KR20030037154A - Wing tip fairing for dummy launcher - Google Patents
Wing tip fairing for dummy launcher Download PDFInfo
- Publication number
- KR20030037154A KR20030037154A KR1020010068261A KR20010068261A KR20030037154A KR 20030037154 A KR20030037154 A KR 20030037154A KR 1020010068261 A KR1020010068261 A KR 1020010068261A KR 20010068261 A KR20010068261 A KR 20010068261A KR 20030037154 A KR20030037154 A KR 20030037154A
- Authority
- KR
- South Korea
- Prior art keywords
- launcher
- dummy
- wing tip
- aircraft
- pairing
- Prior art date
Links
- 230000008878 coupling Effects 0.000 claims abstract description 6
- 238000010168 coupling process Methods 0.000 claims abstract description 6
- 238000005859 coupling reaction Methods 0.000 claims abstract description 6
- 230000001681 protective effect Effects 0.000 claims abstract description 6
- 230000005484 gravity Effects 0.000 claims abstract description 3
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- VRAIHTAYLFXSJJ-UHFFFAOYSA-N alumane Chemical compound [AlH3].[AlH3] VRAIHTAYLFXSJJ-UHFFFAOYSA-N 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims 1
- 238000000034 method Methods 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 abstract description 2
- 239000013585 weight reducing agent Substances 0.000 abstract 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 230000013011 mating Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangement of military equipment, e.g. armaments, armament accessories or military shielding, in aircraft; Adaptations of armament mountings for aircraft
- B64D7/08—Arrangement of rocket launchers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
본 발명은 더미 런처용 윙 팁 페어링에 관한 것으로, 훈련기 또는 전술기의 양쪽 날개 끝에 각각 설치되는 AIM-9 미사일 런처의 더미 런처로서 사용가능한 더미 런처용 윙 팁 페어링에 있어서, 길이가 짧고 소형으로 공력적 형상을 가진 몸체(31)와, 상기 몸체(31)에 형성된 결합홀(38)을 통해 상기 AIM-9 미사일용 런처의 3개의 장착홀(16) 중 적어도 2개의 장착홀에 결합되는 적어도 2개의 장탈착용 볼트(32)와, 상기 항공기 날개(10)측의 전기 커넥터(connector; 12)를 보호하기 위해 상기 전기 커넥터(12)에 끼워지는 보호커버(34), 및 플러터(flutter) 발생시 무게 중심을 변경할 수 있도록 밸러스트(ballast)를 추가 설치할 수 있는 내부 공간(36)을 포함하는 것을 특징으로 한다.The present invention relates to a wing tip pairing for a dummy launcher, a short length and compact aerodynamic in the wing tip pairing for a dummy launcher which can be used as a dummy launcher of the AIM-9 missile launcher respectively installed at the ends of both wings of a trainer or a tactical machine. At least two coupled to at least two mounting holes of the three mounting holes 16 of the AIM-9 missile launcher through a body 31 having a shape and a coupling hole 38 formed in the body 31. Center of gravity when the mounting bolt 32, the protective cover 34 fitted to the electrical connector 12 to protect the electrical connector (12) on the side of the aircraft wing 10, and flutter occurs It is characterized in that it comprises an internal space 36 that can be installed additional ballast (ballast) to change.
이에 의해 항공기의 중량 절감 효과를 얻을 수 있고, 항공기 유지보수에 경제적이며 항공기 유지관리와 정비 등의 작업능률을 크게 높일 수 있다는 이점이 있다.As a result, the weight reduction effect of the aircraft can be obtained, economical in maintenance of the aircraft, and the operation efficiency such as maintenance and maintenance of the aircraft can be greatly improved.
Description
본 발명은 더미 런처(dummy launcher)용 윙 팁 페어링(wing tip fairing)에 관한 것으로, 보다 상세하게는 훈련기와 전술기의 날개 끝에 장착되는 AIM-9 미사일 런처의 더미 장치로서 AIM-9 미사일 런처를 대신하여 훈련용으로 사용가능한 더미 런처용 윙 팁 페어링에 관한 것이다.The present invention relates to wing tip fairing for a dummy launcher, and more particularly, a dummy device of an AIM-9 missile launcher mounted on the wing tip of a trainer and a tactical fighter instead of an AIM-9 missile launcher. The invention relates to a wing tip pairing for a dummy launcher that can be used for training.
일반적으로 F-16 전투기는 미사일을 장착하지 않는 경우에도 양쪽 144파운드(lbs)의 AIM-9 미사일 런처를 장착한 상태에서 비행을 실시한다.Normally, an F-16 fighter jet will fly with both 144 pound (lbs) AIM-9 missile launcher, even without a missile.
또한, 일반적으로 훈련기와 전술기에서 윙 박스(wing box)는 훈련기와 전술기에 관계없이 같은 종류를 사용한다.Also, in general, wing boxes in the trainer and the tactical weapon use the same type regardless of the trainer and the tactical weapon.
따라서, 훈련기의 경우 미사일을 장착하지 않는 경우에도 무거운 런처를 장착해야 한다.Therefore, even in the case of a train without a missile, a heavy launcher must be mounted.
이러한 측면에서, 훈련기에 있어서 무거운 런처를 장착하는 대신에 가볍고 저렴하면서도 공력적 효과를 가지며 장탈착 가능한 더미 런처를 개발해야 할 필요성이 있다.In this respect, there is a need to develop a light, inexpensive, aerodynamic and removable removable launcher instead of mounting a heavy launcher in the trainer.
본 발명은 상술한 필요성에 의해 도출된 것으로, 본 발명의 목적은 훈련기의 날개 끝에 무거운 런처를 장착할 필요없이 가볍고 저렴하면서도 공력적 효과를 유지할 수 있으며 장탈착 가능한 더미 런처용 윙 팁 페어링을 제공하는 데 있다.SUMMARY OF THE INVENTION The present invention is derived from the above-mentioned necessity, and an object of the present invention is to provide a wing tip pairing for a dummy launcher that is light and inexpensive while maintaining an aerodynamic effect, without having to mount a heavy launcher on the wing tip of the trainer. There is.
도 1은 종래의 항공기에 장착되어 있는 윙 팁 페어링을 개략적으로 나타낸 사시도,1 is a perspective view schematically showing a wing tip fairing mounted on a conventional aircraft,
도 2는 본 발명의 더미 런처용 윙 팁 페어링을 개략적으로 나타낸 사시도,Figure 2 is a perspective view schematically showing a wing tip pairing for the dummy launcher of the present invention,
도 3은 본 발명의 더미 런처용 윙 팁 페어링을 개략적으로 나타낸 평면도,3 is a plan view schematically showing the wing tip pairing for the dummy launcher of the present invention,
도 4a는 도 3의 A-A선 또는 B-B선을 따라 얻은 단면을 나타낸 단면도,4A is a cross-sectional view showing a cross section taken along line A-A or line B-B of FIG. 3;
도 4b는 도 3의 C-C선을 따라 얻은 단면을 나타낸 단면도.4B is a cross-sectional view taken along the line C-C in FIG. 3;
* 도면의 주요 부분에 대한 부호의 설명 *Explanation of symbols on the main parts of the drawings
10 ... 항공기 날개10 ... Aircraft Wings
12 ... 전기 커넥터12 ... electrical connectors
14 ... 윙 박스(wing box)14 ... wing box
30 ... 더미 런처30 ... Dummy Launcher
31 ... 몸체31 ... body
32 ... 볼트32 ... bolt
34 ... 보호커버34 ... protective cover
36 ... 내부공간36 ... Internal space
38 ... 결합홀38 ... mating hole
상술한 목적을 달성하기 위해, 본 발명의 더미 런처용 윙 팁 페어링은, 훈련기 또는 전술기의 양쪽 날개 끝에 각각 설치되는 AIM-9 미사일 런처의 더미 런처로 사용가능한 더미 런처용 윙 팁 페어링에 있어서, 길이가 짧고 소형으로 공력적 형상을 가진 몸체와, 상기 몸체에 형성된 결합홀을 통해 상기 AIM-9 미사일용 런처의 3개의 장착홀 중 적어도 2개의 장착홀에 결합되는 적어도 2개의 장탈착용 볼트와, 상기 항공기 날개측의 전기 커넥터(connector)를 보호하기 위해 상기 전기 커넥터에 끼워지는 보호커버, 및 플러터(flutter) 발생시 무게 중심을 변경할 수 있도록 밸러스트(ballast)를 추가 설치할 수 있는 내부 공간을 포함하는 것을 특징으로 한다.In order to achieve the above-mentioned object, the wing tip pairing for the dummy launcher of the present invention is a length in the wing tip pairing for the dummy launcher which can be used as a dummy launcher of the AIM-9 missile launcher respectively installed at the ends of both wings of the trainer or the tactical machine. A short and compact body having an aerodynamic shape, at least two mounting bolts coupled to at least two mounting holes of the three mounting holes of the AIM-9 missile launcher through a coupling hole formed in the body, and A protective cover fitted to the electrical connector to protect the electrical connector on the wing of the aircraft, and an inner space for additionally installing a ballast so as to change the center of gravity when a flutter occurs. It is done.
또한 상술한 본 발명에 있어서, 상기 더미 런처용 윙 팁 페어링은 알루미늄(aluminum) 또는 알루미늄 합금으로 제작되고, 각 더미 런처의 무게가 약 17.5 파운드(lbs)인 것을 특징으로 한다.In addition, in the present invention described above, the wing tip fairing for the dummy launcher is made of aluminum (aluminum) or aluminum alloy, characterized in that the weight of each dummy launcher is about 17.5 pounds (lbs).
이하 본 발명의 바람직한 실시예를 도면을 참조하여 상세하게 설명한다.Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the drawings.
도 2는 본 발명의 더미 런처용 윙 팁 페어링을 개략적으로 나타낸 사시도이다. 도 2를 참조하면, 본 발명의 실시예에 따른 더미 런처(30)용 윙 팁 페어링은 종래의 AIM-9 미사일 런처 대신에 항공기 날개(10)의 끝에 장착된다. 몸체는 알루미늄(aluminum)으로 종래에 비해 비교적 길이가 짧고 소형으로 공력적 형상을 갖도록 제작된다. 무게는 약 17.5 파운드(lbs)가 된다. 또한 외형은 종래의 AIM-9 미사일 런처의 형태와 유사한 공력적 형상으로 형성된다. 즉, 비행중에 더미 런처에 가해지는 힘과 공기흐름에 대하여 적합하도록 형성된다. 또, 길이는 종래의 AIM-9 미사일 런처의 약 1/2 내지 약 3/5의 길이를 갖는다.Figure 2 is a perspective view schematically showing a wing tip fairing for the dummy launcher of the present invention. 2, the wing tip fairing for the dummy launcher 30 according to the embodiment of the present invention is mounted at the end of the aircraft wing 10 instead of the conventional AIM-9 missile launcher. The body is made of aluminum, which is relatively short in length and compact, and has an aerodynamic shape. It weighs about 17.5 pounds (lbs). The contour is also shaped into an aerodynamic shape similar to that of a conventional AIM-9 missile launcher. That is, it is formed to be suitable for the force and air flow applied to the dummy launcher during the flight. The length also has a length of about 1/2 to about 3/5 of a conventional AIM-9 missile launcher.
도 3은 도 2의 더미 런처용 윙 팁 페어링을 개략적으로 나타낸 평면도이고, 도 4a는 도 3의 A-A선 또는 B-B선을 따라 얻은 단면을 나타낸 단면도이며, 도 4b는 도 3의 C-C선을 따라 얻은 단면을 나타낸 단면도이다.3 is a plan view schematically illustrating the wing tip pairing for the dummy launcher of FIG. 2, FIG. 4A is a cross-sectional view taken along line AA or BB of FIG. 3, and FIG. 4B is taken along line CC of FIG. 3. A cross-sectional view showing a cross section.
도 3을 참조하면, 본 발명의 실시예에 따른 더미 런처용 윙 팁 페어링은 항공기 날개(10) 끝에 장탈착용 볼트에 의해 고정된다.Referring to FIG. 3, the wing tip fairing for the dummy launcher according to the embodiment of the present invention is fixed to the end of the aircraft wing 10 by a mounting bolt.
구체적으로, 본 발명의 더미 런처(30)는 도 4a에 도시된 바와 같이 항공기 날개(10) 끝에 장탈착용 볼트(32)에 의해 고정된다. 이때 몸체(31)는 장탈착용 볼트(32)가 관통하도록 형성된 적어도 2개의 결합홀(38)을 포함한다. 결합홀(38)은 AIM-9 미사일 런처의 장착홀(16)과 대응하는 위치에 형성된다. 따라서 항공기 날개 끝에 이미 형성되어 있는 종래의 결합구조를 그대로 사용할 수 있다.Specifically, the dummy launcher 30 of the present invention is fixed by the mounting bolts 32 on the end of the aircraft wing 10 as shown in Figure 4a. In this case, the body 31 includes at least two coupling holes 38 formed to penetrate the mounting bolts 32. The coupling hole 38 is formed at a position corresponding to the mounting hole 16 of the AIM-9 missile launcher. Therefore, the conventional coupling structure already formed on the tip of the aircraft wing can be used as it is.
또한, 본 발명의 더미 런처(30)는 도 4b에 도시된 바와 같이, 보호커버(34)와 내부공간(36)을 포함한다. 보호커버(34)는 항공기 날개(10)의 끝에 돌출된 전기 커넥터(12)를 보호하기 위해 전기 커넥터(12)에 끼워져 전기 커넥터(12)를 덮도록설치된다. 또한, 내부공간(36)은 모래 주머니 등의 밸러스트(ballast)를 추가할 수 있도록 형성된다. 내부공간(36)에는 밸러스트를 추가로 설치하는 경우를 위해 미리 브라켓 부재(bracket member) 등으로 격벽을 형성할 수 있다. 하지만, 별도의 격벽을 형성하지 않는 경우에는 추가로 설치되는 밸러스트를 리벳, 볼트, 스크류 등의 고정부재로 고정할 수 있다.In addition, the dummy launcher 30 of the present invention, as shown in Figure 4b, includes a protective cover 34 and the inner space 36. The protective cover 34 is installed to cover the electrical connector 12 by being fitted to the electrical connector 12 to protect the electrical connector 12 protruding from the end of the aircraft wing 10. In addition, the inner space 36 is formed to add a ballast (ballast) such as sandbags. In the interior space 36, a partition wall may be formed of a bracket member or the like in advance to install a ballast. However, in the case of not forming a separate bulkhead, the ballast additionally installed may be fixed by fixing members such as rivets, bolts, and screws.
이상에서 설명한 바와 같이, 본 발명에 의하면, F-16 등의 AIM-9 미사일 런처를 윙 팁에 장착하는 항공기의 훈련용으로 사용할 수 있는 더미 런처용 윙 팁 페어링을 제공함으로써, 종래의 항공기 날개 끝에 장착되던 2개의 양쪽 런처에서의 144파운드(lbs)와 2개의 양쪽 윙팁 페어링에서의 35 파운드에 대하여 약 100 파운드 이상의 중량 절감 효과를 얻을 수 있다는 이점이 있다.As described above, according to the present invention, by providing a wing tip pairing for the dummy launcher which can be used for training of an aircraft equipped with an AIM-9 missile launcher such as an F-16 to the wing tip, There is an advantage of over 100 pounds of weight savings for 144 pounds (lbs) in both two launcher and 35 pounds in two both wingtip pairings.
또한, 알루미늄 또는 알루미늄 합금으로 제작하여 가볍고 저렴하며 취급이 용이하기 때문에 항공기 유지보수에 경제적이고 항공기 유지관리와 정비 등의 작업능률을 크게 높일 수 있다는 이점이 있다.In addition, since it is made of aluminum or aluminum alloy, it is light, inexpensive, and easy to handle, so it is economical to maintain the aircraft and greatly increase work efficiency such as maintenance and maintenance of the aircraft.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020010068261A KR20030037154A (en) | 2001-11-02 | 2001-11-02 | Wing tip fairing for dummy launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020010068261A KR20030037154A (en) | 2001-11-02 | 2001-11-02 | Wing tip fairing for dummy launcher |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| KR20030037154A true KR20030037154A (en) | 2003-05-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR1020010068261A KR20030037154A (en) | 2001-11-02 | 2001-11-02 | Wing tip fairing for dummy launcher |
Country Status (1)
| Country | Link |
|---|---|
| KR (1) | KR20030037154A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4356984A (en) * | 1980-02-25 | 1982-11-02 | Northrop Corporation | Tow body system-target drone |
| US4711151A (en) * | 1984-10-30 | 1987-12-08 | Frazer-Nash Ltd. | Missile launcher |
| US4736669A (en) * | 1987-02-20 | 1988-04-12 | Varo, Inc. | Aircraft missile launcher mounting apparatus |
| US4745840A (en) * | 1987-02-24 | 1988-05-24 | Varo, Inc. | Modified missile launcher |
-
2001
- 2001-11-02 KR KR1020010068261A patent/KR20030037154A/en not_active Application Discontinuation
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4356984A (en) * | 1980-02-25 | 1982-11-02 | Northrop Corporation | Tow body system-target drone |
| US4711151A (en) * | 1984-10-30 | 1987-12-08 | Frazer-Nash Ltd. | Missile launcher |
| US4736669A (en) * | 1987-02-20 | 1988-04-12 | Varo, Inc. | Aircraft missile launcher mounting apparatus |
| US4745840A (en) * | 1987-02-24 | 1988-05-24 | Varo, Inc. | Modified missile launcher |
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