KR20150005081A - Apparatus and method for analyzing weapon delivery of aircraft - Google Patents

Abstract

Disclosed in the present invention are an apparatus and a method for analyzing weapon release of an aircraft. The apparatus for analyzing weapon release of an aircraft comprises: an aiming unit which provides visibility distance for an aircraft pilot in order to aim a target; an aiming sensor unit which obtains information on a sighting angle and a slant range of the target aimed by the aiming unit; and an analyzing unit which predicts an impact point of a weapon according to launching initial condition of the weapon, and predicts the flight trajectory of the weapon released to the predicted impact point based on the sighting angle and the slant range. The analyzing unit can consecutively correct the speed value and position value of the weapon according to the flight time order of the weapon for multiple points, and can modify the impact point based on the corrected speed value and position value.

Description

[0001] APPARATUS AND METHOD FOR ANALYZING WEAPON DELIVERY OF AIRCRAFT [0002]

The present invention relates to an apparatus and method for analyzing an armed release of an aircraft, and more particularly, to an apparatus and method for analyzing an armed release of an aircraft to improve the accuracy of armed release of the aircraft.

It is important to accurately calculate the impact point of an armed weapon so that the weapon mounted on the aircraft is accurately dropped onto the aimed target. However, in the case of armed release, there are two types of error factors: bias error and random error.

Bias error refers to a consistent and reproducible error factor. For example, when a weapon mounted on an airplane is aimed at a target and dropped several times, it is a case that a point is dropped at a point other than the target to be aimed but dropped. As shown in FIG. 1, although the weapon is dropped at a point off a certain point from the aiming target (Truth), a point where the weapon is dropped forms a certain crowd.

On the other hand, in the case of a random error, the armed weapon is sporadically dropped at a certain point. For example, as shown in FIG. 1, there is an average point at which a weapon is dropped most frequently, but a point at which a weapon is dropped becomes a normal distribution about an average point.

Due to these two types of errors, it is difficult to accurately deliver the weapon mounted on the aircraft to the target. In order to solve this problem, it is necessary to predict the impact point for dropping the weapon mounted on the aircraft more accurately. To predict the impact point more precisely, a new method of armed release analysis is required.

It is an object of the present invention, which is devised in view of the above-mentioned necessity, to provide an apparatus and method for analyzing an armed release of an aircraft which can accurately predict an impact point by numerically analyzing an armed state, an initial launch condition, .

In order to accomplish the above object, according to the present invention, there is provided an apparatus for analyzing an armed release of an aircraft, comprising an aiming unit for providing a visual distance to a pilot of an aircraft so as to aim the target, angle and a slant range of the armed weapons and a launching start point of the armed weapon based on the initial launch conditions of the armed weapons, and based on the view angle and the direct distance, And an interpreting unit for predicting a flight path of the armed weapon, wherein the analyzing unit is configured to sequentially calculate a speed and a position value of the armed weapon in accordance with an order of the armed flight time for a plurality of points constituting the predicted flight path, , And correct the impact point based on the corrected velocity value and the position value.

In this case, the analyzing unit may predict the impact point by reflecting at least one of the arming launch speed, the armed mount state, and the aircraft motion state under the initial condition.

Meanwhile, the analyzing unit may reflect a change in the trajectory of the airflow around the aircraft to the predicted flight trajectory.

The analyzing unit may include a predictor for predicting the first velocity prediction value and the first position prediction value of the arming at a first point among the plurality of points, A second multiplier for multiplying the first estimated velocity value and the first predicted position value multiplied by the first velocity weight and the first position weight, respectively, by a time value; A first velocity value at the first point and a result value obtained by multiplying the second velocity value at the second point and the time value by a sum of the first velocity value and the second velocity value at the first point, 1 < / RTI > position value.

According to another exemplary embodiment of the present invention, a method for analyzing an armed release of an aircraft includes the steps of obtaining a sighting angle and a slant range for a target aimed by a pilot of an aircraft, Estimating an impact point of the weapon based on the view angle and the direct distance, estimating a flight path of the weapon to be dropped onto the predicted impact point based on the view angle and the direct distance, Sequentially correcting the speed and position value of the weapon according to the flight time order of the weapon, and correcting the impact point based on the corrected velocity value and the position value.

In this case, computing the impact point of the weapon may reflect at least one of the arming launch rate, the armed mount state and the aircraft motion state in the initial condition.

The step of predicting the trajectory may include reflecting a change in the trajectory of the airflow around the aircraft to the trajectory.

The step of correcting the velocity value and the position value of the weapon may include the steps of: predicting the first velocity prediction value and the first position prediction value of the weapon at a first point among the plurality of points, Multiplying the first position prediction value by a first velocity weight and a first position weight, respectively, multiplying the first velocity prediction value and the first position prediction value multiplied by the first velocity weight and the first position weight, respectively, Multiplying the result of multiplying the time step value by a second velocity value and a second position value at the second point, which is a previous step point of the first point, 1 velocity value and a first position value.

According to various embodiments of the present invention, an armed state, an initial firing condition, and an initial value mounted on an aircraft are numerically analyzed by time to provide an effect of more precisely predicting an impact point.

FIG. 1 is a view for explaining two kinds of errors that occur when an aircraft is unarmed, FIG.
FIG. 2 is a block diagram for explaining an armed release analyzing apparatus for an aircraft according to an embodiment of the present invention;
3 is a conceptual diagram for schematically explaining an impact point prediction algorithm according to an embodiment of the present invention,
4 is a view for explaining a method of calculating an armed flight path according to an initial value problem solving technique according to an embodiment of the present invention;
5 is a block diagram for describing an armed targeting avionics system applied to an aircraft system,
FIG. 6 is a view for explaining an arming effect when a weapon mounted on an aircraft is separated; FIG.
FIG. 7 is a view for explaining the trajectory and initial condition characteristics in a rotorcraft aircraft;
FIG. 8 is a flow chart for explaining a method for analyzing an armed release of an aircraft according to another embodiment of the present invention,
FIG. 9 is a schematic view for explaining an unmanned aerial drop analysis system in an aircraft platform according to another embodiment of the present invention.

Hereinafter, the present invention will be described in detail with reference to the drawings.

FIG. 2 is a block diagram illustrating an apparatus for analyzing an armed release of an aircraft according to an embodiment of the present invention. Referring to FIG.

Referring to FIG. 2, an apparatus for analyzing an armed robbery of an aircraft according to an embodiment of the present invention includes a collimating unit 210, a collimating sensor unit 230, and an analyzing unit 250.

The aiming unit 210 provides a line of sight so that the pilot of the aircraft can aim the target. For example, the aiming unit 210 may be implemented as an HMD (head mount device) attached to a helmet worn by a pilot.

When the pilot targets the target using the aiming unit 210, the aiming sensor unit 230 senses information on a sighting angle and a slant range of the aimed target, (250).

The analysis unit 250 receives the initial conditions for launching the weapon mounted on the aircraft and predicts the impact point of the weapon according to the input initial conditions of the launch. The interpreting unit 250 may predetermine a primary impact point for the target aimed by the pilot at the current aircraft position. The predicted impact point can be predicted considering the altitude of the aircraft and the altitude of the target.

An algorithm for predicting the impact point will be described in more detail with reference to FIG. 3 is a conceptual diagram for schematically explaining an impact point prediction algorithm according to an embodiment of the present invention.

As shown in FIG. 3, the aircraft is in a flying state above a certain altitude from the ground. The target is also located at an elevation above the ground. This target can change the impact point according to the change of the terrain. At this time, the impact point can be predicted in consideration of the initial firing speed of the armed weapon mounted on the aircraft, the armed mount state, and the aircraft motion state.

And, when the weapon mounted on the aircraft is separated, the air flow around the aircraft changes. The impact point can be predicted by reflecting the change of the air flow. For example, it is possible to reflect changes in the propulsive force of the armed forces, changes in drag and speed, etc. in the impact point prediction.

The analysis unit 250 can estimate the flight path of the armed weapon using the current position coordinate value of the aircraft and the position coordinate value of the predicted impact point. At this time, the analysis unit 250 can predict the flight path of the armed weapon by using the information about the angle of view and the direct distance to the target received from the collimation sensor unit 230.

If the impact point is predicted, the flight trajectory can be corrected by correcting the position value and velocity value according to the time step to calculate the flight trajectory of the armed to the impact point predicted from the current position of the aircraft. The process of correcting the flight trajectory will be described in more detail with reference to FIG.

FIG. 4 is a diagram for explaining a method of correcting a flight trajectory of an armament according to an initial value problem solving technique according to an embodiment of the present invention.

Referring to FIG. 4, the analyzer 250 can sequentially correct the speed and the position of the weapon according to the order of flight time of the weapon against a plurality of points constituting the predicted flight path. That is, the flight trajectory can be corrected by predicting the velocity value and the position value of the armament at the positions of the four points (①, ②, ③, ④) according to the time order and correcting it to the predicted value at the previous point.

Specifically, the analyzing unit 250 includes a predicting unit 251 for predicting the first estimated velocity value and the first predicted position value of the armed at the first point among the plurality of points, respectively. The analyzer 250 includes a first multiplier 252 for multiplying the first velocity prediction value and the first position prediction value by the first velocity weight and the first position weight, respectively. The analysis unit 250 includes a second multiplier 253 for multiplying the first estimated velocity value and the first predicted position value multiplied by the first velocity weight and the first position weight, respectively, by a time value. The analyzer 250 may calculate the sum of the second velocity value at the second point, which is the previous point of the first point, and the result obtained by multiplying the second point value by the time value, And a computing unit 254 for computing a first velocity value and a first position value.

Referring to Equation (1), the fourth points (④) position values (R ₄₎ in shown in FIG. 4 in the first to the fourth point to the position value (R ₃₎ in the third branch (③) It can be calculated by adding the predicted correction value. At this time, the first to the correction value prediction from the four points is located in a predicted value of the four points, each weight in the (k _1, k _2, k _3, and _{k 4) (w 1, w} 2, w 3 and w ₄ ), Multiplying them, and multiplying them by the time step value (Time_step).

5 is a block diagram illustrating an armed aimed anti-aircraft system applied to an aircraft system.

Referring to FIG. 5, the armed aimed anti-aircrafting system includes an HMD 510, a control unit 530 and a aiming sensor 550 and a mission computer 570.

The HMD 510 provides a line of sight to the pilot and transmits information about the target aimed by the pilot to the controller 530. [ The control unit 530 transmits information on the aimed target to the aiming sensor 550. [ The aiming sensor 550 senses the viewing angle and the direct distance of the aimed target and transmits the sensing angle and the directing distance to the control unit 530. The control unit 530 can calculate the impact point of the armed operation by calculating the armed flight trajectory by the armed aiming algorithm. The mission computer 570 can provide an optimal calculation method for predicting the flight trajectory and impact point in real time.

The control unit 530 shown in FIG. 5 may include a sensor pointing and an arming aiming algorithm module. At this time, the arming aiming algorithm can be designed considering the characteristics of each weapon drop mode. Also, we can design the armed aiming algorithm considering characteristics of each aircraft.

FIG. 6 is a view for explaining the effect of the armed separation in the case where a weapon mounted on an aircraft is separated. FIG.

Referring to FIG. 6, when the armed force is separated from the airplane, a change in the dropping trajectory due to the air flow around the airplane occurs. This change in the drop trajectory can be reflected in predicting the flight trajectory of the armed.

6 is a view for explaining a process of separating armed from an aircraft. Referring to the left side view of FIG. 6, the characteristics of the air flow are different depending on whether the aircraft is a fixed-wing aircraft or a rotary-wing aircraft. For fixed-wing aircraft, the longitudinal airflow of the fuselage due to the forward direction of the aircraft must be considered. In the case of a rotorcraft aircraft, consideration should be given to the airflow in the vertical direction component of the rotor due to the rotor downwash.

Referring to the right drawing of FIG. 6, vertical direction components due to the downwash area by the rotor are shown (see upper right drawing). The longitudinal component is shown by the advance state of the aircraft (see bottom right drawing).

As mentioned above, in order to predict the flight trajectory of the armed forces, it is necessary to reflect not only the initial conditions, but also the conditions for air circulation around the aircraft when the armed forces are separated from the aircraft. Especially, in the case of a rotorcraft aircraft, the characteristics of the trajectory of the rotorcraft aircraft can be influenced mainly by the characteristics of the aircraft.

7 is a view for explaining the trajectory and initial condition characteristics in a rotorcraft aircraft. Referring to FIG. 7, in the case of a rotorcraft aircraft, inconsistency occurs between the direction of the velocity vector of the aircraft and the arcing initial condition vector. As shown in the left drawing of Fig. 7, the traveling vector direction and the trajectory shift direction of the aircraft are inconsistent with each other. A port-starboard effect can also be caused by projectile drift. Therefore, the direction and the coordinate system of various velocity condition vectors should be considered in designing the weapon drop algorithm for the rotorcraft aircraft.

The right-hand side of FIG. 7 shows the direction and coordinate system of the various velocity condition vectors that should be considered in the armed release algorithm of the rotorcraft. In the directional coordinate system, the Y axis indicates the north direction, and the X axis indicates the east direction. The body coordinate system can be defined by rotating a predetermined angle clockwise in the directional coordinate system. As the velocity condition vector, weapon velocity, wind velocity, and A / C velocity vector can be considered.

FIG. 8 is a flowchart illustrating a method for analyzing an armed release of an aircraft according to another embodiment of the present invention.

Referring to FIG. 8, a method for analyzing an aircraft's armed release obtains a sighting angle and a slant range for a target aimed by a pilot of an aircraft (S810). The impact point of the weapon is predicted according to the initial conditions of the launch of the weapon (S820). Based on the view angle and the direct distance, the flight path of the armed to be dropped at the predicted impact point is predicted (S830). The arming speed and position value are sequentially corrected in accordance with the order of the armed flight time for a plurality of points constituting the predicted flight trajectory (S840). The impact point is corrected based on the corrected velocity value and the position value (S850).

FIG. 9 is a schematic view for explaining an unmanned aerial drop analysis system in an aircraft platform according to another embodiment of the present invention.

Referring to FIG. 9, the concept of an armed release analysis system that is not dependent on an aircraft platform is described. The types of aircraft include, for example, T-50, FA-50, XKT-1, KO-1, LAH and K-FX. Depending on the characteristics of these aircraft, the weapon drop analysis algorithm can be changed. However, when designing an aircraft-dependent armed release analysis algorithm, there is a problem in that it becomes incompatible with the airline period and becomes costly. To solve this problem, the armed release algorithm designs the armed dropping algorithm based on factors that are unidentified on the aircraft, such as the kind of arming and the arming characteristics. In addition, the armed release analyzing apparatus according to one embodiment of the present invention can provide an optimized armed release analysis result for each user.

The above-described methods according to various embodiments of the present invention may be stored as a code in a computer-readable storage medium. The code for performing the above-described methods according to various embodiments of the present invention may be stored in a memory such as a random access memory (RAM), a flash memory, a ROM (Read Only Memory), an EPROM (Erasable Programmable ROM), an Electrically Erasable and Programmable ROM ), A register, a hard disk, a removable disk, a memory card, a USB memory, a CD-ROM, and the like.

Although illustrative embodiments and applications of the present invention have been shown and described, many changes and modifications may be made without departing from the scope of the present invention, and such modifications may be made by one of ordinary skill in the art to which the present invention pertains It can be clearly understood. Accordingly, the described embodiments are illustrative and not restrictive, and the invention is not limited by the accompanying detailed description, but is capable of modifications within the scope of the claims.

Aiming unit: 210 Aiming sensor unit: 230
Interpretation section: 250 Prediction section: 251
First multiplier: 252 Second multiplier: 253
Operation unit: 254 HMD: 510
Control section: 530 Aiming sensor: 550
Mission Computer: 570

Claims (8)

An apparatus for analyzing a weapon in an aircraft,
An aiming portion providing a line of sight for the pilot of the aircraft to aim at the target;
A collimation sensor unit for acquiring information on a sighting angle and a slant range with respect to a target collimated by the collimating unit; And
And an analysis unit for predicting the impact point of the weapon in accordance with the launch initial condition of the weapon and predicting the flight path of the weapon to be dropped to the predicted impact point based on the view angle and the direct distance,
Wherein the analyzing unit sequentially corrects the speed value and the position value of the weapon according to the order of flight time of the weapon for a plurality of points constituting the predicted flight trajectory, and based on the corrected speed value and the position value And the impact point is corrected. The method according to claim 1,
Wherein the analyzer predicts the impact point by reflecting at least one of an arming launch speed, an armed mount state, and an aircraft motion state under the initial condition. The method according to claim 1,
The analyzing unit,
Wherein the change in the drop trajectory due to the air flow around the aircraft is reflected in the predicted flight trajectory. The method according to claim 1,
The analyzing unit,
A predictor for predicting the first velocity prediction value and the first position prediction value of the arming at a first point of the plurality of points;
A first multiplier for multiplying the first velocity prediction value and the first position prediction value by a first velocity weight and a first position weight, respectively;
A second multiplier for multiplying the first speed prediction value and the first position prediction value, which are multiplied by the first speed weight and the first position weight, respectively, by a time value; And
A second velocity value at the second point being a previous point of the first point and a result obtained by multiplying the second point value by the time value to obtain a first velocity value and a second velocity value at the first point, And an arithmetic unit for calculating a first position value. A method for analyzing an aircraft's armed release,
Obtaining a sighting angle and a slant range for a target aimed by a pilot of an aircraft;
Predicting an impact point of the weapon according to an initial firing condition of the weapon;
Predicting the flight path of the armed to be dropped to the predicted impact point based on the viewing angle and the direct distance;
Sequentially correcting the speed value and the position value of the weapon according to the order of flight time of the weapon for a plurality of points constituting the predicted flight path; And
And modifying the impact point based on the corrected velocity value and the position value. 6. The method of claim 5,
The step of calculating the impact point of the arming includes:
Wherein the at least one of the arming launch rate, the armed mount state, and the aircraft motion state is reflected in the initial condition. 6. The method of claim 5,
Wherein the step of predicting the flight path comprises:
And reflecting the change in the drop trajectory caused by the air flow around the aircraft to the flight trajectory. 6. The method of claim 5,
The step of correcting the velocity value and the position value of the weapon comprises:
Estimating a first estimated velocity value and a first predicted position value of the armed at a first one of the plurality of points;
Multiplying the first velocity prediction value and the first position prediction value by a first velocity weight and a first position weight, respectively;
Multiplying the first speed prediction value and the first position prediction value, which are respectively multiplied by the first speed weight and the first position weight, by a time step value; And
A second velocity value at the second point, which is a previous point of the first point, and a result obtained by multiplying the second point value by the time step value to obtain a first velocity value of the arsenic at the first point And calculating a first position value based on the first position value.

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