IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0031816
(2002-04-05)
|
우선권정보 |
CH-200001094 (2000-05-31) |
국제출원번호 |
PCT/CH01/00248
(2001-04-19)
|
국제공개번호 |
WO01/92104
(2001-12-06)
|
발명자
/ 주소 |
- To, Frederick E.
- Kammer, Res
|
출원인 / 주소 |
|
대리인 / 주소 |
Jenkens & Gilchrist, P.C.
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
4 |
초록
▼
The additional device according to the invention for floats for seaplanes and floatplanes comprises four airtight bladders (10) to which compressed air can be applied, and which extend along the float and rest on side surfaces (11) of the float, which essentially consists of a box (1). The bladders
The additional device according to the invention for floats for seaplanes and floatplanes comprises four airtight bladders (10) to which compressed air can be applied, and which extend along the float and rest on side surfaces (11) of the float, which essentially consists of a box (1). The bladders (10) are composed of a flexible material with little expansion capability or an elastomer material, and are entirely covered with an elastic and watertight textile skin (9). In the state when compressed air is applied, the edges of the box (1), that is to say the side edges (8) and the keel edge (7), are smoothed. Thus, as soon as the aircraft has become airborne, the drag coefficient cDof the float can be considerably reduced. The compressed air is released for the aircraft to land on and take off from water, so that the edges (7, 8) can produce their effect for directional stability (keel edge (7)) and in order to prevent the Coanda effect (side edges 8)).
대표청구항
▼
The additional device according to the invention for floats for seaplanes and floatplanes comprises four airtight bladders (10) to which compressed air can be applied, and which extend along the float and rest on side surfaces (11) of the float, which essentially consists of a box (1). The bladders
The additional device according to the invention for floats for seaplanes and floatplanes comprises four airtight bladders (10) to which compressed air can be applied, and which extend along the float and rest on side surfaces (11) of the float, which essentially consists of a box (1). The bladders (10) are composed of a flexible material with little expansion capability or an elastomer material, and are entirely covered with an elastic and watertight textile skin (9). In the state when compressed air is applied, the edges of the box (1), that is to say the side edges (8) and the keel edge (7), are smoothed. Thus, as soon as the aircraft has become airborne, the drag coefficient cDof the float can be considerably reduced. The compressed air is released for the aircraft to land on and take off from water, so that the edges (7, 8) can produce their effect for directional stability (keel edge (7)) and in order to prevent the Coanda effect (side edges 8)). xis of rotation of the tube is in a horizontal position and the protruding section protruding from the tube is in an upper most position on the tube, the said concave forward facing surface area faces a direction, which direction is a direction of travel that the missile would travel in when the missile is launched, if the missile was not affected by the said missile attachment, which said direction of travel is a forward direction of travel. 7. The missile of claim 6 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 8. The missile of claim 6 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 9. The missile of claim 8 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 10. The missile of claim 1 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 11. The missile of claim 1 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 12. The missile of claim 11 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 13. The missile of claim 1 wherein the said tube is in the form of a cylindrical tube. 14. A missile with a missile attachment which said missile attachment consists of a tube with a protruding section, which said protruding section protrudes outward from the tube, and which said protruding section has a forward facing surface area, with the said tube attached to the missile such that a part of the missile is encircled by the said tube and such that the said tube can be rotated continuously in one direction relative to the part of the missile that is encircled by the tube, with the protruding section able to complete numerous revolutions relative to the missile while revolving around the missile during continuous rotation of the tube around the encircled part of the missile, with the tube having a longitudinal axis of rotation and which said forward facing surface area is slanted forward such that the said forward facing surface area extends laterally away from the tube and such that as the forward facing surface area extends laterally away from the tube the forward facing surface area leans in a forward direction, and which said forward facing surface area is thus slanted forward relative to the longitudinal axis of rotation of the cylindrical tube, and such that if a plurality of lines are drawn radially away from the longitudinal axis of the tube, with each line drawn from a different point on the longitudinal axis to that of another line, and with the lines drawn from points on the longitudinal axis such that the lines could reach the forward facing surface area while drawn through an area in front of the forward facing surface area and while the lines are drawn parallel to one another, with the lines being of such respective lengths that the lines could make contact with the forward facing surface area while remaining parallel, but not be extended beyond the point of contact with the forward facing surface area, then one of the said lines would be shorter in length with respect to another of the said lines. 15. The missile of claim 14 wherein with the missile
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