments disclosed herein may be blurred. It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. , ≪ / RTI > equivalents, and alternatives.

The present invention relates to a method for predicting a change in an aerodynamic force (a force acting on an object (a guided vehicle) by a gas flow around an object (a guided vehicle)) caused by lateral thrust force flow of the guided vehicle.

It depends on the aerodynamic force in order to launch the airborne flying missile (to change the velocity vector). In order to generate maneuver by aerodynamic force, it is necessary to generate the angle (angle of attack) between the flight velocity vector of the missile and the longitudinal axis of the fuselage. Since the body must be rotated until it reaches the angle of attack to obtain the required maneuvering force, there is a time delay involved. In order to reduce the time delay, a side thrust generator which generates a maneuvering force without rotating the body is used.

The side thrusters considered in the present invention obtain reaction force by jetting the high-pressure gas generated from the gas generator in the direction toward the fuselage through the nozzle. A plurality of nozzles are arranged at equidistant intervals in the circumferential direction near the center of gravity of the circular-shaped guide cylinder body, and the direction of the reaction force is controlled 360 degrees by controlling the output of each nozzle.

The jet flow injected from the nozzle interferes with the air flow around the guided car to change the aerodynamic force acting on the guided car. Prediction of these aerodynamic variations is essential for the performance design of missile. In order to predict the amount of aerodynamic change, there is a correlation between the aerodynamic change and each of the variables. Function is required.

In the present invention, an optimal method of predicting the aerodynamic change amount by deriving a correlation function with a minimum resource will be described. This is done by discretizing each variable (expressing a continuously changing variable quantity as a finite data point), simplifying the output size combination of each nozzle, and solving the aerodynamic variation-parameter correlation function for the discrete / And a method of calculating the amount of aerodynamic change over the entire range of the side thrusters from the correlation function.

1 is a block diagram showing an apparatus for predicting a change in aerodynamic force of a vehicle according to an embodiment of the present invention.

As shown in FIG. 1, the apparatus for predicting the aerodynamic force variation of a vehicle according to an embodiment of the present invention includes:

A discretization module 10 for discretizing (simplifying) the variables that determine the amount of change in aerodynamic force of the guided vehicle, in order to minimize temporal and material resources required to predict the aerodynamic variation of the guided vehicle;

A function calculation module (20) for obtaining an aerodynamic change amount - inter-variable correlation function for the discretized variables;

And a prediction module (calculation module) 30 for predicting (calculating) the aerodynamic change amount over the entire range of the side thrusters from the obtained correlation function.

FIG. 2 is a block diagram conceptually showing the operation principle of the side thrusters, and a case in which there are four side thrusters mounted on the body of the air vehicle (guidance).

As shown in FIG. 2, reference numerals S1, S2, S3, and S4 denote nozzles of four side thrusters provided on the body of the air vehicle (touring car) 10, . The control unit controls the direction

Figure 112015070878729-pat00001
) And the desired force (F desired ), the sum of the thrusts of S1 and S3 in the vertical axis direction is F desired * cos
Figure 112015070878729-pat00002
And the sum of the thrusts of S2 and S4 in the horizontal axis direction is F desired * sin
Figure 112015070878729-pat00003
The side thrusters corresponding to S2 and S4 are controlled.

As shown in FIG. 1, if the direction of the thrust exists between S1 and S2, the control unit controls the thruster corresponding to S3 and S4 such that the thrust of the remaining two nozzles S3 and S4 is the same. Given this logic,

Figure 112015070878729-pat00004
And the desired thrust of each nozzle to obtain F desired is expressed by Equation (1).

Figure 112015070878729-pat00005

In the following, the flight speed M, flight altitude (h, km), the magnitude of the angle of attack (?, Deg)

Figure 112015070878729-pat00006
, deg) The method of discretizing the variables is described with reference to Table 1.

Figure 112015070878729-pat00007

As shown in Table 1, in order to minimize the temporal and material resources required for predicting the aerodynamic change amount of the guided vehicle, the discretization module sets parameters for determining the amount of aerodynamic change of the guided car , The flight altitude of the missile, the magnitude of the angle of attack of the missile, and the direction of the angle of attack of the missile) are discretized (preset) as shown in the table of FIG.

Fig. 3 is an exemplary view showing a method of discretizing (simplifying) an output combination of each nozzle. The direction of lateral force is 0, 22.5, 45, and the strength of lateral force is 100%, 50%, 0%. When the lateral thrust strength is 0%, it is the same regardless of the direction of the lateral thrust force. The dislocated side force directions and strength combinations correspond to F0, F1, F2, F3, F4, F5 and F6 in total.

FIGS. 4A-4D illustrate a method for obtaining a correlation function between an aerodynamic change amount and a variable with respect to a given flight speed (M) and altitude (h), showing a method of obtaining an aerodynamic change-variable correlation function. Considering symmetry with respect to F0 to F6 in Fig. 3

Figure 112015070878729-pat00008
. As a result, F0 (
Figure 112015070878729-pat00009
1 ~
Figure 112015070878729-pat00010
5), F1 (
Figure 112015070878729-pat00011
1 ~
Figure 112015070878729-pat00012
9), F2 (
Figure 112015070878729-pat00013
1 ~
Figure 112015070878729-pat00014
9), F3 (
Figure 112015070878729-pat00015
1 ~
Figure 112015070878729-pat00016
16), F4 (
Figure 112015070878729-pat00017
1 ~
Figure 112015070878729-pat00018
16), F5 (
Figure 112015070878729-pat00019
1 ~
Figure 112015070878729-pat00020
9), F6 (
Figure 112015070878729-pat00021
1 ~
Figure 112015070878729-pat00022
9) are derived. For each of the 73 combinations, the amount of aerodynamic change due to the change of α is analyzed by computational fluid dynamics or wind tunnel test.

Fig. 5 is a graph showing a method for calculating the aerodynamic change amount for the entire range of the side thrusters operating range from the discretized (simplified) variable. From the correlation function obtained from Fig. 4 for a given flight speed (M) It shows how to calculate the amount of aerodynamic change over the entire operating range. When the method of calculating the aerodynamic change amount according to the embodiment of the present invention is not used,

Figure 112015070878729-pat00023
= 0 to 337.5, 22.5 degree intervals) x 3 (F desired = 100%, 50%, 0%) x 16
Figure 112015070878729-pat00024
= 0 to 337.5, 22.5 degree intervals) = 768 combinations or tests are required. Accordingly, the present invention can reduce the time and cost required for predicting the aerodynamic change amount by 95%.

As described above, the apparatus and method for predicting aerodynamic variation of a flying body according to an embodiment of the present invention can predict the amount of aerodynamic change due to a lateral jet over the entire operating range of a side impactor, It is possible to reduce the time and cost required for the system.

The foregoing detailed description should not be construed in all aspects as limiting and should be considered illustrative. The scope of the present invention should be determined by rational interpretation of the appended claims, and all changes within the scope of equivalents of the present invention are included in the scope of the present invention.

Claims (3)

An apparatus for predicting an aerodynamic amount of change in a guide gun having a side thruster provided in a body of a guided vehicle and including a nozzle and controlling the intensity of a jet jetted from the nozzle,
The flying height, the direction and magnitude of the angle of attack, and the thrust direction of the side thrusters, among the variables that determine the amount of change in aerodynamic force of the guided car, so as to minimize the temporal and material resources required for predicting the aerodynamic- A discretization module for discretizing jet strength;
A function calculation module for obtaining an aerodynamic change amount-variable correlation function for the discretized variables;
And a prediction module for predicting an aerodynamic amount of change in the entire operating range of the side thruster from the obtained correlation function. delete A method for predicting a change in aerodynamic force of a guided car which is installed in a body of a guided vehicle and includes a nozzle and which has a side thrust for controlling the intensity of a jet jetted from the nozzle,
The flying height, the magnitude and direction of the angle of attack, and the direction of the thrust of the side thrusters and the direction of the thrust of the side impactors, among the variables for determining the amount of change in aerodynamic force of the guided missile so that the temporal and material resources required for predicting the aerodynamic- Discretizing the intensity;
Obtaining an aerodynamic change amount-variable correlation function for the discretized variables;
And estimating an aerodynamic amount of change of the aerodynamic force with respect to the entire operating range of the side impactor from the obtained correlation function.
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110517547A (en) * 2019-08-23 2019-11-29 重庆大学 Mechanics intelligent analysis system based on human-computer interaction

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100408831B1 (en) * 2001-08-22 2003-12-06 한국항공우주산업 주식회사 Method for direct caculating velocity of the standard atmosphere flutter
KR101038508B1 (en) * 2010-12-01 2011-06-01 엘아이지넥스원 주식회사 Device and method of wind tunnel testing
KR101105450B1 (en) * 2010-05-07 2012-01-17 한국항공우주산업 주식회사 System and the method for aerodynamic forces analysis of helicopter rotor
KR101472388B1 (en) * 2013-05-03 2014-12-15 한국항공우주산업 주식회사 Aerodynamic Characteristics and performance Prediction Device of Light Armed Helicopter with External Weapon Systems

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100408831B1 (en) * 2001-08-22 2003-12-06 한국항공우주산업 주식회사 Method for direct caculating velocity of the standard atmosphere flutter
KR101105450B1 (en) * 2010-05-07 2012-01-17 한국항공우주산업 주식회사 System and the method for aerodynamic forces analysis of helicopter rotor
KR101038508B1 (en) * 2010-12-01 2011-06-01 엘아이지넥스원 주식회사 Device and method of wind tunnel testing
KR101472388B1 (en) * 2013-05-03 2014-12-15 한국항공우주산업 주식회사 Aerodynamic Characteristics and performance Prediction Device of Light Armed Helicopter with External Weapon Systems

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110517547A (en) * 2019-08-23 2019-11-29 重庆大学 Mechanics intelligent analysis system based on human-computer interaction

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