KR101350929B1 - High density air shooting unit by using gps and ins - Google Patents

Abstract

The present invention relates to an aerial photography apparatus making aerial photography possible by combining an aircraft automatic photography system capable of automatically and rapidly obtaining an image having information of changes in urban terrain with a GPS, more particularly, to an ultra high precision aerial photography apparatus, which uses improved GPS and INS, capable of obtaining image data and spatial information by tracing a photography planning route coordinate inputted in a computer through an automatic photography system without dispatching manpower to a field, calculating a photography distance for a subject to be photographed using altitude and photography angle of an aircraft, obtaining an clear and accurate photography image by controlling a photography ratio according to the distance, capable of easily understanding the vicinity of the corresponding by confirming not only a plan view image but also a side view image of a specific region through a numerical map, therefore, convenience of use of the numerical map can be maximally increased and capable of solving a problem of editing a photography image obtained after photographing a plan view image and a side view image of the same terrain from the aircraft.

Description

HIGH DENSITY AIR SHOOTING UNIT BY USING GPS AND INS using GPS and INS

The present invention provides an aerial photographing apparatus for combining aerial photographing system (GPS) and global positioning system (GPS) capable of automatically obtaining images of rapidly changing urban changes. In more detail, the automatic shooting system can be used to obtain the image data and spatial information by tracking the photographing plan coordinates entered into the computer without the input of personnel, and by using the aircraft's altitude and shooting angle By calculating the shooting distance and adjusting the shooting ratio according to the distance, you can get a clearer and more accurate shot image, and you can check the planar image and the side image of the specific area through the digital map. You can easily understand the surroundings, and can maximize the convenience of using the numerical map, It relates to a high-precision aerial photography system using a flat shooting and side shoots after the improvement to eliminate the hassle of editing the captured images and ensure jipieseu ahyien S for the same features in the group.

Advances in photography and aviation have had a significant impact on photorealistic mapping. In other words, the plane can be taken in the vertical direction and the GPS coordinate information is applied to the photographed image to create a realistic numerical map.

Aerial photographing technology is largely manned and photographed by pilots and photographers sitting next to airplane cockpits and cameras, and equipped with radio transmitter and receiver controls on aircraft that can't carry people, such as model helicopters or airships. It is divided into unmanned shooting technology.

The aerial shooting system uses an airplane equipped with a recording device to move to a shooting plan area so that the pilot can move the aircraft along the path of the shooting area so that the photographer can acquire data using the shooting device. It consists of automatic navigation system. The airship imaging system is a method for eliminating the high cost, excessive time, and data complexity of airborne surveying and remote sensing techniques, and air ship airbags capable of filling light aircraft such as hydrogen and helium. It consists of a controller, a gondola equipped with an engine, a shooting system for acquiring images, a ground control system, and a controller.

At this time, by using the image transmission and reception equipment to selectively capture a good image of the image seen from the shooting system to take the image without considering the scale. GPS is required to take into account the spatial position, scale, and altitude of the shooting system. 3D position measurement using GPS is a method of receiving a radio wave transmitted from GPS satellites and calculating a 3D position using the time and satellite signals reached from each satellite.

GPS can be used to acquire a three-dimensional position and determine whether the aircraft is operating along the planned route based on the GPS, and to control when departing the planned route. Inertial navigation is the determination of the position, velocity and posture of an antibody using the output physical quantities (angular velocity and acceleration) of an inertial sensor attached to a platform. The basic principle is based on Newton's laws of motion The solution to the navigation is from differential equations relating to acceleration, velocity and displacement.

Inertial sensors are classified into an accelerometer that detects translational motion and a gyroscope that detects rotational motion. In order to find out the position, speed and attitude of the aircraft through the system using inertial navigation, it is possible to obtain information on the state and angular velocity of the aircraft which cannot be obtained by using the GPS receiver to obtain three-dimensional coordinates. In this process, the subtle displacement of the aircraft, which is difficult for the person using the radio remote controller, to grasp in advance, facilitates the steering.

However, the INS device has a disadvantage in that an error accumulates as the distance from the initialization time increases.

In order to compensate for this drawback, GIS / INS method is a method that obtains three-dimensional location information from GPS receiver and initializes the information about the position, speed, and attitude of the vehicle at every GPS receiving interval. Accurate three-dimensional position data from GPS receivers and precise position, velocity and attitude information of the vehicle can be acquired simultaneously while solving the problems of both systems.

In the case of a shooting system using an airship, an increasing number of cases are used to acquire image information. However, there is a simple attempt to shoot with a camera, but by simultaneously acquiring and utilizing image data and spatial information (GPS / INS data), 3D Attempts to reproduce spatial information have not been made.

Currently, a method of acquiring spatial information along with shooting from the ground by mounting a GPS / INS on a vehicle has been proposed, but the location accuracy is poor in the urban area with high density of buildings due to multipath signal, one of the disadvantages of the GPS receiver. Become.

In addition, it is used to correct the image after acquiring GPS data and INS data, or to facilitate the manipulation in the acquisition process. However, no method of acquiring image data and spatial data while inducing and photographing a planned path without human control is being considered.

Accordingly, Korean Patent No. 0556103 (February 22, 2006) "Aeronautical Photography Method Using Automatic Shooting System" has been disclosed, and has achieved remarkable growth in the aerial photographing method using an automatic photographing system.

On the other hand, since the digital map photographs the ground in the vertical direction in the aircraft, the digital map user has no choice but to check the plane of the feature.

However, the user has no experience in seeing the feature of the feature of the feature, and only grasps the numerical map by associating the feature of the feature and the layout of the feature, so the image of the plane is photographed by the elderly with low spatial perception and cognitive ability. It was difficult to see and understand the baseline digital map and apply it to the actual terrain.

In addition, since the heights of the flat features are all the same look, the user of the digital map familiar with the area had a lot of inconvenience in understanding the digital map without the altitude information.

On the other hand, a tendency to photograph the side of the feature during aerial photography for the three-dimensional digital map.

However, when photographing the side of a particular feature, since the far distance must be taken compared to the plane even at the same altitude, there was a hassle and inconvenience of having to edit each image individually after finishing the shooting.

In order to improve this, Korean Patent No. 0937049 (2010.01.07.) Has disclosed a view angle control system of an aerial photography camera for general drawing production.

However, the registered patent has been derived in the form that the pressing rod and the guide is in the form of a simple contact guide can not calculate the exact angle at the time of one side wear.

In particular, since only the screw is pushed up and down by the screw, the pressure applied to both ends of the pressure bar coupled with the guide is easily changed by the influence of altitude, wind, etc., and thus, uneven wear occurs, which causes measurement errors.

In addition, since an arithmetic calculation is performed without calculating the photographing angle, an error may occur.

Republic of Korea Patent Registration No. 10-0556103 (2006.02.22.) "Aerial Photography Method Using Automatic Shooting System" Republic of Korea Patent Registration No. 10-0937049 (2010.01.07.) "Angle View Control System of Aerial Photography Camera for General Drawing Production"

The present invention was created in view of the above-mentioned problems in the prior art, and was developed to solve this problem, and by using the automatic shooting system and the shooting angle measurement concept by utilizing the automatic shooting system of GPS / INS flight line input of manpower It is more economical and has high efficiency because it can capture image data and spatial information by tracking the coordinates of the photographing plan route input to the computer, and it can be constructed in a large area in a short period of time. Cost reduction effect can be obtained, and spatial information of several places can be acquired at the same time in a short time, so it is economical and high quality data can be obtained, and the shooting ratio of the subject is automatically adjusted to obtain accurate subject image. In addition, the numerical image of the side of the user It can be checked directly on the map, and can be secured in one flight without having to perform multiple photographing operations to secure side image information for this, minimizing the incurred additional costs for producing more effective and efficient digital maps. Its main purpose is to provide an ultra-precision aerial photographing apparatus using GPS and INS.

The present invention is a means for achieving the above object, by using an airship automatic shooting system equipped with airship air sac, gondola, automatic shooting system (CCNPS), GPS receiving antenna and MEMS Inertial Navigation Unit (IMU) Camera 120 comprising two and three cameras 122 and 123 each equipped with a first camera 121 and zoom lens devices 124 and 124 'when performing aerial photography; The reference base 111 for fixing the first camera 121 and the rotating bases 112 and 112 'for fixing the second and third cameras 122 and 123, respectively, and the reference base 111 are fixed to the center. The pair of pivoting tables 112 and 112 'is fixed to both ends so that the first, second, and third cameras 121, 122, and 123 are arranged in a row, and the reference table and the reference table. Screw 114, which is rotatably mounted on the base 111, and a trapezoid-shaped guide 115 formed side by side on the pivoting tables 112 and 112 ', respectively, so that the distance between one surface facing each other is gradually narrowed downward. , 115 'and a presser 116 formed at the center of the nut portion 116a through which the screw 114 is engaged, and both ends slidably engaged with the one surface of the guides 115 and 115'. One support frame 110; The appliance part 100 of the drive motor 130 which provides power for the rotation of the screw 114:

A screw counter 210 for counting the number of revolutions of the screw 114; The second and third cameras 122 and 123 of the second and third cameras 122 and 123 are provided through the moving distance of the pressing table 116 and the length L1 of the pressing table 116 according to the rotation speed of the screw 114 input from the screw counter 210. A photographing angle calculation module 220 programmed to calculate photographing angles θ1 and θ1 'and installed in a computer; A GPS receiver 270 for detecting GPS coordinates; A GPS identification module 230 programmed to receive the GPS coordinates from the GPS receiver 270 and confirm the current position of the aircraft A and installed in the computer; Positioning module 240 is programmed to receive and confirm the altitude (H) of the aircraft (A) while communicating with the air measurement unit 300 is installed on the computer; A photographing distance calculation module 280 programmed to receive photographing angles [theta] 1, [theta] 1 ') and altitude H to calculate photographing distances of the second and third cameras 122 and 123 and installed in the computer; Adjust the zoom lens apparatuses 124 and 124 'to correspond to the shooting distances and altitudes H of the second and third cameras 122 and 123 so that the magnification and the first cameras of the second and third cameras 122 and 123 are adjusted. A zoom lens device adjustment module 290, which is programmed to be processed to match the shooting magnification of 121) and installed in a computer; Received the GPS and the shooting angle (θ1, θ1 ') information of the shooting area from the GPS confirmation module 230 and the shooting angle calculation module 220 is transmitted from the first, second, third camera (121, 122, 123) Input to the photographing image data, and calculates the altitude (H) confirmed by the positioning module 240 and the photographing angles (θ1, θ1 ') confirmed by the photographing angle calculation module 220, the first, second, third camera (21, 22 and 23 confirm the moving distances D and D 'of the aircraft A, which are photographing the same spot, and photographed image data photographed by the first camera 121 and photographing of the first camera 121. Data classification module installed in the computer is programmed to link and store the photographed image data taken by the second and third cameras 122 and 123, respectively, at points separated from each other by moving distances D and D '. Computer unit 200 of 250: and altitude meter 330 that measures the altitude H of the aircraft A, and transmits the measured altitude H to the positioning module 240. The air measurement section (300) comprising: a; A vertical rod 800 vertically fixed to any one of the holders 113 and 113 'with the same distance from both sides with respect to the screw 114; A cylindrical guide 810 fixed to the pressing member 116 to guide the pressing member 116 to move up and down without being shaken while the vertical rod 800 is fitted; A hemispherical ball receiving groove 820 formed at both ends of the pressing table 116; A lubricant 830 applied to the inner circumferential surface of the ball receiving groove 820; Cloud ball 840 accommodated in the ball storage groove 820; A through hole 860 is formed to expose a part of the cloud ball 840 so as to be in point contact with the guides 115 and 115 'without being released from the ball 840. Ball tips 850 screwed at both ends; First and second bolt grooves (BH, NH) formed in a stepped shape with a step on the pressing table (116); A fixing bolt B1 protruding integrally with one side of an outer circumferential surface of the cylindrical guide 810 to be fastened to the first bolt groove BH; A through hole TH formed through the center of the fixing bolt B1 in a longitudinal direction; An anti-loosening bolt B2 fastened to the second bolt groove NH after passing through the through hole TH; It is installed on one side of the guide (115, 115 ') to measure the inclination of the guide (115, 115') in real time, and transmit the result to the photographing angle calculation module 220 to compare the arithmetic calculated value and the measured value to shoot A digital protractor DA for transmitting an actual value to finally confirm the angle [theta] 1; And a position changing unit (POS) between the reference stage 111 and the pivoting stages 112 and 112 ′, the first, second and third cameras 121, 122 and 123 being rotated within a predetermined radius. (POS), the fixed base 900 is fixed to each of the reference stage 111 and the rotating table (112, 112 '), the reference table 111 and the rotating table (112, 112') is controlled by the control module 470 The fixed base 900 is formed in the lower portion of the lower open cylindrical shape in which the lower surface is recessed to form an outer catching jaw 920, and the gap between the outer catching jaw 920 and the bottom. On the inside, a circular inner locking jaw 930 is formed, a sun gear 910 is formed on the opposite surface of the outer locking jaw 920, and the inner locking jaw 930 is formed at a lower end of the camera base 940. ) And the engaging portion (TT) is formed so as to be caught at the same time by the outer locking jaw 920 and move along it, the camera The base 940 is equipped with a camera transfer motor 950 including an encoder 960, the rotation axis of the camera transfer motor 950 is provided with a planetary gear 970 which is tooth-coupled with the sun gear 910, The rotating tables (112, 112 ') and the reference table 111 has a hemispherical shape, and the reflection shade 1100 coated with aluminum on the inner surface is fixed, respectively, the reflection shade 1100 is divided into two members of the rotating table ( 112 and 112 'and bolts or screws are provided on the fixed guide block (FBL) provided in the reference base 111; On the inner surface of the reflection shade 1100, three sound wave oscillation units 2000 are installed at intervals of 120 ° in a radial direction at positions that do not interfere with the first, second, and third cameras 121, 122, and 123, and the sound wave oscillation unit ( 2000 is a case 2100 of which the tip is opened and the locking jaw 2200 is provided, and the air formed in the case 2100 and the outlet formed in the case 2100 are gradually narrowed in the part of the outer peripheral surface of the case 2100. Inlet 2300, the air inlet 2400 formed in the opposite shape to the air inlet 2300 at the point facing the air inlet 2300 in the radial direction, and a spring built in the case (2100) 2800, the flow bracket 2500 fitted to the front end of the case 2100 and the hooking jaw 2200 and the air suction port 2300 which is the rear end of the flow bracket 2500. Tapered inclined surface 2600 and the flow bra It provides a high-precision air-up apparatus using the jipieseu (GPS) and ahyien S (INS) being configured including; the sound wave launcher 2700 fixed to the distal end surface of (2500).

According to the present invention, since the side image and the plane image are initially photographed at the same magnification with respect to the same feature, and photographed at an accurate photographing ratio for each subject, it is possible to eliminate the hassle of editing the acquired image data later. The effect of improving the work and the digital mapping work efficiency can be obtained.

In addition, the measurement angle can be duplicated by arithmetic method and actual measurement method to compare and compare the two to reduce or correct errors, thereby improving accuracy, and the automatic photographing system can be combined to obtain image data and spatial data easily and easily. Can be.

1 is a schematic diagram of a method for acquiring image data and spatial information using a GPS / INS airship automatic photographing system (CCNPS) applied to the present invention;
2 is a view schematically showing a photographed image applied to the present invention,
3 and 4 is a view schematically showing the appearance of aerial photography based on the angle of view adjustment function constituting the automatic shooting ratio adjustment system according to the present invention,
Figure 5 is an exploded perspective view showing a state of the support frame constituting the automatic shooting ratio adjustment system according to the present invention,
6 is a front view showing the operation of the support frame constituting the automatic shooting ratio adjustment system according to the present invention,
7 is a block diagram showing the configuration of the angle of view adjustment function constituting the automatic shooting ratio adjustment system according to the present invention,
8 is a view schematically showing a digital map image by the angle of view adjustment function constituting the automatic shooting ratio adjustment system according to the present invention,
9 is a view schematically showing another embodiment of the aerial photography based on the angle of view adjustment function constituting the automatic shooting ratio adjustment system according to the present invention,
10 is an exemplary diagram further improving the structure of the support frame constituting the automatic shooting ratio adjustment system according to the invention,
11 is an exemplary view showing an example of fastening the cylindrical fixture improved according to the present invention,
12 is an exemplary cross-sectional view showing another configuration improved in accordance with the present invention,
Figure 13 is an exemplary cross-sectional view showing a configuration example for preventing the appearance of the interference in accordance with the present invention.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Before describing the present invention, the following specific structural or functional descriptions are merely illustrative for the purpose of describing an embodiment according to the concept of the present invention, and embodiments according to the concept of the present invention may be embodied in various forms, And should not be construed as limited to the embodiments described herein.

In addition, since the embodiments according to the concept of the present invention can make various changes and have various forms, specific embodiments are illustrated in the drawings and described in detail herein. However, it should be understood that the embodiments according to the concept of the present invention are not intended to limit the present invention to specific modes of operation, but include all modifications, equivalents and alternatives falling within the spirit and scope of the present invention.

Since the present invention has been completed by incorporating the above-described prior patent No. 0556103 to the previously registered patent No. 0937049 described below, all the features of the device configuration described below are those described in the Patent No. 0937049.

Particularly, the present invention utilizes the concept included in the automatic photographing system in the registered patent No. 0556103, and compares the measured and calculated values by duplexing the photographing angle measurement in the configurations disclosed in the registered patent No. 0937049. By doing so, it is possible to obtain an accurate angle of view, and in addition to this, there is a main feature in the improved workability by facilitating the desorption of the cylindrical guide.

Therefore, the device configuration, features and operation relations described below will be referred to the contents of the Patent No. 0937049 as it is, and will be described in detail with respect to the configuration associated with the main features of the present invention at the rear end.

First, the present invention, as shown in Figure 1, in the INS system mounted on the airship body in relation to the term X axis is the longitudinal axis (roll) of the aircraft, Y axis is the right wing (pitch), Z axis is the yaw rotation element to be.

The three-dimensional position (X0, Y0, Z0) of the camera focus mounted on the gondola of the GPS / INS airship is the three-dimensional position calculated from the GPS antenna and the three-dimensional position of the GPS antenna and camera focus position. It is calculated through the correction of the difference in distance, and GPS / INS spatial information is acquired together at the moment when the image data is acquired.

The acquired GPS / INS data is input to an automatic photographing system (CCNPS). Then, the acquired GPS / INS data enters a corresponding course (a course) and moves along the planned three- Obtain information.

The present invention by applying the basic concept of the automatic shooting system as it is, by performing arithmetic operation by extracting the photographing angle (view angle) information of the height of the aircraft and the subject of the camera installed in the aircraft, that is, the building for automatic adjustment of the shooting ratio The shooting distance of the subject (building) can be calculated, and the zoom ratio can be automatically adjusted by implementing the zoom function according to the calculated shooting distance.

To this end, a description of how to obtain the shooting angle as described below is mainly, this part is very important, for example, as shown in Figures 2 to 4, the first camera 121 to shoot In order to photograph the specific building B, which is a point, with the second and third cameras 122 and 123, as shown in the drawing, at the first position S1 of which the aircraft A is vertically above the building B, It should move to the second position S2 or the third position S3, which is to the side.

In addition, in order to arrange the first, second, and third positions S1, S2, and S3 in a line with respect to the building B, the first, second, and third cameras may be arranged in a direction parallel to the traveling direction of the aircraft A. Must be fixed to the support frame 110 so that 121, 122, 123 are disposed.

Here, the support frame 110 is to fix the first, second, third, cameras 121, 122, 123 to the aircraft (A), its structure and operation will be described in more detail below. On the other hand, the second and third cameras 122 and 123 are installed outside the support frame 110, and are equipped with zoom lens devices 124 and 124 'that can adjust the angle of view, that is, the shooting magnification.

The zoom lens devices 124 and 124 'are conventional devices that automatically adjust the shooting magnification by moving the focal length of the lens, and have general zoom in and zoom out functions. In addition, the zoom lens devices 124 and 124 'are automatically operated by a motor (not shown), and this operation is controlled by the zoom lens device adjustment module 290 of the computer unit 200. Since the zoom lens devices 124 and 124 'and the zoom lens device adjusting module 290 are well known and commonly applied to general digital cameras and photographing apparatuses, the description thereof will be omitted.

As can be seen in Figure 2 (b), the photographed image taken sideways shows the side of the feature including the building (B).

In other words, it is possible to check the height of the feature, and furthermore, when the resolution is high, the appearance of the feature familiar to the user can be distinguished. Therefore, when the user cannot understand the terrain in the planar photographing image, the side photographing image of the same point can be output, so that the numerical map can be easily analyzed and utilized.

On the other hand, the side-shooting of the feature is different from the altitude and position (S1, S2, S3) of the aircraft A according to the shooting angles (θ1, θ1 ') of the second and third cameras 122 and 123, even if the location is different. This can be taken. Therefore, the angle of view adjustment function according to the present invention provides information on the area photographed by the corresponding second and third cameras 122 and 123 relative to the shooting angles θ1 and θ1 'of the second and third cameras 122 and 123. It should be self-identifying.

In addition, the aircraft A may not only travel in a straight line but also may turn at a constant turning angle θ2 as shown in FIG. 4 to fly in a different direction, regardless of the turning angle θ2. The information about the area photographed by (122, 123) should also be known accurately.

To this end, the angle of view adjustment function according to the present invention checks the current altitude H and the moving distances D and D 'of the aircraft A and the shooting angles θ1 and θ1' of the second and third cameras 122 and 123. When the aircraft A operates the moving distances D and D 'calculated at a predetermined altitude H, the second and third cameras 122 and 123 automatically control the photographing of the ground. That is, when the altitude H of the current aircraft A and the shooting angles θ1 and θ1 'of the second and third cameras 122 and 123 are checked, the second and third cameras 122 and 123 should operate. The moment can be calculated from the movement distances D and D 'of the aircraft A.

Of course, the second and third cameras 122 and 123 perform continuous shooting (including video shooting) regardless of the moving distances D and D 'of the aircraft A, but move when classifying the collected side photographing images. The distances D, D ', altitude H, and shooting angles θ1 and θ1' may be classified and linked to planar images of the same area.

Operation of the angle of view adjustment function according to the present invention will be described in detail below with reference to the block diagram.

Figure 5 is an exploded perspective view showing a state of the support frame according to the present invention, Figure 6 is a front view showing the operation of the support frame according to the present invention, will be described with reference to this.

The support frame 110 according to the present invention, while fixing the first, second, third cameras 121, 122, 123 rotatably to the aircraft A, the angle of view adjustment function is the second, third cameras 122, 123 It is to be able to accurately grasp the operation state of the reference stage 111 and the second and third cameras (122, 123) to securely fix the first camera 121, the rotating table ( 112, 112 'and the first, second, and third cameras 121, 122, and 123 are fixed in a row via the reference table 111 and the pivot tables 112 and 112', but the pivot tables 112 and 112 'are rotated. Guides 113 and 113 ', which are fixed to each other, screws 114 rotatably installed on the reference table 111, and trapezoidal guides installed on the pivot tables 112 and 112', respectively. 115, 115 ′ and a press table 116 slidably engaged with the guides 115, 115 ′, respectively, while moving up and down along the screw 114.

As shown, the first, second, and third cameras 121, 122, and 123 are suspended to photograph downward, and the performance may vary depending on the shooting purpose.

The second and third cameras 122 and 123 disposed at both ends of the edges of the first, second and third cameras 121, 122 and 123 installed in this way rotate to face each other. That is, when the photographing angles θ1 and θ1 'of the second camera 122 face the first camera 121 at 30 degrees, the photographing angle of the third camera 123 is toward the first camera 121 at −30 degrees. . To this end, the first and second cameras 121, 122, and 123 are connected to the reference base 111 and the pivoting bands 112 and 112 'in a row, the fixing bases 113 and 113', and the reference base 111. ) And a screw 114 and a guide 115, 115 ′ mounted on each of the rotating table 112 and 112 ′, and a pressing table 116 engaged with both ends of the guide 115 and 115 ′.

As shown in FIG. 6, the pressure bar 116 includes a nut portion 116a having a pitch that matches with the pitch of the screw 114, and the screw through the engagement of the screw 114 and the nut portion 116a. Along the 114 it is configured to move up and down. At this time, the screw 114 is rotated by the rotational force of the drive motor 130 via the reducer 140, and the lifting and lowering of the pressure table 116 will be determined according to the rotation direction.

On the other hand, when the drive motor 130 rotates in the direction of lowering the pressing table 116, the pressing table 116 moves downward along the screw 114 as shown in Figure 6 (b). At this time, one surface of the guide (115, 115 ') that both ends of the presser 116 is engaged with each other is formed to be inclined downward, so that the interval between the guide (115, 115') is narrowed. On the other hand, since the pressing bar 116 maintains its original length when lifting up and down, the guides 115 and 115 'are forced outward as the pressing bar 116 moves downward.

Of course, this force is spaced apart from the guides (115, 115 '), and the second fixing pins (112a, 112a') located below the fixing pins (112a, 112a ') rotatably fixing the pivot (112, 112') The three cameras 122 and 123 rotate toward the first camera 121 at the same photographing angles θ1 and θ1 '.

Unexplained withdrawal number '111a' refers to the 'fixing pin' for fixing the reference base 111 and the fixing base (113, 113).

Here, the photographing angles θ1 and θ1 'of the second and third cameras 122 and 123 may be a distance L2 between the pressing table 116 and the fixing tables 113 and 113' relative to the length L1 of the pressing table 116. , L2 '). At this time, the interval (L2, L2 ') can be calculated based on the number of revolutions of the screw 114, for this purpose, the angle of view adjustment function according to the present invention the screw counter 210 to count the number of revolutions of the screw 114 7).

In more detail, through the pitch and the structure of the pitch, the movement distance of the pressing table 116 to linearly move by the rotation of the screw 114 can be set. In other words, when the screw 114 is rotated two times, the presser 116 may move 1 mm or more or less than 1 mm.

As a result, when the screw counter 210 counts the number of revolutions of the screw 114, it is possible to calculate the moving distance of the pressure table 116 according to the set content, through which the gap (L2, L2 ') can be confirmed. have.

In addition, the photographing angles θ1 and θ1 'of the second and third cameras 122 and 123 are calculated through the checked intervals L2 and L2', and the photographing angles θ1 and θ1 'are calculated. The moving distances D and D 'from the current altitude H of the aircraft A to the second and third positions S2 and S3 corresponding to the first position S1 can be checked.

7 to 9, the angle of view adjustment function according to the present invention includes a device unit 100 and a computer unit 200, and the computer unit 200 is interlocked with the aviation measurement unit 300 installed in the aircraft A. To work.

The device unit 100 includes a support frame 110, cameras 121, 122, and 123 (hereinafter, 120), a driving motor 130, and a speed reducer 140.

Since the description of the device unit 100 has been described above, the description thereof is omitted here.

The computer unit 200 includes a screw counter 210 for counting the number of revolutions of the screw 114 and the second and third cameras 122 and 123 according to the number of revolutions of the screw 114 counted by the screw counter 210. Receiving GPS coordinates from the shooting angle calculation module 220 for calculating the shooting angles θ1 and θ1 ', the GPS receiver 270 for detecting the GPS coordinates, and the GPS receiver 270, and thus the current position of the aircraft A. GPS confirmation module 230 for confirming, the positioning module 240 for confirming the current state of the aircraft (A) while communicating with the air measurement unit 300, and the camera 120 photographed image for the same area A data classification module 250 for classifying and storing the data classification module 250, a data communication module 260 for transmitting the captured image data classified by the data classification module 250 to the integrated data management unit 400 located on the ground, and a photographing angle θ1. photographing distance calculation module 280 for calculating the photographing distances of the second and third cameras 122 and 123 by checking the? Zoom lens device adjustment module for checking the shooting distances of the cameras 122 and 123 and the altitude H, which is the shooting distance of the first camera 121, and adjusting the zoom lens devices 124 and 124 'according to the ratio. 290.

At this time, the module 220, 230, 240, 250, 260, 280, 290 constituting the computer unit 200 is a device composed of software programmed for the task and hardware (computer) applied to drive the software As such, the software and hardware (computer) of each module (220, 230, 240, 250, 260, 280, 290) can be applied to the known technology for the operation, through which those skilled in the art to the present invention It can be implemented easily.

On the other hand, the aviation measurement unit 300 installed for the operation of the aircraft (A) is a direction measuring instrument 310 for detecting the turning angle (θ2) of the aircraft (A), and the tilt sensor for detecting the horizontal state of the aircraft (A) And an altitude meter 330 for measuring the altitude of the aircraft A.

The aviation measurement unit 300 is for reference to the shooting operation affected by the operating state of the aircraft (A), the information provided from the aviation measurement unit 300 is whether the utilization of the photographed image taken by the camera 120 And criteria for classification.

For reference, the information of the air measurement unit 300 is recorded as data, such as a black box of the aircraft (A), the positioning module 240 according to the present invention to check the corresponding data transmitted to the black box from the air measurement unit 300 Can be.

In addition, the positioning module 240 may be set to check the data of the air measurement unit 300 delivered to the digital aeronautical instrument board, to confirm the corresponding data.

The implementation of the angle of view adjustment function according to the present invention will be described sequentially.

1. The photographer sets the shooting angles θ1 and θ1 'of the second and third cameras 122 and 123 before the photographing operation using the camera 120.

The setting of the photographing angles θ1 and θ1 'is performed by controlling the driving motor 130 of the operator. That is, when the operator operates the drive motor 130, the rotational force of the drive motor 130 is transmitted to the screw 114 through the reducer 140, and the rotation of the screw 114 moves the press table 116. In this case, the second and third cameras 122 and 123 are rotated.

On the other hand, the screw counter 210 counts the number of revolutions of the screw 114, according to the set angle photographing operation module 220 is the interval (L2, L2) between the pressing table 116 and the fixing table (113, 113 ') Calculate '). As described above, the length L1 of the pressing table 116 is a fixed value, and the intervals L2 and L2 'between the pressing table 116 and the fixing tables 113 and 113' are variable values, but the screw 114 is fixed. Since the variable value can be known by the number of revolutions, the photographing angle calculation module 220 can accurately calculate the photographing angles θ1 and θ1 'of the second and third cameras 122 and 123.

2. The positioning module 240 checks the flight measurement unit 300 from time to time while checking the operating state of the aircraft (A) in real time, and according to the confirmed operating state to determine whether to drive the camera 120 or the camera 120 ) Determines whether to use the captured image or classifies the captured image.

In the embodiment according to the present invention will be described that the camera 120 automatically executes a continuous shooting operation at a predetermined interval.

3. The camera 120 proceeds the shooting operation at a predetermined interval (including video recording), the data classification module 250 is taken in the shooting image data output and the shooting time, GPS in the shooting area, aviation measurement unit 300 Enter the confirmed information and the photographing angles θ1 and θ1 '.

4. Even when all aerial photographing work is completed or aerial photographing, the data classification module 250 proceeds to classify photographed image data for the same region.

As described above, in order to classify the photographing image data of the first camera 121 photographing the same region as the photographing region of the second and third cameras 122 and 123 photographing the side surface of the feature, the photographing angle? 1, The travel distances D and D 'of the aircraft A corresponding to θ1') are required.

Of course, since the aerial photography was taken at an altitude H within the error range, the data classification module 250 may have a fixed altitude H and the shooting angles θ1 and θ1 'of the second and third cameras 122 and 123. ) Can calculate the moving distances (D, D ') of the aircraft (A), which is the position of the second and third cameras 122 and 123 capable of capturing the same region as the first camera 121.

As a result, the data classification module 250 at intervals of the photographed images photographed by the first camera 121 and the moving distances D and D 'among the photographed images photographed by the second and third cameras 122 and 123. The photographed images will be considered to photograph the same area and will be classified together. For reference, the moving distances D and D 'of the captured image may be calculated through GPS coordinates included in the captured image data.

Meanwhile, as shown in FIG. 4, the aircraft A travels in a direction parallel to the first, second, and third cameras 121, 122, and 123 arranged in a row, and the second position S2 from the first position S1. It may be moved to, but may be turned to a constant turning angle θ2, to move from the first position (S1) to another second position (S2 '). In this case, if the building B photographed by the first camera 121 coincides with the moving distances D and D ', which are horizontal straight distances of the aircraft A, the second and third cameras 122 and 123 ) May be considered to photograph the same building (B) and classify them together.

In other words, it is possible to easily create a digital map that allows a user to check various aspects of a particular feature.

In addition, even a single aerial shot is expected to secure economical production of digital maps with abundant information by securing various side photographs of the features located on the ground.

In addition, it demonstrates with reference to FIG. 3 and FIG.

As shown in the figure, the difference of the photographing angles? 1 and? 1 'causes not only the difference of the moving distance D and D' but also the difference of the photographing distance.

That is, the size of the building B to be photographed is inevitably changed due to the difference in the photographing distance when photographing the plane of the building B and when photographing the side of the building B.

Therefore, the computer unit 200 implementing the angle of view adjustment function according to the present invention further includes a photographing distance calculation module 280 and a zoom lens device adjustment module 290.

The photographing distance calculation module 280 checks the altitude H and the photographing angles θ1 and θ1 'of the aircraft A and calculates a photographing distance for the building B.

The zoom lens device adjustment module 290 checks the information on the shooting distance calculated by the shooting distance calculation module 280 to operate the zoom lens devices 124 and 124 'mounted on the second and third cameras 122 and 123. . That is, the zoom lens devices 124 and 124 'are driven so that the photographing distances of the second and third cameras 122 and 123 match the altitude H, so that the second and third cameras 122 and 123 photograph the side surfaces. The photographed image is to have the same / similar magnification as the planar photographed image photographed by the first camera 121.

5. When the captured image data is classified, the data communication module 260 transmits the classified captured image data to the data integrated management unit 400.

Hereinafter, the integrated data management unit 400 will be described in detail with reference to FIG. 7.

Integrated data management unit 400 is a data receiving module 410 for receiving the photographed image data transmitted from the data communication module 260, and the photographed image data received by the data receiving module 410 side photographed image data and plane photographing When the new image data is received and the new image data is received, the corresponding data stored in the side image image database 430 and the plane image image database 440 are updated. The editing update module 420, the side photographing image database 430 and the planar photographing image database 440 respectively storing side photographing image data and planar photographing image data, and a control signal are inputted by a user's input device. Input module 450 and the following search module 480 and GPS according to the control signal input to the input module 450 A control module 470 for controlling the operation of the coordinate linking module 490 and the output module 460, a search module 480 for searching data of the side photographing image database 430 and the planar photographing image database 440; GPS coordinates are synthesized by applying a GPS coordinate system to the captured images of the captured image data retrieved by the search module 480 based on the GPS coordinates included in each of the captured image data, but synthesizing the GPS coordinate system based on the plane information set for each structure. Link module 490, and output module 460 for outputting a digital map through the output device synthesized GPS coordinates and the photographed image.

In this case, the modules 410, 420, 450, 460, 470, 480, and 490 constituting the data integration management unit 400 are software programmed for a corresponding task and hardware (computer) applied to drive the software. With the device configured, the software and hardware (computer) of each module 410, 420, 450, 460, 470, 480, 490 can be applied to the known technology for the corresponding operation, and thus those skilled in the art will see The invention can be easily carried out.

For reference, the input device may be a conventional keyboard or various buttons and the like, and the output device may be a conventional monitor or the like.

The data receiving module 410 may wirelessly receive the captured image data in real time from the data communication module 260 of the computer unit 200, and after receiving the photographed image, the received image data stored in a separate storage medium may be input. You might get it.

The editing update module 420 manages data of the side photographing image database 430 and the planar photographing image database 440 storing the photographed image data, and the side of the photographed image data input through the data receiving module 410. When it is determined that the image data is different from the photographed image data stored in the photographed image database 430 and the planar photographed image database 440, the operation of updating the photographed image database 430 and the planar photographed image database 440 is performed.

In reality, since the digital map maker will use the aircraft A for aerial photography where the topographical change has occurred, the producer manipulates the editing update module 420 to produce the side photographing image database 430 and the planar photographing image database 440. Will be updated directly.

The updated side photographing image database 430 and the planar photographing image database 440 may provide a digital map of the terrain required by the user.

In more detail, the user inputs the relevant information of the region P to which the user wants to operate the input module 450.

The control module 470 operates the search module 480 to search the planar photographing image database 440, and the GPS coordinate linking module 490 synthesizes and applies the GPS coordinate system to the retrieved photographed image. 460). In this case, the GPS coordinate system will be synthesized based on the area P.

On the other hand, if the user wants to see the side view of the area (P), the search module 480 searches the side photographing image database 430, the GPS coordinate link module 490 is the area (P) in the retrieved photographed image The GPS coordinate system is synthesized and applied based on), and is output through the output module 460. At this time, the area P is set to the plane of an arbitrary structure (building B).

This applies to the principle that the plane must be visible even if the side view of the structure is visible, and the plane information is set for each of the structures included in the side photographing image and the plane photographing image, so that the GPS coordinate linking module 490 displays the plane information. GPS coordinate system can be applied as a standard. Here, the plane information will include GPS coordinates.

As a result, the GPS coordinate system is accurately synthesized even in the plane image and the side image image having a large overall image difference, so that the user can always use the digital map by checking the accurate GPS coordinate regardless of image change.

The present invention is configured to automatically adjust the shooting ratio through such an angle of view adjustment function, at this time during the angle of view to reduce the frictional resistance between the guide (115, 115 ') formed on the pressure bar 116 and the support frame 110 and accurate and A structural improvement as shown in FIG. 10 may be further made for uniform elevating control.

As shown in FIG. 10, the present invention may further include a pair of vertical rods 800 to evenly raise and lower the pressure bar 116.

The vertical rod 800 has a lower end integrally fixed to any one of the two fixing rods 113 and 113 'to maintain a vertical state.

In particular, the vertical bar (800) is fixed to the spaced apart at the same distance from the screw 114 with the screw 114 therebetween.

In addition, a cylindrical guide 810 is provided to allow the vertical bar 800 to be fitted, and each of the pair of cylindrical guides 810 is integrally formed on the pressure bar 116 to fit the vertical bar 800. It is provided fixed.

Therefore, the vertical bar 800 is a kind of guide, and the cylindrical guide 810 is moved up and down along the vertical bar 800, so that the left and right sides of the pressure bar 116 can be raised and lowered uniformly. It becomes possible.

In addition, both ends of the pressing table 116 is provided with a friction reducing member to reduce the frictional resistance with the guides (115, 115 ').

In this case, the friction reducing member is composed of a spherical ball (Ball) and a stopper, that is, a tip (Tip) to prevent the separation thereof. However, since it is composed of the same structure at both ends of the pressure zone 116 will be described with only one side.

As shown in the enlarged cross-sectional view of the main portion shown in FIG. 10, the hemispherical ball storage groove 820 is formed at the end of the presser 116 in a concave shape, and the lubricant is formed on the inner circumferential surface of the ball storage groove 820. 830 is applied.

At this time, the lubricant 830 is to allow the ball accommodated in the ball receiving groove 820, that is, the rolling ball 840 to be described later to slide smoothly.

In addition, a stepped portion TL is formed on an outer circumferential surface of the ball storage groove 820, and a screw thread is formed in the stepped portion TL.

In this case, the step portion TL is for fixing the ball tip 850 to be described later.

In addition, the ball tip 850 is a kind of stopper, so that the through hole 860 is formed in the center to expose a part of the cloud ball 840 to be accommodated in the ball storage groove 820.

In addition, the ball tip 850 is screwed to the step portion (TL) by being easily fixed to both ends of the pressing table 116, the ball ball 840 housed in the ball receiving groove 820 is not separated It will serve to hold.

When the frictional resistance member is installed in such a structure, the contact with the guides 115 and 115 'is limited to the rolling balls 840, and the frictional resistance is almost absent because the rolling contact is almost close to the point contact.

Therefore, there is almost no abrasion due to friction, which prevents uneven wear, and evenly adjusts the angle of view of the camera precisely when the presser rod 116 is moved up and down along the screw 114, thereby accurately adjusting the angle of view of the camera. Can be reduced.

In addition, as shown in FIG. 11, which is an exemplary cross-sectional view showing an enlarged portion of FIG. 10, the cylindrical guide 810 may be fastened by screwing to facilitate assembly and disassembly.

However, the screwing method has a limitation that it is difficult to accurately position the cylindrical guide 810. That is, the vertical guide 800 is to be fitted to the cylindrical guide 810, but when the cylindrical guide 810 is fixed while being twisted, the vertical rod 800 faces a limit that can not fit.

In order to solve this problem, in the present invention, a first bolt groove (BH) is formed in the pressing table (116), and provided with a fixing bolt (B1) fastened to the first bolt groove (BH), the fixing bolt (B1) ) Is integrally formed with one side of the outer circumferential surface of the cylindrical guide 810 and has a structure formed to protrude therefrom.

At this time, the first bolt groove (BH) is formed in a stepped stepped step, the groove formed on the innermost step is a second bolt groove (NH) to be fastened to the anti-loosening bolt (B2) to be described later.

In addition, the fixing bolt (B1) is formed through holes (TH) over the entire length in a hollow state inside.

In addition, the through hole (TH) is configured to pass through the cylindrical guide 810 and communicate with the inner hollow side, the clearance groove (GH) is stepped on the inner circumferential surface of the head when tightening the anti-loosening bolt (B2) The inner diameter of the cylindrical guide 810 and the same on the same plane so as not to interfere with the vertical bar 800 when moving up and down.

And, the anti-loosening bolt (B2) is fastened to the second bolt groove (NH) through the through hole (TH), in this case, if the thread is processed only a part of the end of the anti-loosening bolt (B2) to tighten the work. You can do it faster and smoother.

As such, when the bolt is doubled, the cylindrical guide 810 is screwed to an appropriate point, and the fixing bolt B1 is fixed to the fixing bolt B1 by the anti-loosening bolt B2 in a fixed position so that the vertical rod 800 can be fitted. If it is thrown away, it can be completely fixed so that it will not flow in that position.

In addition, as shown in FIG. 10, a digital protractor DA is installed on one side of the guides 115 and 115 ′, and the digital protractor DA is electrically connected to the photographing angle calculation module 220 (see FIG. 6). .

Therefore, the digital protractor DA measures the inclination of the guides 115 and 115 'in real time, and transmits the result to the photographing angle calculation module 220, and the photographing angle θ1 calculated by the above-described operation. By comparing and judging the two, it checks whether it is an error range, and when it is out of the error range, it is possible to calculate a more accurate and perfect shooting angle by re-measuring or checking for abnormality.

In addition, as shown in FIG. 12, the first, second, and third cameras 121, 122, and 123 are configured to rotate within a predetermined radius, thereby avoiding the shooting radius and the avoidance when the interference appears. This makes the function even more efficient.

To this end, a position change unit (POS) is provided at the lower ends of the pivoting bands 112 and 112 'and the reference base 111.

At this time, the position change unit (POS) includes a fixed base 900 that is fixed to the lower end of the rotating table (112, 112 ') and the reference table (111).

Here, the rotating table (112, 112 ') and the reference table 111 is installed in a telescopic form so that the height can be adjusted, it is controlled by the control module 470 described above.

To this end, the telescopic operation of the rotating table (112, 112 ') and the reference table 111 may be made through an operating cylinder (not shown).

In addition, the fixing base 900 is preferably formed in a circular shape, as shown in the figure, it may be configured to include a protrusion (DT) protruding downward only the edge portion to maintain the concave state.

In addition, an outer locking jaw 920 vertically bent to protrude outward from the protrusion DT in a radial direction is formed outside the end of the protrusion DT.

On the other hand, the sun gear 910 is formed on the inner surface of the protrusion DT along the radial direction.

The inner locking jaw 930 protrudes at the same height as the protrusion DT in the fixed base 900 at intervals from the protrusion DT. The inner locking jaw 930 has a circular band shape. Is formed to protrude into.

On the other hand, the camera base 940 is provided to be rotated in the circumferential direction along the fixed base 900.

The camera base 940 is equipped with a sensing sensor (SEN) for detecting an interference body such as a bird, and the first, second, third cameras (121, 122, 123) and the zoom lens device (124, 124 ') is fixed to the bottom.

In addition, the engaging portion TT is bent at the bottom while having a circular curvature so as to be caught by the outer locking jaw 920 and the inner locking jaw 930.

Therefore, the camera base 940 is fixed to the fixed base 900 in a state where the locking portion TT is caught on the inner locking jaw 930 and the outer locking jaw 920.

On the other hand, a camera transfer motor 950 is fixed to the camera base 940, and an encoder 960 is mounted to the camera transfer motor 950.

In addition, the planetary gear 970 is fixed to the rotation axis of the camera transfer motor 950, the planetary gear 970 is tooth-coupled with the sun gear 910.

The camera transfer motor 950 and the encoder 960 are controlled in communication with the control module 470.

Accordingly, when shooting interference is caused by an object injured in the air such as a bird during aerial photography, the detection sensor SEN detects this, and the control module 470 that receives the detection signal receives the camera transfer motor 950. By changing the position of the first, second, third camera (121, 122, 123) by driving a) it is possible to eliminate the interference phenomenon in a very short time without changing the course of the aircraft.

At this time, the movement of the camera transfer motor 950 reads the signal sent from the encoder 960 on the basis of the home position so that the control module 470 easily and accurately the first, second, and third cameras by a well-known arithmetic operation control method. It is possible to control the respective positions (121, 122, 123).

In other words, when an interference occurs, the position of the first, second, and third cameras 121, 122, and 123 may be changed to eliminate interference, and may be photographed as it is.If necessary, the camera may return to the home position after the interference is eliminated to continue shooting. Can be controlled to perform.

In addition, as shown in FIG. 13, a configuration for preventing the appearance of the interferer itself may be added.

That is, as shown in Figure 13, it is configured to further include a sound wave projector 2700 for emitting sound waves to prevent the appearance of the interference.

The sound wave emitter 2700 detects the interferer to reduce the number of times to repeat the re-photographing, thereby enabling more efficient and stable aerial photography.

To this end, the reflector 1100 is fixed to the pivoting bands 112 and 112 'and the reference base 111.

The reflection shade 1100 is provided in the form including the first, second, and third cameras 121, 122, and 123, respectively, as a kind of covering, and has a surface so that the sound waves can be disturbed and mixed to emit as much as possible. Preference is given to using very smoothly coated aluminum.

In particular, the reflection shade 1100 is made of a half-spherical shape divided into half, the fixing bracket 1200 is protruded in the center of the top, respectively, the fixing bracket 1200 is the rotating table (112, 112 '), respectively And screws or bolts are fixed to the fixing guide blocks FBL respectively protruding from the reference base 111.

Therefore, the reflection shade 1100 is finally fixed to the fixing guide block (FBL) has a hemispherical shape.

In addition, the sound wave oscillation unit 2000 is disposed on the inner circumferential surface of the reflection shade 1100 at intervals of 120 ° in the radial direction at points on the same line that do not interfere with the first, second, and third cameras 121, 122, and 123. Is installed.

At this time, the reason for disposing the sound wave oscillation unit 2000 at intervals of 120 ° is to minimize the sound waves canceled by the extinction interference during sound wave oscillation so as not to be installed facing each other.

On the other hand, the sound wave oscillation unit 2000 has a case 2100 fixed to the inner surface of the reflection shade 1100.

The case 2100 is disposed to be inclined according to the internal curvature of the reflection shade 1100.

A locking jaw 2200 is formed at the tip of the case 2100.

The locking jaw 2200 is a means for preventing the separation of the sound wave projector 2700, which will be described later.

Of course, although the assembly structure in the city is excluded, the locking step 2200 can be configured by being fixed to the front end of the case 2100 in various forms such as a fastening method through a screw thread or a fixing method using bolts / screws.

In particular, the air inlet 2300 is drilled in the outer peripheral surface of the front end of the case 2100 in consideration of the direction of the aircraft, and the air outlet 2400 is formed on the opposite side thereof in a radial direction.

At this time, the inlet side of the air inlet 2300 is larger in diameter, that is, in other words, the case 2100 inside the case 2100 is formed to taper in the form of gradually decreasing diameter, so that the air intake is well, the inside of the case 2100 The outlet is narrowed so that the inlet flows at a high speed.

In addition, the air outlet 2400 is naturally formed in a shape opposite to the air inlet 2300 because the internal air must be quickly exhausted.

In addition, a spring 2800 is provided inside the case 2100, and the flow bracket 2500 is grounded at an end of the spring 2800.

The flow bracket 2500 is inserted into the case 2100 and configured to flow up and down therein, and a sound wave emitter 2700 is installed at a front end thereof.

In this case, the sound wave emitter 2700 should be kept exposed outside the front end of the case 2100, and the rear end of the floating bracket 2500 is fixed to the locking jaw 2200.

In addition, the rear end body of the flow bracket 2500 should be tapered to have an inclined surface 2600, and the usual position of the inclined surface 2600 should be disposed to face the air inlet 2300.

Accordingly, when the aircraft is flying, the air flows through the air intake port 2300 at high speed and pressurizes the inclined surface 2600.

Then, since the inclined surface 2600 is pressed, the inclined surface 2600 overcomes the pressure of the spring 2800 and is pressed.

In addition, when the inflow of air is reduced, the flow bracket 2500 is returned to its original position.

As the operation is repeated, the sound wave emitter 2700 gives strength or fluctuations to the sound wave oscillation while repeating the lifting and exiting with respect to the front end surface of the case 2100.

Then, the sound wave hits the inner surface of the reflection shade 1100 and then spreads radially to disturb the work, thereby blocking the source of the interference, such as a bird approaching the surroundings.

800: vertical bar 810: cylindrical guide
820: ball receiving groove 830: lubricant
840: Cloud Ball 850: Ball Tip
860: through hole

Claims (1)

When performing aerial photography using an airship autonomous system equipped with an airship air bag, a gondola, an automatic photographing system (CCNPS), a GPS receiving antenna, and an MEMS Inertial Navigation Unit (IMU), the first camera 121 and A camera 120 including two and three cameras 122 and 123 equipped with zoom lens devices 124 and 124 ', respectively; The reference base 111 for fixing the first camera 121 and the rotating bases 112 and 112 'for fixing the second and third cameras 122 and 123, respectively, and the reference base 111 are fixed to the center. The pair of pivoting tables 112 and 112 'is fixed to both ends so that the first, second, and third cameras 121, 122, and 123 are arranged in a row, and the reference table and the reference table. Screw 114, which is rotatably mounted on the base 111, and a trapezoid-shaped guide 115 formed side by side on the pivoting tables 112 and 112 ', respectively, so that the distance between one surface facing each other is gradually narrowed downward. , 115 'and a presser 116 formed at the center of the nut portion 116a through which the screw 114 is engaged, and both ends slidably engaged with the one surface of the guides 115 and 115'. One support frame 110; The appliance part 100 of the drive motor 130 which provides power for the rotation of the screw 114:
A screw counter 210 for counting the number of revolutions of the screw 114; The second and third cameras 122 and 123 of the second and third cameras 122 and 123 are provided through the moving distance of the pressing table 116 and the length L1 of the pressing table 116 according to the rotation speed of the screw 114 input from the screw counter 210. A photographing angle calculation module 220 programmed to calculate photographing angles θ1 and θ1 'and installed in a computer; A GPS receiver 270 for detecting GPS coordinates; A GPS identification module 230 programmed to receive the GPS coordinates from the GPS receiver 270 and confirm the current position of the aircraft A and installed in the computer; Positioning module 240 is programmed to receive and confirm the altitude (H) of the aircraft (A) while communicating with the air measurement unit 300 is installed on the computer; A photographing distance calculation module 280 programmed to receive photographing angles [theta] 1, [theta] 1 ') and altitude H to calculate photographing distances of the second and third cameras 122 and 123 and installed in the computer; Adjust the zoom lens apparatuses 124 and 124 'to correspond to the shooting distances and altitudes H of the second and third cameras 122 and 123 so that the magnification and the first cameras of the second and third cameras 122 and 123 are adjusted. A zoom lens device adjustment module 290, which is programmed to be processed to match the shooting magnification of 121) and installed in a computer; Received the GPS and the shooting angle (θ1, θ1 ') information of the shooting area from the GPS confirmation module 230 and the shooting angle calculation module 220 is transmitted from the first, second, third camera (121, 122, 123) Input to the photographing image data, and calculates the altitude (H) confirmed by the positioning module 240 and the photographing angles (θ1, θ1 ') confirmed by the photographing angle calculation module 220, the first, second, third camera (21, 22 and 23 confirm the moving distances D and D 'of the aircraft A, which are photographing the same spot, and photographed image data photographed by the first camera 121 and photographing of the first camera 121. Data classification module installed in the computer is programmed to link and store the photographed image data taken by the second and third cameras 122 and 123, respectively, at points separated from each other by moving distances D and D '. Computer unit 200 of 250: and altitude meter 330 that measures the altitude H of the aircraft A, and transmits the measured altitude H to the positioning module 240. The air measurement section (300) comprising: a; A vertical rod 800 vertically fixed to any one of the holders 113 and 113 'with the same distance from both sides with respect to the screw 114; A cylindrical guide 810 fixed to the pressing member 116 to guide the pressing member 116 to move up and down without being shaken while the vertical rod 800 is fitted; A hemispherical ball receiving groove 820 formed at both ends of the pressing table 116; A lubricant 830 applied to the inner circumferential surface of the ball receiving groove 820; Cloud ball 840 accommodated in the ball storage groove 820; A through hole 860 is formed to expose a part of the cloud ball 840 so as to be in point contact with the guides 115 and 115 'without being released from the ball 840. Ball tips 850 screwed at both ends; First and second bolt grooves (BH, NH) formed in a stepped shape with a step on the pressing table (116); A fixing bolt B1 protruding integrally with one side of an outer circumferential surface of the cylindrical guide 810 to be fastened to the first bolt groove BH; A through hole TH formed through the center of the fixing bolt B1 in a longitudinal direction; An anti-loosening bolt B2 fastened to the second bolt groove NH after passing through the through hole TH; It is installed on one side of the guide (115, 115 ') to measure the inclination of the guide (115, 115') in real time, and transmit the result to the photographing angle calculation module 220 to compare the arithmetic calculated value and the measured value to shoot A digital protractor DA for transmitting an actual value to finally confirm the angle [theta] 1; And a position changing unit (POS) between the reference stage 111 and the pivoting stages 112 and 112 ′, the first, second and third cameras 121, 122 and 123 being rotated within a predetermined radius. (POS), the fixed base 900 is fixed to each of the reference stage 111 and the rotating table (112, 112 '), the reference table 111 and the rotating table (112, 112') is controlled by the control module 470 The fixed base 900 is formed in the lower portion of the lower open cylindrical shape in which the lower surface is recessed to form an outer catching jaw 920, and the gap between the outer catching jaw 920 and the bottom. On the inner side, a circular inner catching jaw 930 is formed, and a sun gear 910 is formed on the opposite side of the outer catching jaw 920, and the inner catching jaw 930 is formed at the bottom of the camera base 940. Hanging part (TT) is formed so as to be caught at the same time and the outer locking jaw 920 and move along it, the camera be Switch 940 is provided with a camera feed motor 950 including an encoder 960 is mounted, the rotational axis of the camera feed motor 950 is equipped a planetary gear 970 that is coupled teeth and the sun gear 910,
The rotating tables (112, 112 ') and the reference table 111 has a hemispherical shape, and the reflection shade 1100 coated with aluminum on the inner surface is fixed, respectively, the reflection shade 1100 is divided into two members of the rotating table ( 112 and 112 'and bolts or screws are provided on the fixed guide block (FBL) provided in the reference base 111;
Three sound wave oscillation units 2000 are installed on the inner surface of the reflection shade 1100 at intervals of 120 ° in a radial direction at positions that do not interfere with the first, second and third cameras 121, 122, and 123.
The sound wave oscillation unit 2000 has a case 2100 having a part of a tip open and a locking jaw 2200, and an inlet at a part of the outer circumferential surface of the case 2100 and an outlet formed inside the case 2100. An air inlet 2300 formed to be narrower, an air outlet 2400 formed in a shape opposite to the air inlet 2300 at a point facing the air inlet 2300 in a radial direction, and the inside of the case 2100. A spring 2800 embedded in the casing, the flow bracket 2500 fitted to the front end of the case 2100 and the hooking jaw 2200, and the air suction port 2300 which is a rear end of the flow bracket 2500. Tapered inclined surface (2600) and a sound wave projector (2700) fixed to the front end surface of the flow bracket (2500); and GPS (INS) characterized in that it comprises a Ultra-precision aerial photography using).

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