KR20090008700A - Method for obtaining weapon separation coefficient of aircraft - Google Patents

Abstract

A testing method for obtaining ballistic separation coefficients of an aircraft is less dependent on weather conditions and can remove failure factors of ballistic testing flights due to the interference of tide. A testing method for obtaining ballistic separation coefficients of an aircraft comprises: a step of mounting a differential GPS(Global Positioning System) and a high speed camera on the aircraft and recording ballistic separation time and aircraft location; a step of disposing a photographing system on the ground to photograph ballistic impact images; a step of analyzing the impact images to obtain an impact time and an impact point; and a step of calculating a time taken in the ballistic drop, and a ballistic moving surface distance.

Description

Test method for acquiring the armed separation factor of an aircraft {METHOD FOR OBTAINING WEAPON SEPARATION COEFFICIENT OF AIRCRAFT}

The present invention relates to an armed separation coefficient acquisition test method for measuring the impact point, and the like by dropping the armed from the aircraft, and more specifically, to obtain an armed separation coefficient, and more specifically, an integrated mission display computer onboard the aircraft (integrated mission display computer) Arming to improve arming accuracy by assessing and reflecting the ballistic separation effect on the flight operation program based on the difference between the armed aiming and actual impact points set by the operational flight program The present invention relates to a separation coefficient acquisition test method.

FIG. 1 shows the movement trajectory of the armed 20 dropped from the aircraft 10 until reaching the ground in the conventional armed separation coefficient acquisition test. For reference, in relation to the symbol or abbreviation described in FIG. 1, 'H' is the altitude above sea level of the armed 20 at the time of armed drop, 'HAT' is the height above the impact point (height above target), 'Rb 'Is the surface distance the armed,' MSL 'is the mean sea level (mean sea level).

The trajectory of the armed 20 is different from the trajectory predicted from the general rigid body drop movement due to the armed shape, the atmospheric state, the armed separation effect, and the like. In particular, the abnormal air flow around the aircraft 10 affects the drop trajectory of the armed arm within a predetermined range immediately after the armed arm is separated, which is called an armed separation effect or a flow filed effect.

That is, as shown in FIG. 1, according to the actual trajectory until the armed 20 reaches the ground, the aircraft 20 exhibits an abnormal state within the armed separation effect area around the aircraft and then follows the normal state trajectory. The impact point and the actual impact point aimed by the normal flight operation program embedded in (10) are different.

The effect of armed separation is largely contributing to impact error, but it depends on the aircraft type and cannot be predicted by theoretical modeling. It is common to incorporate them into operational programs.

Conventionally, the armed 20 is dropped during an armed test flight of an aircraft 10 equipped with a differential GPS (DGPS) and an electro-optical tracking system for evaluation of impact errors. In addition, a method of tracking the trajectory of the armed 20 until the armed 20 is separated from the aircraft 10 and landed on the ground has been used.

The electro-optical tracking device has a disadvantage that it cannot be accurately tracked according to the weather, although it is an expensive equipment including a high resolution video camera and a video tracker, a moving picture control / analyzer.

In addition, if a bird passes between the tracking trajectories during the tracking process, the arming cannot be traced and the armed separation factor acquisition test should be repeated. Therefore, there is a problem that an additional flight sortie occurs and thus the cost increases.

An object of the present invention is to provide a test method for acquiring armed separation coefficients, which has little dependence on weather and is not affected by tidal interference or the like.

Another object of the present invention is to provide a method capable of accurately measuring the fall time and impact point of an armed weapon dropped from an aircraft even without using an expensive electro-optical tracking device.

Summary of the Invention The present invention, which has been studied through the problems of the prior art as described above, has been made as follows.

(1) Armed separation factor acquisition test method for correcting the difference between the target impact point and the actual impact point predicted by the flight operation program embedded in the aircraft, wherein the aircraft is equipped with a precision positioning system (DGPS) and a high speed camera. Recording the armed separation time and the position of the aircraft; placing an imaging system on the ground to capture an armed impact image; analyzing the impact image to determine the impact time and impact point; And calculating an index distance (Rb) at which the TOF) and the armed are moved.

(2) The test method according to (1), wherein the imaging system includes a high speed camera for measuring impact time and two or more digital cameras for measuring impact point.

(3) The arming separation coefficient acquisition test according to (2), wherein the reference point is set at three or more positions around the target impact point when the imaging system is arranged, and information on the position of the reference point is confirmed by DGPS. Way.

(4) The arming separation coefficient acquisition test method according to (3), wherein the reference point is arranged on the same circumference and the angle between the reference points is set to 90 degrees or 180 degrees.

(5) The arming separation coefficient acquisition test method according to (2), wherein the digital camera is capable of continuous shooting for 10 seconds or more and has a resolution of 10 million pixels or more.

(6) The method according to any one of (1) to (5), wherein the TOF and Rb are used to determine the horizontal speed and acceleration at the moment of separation of the armed arm and the vertical speed and acceleration, and the flight operation program. And comparing the data with the data.

According to the present invention, by using the imaging system placed on the ground, the dependence on the weather is small and the failure factor of the armed test flight due to the interference of birds can be eliminated, and the imaging system is composed of the digital camera and the high speed camera on the ground. Test cost is reduced by eliminating the need for conventional expensive electro-optical tracking devices.

In addition, the arming separation effects evaluated based on precisely measured arming time and impact point can be reflected in the flight operation program to improve arming accuracy.

EMBODIMENT OF THE INVENTION Hereinafter, with reference to drawings, specific embodiment for implementing this invention is described.

FIG. 2 is a flowchart showing various steps (S210 to S280) included in the arming separation coefficient acquisition test according to one embodiment of the present invention in carrying out the arming test as shown in FIG. 1. Measurement information or analysis information is illustrated along with the equipment in need.

First, in step S210, the aircraft 10 for carrying out the armed separation coefficient acquisition test is equipped with a high-speed camera for armed separation shooting, for example, after shooting at 250 fps (frame per second), the armed 20 is analyzed through image analysis. Extract the time at the moment of separation from the aircraft 10. 3 shows an example of an image captured by the high speed camera at the moment of separation of the armed 20 during flight in accordance with step S210.

In step S220, the data obtained from the DGPS attached to the aircraft 10 is analyzed to extract the aircraft position at the moment of armed separation.

Next, in steps S230 and S240, the impact time and the impact point when the armed 20 reaches the ground are measured using an imaging system arranged on the ground to observe the area near the target impact point. To this end, the imaging system may include a high speed camera for impact time analysis and a digital camera for impact point analysis.

4 illustrates a preferred embodiment of the imaging system 100 including the high speed camera 150 and two digital cameras 161 and 162 placed on the ground for the implementation of steps S230 and S240.

For time synchronization between the high-speed camera 150 on the ground and the high-speed camera of the aircraft 10, all image data recorded in the high-speed camera is stored in IRIG-B time code, and after shooting at 250 fps, the image analysis is performed through the image analysis. Extract the moment of time. FIG. 5 shows an example of an image captured by the high speed camera 150 at the moment when the armed 20 hits the ground in step S230.

In performing step S240 of FIG. 2 according to the embodiment illustrated in FIG. 4, a plurality of reference points 131 to 134 are set in the vicinity of the target impact point, and the position of the reference points 131 to 134 is previously used by using the DGPS equipment. The exact position of the impact point 110 may be determined by comparing the position of the impact point 110 with the positions of the reference points 131 to 134 by analyzing the images photographed by the digital cameras 161 and 162.

By placing a plurality of reference points (131 to 134) on one circumference to equalize the distance from the target impact point to each reference point, and the angle between the reference points to form 90 degrees or 180 degrees, two It is preferable to provide a digital camera (e.g., 161) at a predetermined position to face the target impact point while bisecting the reference point (e.g., 131 and 132), since coordinate setting and coordinate calculation become easy.

Further, in arranging the reference point, setting the reference coordinate system becomes more concise if the target points are directed toward the east, west, east and south directions.

In order to determine the coordinates of the impact point 110, at least two digital cameras 161 and 162 are required, and as described above, according to the arrangement relationship between the reference points 131 to 134 and the digital cameras 161 and 162, the digital camera ( When installing 161 and 162, the two cameras 161 and 162 make an angle of 90 degrees around the target impact point.

Meanwhile, although four reference points 131 to 134 are illustrated in FIG. 4, even if only at least three reference points (for example, 131 to 133) are set, the position of the impact point 110 may be determined, and the impact point 110 may be determined. You can also increase the number of reference points and digital cameras to measure position more precisely.

The digital cameras 161 and 162 may be used in the present invention as long as they have a function capable of continuous shooting of 10 seconds or more, and the resolution is preferably 10 million pixels or more for precise measurement of the impact point 110.

Based on the arrangement relationship between the digital cameras 161 and 162 and the reference points 131 to 133 illustrated in FIG. 4, in the case where continuous shooting of the moment when the armed weapon 20 is impacted is taken, the horizontal pixel position of the impact point is read from the image. Thus, the gaze angle from the positions of the reference points 131, 132; 132, 133 can be calculated. FIG. 6 shows an example of an image obtained by digital cameras 161 and 162 capturing the position where the armed 20 reaches the ground.

Next, in step S260 of FIG. 2, the arming 20 separated from the aircraft 10 by using the arming separation time, the aircraft position, the impact time, and the location of the impact point 110 extracted by the steps S210 to S250. The time of fall (TOF), which is the time required to reach the surface of the ground, and the ground distance Rb in which the armed 20 separated from the aircraft 10 moved to the impact point are obtained.

More specifically, the TOF can be obtained by the difference between the time of the armed separation moment in the aircraft 10 and the time of the armed impact moment on the ground. Rb can be obtained from the difference of the ground positions of.

Next, in steps S270 and S280, armed separation coefficients are obtained using TOF and Rb, and reflected in the flight operation program of the aircraft. More specifically, by using the TOF and Rb to obtain the horizontal velocity and acceleration at the moment of separation, and the vertical velocity and acceleration and compare / modify the data with the existing flight operation program, the arming accuracy can be improved. Will be.

As mentioned above, although preferred embodiment of this invention was described, the scope of the present invention is not limited to the said embodiment, A various deformation | transformation embodiment is possible without deviating from the essence and essential characteristic structure of this invention, of course. to be. Therefore, the above-described embodiments in this specification are illustrative only and do not have a limiting meaning, the scope of the present invention should be understood to include the matter described in the appended claims and all modifications that can be understood therefrom. do.

BRIEF DESCRIPTION OF THE DRAWINGS Explanatory drawing which shows the movement trace from an aircraft to an impact point to an impact point.

2 is a flowchart of an armed separation factor acquisition test in accordance with one embodiment of the present invention.

Fig. 3 is a diagram showing an example of capturing the moment when the armed is separated during the flight of the aircraft equipped with the armed by the high speed camera.

4 is a schematic diagram of an imaging system arranged on the ground for precise measurement of the impact position and the impact time of the armed at the time of acquisition of the armed separation coefficient of the aircraft, in accordance with a preferred embodiment of the present invention;

5 is a diagram showing an example in which a high speed camera captures the moment when the armed dropped from the aircraft lands on the ground according to a preferred embodiment of the present invention.

6 is a diagram illustrating a process of obtaining a horizontal pixel position by photographing an armed impact moment with a digital camera according to a preferred embodiment of the present invention.

<Description of the symbols for the main parts of the drawings>

10: aircraft 20: armed

100: imaging system 110: impact point

131, 132, 133, 134: Reference point 150: High speed camera

161, 162: digital camera

Claims (6)

In the test method for acquiring the armed separation coefficient for correcting the difference between the target impact point and the actual impact point predicted by the flight operation program embedded in the aircraft, Equip the aircraft with a precision positioning system (DGPS) and a high-speed camera to record the time of armed separation and the aircraft's position, Placing an imaging system on the ground to shoot an armed impact image, Analyzing the impact image to find the impact time and impact point, And calculating a time (TOF) spent on the fall of the armed force and an index distance (Rb) of the armed movement. The method of claim 1, The terrestrial imaging system includes a high speed camera for measuring impact time and two or more digital cameras for measuring impact point. The method of claim 2, An arming separation coefficient acquisition test method characterized by setting a reference point at three or more positions around a target impact point at the time of arranging an imaging system, and confirming the information about the position of a reference point by DGPS. The method of claim 3, The reference point is arranged on the same circumference and the angle between the reference point is set to 90 degrees or 180 degrees, the armed separation coefficient acquisition test method. The method of claim 2, The digital camera is capable of continuous shooting for 10 seconds or more, and has a resolution of 10 million pixels or more. The method according to any one of claims 1 to 5, Arming separation factor further comprising the step of obtaining the horizontal velocity and acceleration and the vertical velocity and acceleration at the moment of separation of the arm using TOF and Rb, and comparing the data to the flight operation program. Acquisition test method.

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