KR100483953B1 - Aircraft Launcher Attached on the Top of a Ground Vehicle - Google Patents
Aircraft Launcher Attached on the Top of a Ground Vehicle Download PDFInfo
- Publication number
- KR100483953B1 KR100483953B1 KR10-2001-0081375A KR20010081375A KR100483953B1 KR 100483953 B1 KR100483953 B1 KR 100483953B1 KR 20010081375 A KR20010081375 A KR 20010081375A KR 100483953 B1 KR100483953 B1 KR 100483953B1
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- KR
- South Korea
- Prior art keywords
- aircraft
- take
- ground
- saddle
- mounting saddle
- Prior art date
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- 230000010355 oscillation Effects 0.000 claims 3
- 238000000926 separation method Methods 0.000 abstract description 2
- 208000010201 Exanthema Diseases 0.000 description 2
- 201000005884 exanthem Diseases 0.000 description 2
- 206010037844 rash Diseases 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
- B60P3/06—Vehicles adapted to transport, to carry or to comprise special loads or objects for carrying vehicles
- B60P3/11—Vehicles adapted to transport, to carry or to comprise special loads or objects for carrying vehicles for carrying aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60Y—INDEXING SCHEME RELATING TO ASPECTS CROSS-CUTTING VEHICLE TECHNOLOGY
- B60Y2200/00—Type of vehicle
- B60Y2200/10—Road Vehicles
- B60Y2200/14—Trucks; Load vehicles, Busses
- B60Y2200/145—Haulage vehicles, trailing trucks
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- Public Health (AREA)
- Transportation (AREA)
- Mechanical Control Devices (AREA)
- Handcart (AREA)
Abstract
본 발명은 항공기의 이륙에 필요한 적합한 활주로가 없는 곳에서 지상차량 또는 선박에 설치하여 항공기를 이륙 발진(launch)시킬 수 있는 발명으로서, 지상차량 또는 선박이 항공기의 이륙에 필요한 지상활주 속도로 달리면 본 발명의 항공기 거치 안장에 설치된 항공기는 이륙에 필요한 양력을 얻어서 4절 레버 크랭크 기구의 조합으로 구성된 지지대가 위로 떠오르면서 항공기를 체결하고 있던 잠금 고리를 벗기고 항공기를 이륙 발진시키도록 해주는 장치에 관한 것이다. The present invention is an invention that can be launched on the ground vehicle or ship in the place where there is no suitable runway required for takeoff of the aircraft, launching the aircraft take off (launch), if the ground vehicle or the ship is running at the ground running speed required for takeoff of the aircraft The aircraft installed in the aircraft mounting saddle of the present invention relates to a device for obtaining the lift necessary for take-off, to lift the support ring consisting of a combination of the four lever lever crank mechanism to lift off the lock ring that was fastening the aircraft and take off the aircraft.
본 발명은 2조의 4절 레버 크랭크 장치로 구성된 지지대와 그 지지대 위에 부분적인 피칭 운동을 할 수 있도록 핀과 베어링으로 연결된 항공기 거치 안장 및 항공기를 거치안장에 확보했다가 분리시켜주는 잠금/분리 장치로 이루어진다.The present invention provides a support consisting of two sets of four lever crank devices and an aircraft mounting saddle connected with pins and bearings to secure a partial pitching movement on the support and a lock / separation device that secures and separates the aircraft from the mounting saddle. Is done.
Description
본 발명은 평탄한 활주로가 없는 곳에서 이륙을 하고자 하는 항공기 또는 무인항공기나 활공기에서와 같이 착륙바퀴가 없거나 불완전한 항공기의 원활한 이륙을 위해서 지상 운송체(Ground Vehicle, 차량 및 선박)를 이용하여 항공기를 이륙 발진시킬 수 있는 것으로 The present invention uses a ground vehicle (vehicle and a ship) for smooth takeoff of an aircraft that intends to take off in a place without a flat runway or an unmanned landing wheel or an incomplete aircraft such as an unmanned aerial vehicle or a glider. I can make a rash
지상운송체가 항공기의 지상활주 부분을 대신해주면 본 발명을 통하여 항공기가 이륙에 필요한 이륙회전(rotation), 부양(lift-off) 및 발진(launch)을 하도록 해주는 지상운반체에 장착하는 항공기 이륙 발진장치에 관한 것이다.If the ground carrier replaces the ground slide portion of the aircraft, the aircraft take-off oscillator mounted on the ground carrier to allow the aircraft to take off the rotation, lift-off and launch required for takeoff through the present invention It is about.
종래의 항공기의 경우 평탄한 활주로가 확보되지 못하거나 활주로가 손상되었을 경우 자체적인 착륙장치로 이륙활주가 곤란하여 이륙이 불가능하며, 착륙장치가 없는 무인항공기의 경우 공압 또는 전동에 의한 발사대를 사용하기 때문에 별도의 긴 발사대 레일과 부수동력장치 등을 가지고 다니거나 설치해야 하는 불편함이 있었다In the case of conventional aircraft, if the runway is not secured or the runway is damaged, it is difficult to take off due to its own landing device, which is difficult to take off.In the case of an unmanned aerial vehicle without a landing device, a pneumatic or electric launch pad is used. It was inconvenient to carry or install a separate long launch pad rail and auxiliary power unit.
본 발명은 지상 운반체 위에 간단하게 고정된 이륙 발진장치에 항공기를 장착하고 항공기의 이륙에 필요한 이륙회전(rotation)과 부상(lift-off) 기동을 할 수 있도록 해주는 기구물과 항공기를 거치안장에 고정하고 발진시 분리시켜주는 잠금/분리 장치를 써서 활주로가 없는 곳에서 항공기를 편리하게 이륙시킬 수 있도록 하는 것이다.The present invention is to mount the aircraft to the takeoff oscillator simply fixed on the ground carrier and to fix the aircraft to the mounting saddle and the mechanism to enable the take-off rotation (lift-off) maneuver required for takeoff of the aircraft The lock / separation device allows the aircraft to take off conveniently without a runway.
본 발명은 지상 운송체에 고정되는 밑판과,The present invention is a base plate fixed to the ground vehicle,
밑판의 전방에 설치된 연결판과 상측의 거치안장의 사방에서 4절 레버 크랭크로 연결하는 크랭크장치와,A crank device for connecting with four lever lever cranks from all sides of the connecting plate installed at the front of the base plate and the upper mounting saddle;
거치안장의 하측에 설치되어 항공기의 걸쇠고리 핀을 고정/해체시키는 잠금장치로 구성됨을 특징으로 하는 것이다.It is installed on the lower side of the mounting saddle is characterized in that consisting of a locking device for fixing / releasing the latch pin of the aircraft.
본 발명은 2조의 4절 레버 크랭크 기구로 구성된 크랭크장치(30)와,The present invention is a crank device 30 composed of two sets of four lever crank mechanism,
크랭크장치(30)의 위에 부분적인 피칭 운동을 할 수 있도록 베어링으로 연결되는 베어링 고정핀(14)으로 연결된 거치안장(4) 및 항공기(8)를 지상 운송체(13)에 고정시키고 있다가 이륙시키는 경우에 잠금상태를 해제하는 잠금장치(20)로 구성된다.The saddle 4 and the aircraft 8 which are connected to the bearing fixing pin 14 connected to the bearing to the partial cranking movement on the crank device 30 are fixed to the ground vehicle 13 and then taken off. If the lock is configured to lock the device 20 to release the state.
도 1은 본 발명의 전체적인 모습을 보이는 사시도에 관한 것으로, 지상 운반체(13)에 연결되는 밑판(1)의 전방으로 밑판(1)의 일부분을 하측에서부터 감싸면서 상측으로 돌출되는 연결판(2)이 설치된다.1 is a perspective view showing the overall appearance of the present invention, the connecting plate (2) protruding upward while wrapping a portion of the base plate (1) from the lower side in front of the base plate (1) connected to the ground carrier (13) This is installed.
상기 연결판(2)의 사방에서는 4절 레버 크랭크(3)가 상측으로 돌출되어 크랭크작용이 이루어지도록 하는 크랭크장치(30)를 구성한다.Four sides of the connecting plate (2) constitutes a crank device (30) so that the four-section lever crank (3) protrudes upward to achieve the crank action.
크랭크장치(30)의 상측으로 항공기(8)가 올려지는 거치안장(4)의 양측으로 중앙에서 베어링이 삽입되어 운동이 가능한 베어링 고정핀(14)에 의하여 연결되는 측면봉(5)이 형성되며, 측면봉(5)의 양측에서 4절 레버 크랭크(3)와 사방에서 연결되는 하측봉(6)이 거치안장(4)의 전방과 후방에 설치된다.Side rods 5 are formed on both sides of the mounting saddle 4 on which the aircraft 8 is lifted to the upper side of the crank device 30 and connected by bearing fixing pins 14 capable of movement by inserting bearings in the center thereof. On both sides of the side bar (5), the four-bar lever crank (3) and the lower bar (6) connected in all directions are installed at the front and rear of the mounting saddle (4).
상기 밑판(1)의 후방에는 거치안장(4)이 정지위치시에 올려지는 받침판(15)이 설치된다.At the rear of the base plate 1, a supporting plate 15 is installed on which the mounting saddle 4 is raised at the stop position.
또한 거치안장(4)의 하측에는 항공기(8)에 설치된 걸쇠고리 핀(12)이 위치하여 잠금고리(11)가 핀(10)에 회전 가능하게 결합하고, 잠금고리(11)를 후방으로 돌출시킨 이탈 레버암(9)의 후방에서 당김줄(7)이 연결되어 밑판(1)에 연결되는 잠금장치(20)를 설치하는 것이다.In addition, the lower side of the mounting saddle (4) is provided with a latch ring pin 12 installed in the aircraft (8) lock ring 11 is rotatably coupled to the pin 10, protruding the lock ring 11 to the rear The pulling line 7 is connected to the rear of the release lever arm 9 to install the locking device 20 connected to the base plate (1).
이러한 구성으로 이루어진 본 발명은 차량이나 선박과 같은 지상 운송체(13)의 상측으로 밑판(1)이 연결되어 있고, 잠금장치(20)에 의하여 항공기(8)의 걸쇠고리 핀(12)이 고정된 상태를 유지하면서 거치안장(4)이 받침판(15)에 올려지는 동시에 항공기(8)가 거치된 상태를 유지하게 된다.In the present invention having such a configuration, the bottom plate 1 is connected to the upper side of the ground vehicle 13 such as a vehicle or a ship, and the latch ring 12 of the aircraft 8 is fixed by the locking device 20. While maintaining the mounted state, the mounting saddle 4 is placed on the support plate 15 while maintaining the mounted state of the aircraft 8.
이와 같이 항공기(8)가 지상 운송체(13)의 상측에 설치된 상태에서 항공기(8)를 발진시키기 위해서는 지상 운송체(13)가 전진하면서 양력을 받게 된다.As described above, in order to launch the aircraft 8 in a state where the aircraft 8 is installed above the ground vehicle 13, the ground vehicle 13 is lifted while moving forward.
항공기(8)가 양력을 받아 위로 떠오르게 되면 크랭크장치(30)는 4절 레버 크랭크(3)에 의하여 밑판(1)의 연결판(2)과 거치안장(4)의 외부 구조물인 측면봉(5)과 하측봉(6)에 연결되어 있어서 항공기(8)의 자세가 수평을 유지할 수 있게 해주는 역할을 한다.When the aircraft 8 is lifted up and lifted up, the crank device 30 is a side rod 5 which is an outer structure of the connecting plate 2 of the base plate 1 and the mounting saddle 4 by means of the lever crank 3. ) And the lower rod (6) serves to keep the attitude of the aircraft (8) level.
삭제delete
거치안장(4)은 베어링 고정핀(14)을 통하여 측면봉(6)과 연결되어 있고, 하측봉(6)과의 사이에 주어지는 간극만큼의 세로운동(피칭)을 할 수 있는 여유를 가지도록 설치하여 항공기(8)가 이륙을 위한 회전운동(rotation)을 할 수 있도록 한다. Mounting saddle (4) is connected to the side rod (6) through the bearing fixing pin (14), so as to have room for vertical movement (pitching) as much as a gap given between the lower rod (6) To allow the aircraft 8 to rotate for takeoff.
받침판(15)은 지상 운송체(13)가 정지상태 또는 속도가 저속일 때 항공기(8)를 거치한 거치안장(4)과 크랭크장치(30)가 올려지는 받침대로서 그 상면은 완충고무로 되어 있다.The support plate 15 is a stand on which the saddle 4 and the crank device 30 mounted on the aircraft 8 are mounted when the ground vehicle 13 is at a stopped state or at a low speed. have.
지상 운송체(13)의 속도가 항공기의 이륙속도에 이르게 되면 항공기(8)의 이륙 회전기동(rotation)에 따라 항공기(8)에 양력이 크게 발생하게 되고 이에 따라 크랭크장치(30)와 거치안장(4)이 항공기(8)와 함께 위로 들려 올라가는 형태가 된다.When the speed of the ground vehicle 13 reaches the take-off speed of the aircraft, lift force is greatly generated in the aircraft 8 according to the take-off rotation of the aircraft 8, and accordingly, the crank device 30 and the saddle mounted thereon. (4) is lifted up with the aircraft (8).
이때 거치안장(4)의 하부 중앙에 설치된 잠금장치(20)가 당김줄(7)에 의하여 당겨지면 잠금장치(20)의 이탈 레버암(9)이 하측으로 당겨져서 항공기(8)는 거치안장(4)에서 이탈되어 이륙발진을 하게 된다.At this time, when the locking device 20 installed in the lower center of the mounting saddle 4 is pulled by the pull string 7, the release lever arm 9 of the locking device 20 is pulled downward so that the aircraft 8 is mounted on the mounting saddle. Departure from (4) will take off rash.
즉, 거치안장(4)의 하부 중앙에 설치된 걸쇠고리 핀(12)이 평상시에는 잠금고리(11)에 걸려서 항공기(8)를 고정(잠금)시켰다가 이륙을 할 때는 이탈 레버암(9)이 당김줄(7)에 의하여 당겨짐으로써 잠금고리(11)가 핀(10)을 축으로 회전되어 걸쇠고리 핀(12)과 분리되므로 항공기(8)를 이탈시켜 양력으로 이륙되도록 하는 것이다.That is, the latch ring 12 installed in the lower center of the mounting saddle (4) is normally caught in the lock ring (11) to lock (lock) the aircraft (8) when the takeoff lever arm (9) when taking off The pull ring 7 is pulled by the locking ring 11 is rotated about the pin 10 is separated from the latch ring pin 12 so that the aircraft 8 is to be taken off by lifting force.
본 발명은 활주로가 없거나 손상된 곳에서 지상 운송체의 이동으로 크랭크장치와 잠금장치를 통하여 유인 또는 무인 항공기를 안전하게 이륙시킬 수 있는 것이다.The present invention can safely take off a manned or unmanned aerial vehicle through the crank device and the lock by the movement of the ground vehicle in the absence or damaged runway.
도 1 은 본 발명의 외형 사시도1 is an external perspective view of the present invention
도 2 는 본 발명의 작동상태에 대한 정면도Figure 2 is a front view of the operating state of the present invention
도 3 은 본 발명의 잠금장치에 대한 작동상태도Figure 3 is an operating state diagram for the locking device of the present invention
[도면의 주요 부분에 대한 부호의 설명][Description of Symbols for Main Parts of Drawing]
1 : 밑판 2 : 연결판1: base plate 2: connecting plate
3 : 4절 레버 크랭크 4 : 거치안장3: Section 4 lever crank 4: Mounting saddle
5 : 측면봉 6 : 하측봉5: side bar 6: lower side bar
7 : 당김줄 8 : 항공기7: pull string 8: aircraft
9 : 이탈 레버암 10 : 핀9: release lever arm 10: pin
11 : 잠금고리 12 : 걸쇠고리 핀11: locking ring 12: clasp pin
13 : 지상 운송체 20 : 잠금장치13: ground vehicle 20: locking device
30 : 크랭크장치30: crank device
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR10-2001-0081375A KR100483953B1 (en) | 2001-12-19 | 2001-12-19 | Aircraft Launcher Attached on the Top of a Ground Vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR10-2001-0081375A KR100483953B1 (en) | 2001-12-19 | 2001-12-19 | Aircraft Launcher Attached on the Top of a Ground Vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| KR20030050841A KR20030050841A (en) | 2003-06-25 |
| KR100483953B1 true KR100483953B1 (en) | 2005-04-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR10-2001-0081375A KR100483953B1 (en) | 2001-12-19 | 2001-12-19 | Aircraft Launcher Attached on the Top of a Ground Vehicle |
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| Country | Link |
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| KR (1) | KR100483953B1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100832898B1 (en) * | 2007-07-31 | 2008-05-28 | 이재빈 | Model plane safety carrier and placer |
| KR101872276B1 (en) * | 2016-12-02 | 2018-06-29 | 김성남 | A jet assisted take-off for the unmanned vehicle |
| CN110667874B (en) * | 2019-11-04 | 2024-06-14 | 中国科学院工程热物理研究所 | Detachable unmanned aerial vehicle bearing structure, put and fly device and put and fly recovery system |
| US11787561B2 (en) * | 2021-04-20 | 2023-10-17 | Insitu, Inc. | Adapter assemblies for aircraft and launchers for deploying aircraft |
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| US4678143A (en) * | 1982-12-17 | 1987-07-07 | Frazer-Nash Ltd. | Launcher for remotely piloted aircraft |
| US5626310A (en) * | 1994-11-21 | 1997-05-06 | Kelly Space & Technology, Inc. | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
| US6145789A (en) * | 1998-03-23 | 2000-11-14 | Gray Matter Holdings, Llc | Remotely controlled aircraft |
-
2001
- 2001-12-19 KR KR10-2001-0081375A patent/KR100483953B1/en active IP Right Grant
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3948467A (en) * | 1974-01-19 | 1976-04-06 | Dornier Gmbh | Device for position stabilization |
| US4678143A (en) * | 1982-12-17 | 1987-07-07 | Frazer-Nash Ltd. | Launcher for remotely piloted aircraft |
| JPS60121197A (en) * | 1983-11-07 | 1985-06-28 | ジイ・キユ・デフエンス・イクイプマント・リミテツド | Load expanding device |
| US5626310A (en) * | 1994-11-21 | 1997-05-06 | Kelly Space & Technology, Inc. | Space launch vehicles configured as gliders and towed to launch altitude by conventional aircraft |
| US6145789A (en) * | 1998-03-23 | 2000-11-14 | Gray Matter Holdings, Llc | Remotely controlled aircraft |
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