JP2010085040A - Impact observation system - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To instantly observe a situation of an area including an impact point. <P>SOLUTION: A speed reduction mechanism for lowering a dropping speed of an observation device 20 than a dropping speed of a missile 10, a photographing part for photographing the area including the impact point of the missile 10, and a radio transmission part carrying out radio transmission of photograph data are mounted in the observation device 20 housed in the missile 10 and discharged to the outside before impact. Also, the impact observation system includes a reception display 41 receiving and displaying the photographed data radio-transmitted from the observation device 20. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to a landing observation system for observing a situation of a region including a landing point such as a rocket bullet.

  Conventionally, in order to confirm the impact effect of fired rockets, etc., observations are made by moving a forward observer forward to the landing point after landing, and unmanned observation systems using UAV are known. There exists a thing of the structure disclosed by the nonpatent literature 1 by the name of a reconnaissance machine system.

The new unmanned reconnaissance aircraft system includes helicopter type drones, launch and recovery devices, follow-up devices, control devices, etc., and the drones fly to a reconnaissance point, for example, to reconnaissance. That's it.
Technical Equipment Officer, Accounting Equipment Bureau, 2006 Policy Evaluation Document (Post-project evaluation), New Unmanned Reconnaissance System, [ONLINE], [Search July 14, 2008], Internet <http: //www.mod .go.jp / j / info / hyouka / 18 / jigo / sankou / jigo08_sankou.pdf>

  However, in the new unmanned reconnaissance aircraft system, after landing, the unmanned reconnaissance aircraft is started and the status of the landing point is confirmed, so it takes time to confirm the status, and therefore the next bullet There is a problem that it is difficult to timely determine whether or not shooting is necessary.

  Accordingly, an object of the present invention is to provide an impact observation system that can immediately observe the situation of an area including an impact point.

  In order to achieve the above object, the present invention provides an observation device stored in a flying object and released to the outside before landing so as to make the descent speed of the observation device slower than that of the flying object. It is equipped with a mechanism, an imaging unit for imaging an area including the landing point of the flying object, and a wireless transmission unit for wirelessly transmitting the imaging data, and receiving imaging data wirelessly transmitted from the observation device And a reception display device for displaying.

  According to the present invention, it is possible to immediately observe the situation of the region including the landing point immediately before landing.

The best mode for carrying out the present invention will be described below with reference to the drawings. FIG. 1 is an explanatory diagram showing a schematic configuration of a landing observation system according to an embodiment of the present invention, FIG. 2 is a schematic sectional view taken along line II of the flying object shown in FIG. 1, and FIG. FIG.
The landing observation system A according to an embodiment of the present invention includes a flying object 10, a launching device 30 for launching the flying object 10, and a base station 40.

The launching device 30 can launch a single-shot or multiple-shot flying object 10 mounted thereon.
The flying object 10 includes rockets and missiles capable of obtaining thrust by burning propellant that is a propellant and jetting of compressed gas and flying by itself. In this embodiment, the flying object 10 Two observation devices 20 and 20 are stored in the body 11 as shown in FIG.

  The number of observation devices 20 stored in the flying object 10 is not limited to the two described above, and may be one or three or more. That is, the number of observation devices may be appropriately increased or decreased depending on the performance of the imaging unit described later, the size of the imaging region, and the like.

For example, as shown in FIG. 2, the observation device 20 is arranged symmetrically on both side positions centering on the axis O <b> 1 of the body 11, and for example, an airbag that is inflated by a gas generator (none of which is shown). For example, it is emitted in the radial direction with the axis O1 as the center.
The distance to be emitted is appropriately set depending on the number of observation devices, the performance of the imaging unit mounted on the observation device 20, the size of the imaging region, and the like.

  As shown in FIG. 3, the observation apparatus 20 has a wireless transmission unit 22 disposed in the apparatus main body 21, a reduction mechanism 23 at one end 21a of the apparatus main body 21, and an imaging unit at the other end 21b. 24 is arranged.

  The deceleration mechanism 23 is for making the descending speed of the observation apparatus 20 itself slower than the descending speed of the flying object 10, and in this embodiment, the inflatable value 25 and the observation apparatus 20 are released from the flying object 10. After that, the value 25 is discharged to the outside at a predetermined timing to be expanded, and a value release unit 26 is provided.

  The value 25 is a balloon having a large air resistance that gradually expands after being released, but is not limited to this value, and a jump-out metal fin, a parachute, or the like can be used.

The deceleration mechanisms 23 and 23 of the observation devices 20 and 20 shown in the present embodiment are set so that the observation devices 20 have the same descent speed. Specifically, the same value is used.
In FIG. 1, the value 25 indicated by (C) is in the middle of expansion, and (D) indicates that the expansion has been completed.

The apparatus main body 21 is formed in a cylindrical shape, and an imaging unit 24 for imaging the region a including the landing point P, a wireless transmission unit 22 for wirelessly transmitting imaging data, and an unillustrated inside are formed therein. A power supply is provided.
The imaging unit 24 can use an IR camera or the like that captures still image data or moving image data, and a lens 24 a is disposed at the other end (lower end) of the apparatus main body 21.

  That is, the descending observation device 20 has one end portion 21a of the device main body 21 always directed upward by the value 25, and therefore the other end portion is always directed downward, so that the lens 24a is disposed at the other end portion. The lens 24a always faces the ground when descending. If a wide-angle lens is used as the lens 24a, a wider area can be photographed.

  The wireless transmission unit 22 has a function of wirelessly transmitting image data captured by the image capturing unit 24 to the reception display device 41 described below.

The base station 40 is provided with a reception display device 41.
The reception display device 41 includes a receiving unit that receives shooting data such as still image data and moving image data wirelessly transmitted from the wireless transmission unit 22 of the flying object 10 and a display that displays the received shooting data (both illustrated). No)). In FIG. 1, reference numeral 42 denotes an antenna.

The operation of the landing observation system configured as above will be described.
First, after the flying object 10 is launched from the launching device 30, for example, when the fuel of the rocket motor is terminated at the position indicated by (a), the flying object 10 then flies in a ballistic manner, and a predetermined pre-landing condition indicated by (A). The observation devices 20 and 20 are released at the altitude.

  When the observation devices 20 and 20 are released, the value 25 and 25 arranged on the observation devices 20 and 20 start to expand, and with the expansion, the descent speed of the observation device 20 becomes smaller than the descent speed of the flying object 10, and the observation is performed. The flying object 10 lands before the device 20.

That is, the landing point P of the flying object 10 after landing is included by the imaging unit 24 mounted on the observation apparatus 20... From the landing of the flying object 10 until the observation apparatuses 20, 20 land. A wide area a is imaged, and the captured image data is wirelessly transmitted to the base station 40 by the wireless transmission unit 22.
In the base station 40, the operator determines whether or not to launch the next bullet while viewing the image of the region a including the landing point P of the flying object 10 displayed on the display (not shown).

According to one embodiment of the present invention having the above configuration, the following effects can be obtained.
・ It is possible to reliably observe and grasp the situation in a wide area including the landing point before the landing of the flying object.
Since a plurality of observation devices are released from the flying object, it is possible to photograph a wider area including the landing point or an area around the landing point.
-Since the ballute is used as the deceleration mechanism, the effect of the wind can be reduced after shooting from the flying object, and the area including the landing point can be reliably photographed.

The present invention is not limited to the above-described embodiments, and the following modifications can be made.
In the embodiment described above, an example in which each speed reduction mechanism is set so that each observation device has the same descent speed has been described. However, each speed reduction mechanism is set so that each observation device has a different descent speed. May be. Thereby, the photographing time can be lengthened.

In the above-described embodiment, the configuration in which the imaging unit is fixed to the apparatus main body has been described. However, a configuration in which a depression turning mechanism unit that turns the imaging unit or the entire observation apparatus with a depression angle may be provided. Thereby, since it can image | photograph by scanning a wide range, it becomes easier to confirm the condition of the wider range including an impact point.

A plurality of photographing units arranged to photograph different areas may be provided in one observation device.

It is explanatory drawing which shows schematic structure of the landing observation system which concerns on one Embodiment of this invention. It is a schematic sectional drawing in alignment with the II line | wire shown in FIG. It is a schematic block diagram of an observation apparatus.

Explanation of symbols

DESCRIPTION OF SYMBOLS 10 Flying object 20 Observation apparatus 22 Wireless transmission part 23 Deceleration mechanism 24 Imaging part 41 Reception display apparatus P Landing point

Claims (5)

In the observation device that is stored in the flying object and released to the outside before the landing of the flying object, the deceleration mechanism for making the descent speed of the observation apparatus slower than the falling speed of the flying object, the landing of the flying object An imaging unit for imaging an area including a point, and a wireless transmission unit for wirelessly transmitting imaging data;
A landing observation system comprising: a reception display device that receives and displays radiographed data transmitted from an observation device.   2. The observation apparatus according to claim 1, wherein a radio transmission unit is provided in the apparatus main body, a speed reduction mechanism is provided at one end of the apparatus main body, and an imaging unit is provided at the other end. The landing observation system described.   The landing observation system according to claim 1, wherein a plurality of observation devices are stored in the flying object.   The landing observation system according to any one of claims 1 to 3, wherein each speed reduction mechanism is set so that each observation device has the same descending speed.   The landing observation system according to any one of claims 1 to 4, further comprising a depression turning mechanism that turns the photographing unit or the entire observation apparatus with a depression.

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