US20080203216A1 - Multi-Environment Engine - Google Patents
Multi-Environment Engine Download PDFInfo
- Publication number
- US20080203216A1 US20080203216A1 US11/917,602 US91760206A US2008203216A1 US 20080203216 A1 US20080203216 A1 US 20080203216A1 US 91760206 A US91760206 A US 91760206A US 2008203216 A1 US2008203216 A1 US 2008203216A1
- Authority
- US
- United States
- Prior art keywords
- missile
- wing
- missile according
- submerged
- water
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 43
- 238000000034 method Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 239000003381 stabilizer Substances 0.000 claims description 4
- 230000009189 diving Effects 0.000 abstract description 3
- 238000005339 levitation Methods 0.000 abstract 2
- 241000272517 Anseriformes Species 0.000 description 8
- 230000005540 biological transmission Effects 0.000 description 6
- 239000011888 foil Substances 0.000 description 6
- 230000002829 reductive effect Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 241000251468 Actinopterygii Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 229910052744 lithium Inorganic materials 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C35/00—Flying-boats; Seaplanes
- B64C35/001—Flying-boats; Seaplanes with means for increasing stability on the water
- B64C35/003—Flying-boats; Seaplanes with means for increasing stability on the water using auxiliary floats at the wing tips
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
Definitions
- This invention relates to the field of missiles that change environments. More particularly, the invention relates to a missile that is capable of operating in air, on the surface of the water and under water.
- Missiles that are fired from a submerged submarine, climb and have an air flight phase are also known.
- such missiles are very expensive and are hard to maneuver in water and are generally ejected from the submarine with compressed air. These missiles are therefore just able to reach the surface but cannot operate under the water effectively.
- Certain missiles are encapsulated during their underwater phase, with a disposable capsule.
- This invention aims at eliminating the drawbacks of the devices referred to above.
- This invention has as its object to propose a missile that has a high maneuverability in air, under water and on the surface of the water for a reasonable cost and a low weight.
- the multi-environment missile comprises a body, wings and a propulsion system, whereby at least one wing can be folded between a first lift position for flight, a second lift position for operating on the surface of the water, and a third submerged position.
- the wings can thus be adapted to each type of aerial, underwater or surface operation.
- the foldable wing comprises at least one joint around an axis that is approximately parallel to the longitudinal axis of the body, whereby said joint is active between at least one of said three positions and another of said three positions.
- the foldable wing can be deployed to increase the lift in the air and folded to reduce drag in the water.
- the foldable wing can comprise two joints around an axis that is approximately parallel to the longitudinal axis of the body.
- the foldable wing can comprise a telescoping portion that makes it possible to vary the span of the missile.
- the telescoping portion can be placed beyond the second joint leaving the body.
- the telescoping portion can be deployed in the second lift position for operating on the surface of the water.
- the foldable wing can be mounted behind the body, whereby canard surfaces are placed to the front of the body.
- the body can have a long profile ensuring lift during operations in air.
- the missile In the second lift position for operating on the surface of the water, the missile can benefit from lift that is increased by ground effect.
- the ground effect can be advantageous for the lift-off and splashdown phases.
- the wing in the first lift position for the flight, has a part that is close to the body and end slats that extend upward, whereby the close part of the body is approximately horizontal.
- the close part of the body ensures powerful lift.
- the end slats that are placed in the extension of the part of the body that is close to each wing reduce wingtip turbulence and decrease aerodynamic drag.
- the body can be shaped like a water droplet or a fish, preferably with a height that is greater than its width. Reduced drag can be produced.
- the end slats can form stabilizers in the third submerged position.
- the end slats can be oriented downward, opposite their position that is oriented upward and is used in flight.
- the end slats can form part of the hydroplane skids, or water wings, in the second lift position.
- An end zone of said close part of the body can also be part of the hydroplane skids in the second lift position.
- the close part of the body can comprise several articulated sections.
- One of the sections can be stationary relative to the body. It is preferable to provide a single joint for folding the wing. A significant increase in weight can be produced.
- a missile can comprise a body, wings, and a propulsion system, whereby at least one wing comprises an end slat that can pivot between a first position that is oriented upward for flight, a second lift position for operating on the surface of the water, and a third submerged position. Said end slat can be oriented approximately at 45° upward in the second lift position for operating on the surface of the water. Said end slat can be oriented approximately downward in the third submerged position. The same part thus performs three separate functions.
- the wing in the second lift position for operating on the surface of the water, has a V-shape in a vertical plane to form a hydroplane skid.
- the missile can also comprise a retractable hydroplane skid. On the surface of the water, said missile can rest on a retractable foil and two foils formed by the wings opposite the body. The three foils form a lift triangle.
- the retractable foil can be placed at the front of the missile, and the two foils formed by the wings can be placed behind the missile. Said two foils may be non-retractable.
- the wing in the third submerged position, has two parts that are folded against one another.
- the wing thus can have a long profile that is suited to the movement of the missile underwater.
- the wing can have a section in cutaway along a vertical plane that is parallel to the longitudinal axis of the missile, such that said section tends to make said missile slip during its submerged travel into the third submerged position.
- the missile may have a slightly positive, essentially constant floatability. In case of breakdown, the missile then rises to the surface and can be recovered.
- the propulsion system comprises a propeller that can propel said missile into flight on the surface of the water and while diving.
- the propeller can be streamlined.
- the propulsion system can comprise movable flaps between an aerial propulsion position and an aquatic propulsion position.
- the propulsion system can comprise at least one movable flap that can obstruct a lower intake and comprises at least one mobile flap that can block an upper intake.
- the lower intake is opened for the passage of water.
- the upper intake is opened for the passage of air.
- the propulsion system can comprise a variable-speed motor, for example an electric motor and a transmission with two speeds, one greatly reductive to drive the propeller at low speed in the water, and the other to drive the propeller at high speed in the air.
- the electric motor can be of the brushless type, powered by a battery or a fuel cell.
- a turbine is mounted in a rear fin.
- the turbine may be of the turboreactor type or of the type that drives a generator for recharging batteries, for example ion-lithium batteries.
- the propeller may or may not be streamlined.
- a first lift position for the flight is provided with a body, wings and a propulsion system, a first lift position for the flight, a second lift position for operating on the surface of the water, and a third submerged position are imparted to at least one foldable wing.
- the same propulsion system is active in flight, on the surface of the water, and submerged.
- the foldable wing is deployed for flight and folded for submersion.
- the missile can travel in flight, submerged and on the surface by using numerous elements that are common to these three modes.
- the transition between these modes is carried out in a simple way while underway by adopting the surface mode.
- the missile is particularly well suited for oceanographic research, coastal surveillance and the inspection of ocean floors.
- FIG. 1 is a front elevation view of a missile according to an embodiment, in aerial position;
- FIG. 2 is a top elevation view of the missile of FIG. 1 , in aerial position;
- FIG. 3 is a side elevation view of the missile of FIG. 1 , in aerial position;
- FIG. 4 is a perspective view of the missile of FIG. 1 , in aerial position;
- FIG. 5 is a front elevation view of the missile of FIG. 1 , in surface position;
- FIG. 6 is a top elevation view of the missile of FIG. 1 , in surface position;
- FIG. 7 is a side elevation view of the missile of FIG. 1 , in surface position;
- FIG. 8 is a front elevation view of the missile of FIG. 1 , in submerged position;
- FIG. 9 is a top elevation view of the missile of FIG. 1 , in submerged position;
- FIG. 10 is a side elevation view of the missile of FIG. 1 , in submerged position
- FIG. 11 is a detail perspective view of the missile of FIG. 1 , in aerial position.
- the multi-environment missile 1 comprises a body 2 of elongated shape along a longitudinal axis 3 , two wings 4 and 5 that are symmetrical relative to a plane that passes through the axis 3 , canard surfaces 6 and 7 that are symmetrical relative to the same plane and a thruster 8 .
- the body 2 has a front section 2 a that is generally ogival in shape and a rear section 2 b that gradually tapers toward the rear.
- the canard surfaces 6 and 7 are articulated on the front section 2 a , while the wings 4 and 5 are attached to the rear section 2 b of the body 2 .
- the canard surfaces 6 and 7 can be moved angularly along an axis that is perpendicular to the longitudinal axis 3 relative to the front section 2 a by means of actuators, not shown, arranged inside the body 2 , for example of the electric type.
- the body 2 can be more tall than wide.
- the body 2 can be shaped like a water droplet.
- the thruster 8 comprises an inlet part 8 a , a central part 8 b , and an ejection part 8 c .
- the inlet part 8 a is arranged longitudinally at the wings 4 and 5 and extends above and below the rear section 2 b of the body 2 .
- the inlet part 8 a has a general tapered shape of smaller diameter toward the rear, which allows an acceleration of the fluid that passes through said inlet part 8 a .
- the central part 8 b is arranged longitudinally essentially at the trailing edge of the wings 4 and 5 and is provided with a propeller 9 that is driven by an electric motor, not shown, via a speed adapter, for example a transmission with two speeds that are relatively far apart.
- the ejection part 8 c has a rectangular cross-section, whereas the inlet parts 8 a and central parts 8 b have a circular cross-section.
- the electric motor can be driven by a fuel cell or by batteries.
- Missile 1 can comprise a rear fin.
- a turbine can be placed in the rear fin.
- the propeller 9 may or may not be streamlined.
- the outlet part 8 c comprises two upper flaps 10 and lower flaps 11 jointed around axes that are essentially parallel to the longitudinal axis 3 , and two side flaps 12 and 13 that are perpendicular to the flaps 10 and 11 and are articulated around axes that are essentially perpendicular to the longitudinal axis 3 .
- the movement of the flaps 10 and 11 makes it possible to vary the outflow from the thruster 8 in a vertical plane, while the maneuvering of the flaps 12 and 13 makes it possible to vary the outflow from the thruster 8 in a horizontal plane, which allows a missile bearing control, while the flaps 10 and 11 allow pitch control.
- the position of the flaps 10 to 13 can be determined by electric actuators, not shown.
- the wing 4 comprises a section 14 that is stationary relative to the body 2 , a section 15 that is articulated relative to the section 14 , a section 16 that is articulated relative to the section 15 , and end slats 17 .
- the sections 15 and 16 are arranged in the extension of the stationary section 14 .
- the leading edges of the sections 14 , 15 and 16 are aligned and perpendicular to the axis 3 . The same is true for the trailing edges of the sections 14 , 15 and 16 .
- the end slat 17 is folded perpendicularly to form a wing-tip that makes it possible to reduce turbulence, to increase stability and lift, and to reduce drag.
- the sections 14 , 15 and 16 can be arranged in the same plane, parallel to the longitudinal axis 3 or passing through the longitudinal axis 3 .
- the section 15 is articulated on the section 14 via an axis 18 .
- the section 16 is articulated on a section 15 via an axis 19 .
- the sections 15 and 16 are attached to one another. The number of joints is reduced, thereby reducing weight.
- the end slats 17 are attached or articulated on the section 16 .
- the axes 18 and 19 are parallel to one another and parallel to the longitudinal axis 3 .
- the axes 18 , 19 and 20 are coplanar.
- the wings 4 and 5 are deployed to offer a large lifting surface, while the canard surfaces 6 and 7 ensure excellent maneuverability and the end slats 17 improve the aerodynamic performance.
- the front part 8 a of the thruster 8 comprises at least two flaps that make it possible to block selectively an opening that is arranged above the body 2 for the purpose of travel in air, and an opening that is located below the body 2 for the purpose of underwater travel and certain surface maneuvers.
- the lower flap that is located under the body 2 is closed, while the upper flap that is located above the body 2 is open, allowing the entry of air into the inlet part 8 a .
- the high speed of the transmission is then engaged, which ensures a rotating speed of the propeller 9 that is suitable for the air.
- the missile 1 is equipped with a front skid 21 that makes it possible to slide on the water for hydroplane operation.
- the skid 21 comprises a leg 22 that can be retracted in the body 2 and a shoe 23 .
- the skid 21 has a general T shape, inverted in cross-section (see also the front view of FIG. 5 ).
- the skid 21 is attached to the front section 2 a of the body 2 , essentially at the same longitudinal level as the canard surfaces 6 and 7 .
- the skid 21 is retracted into the aerial and underwater navigation positions so as to reduce drag and is extended into the active position of the body 2 in the surface navigation position so as to offer support on the water.
- the section 15 of the wings 4 and 5 is slightly inclined relative to the stationary section 14 , for example by an angle on the order of 10 to 30°.
- the section 16 is also inclined relative to the section 15 , for example by an angle on the order of 15 to 40°.
- the zone of the end slat 17 that is close to the axis of articulation 20 and the zone of the section 16 that is also close to the axis of articulation 20 form a rear hydroplane skid with a V-shaped cross-section (see also FIG. 5 ) that offers excellent stability during travel at an adequate speed on the surface of the water to lift the body 2 of the missile 1 above the water.
- the thruster 8 can adopt the same mode of operation as above. However, in the case of a choppy water surface, it may prove advantageous to close the upper intake flap of the thruster 8 and to open the lower flap so as to facilitate the entry of water into the thruster 8 .
- the transmission is then put on low speed to provide to the propeller a propulsion speed that is compatible with the propulsion in the water.
- the underwater mode of operation is illustrated in FIGS. 8 to 10 .
- the section 15 is folded at 180° relative to the position that is illustrated in FIGS. 1 to 4 and positioned under the stationary section 14 .
- the section 16 is positioned in the extension of the section 15 , relative to the zero angle, also in contact with the lower surface of the stationary section 14 .
- the end slats 17 are perpendicular to the section 16 and directed downward close to the body 2 .
- the missile 1 thus offers a reduced span, reducing the hydrodynamic drag.
- the thruster 8 is in aquatic propulsion mode described above, with a propeller 9 with a slow rotating speed via a transmission that operates with a reducing gear.
- the skid 21 is retracted so as to reduce drag.
- the depth control is carried out using flaps 10 and 11 of the ejection part 8 c of the thruster 8 .
- the canard surfaces 6 and 7 can also be used for depth control and roll stabilization.
- the direction control is ensured by the flaps
- the profile of the wing has a particular importance.
- the section 14 can have a profile called SD 7037.
- the profile of sections 15 and 16 may also not be identical.
- the profiles of said sections 14 to 16 are arranged so that each section in the aerial navigation position that is illustrated in FIGS. 1 to 4 , whereby the wings 4 and 5 are deployed with maximum span, offers a positive lift, tending to increase the altitude of the missile and also such that in the underwater navigation position that is illustrated in FIGS.
- the wing 4 , 5 whose profile results from the superposition of the section 14 and the section 15 partly, and section 14 and section 16 for another part, has a negative lift that tends to increase the depth of submersion of the missile 1 .
- the missile 1 when the missile 1 is traveling under water, under the action of the thruster 8 , the missile 1 has a greater tendency to dive as speed increases.
- the end slats 17 are then used as a stabilizer, reducing the twisting movement of the missile.
- the end slats 17 ensure a triple function of the wing-tip in aerial navigation, hydroplane skid by travel on the surface of the water, and underwater navigation stabilizer.
- the wing 4 has a positive lift in deployed position of aerial navigation and a negative lift in folded position of underwater navigation.
- the stationary section 14 can be provided on its inside surface with a movable flap that can travel downward and that makes it possible to increase the lift, in particular at low speed, for the lift-off.
- the thruster 8 can be provided with counter-rotating propellers, which proves particularly advantageous for preventing reaction torque.
- end slats 17 that are articulated relative to the section 16 so that their angular position relative to the section 16 can be modified. It is also possible to specify that the body 2 have a profile, viewed in longitudinal section, which offers lift during travel in air so as to facilitate the lift-off of the missile and to reduce the necessary wing length.
- the wing 4 comprises a telescoping portion 24 to which is attached the end slat 17 , designed, for example, in one piece and able to be deployed between an extended position relative to the section 16 and a retracted position, visible in FIG. 11 . It is seen that the majority of the portion 24 is placed in the section 16 .
- the telescoping portion 24 can be deployed in the surface navigation position to be used as a hydroplane skid in collaboration with the end slat 17 .
- the telescoping portion 24 can be optimized to offer an excellent hydroplane skid profile, while the section 16 can be optimized to offer an excellent wing profile.
- the telescoping portion 24 is retracted in aerial and underwater navigation.
- the end slat 17 can be perpendicular to the telescoping portion 24 .
- the multi-environment missile 1 is able to move in three separate environments, thus offering very high flexibility of operation despite significant constraints inherent to these three environments.
- the multi-environment missile 1 offers good aerial performance owing to the large surface area of the wings 4 and 5 that are deployed, the canard slats 6 and 7 and the orientable thrust of the vector thruster 8 , thus owing to the longitudinal profile of the body 2 that ensures an additional lift, and the end slats 17 that form the wing tips.
- the surface navigation performance is ensured by the front skid 21 and the rear skids that are formed by the end slats 17 in cooperation with the section 16 or the telescoping portion 24 .
- the folded wings 4 and 5 ensure a negative lift that allows the multi-environment missile 1 to dive while traveling under the action of the vector thruster 8 .
- the multi-environment missile can thus pass from the presence of ballasts currently used in submarines, creating a significant reduction of the space requirement and the weight to be taken on board, and increased maneuverability regardless of the mode of navigation.
- the multi-environment missile has a bulk density that is slightly less than 1, such that in the case of a failure while diving, the multi-environment missile 1 rises to the surface, the thruster 8 being stopped. An audible, visual or radio alarm can then be implemented.
- the multi-environment missile 1 is therefore perfectly suited for implementation from light infrastructures, such as motor boats, pleasure boats, simple pontoons, and can be used for moving quickly from one point to the next while carrying out underwater inspections while underway by adopting a surface navigation mode.
- the multi-environment missile 1 draws close to the water surface.
- the front skid 21 is extended from the body 2 .
- the sections 15 and 16 are pivoted around their axes of articulation 18 and 19 to impart to the wings 4 and 5 the surface navigation profile that is illustrated in FIG. 5 .
- the multi-environment missile 1 can then rest on the surface of the water and navigate on the surface.
- the lower flaps of the section 14 can be used to increase the lift temporarily and to reduce the splashdown speed.
- a ground effect can also be created.
- the liftoff operation is carried out in reverse order.
- the thruster 8 is gradually slowed down.
- the transmission is passed to the lower speed, so that the propeller rotates at a speed that is compatible with the water.
- the lower flap of the thruster 8 is opened, and the upper flap is closed.
- the two flaps can be closed until the multi-environment missile is stopped, which gradually sinks into the water due to the absence of lift of the hydroplane skids due to the drop in speed.
- the skid 21 is retracted into the body 2 .
- the section 16 of the wings 4 and 5 is pivoted in alignment with the section 15 , and the section 15 is pivoted at 180° under the section 14 .
- the thruster is then put into operation in the underwater propulsion mode with a propeller 9 that rotates at slow speed and an open lower flap.
- the thruster 8 of the bi-mode type, is particularly advantageous if a single thruster is sufficient, creating a considerable reduction of the weight and the space requirement of the propulsion means.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
Description
- This invention relates to the field of missiles that change environments. More particularly, the invention relates to a missile that is capable of operating in air, on the surface of the water and under water.
- Today, submarines that operate on the surface and under water are known. In the past, seaplanes were also developed that were able to land on the water but were not very seaworthy.
- Missiles that are fired from a submerged submarine, climb and have an air flight phase are also known. However, such missiles are very expensive and are hard to maneuver in water and are generally ejected from the submarine with compressed air. These missiles are therefore just able to reach the surface but cannot operate under the water effectively. Certain missiles are encapsulated during their underwater phase, with a disposable capsule.
- This invention aims at eliminating the drawbacks of the devices referred to above.
- This invention has as its object to propose a missile that has a high maneuverability in air, under water and on the surface of the water for a reasonable cost and a low weight.
- The multi-environment missile comprises a body, wings and a propulsion system, whereby at least one wing can be folded between a first lift position for flight, a second lift position for operating on the surface of the water, and a third submerged position. The wings can thus be adapted to each type of aerial, underwater or surface operation.
- In one embodiment, the foldable wing comprises at least one joint around an axis that is approximately parallel to the longitudinal axis of the body, whereby said joint is active between at least one of said three positions and another of said three positions. The foldable wing can be deployed to increase the lift in the air and folded to reduce drag in the water.
- The foldable wing can comprise two joints around an axis that is approximately parallel to the longitudinal axis of the body.
- The foldable wing can comprise a telescoping portion that makes it possible to vary the span of the missile. The telescoping portion can be placed beyond the second joint leaving the body. The telescoping portion can be deployed in the second lift position for operating on the surface of the water.
- The foldable wing can be mounted behind the body, whereby canard surfaces are placed to the front of the body.
- The body can have a long profile ensuring lift during operations in air.
- In the second lift position for operating on the surface of the water, the missile can benefit from lift that is increased by ground effect. The ground effect can be advantageous for the lift-off and splashdown phases.
- In one embodiment, in the first lift position for the flight, the wing has a part that is close to the body and end slats that extend upward, whereby the close part of the body is approximately horizontal. The close part of the body ensures powerful lift. The end slats that are placed in the extension of the part of the body that is close to each wing reduce wingtip turbulence and decrease aerodynamic drag.
- The body can be shaped like a water droplet or a fish, preferably with a height that is greater than its width. Reduced drag can be produced.
- The end slats can form stabilizers in the third submerged position. The end slats can be oriented downward, opposite their position that is oriented upward and is used in flight.
- The end slats can form part of the hydroplane skids, or water wings, in the second lift position. An end zone of said close part of the body can also be part of the hydroplane skids in the second lift position.
- The close part of the body can comprise several articulated sections. One of the sections can be stationary relative to the body. It is preferable to provide a single joint for folding the wing. A significant increase in weight can be produced.
- In other words, a missile can comprise a body, wings, and a propulsion system, whereby at least one wing comprises an end slat that can pivot between a first position that is oriented upward for flight, a second lift position for operating on the surface of the water, and a third submerged position. Said end slat can be oriented approximately at 45° upward in the second lift position for operating on the surface of the water. Said end slat can be oriented approximately downward in the third submerged position. The same part thus performs three separate functions.
- In one embodiment, in the second lift position for operating on the surface of the water, the wing has a V-shape in a vertical plane to form a hydroplane skid.
- The missile can also comprise a retractable hydroplane skid. On the surface of the water, said missile can rest on a retractable foil and two foils formed by the wings opposite the body. The three foils form a lift triangle. The retractable foil can be placed at the front of the missile, and the two foils formed by the wings can be placed behind the missile. Said two foils may be non-retractable.
- In one embodiment, in the third submerged position, the wing has two parts that are folded against one another. The wing thus can have a long profile that is suited to the movement of the missile underwater.
- The wing can have a section in cutaway along a vertical plane that is parallel to the longitudinal axis of the missile, such that said section tends to make said missile slip during its submerged travel into the third submerged position. The missile may have a slightly positive, essentially constant floatability. In case of breakdown, the missile then rises to the surface and can be recovered.
- In one embodiment, the propulsion system comprises a propeller that can propel said missile into flight on the surface of the water and while diving. The propeller can be streamlined. The propulsion system can comprise movable flaps between an aerial propulsion position and an aquatic propulsion position. The propulsion system can comprise at least one movable flap that can obstruct a lower intake and comprises at least one mobile flap that can block an upper intake. The lower intake is opened for the passage of water. The upper intake is opened for the passage of air. The propulsion system can comprise a variable-speed motor, for example an electric motor and a transmission with two speeds, one greatly reductive to drive the propeller at low speed in the water, and the other to drive the propeller at high speed in the air. The electric motor can be of the brushless type, powered by a battery or a fuel cell.
- In one variant, a turbine is mounted in a rear fin. The turbine may be of the turboreactor type or of the type that drives a generator for recharging batteries, for example ion-lithium batteries. The propeller may or may not be streamlined.
- According to the process of moving a multi-environment missile that is provided with a body, wings and a propulsion system, a first lift position for the flight, a second lift position for operating on the surface of the water, and a third submerged position are imparted to at least one foldable wing.
- Advantageously, the same propulsion system is active in flight, on the surface of the water, and submerged.
- In one embodiment, the foldable wing is deployed for flight and folded for submersion.
- Thanks to the invention, the missile can travel in flight, submerged and on the surface by using numerous elements that are common to these three modes. The transition between these modes is carried out in a simple way while underway by adopting the surface mode. The missile is particularly well suited for oceanographic research, coastal surveillance and the inspection of ocean floors.
- This invention will be better understood from the study of the detailed description of several embodiments taken as examples that are in no way limiting and illustrated by the accompanying drawings, in which:
-
FIG. 1 is a front elevation view of a missile according to an embodiment, in aerial position; -
FIG. 2 is a top elevation view of the missile ofFIG. 1 , in aerial position; -
FIG. 3 is a side elevation view of the missile ofFIG. 1 , in aerial position; -
FIG. 4 is a perspective view of the missile ofFIG. 1 , in aerial position; -
FIG. 5 is a front elevation view of the missile ofFIG. 1 , in surface position; -
FIG. 6 is a top elevation view of the missile ofFIG. 1 , in surface position; -
FIG. 7 is a side elevation view of the missile ofFIG. 1 , in surface position; -
FIG. 8 is a front elevation view of the missile ofFIG. 1 , in submerged position; -
FIG. 9 is a top elevation view of the missile ofFIG. 1 , in submerged position; -
FIG. 10 is a side elevation view of the missile ofFIG. 1 , in submerged position, and -
FIG. 11 is a detail perspective view of the missile ofFIG. 1 , in aerial position. - As illustrated in
FIGS. 1 to 10 , themulti-environment missile 1 comprises abody 2 of elongated shape along alongitudinal axis 3, twowings axis 3, canard surfaces 6 and 7 that are symmetrical relative to the same plane and athruster 8. Thebody 2 has afront section 2 a that is generally ogival in shape and arear section 2 b that gradually tapers toward the rear. The canard surfaces 6 and 7 are articulated on thefront section 2 a, while thewings rear section 2 b of thebody 2. The canard surfaces 6 and 7 can be moved angularly along an axis that is perpendicular to thelongitudinal axis 3 relative to thefront section 2 a by means of actuators, not shown, arranged inside thebody 2, for example of the electric type. As a variant, thebody 2 can be more tall than wide. Thebody 2 can be shaped like a water droplet. - The
thruster 8 comprises aninlet part 8 a, acentral part 8 b, and anejection part 8 c. Theinlet part 8 a is arranged longitudinally at thewings rear section 2 b of thebody 2. Theinlet part 8 a has a general tapered shape of smaller diameter toward the rear, which allows an acceleration of the fluid that passes through saidinlet part 8 a. Thecentral part 8 b is arranged longitudinally essentially at the trailing edge of thewings propeller 9 that is driven by an electric motor, not shown, via a speed adapter, for example a transmission with two speeds that are relatively far apart. Theejection part 8 c has a rectangular cross-section, whereas theinlet parts 8 a andcentral parts 8 b have a circular cross-section. The electric motor can be driven by a fuel cell or by batteries.Missile 1 can comprise a rear fin. A turbine can be placed in the rear fin. Thepropeller 9 may or may not be streamlined. - The
outlet part 8 c comprises twoupper flaps 10 andlower flaps 11 jointed around axes that are essentially parallel to thelongitudinal axis 3, and twoside flaps flaps longitudinal axis 3. The movement of theflaps thruster 8 in a vertical plane, while the maneuvering of theflaps thruster 8 in a horizontal plane, which allows a missile bearing control, while theflaps flaps 10 to 13 can be determined by electric actuators, not shown. - Whereby the two
wings wing 4 will be described below. - Starting from the
rear section 2 b of thebody 2 of themissile 1, thewing 4 comprises asection 14 that is stationary relative to thebody 2, asection 15 that is articulated relative to thesection 14, asection 16 that is articulated relative to thesection 15, andend slats 17. In the aerial navigation position illustrated inFIGS. 1 to 4 , thesections stationary section 14. The leading edges of thesections axis 3. The same is true for the trailing edges of thesections end slat 17 is folded perpendicularly to form a wing-tip that makes it possible to reduce turbulence, to increase stability and lift, and to reduce drag. Thesections longitudinal axis 3 or passing through thelongitudinal axis 3. Thesection 15 is articulated on thesection 14 via anaxis 18. Thesection 16 is articulated on asection 15 via anaxis 19. Advantageously, thesections section 16. Theaxes longitudinal axis 3. - In the position that is illustrated in
FIGS. 1 and 4 , theaxes - In the aerial navigation position, the
wings end slats 17 improve the aerodynamic performance. - The
front part 8 a of thethruster 8 comprises at least two flaps that make it possible to block selectively an opening that is arranged above thebody 2 for the purpose of travel in air, and an opening that is located below thebody 2 for the purpose of underwater travel and certain surface maneuvers. For aerial navigation, the lower flap that is located under thebody 2 is closed, while the upper flap that is located above thebody 2 is open, allowing the entry of air into theinlet part 8 a. The high speed of the transmission is then engaged, which ensures a rotating speed of thepropeller 9 that is suitable for the air. - In the surface navigation position, illustrated in
FIGS. 5 to 7 , it is seen that themissile 1 is equipped with a front skid 21 that makes it possible to slide on the water for hydroplane operation. The skid 21 comprises aleg 22 that can be retracted in thebody 2 and a shoe 23. The skid 21 has a general T shape, inverted in cross-section (see also the front view ofFIG. 5 ). The skid 21 is attached to thefront section 2 a of thebody 2, essentially at the same longitudinal level as the canard surfaces 6 and 7. The skid 21 is retracted into the aerial and underwater navigation positions so as to reduce drag and is extended into the active position of thebody 2 in the surface navigation position so as to offer support on the water. - In the surface navigation position, the
section 15 of thewings stationary section 14, for example by an angle on the order of 10 to 30°. Thesection 16 is also inclined relative to thesection 15, for example by an angle on the order of 15 to 40°. The zone of theend slat 17 that is close to the axis of articulation 20 and the zone of thesection 16 that is also close to the axis of articulation 20 form a rear hydroplane skid with a V-shaped cross-section (see alsoFIG. 5 ) that offers excellent stability during travel at an adequate speed on the surface of the water to lift thebody 2 of themissile 1 above the water. - In the surface navigation position illustrated in
FIGS. 5 to 7 , thethruster 8 can adopt the same mode of operation as above. However, in the case of a choppy water surface, it may prove advantageous to close the upper intake flap of thethruster 8 and to open the lower flap so as to facilitate the entry of water into thethruster 8. The transmission is then put on low speed to provide to the propeller a propulsion speed that is compatible with the propulsion in the water. - The underwater mode of operation is illustrated in
FIGS. 8 to 10 . Thesection 15 is folded at 180° relative to the position that is illustrated inFIGS. 1 to 4 and positioned under thestationary section 14. Thesection 16 is positioned in the extension of thesection 15, relative to the zero angle, also in contact with the lower surface of thestationary section 14. The end slats 17 are perpendicular to thesection 16 and directed downward close to thebody 2. Themissile 1 thus offers a reduced span, reducing the hydrodynamic drag. Thethruster 8 is in aquatic propulsion mode described above, with apropeller 9 with a slow rotating speed via a transmission that operates with a reducing gear. The skid 21 is retracted so as to reduce drag. The depth control is carried out usingflaps ejection part 8 c of thethruster 8. The canard surfaces 6 and 7 can also be used for depth control and roll stabilization. The direction control is ensured by theflaps - Of course, for the travel of the missile by aerial navigation and underwater navigation, the profile of the wing has a particular importance. The profiles of the
sections 14, on the one hand, and 15 and 16, on the other hand, can be different. By way of example, thesection 14 can have a profile called SD 7037. The profile ofsections sections 14 to 16 are arranged so that each section in the aerial navigation position that is illustrated inFIGS. 1 to 4 , whereby thewings FIGS. 8 to 10 , thewing section 14 and thesection 15 partly, andsection 14 andsection 16 for another part, has a negative lift that tends to increase the depth of submersion of themissile 1. Thus, when themissile 1 is traveling under water, under the action of thethruster 8, themissile 1 has a greater tendency to dive as speed increases. The end slats 17 are then used as a stabilizer, reducing the twisting movement of the missile. - In other words, the
end slats 17 ensure a triple function of the wing-tip in aerial navigation, hydroplane skid by travel on the surface of the water, and underwater navigation stabilizer. Thewing 4 has a positive lift in deployed position of aerial navigation and a negative lift in folded position of underwater navigation. In addition, thestationary section 14 can be provided on its inside surface with a movable flap that can travel downward and that makes it possible to increase the lift, in particular at low speed, for the lift-off. - The
thruster 8 can be provided with counter-rotating propellers, which proves particularly advantageous for preventing reaction torque. - By way of variant, it is possible to provide
end slats 17 that are articulated relative to thesection 16 so that their angular position relative to thesection 16 can be modified. It is also possible to specify that thebody 2 have a profile, viewed in longitudinal section, which offers lift during travel in air so as to facilitate the lift-off of the missile and to reduce the necessary wing length. - In the embodiment illustrated in
FIG. 11 , thewing 4 comprises atelescoping portion 24 to which is attached theend slat 17, designed, for example, in one piece and able to be deployed between an extended position relative to thesection 16 and a retracted position, visible inFIG. 11 . It is seen that the majority of theportion 24 is placed in thesection 16. Thetelescoping portion 24 can be deployed in the surface navigation position to be used as a hydroplane skid in collaboration with theend slat 17. Thetelescoping portion 24 can be optimized to offer an excellent hydroplane skid profile, while thesection 16 can be optimized to offer an excellent wing profile. Thetelescoping portion 24 is retracted in aerial and underwater navigation. Theend slat 17 can be perpendicular to thetelescoping portion 24. - Thus, the
multi-environment missile 1 is able to move in three separate environments, thus offering very high flexibility of operation despite significant constraints inherent to these three environments. Themulti-environment missile 1 offers good aerial performance owing to the large surface area of thewings canard slats vector thruster 8, thus owing to the longitudinal profile of thebody 2 that ensures an additional lift, and theend slats 17 that form the wing tips. The surface navigation performance is ensured by the front skid 21 and the rear skids that are formed by theend slats 17 in cooperation with thesection 16 or thetelescoping portion 24. - In underwater navigation, the folded
wings multi-environment missile 1 to dive while traveling under the action of thevector thruster 8. The multi-environment missile can thus pass from the presence of ballasts currently used in submarines, creating a significant reduction of the space requirement and the weight to be taken on board, and increased maneuverability regardless of the mode of navigation. The multi-environment missile has a bulk density that is slightly less than 1, such that in the case of a failure while diving, themulti-environment missile 1 rises to the surface, thethruster 8 being stopped. An audible, visual or radio alarm can then be implemented. Themulti-environment missile 1 is therefore perfectly suited for implementation from light infrastructures, such as motor boats, pleasure boats, simple pontoons, and can be used for moving quickly from one point to the next while carrying out underwater inspections while underway by adopting a surface navigation mode. - In operation, to pass from the aerial navigation mode into the surface navigation mode, the
multi-environment missile 1 draws close to the water surface. The front skid 21 is extended from thebody 2. - The
sections articulation wings FIG. 5 . Themulti-environment missile 1 can then rest on the surface of the water and navigate on the surface. At the time of splashdown, the lower flaps of thesection 14 can be used to increase the lift temporarily and to reduce the splashdown speed. A ground effect can also be created. The liftoff operation is carried out in reverse order. - To pass from the surface navigation mode to the underwater navigation mode, the
thruster 8 is gradually slowed down. The transmission is passed to the lower speed, so that the propeller rotates at a speed that is compatible with the water. Then, the lower flap of thethruster 8 is opened, and the upper flap is closed. Alternately, the two flaps can be closed until the multi-environment missile is stopped, which gradually sinks into the water due to the absence of lift of the hydroplane skids due to the drop in speed. The skid 21 is retracted into thebody 2. Thesection 16 of thewings section 15, and thesection 15 is pivoted at 180° under thesection 14. The thruster is then put into operation in the underwater propulsion mode with apropeller 9 that rotates at slow speed and an open lower flap. Thethruster 8, of the bi-mode type, is particularly advantageous if a single thruster is sufficient, creating a considerable reduction of the weight and the space requirement of the propulsion means.
Claims (20)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0506119A FR2887224B1 (en) | 2005-06-16 | 2005-06-16 | MULTIMILIED EQUIPMENT |
FR0506119 | 2005-06-16 | ||
PCT/FR2006/001340 WO2006134267A1 (en) | 2005-06-16 | 2006-06-14 | Multi-environment engine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20080203216A1 true US20080203216A1 (en) | 2008-08-28 |
Family
ID=35929854
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/917,602 Abandoned US20080203216A1 (en) | 2005-06-16 | 2006-06-14 | Multi-Environment Engine |
Country Status (7)
Country | Link |
---|---|
US (1) | US20080203216A1 (en) |
EP (1) | EP1996461A1 (en) |
JP (1) | JP2008543647A (en) |
CA (1) | CA2611765A1 (en) |
FR (1) | FR2887224B1 (en) |
IL (1) | IL188137A0 (en) |
WO (1) | WO2006134267A1 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2452869A1 (en) * | 2010-11-11 | 2012-05-16 | ATLAS ELEKTRONIK GmbH | Unmanned underwater vehicle |
EP2412628A3 (en) * | 2010-07-29 | 2015-08-05 | Rolls-Royce plc | Aerospace vehicle yaw generating tail section |
ES2570079A1 (en) * | 2014-11-13 | 2016-05-13 | Advance Intelligent Developments S.L. | Convertible boat (Machine-translation by Google Translate, not legally binding) |
WO2018031063A1 (en) * | 2016-08-09 | 2018-02-15 | Li Fang | Flying underwater imager with multi-mode operation for locating and approaching underwater objects for imaging |
CN108058796A (en) * | 2017-11-24 | 2018-05-22 | 中国船舶科学研究中心(中国船舶重工集团公司第七0二研究所) | A kind of amphibious unmanned platform of air-sea and its operating method |
CN108583875A (en) * | 2018-05-21 | 2018-09-28 | 中国空气动力研究与发展中心计算空气动力研究所 | The latent empty general purpose vehicle layout of one kind |
US10640187B2 (en) | 2016-08-09 | 2020-05-05 | Li Fang | Flying underwater imager with multi-mode operation for locating and approaching underwater objects for imaging and maintaining depths and altitudes |
US20200377238A1 (en) * | 2019-04-12 | 2020-12-03 | Elliot Goldman | Thrust vector control mechanism |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2012135718A1 (en) * | 2011-03-30 | 2012-10-04 | Juliet Marine Systems, Inc. | High speed surface craft and submersible vehicle |
KR102250863B1 (en) * | 2019-10-21 | 2021-05-13 | 선문대학교 산학협력단 | WIG Ship |
CN114435533B (en) * | 2022-01-28 | 2022-10-04 | 北京大学 | Retractable hydrofoil mechanism |
Citations (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1466551A (en) * | 1921-12-06 | 1923-08-28 | Bristol Aeroplane Co Ltd | Aircraft, submarine, torpedo, and other totally immersed craft or structure |
US2937824A (en) * | 1955-07-11 | 1960-05-24 | Aerojet General Co | Bi-medium rocket-torpedo missile |
US2961928A (en) * | 1958-11-03 | 1960-11-29 | Rosenthal Henry | Folding wing projectile |
US3088403A (en) * | 1959-05-26 | 1963-05-07 | James T Bartling | Rocket assisted torpedo |
US3415467A (en) * | 1967-01-30 | 1968-12-10 | Joseph A. Barringer | Retrievable rocket with folded wings |
US3613617A (en) * | 1960-03-17 | 1971-10-19 | Us Navy | Rocket-thrown weapon |
US3636877A (en) * | 1964-06-02 | 1972-01-25 | Us Navy | Antisubmarine missile |
US3745956A (en) * | 1970-05-29 | 1973-07-17 | Thomson Csf | Self-guidance methods and devices for anti-submarine missiles |
US3827655A (en) * | 1963-12-04 | 1974-08-06 | Us Navy | Short range guided missile |
US3867893A (en) * | 1960-02-11 | 1975-02-25 | Us Navy | Rocket-thrown missile |
US4215630A (en) * | 1978-03-06 | 1980-08-05 | General Dynamics Corporation Pomona Division | Anti-ship torpedo defense missile |
US4262862A (en) * | 1978-02-18 | 1981-04-21 | Messerschmitt-Bolkow-Blohm Gesellschaft mit beschraankter Haftung | Apparatus for changing the wing positions of swingable wings of a missile |
US4372239A (en) * | 1980-03-03 | 1983-02-08 | General Dynamics, Pomona Division | Undersea weapon with hydropulse system and periodical seawater admission |
US4588146A (en) * | 1984-03-29 | 1986-05-13 | The United States Of America As Represented By The Secretary Of The Army | Biaxial folding lever wing |
US5012717A (en) * | 1964-09-29 | 1991-05-07 | The United States Of America As Represented By The Secretary Of The Navy | Air-to-subsurface missile system |
US5078339A (en) * | 1989-07-07 | 1992-01-07 | Israel Aircraft Industries Ltd. | Unmanned aircraft having a pivotably movable double wing unit |
US5141175A (en) * | 1991-03-22 | 1992-08-25 | Harris Gordon L | Air launched munition range extension system and method |
US5437230A (en) * | 1994-03-08 | 1995-08-01 | Leigh Aerosystems Corporation | Standoff mine neutralization system and method |
US5615846A (en) * | 1994-11-04 | 1997-04-01 | Gec Marconi Dynamics Inc. | Extendable wing for guided missles and munitions |
US5615847A (en) * | 1995-09-11 | 1997-04-01 | The United States Of America As Represented By The Secretary Of The Navy | Submarine launched unmanned aerial vehicle |
US5929370A (en) * | 1995-06-07 | 1999-07-27 | Raytheon Company | Aerodynamically stabilized projectile system for use against underwater objects |
US5955698A (en) * | 1998-01-28 | 1999-09-21 | The United States Of America As Represented By The Secretary Of The Navy | Air-launched supercavitating water-entry projectile |
US6581871B2 (en) * | 2001-06-04 | 2003-06-24 | Smiths Aerospace, Inc. | Extendable and controllable flight vehicle wing/control surface assembly |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2444332A (en) * | 1944-12-07 | 1948-06-29 | Briggs Earl | Wing folding arrangement for submersible aircraft |
GB627953A (en) * | 1947-09-09 | 1949-08-18 | Godfrey Alan Merricks | An improved aircraft |
US3302602A (en) * | 1965-02-26 | 1967-02-07 | Korganoff Alexandre | Submersible vessels |
DE8717355U1 (en) * | 1987-08-26 | 1988-11-24 | Dornier GmbH, 88039 Friedrichshafen | Device for maintaining the floating stability of seaplanes |
IL92526A (en) * | 1989-12-01 | 1993-04-04 | Amiran Steinberg | Sea vessel |
US6619584B1 (en) * | 2002-03-11 | 2003-09-16 | Robin Haynes | Road/air vehicle |
-
2005
- 2005-06-16 FR FR0506119A patent/FR2887224B1/en not_active Expired - Fee Related
-
2006
- 2006-06-14 WO PCT/FR2006/001340 patent/WO2006134267A1/en active Application Filing
- 2006-06-14 US US11/917,602 patent/US20080203216A1/en not_active Abandoned
- 2006-06-14 EP EP06764787A patent/EP1996461A1/en not_active Withdrawn
- 2006-06-14 JP JP2008516376A patent/JP2008543647A/en active Pending
- 2006-06-14 CA CA002611765A patent/CA2611765A1/en not_active Abandoned
-
2007
- 2007-12-13 IL IL188137A patent/IL188137A0/en unknown
Patent Citations (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1466551A (en) * | 1921-12-06 | 1923-08-28 | Bristol Aeroplane Co Ltd | Aircraft, submarine, torpedo, and other totally immersed craft or structure |
US2937824A (en) * | 1955-07-11 | 1960-05-24 | Aerojet General Co | Bi-medium rocket-torpedo missile |
US2961928A (en) * | 1958-11-03 | 1960-11-29 | Rosenthal Henry | Folding wing projectile |
US3088403A (en) * | 1959-05-26 | 1963-05-07 | James T Bartling | Rocket assisted torpedo |
US3867893A (en) * | 1960-02-11 | 1975-02-25 | Us Navy | Rocket-thrown missile |
US3613617A (en) * | 1960-03-17 | 1971-10-19 | Us Navy | Rocket-thrown weapon |
US3827655A (en) * | 1963-12-04 | 1974-08-06 | Us Navy | Short range guided missile |
US3636877A (en) * | 1964-06-02 | 1972-01-25 | Us Navy | Antisubmarine missile |
US5012717A (en) * | 1964-09-29 | 1991-05-07 | The United States Of America As Represented By The Secretary Of The Navy | Air-to-subsurface missile system |
US3415467A (en) * | 1967-01-30 | 1968-12-10 | Joseph A. Barringer | Retrievable rocket with folded wings |
US3745956A (en) * | 1970-05-29 | 1973-07-17 | Thomson Csf | Self-guidance methods and devices for anti-submarine missiles |
US4262862A (en) * | 1978-02-18 | 1981-04-21 | Messerschmitt-Bolkow-Blohm Gesellschaft mit beschraankter Haftung | Apparatus for changing the wing positions of swingable wings of a missile |
US4215630A (en) * | 1978-03-06 | 1980-08-05 | General Dynamics Corporation Pomona Division | Anti-ship torpedo defense missile |
US4372239A (en) * | 1980-03-03 | 1983-02-08 | General Dynamics, Pomona Division | Undersea weapon with hydropulse system and periodical seawater admission |
US4588146A (en) * | 1984-03-29 | 1986-05-13 | The United States Of America As Represented By The Secretary Of The Army | Biaxial folding lever wing |
US5078339A (en) * | 1989-07-07 | 1992-01-07 | Israel Aircraft Industries Ltd. | Unmanned aircraft having a pivotably movable double wing unit |
US5141175A (en) * | 1991-03-22 | 1992-08-25 | Harris Gordon L | Air launched munition range extension system and method |
US5437230A (en) * | 1994-03-08 | 1995-08-01 | Leigh Aerosystems Corporation | Standoff mine neutralization system and method |
US5615846A (en) * | 1994-11-04 | 1997-04-01 | Gec Marconi Dynamics Inc. | Extendable wing for guided missles and munitions |
US5929370A (en) * | 1995-06-07 | 1999-07-27 | Raytheon Company | Aerodynamically stabilized projectile system for use against underwater objects |
US5615847A (en) * | 1995-09-11 | 1997-04-01 | The United States Of America As Represented By The Secretary Of The Navy | Submarine launched unmanned aerial vehicle |
US5955698A (en) * | 1998-01-28 | 1999-09-21 | The United States Of America As Represented By The Secretary Of The Navy | Air-launched supercavitating water-entry projectile |
USH1938H1 (en) * | 1998-01-28 | 2001-02-06 | The United States Of America As Represented By The Secretary Of The Navy | Supercavitating water-entry projectile |
US6581871B2 (en) * | 2001-06-04 | 2003-06-24 | Smiths Aerospace, Inc. | Extendable and controllable flight vehicle wing/control surface assembly |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2412628A3 (en) * | 2010-07-29 | 2015-08-05 | Rolls-Royce plc | Aerospace vehicle yaw generating tail section |
EP2452869A1 (en) * | 2010-11-11 | 2012-05-16 | ATLAS ELEKTRONIK GmbH | Unmanned underwater vehicle |
ES2570079A1 (en) * | 2014-11-13 | 2016-05-13 | Advance Intelligent Developments S.L. | Convertible boat (Machine-translation by Google Translate, not legally binding) |
WO2018031063A1 (en) * | 2016-08-09 | 2018-02-15 | Li Fang | Flying underwater imager with multi-mode operation for locating and approaching underwater objects for imaging |
US10065715B2 (en) | 2016-08-09 | 2018-09-04 | Li Fang | Flying underwater imager with multi-mode operation for locating and approaching underwater objects for imaging |
US10640187B2 (en) | 2016-08-09 | 2020-05-05 | Li Fang | Flying underwater imager with multi-mode operation for locating and approaching underwater objects for imaging and maintaining depths and altitudes |
CN108058796A (en) * | 2017-11-24 | 2018-05-22 | 中国船舶科学研究中心(中国船舶重工集团公司第七0二研究所) | A kind of amphibious unmanned platform of air-sea and its operating method |
CN108583875A (en) * | 2018-05-21 | 2018-09-28 | 中国空气动力研究与发展中心计算空气动力研究所 | The latent empty general purpose vehicle layout of one kind |
US20200377238A1 (en) * | 2019-04-12 | 2020-12-03 | Elliot Goldman | Thrust vector control mechanism |
US11649071B2 (en) * | 2019-04-12 | 2023-05-16 | Exoterra Resource, Llc | Thrust vector control mechanism |
Also Published As
Publication number | Publication date |
---|---|
WO2006134267A1 (en) | 2006-12-21 |
IL188137A0 (en) | 2008-03-20 |
FR2887224B1 (en) | 2008-10-17 |
CA2611765A1 (en) | 2006-12-21 |
EP1996461A1 (en) | 2008-12-03 |
FR2887224A1 (en) | 2006-12-22 |
JP2008543647A (en) | 2008-12-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US20080203216A1 (en) | Multi-Environment Engine | |
CN110077588B (en) | Sea, land and air submerged four-purpose aircraft capable of taking off and landing vertically | |
EP2440455B1 (en) | Wingtip and sponson interaction on an amphibious aircraft | |
US8671868B2 (en) | Underwater vessel with above-water propulsion | |
CA2554984A1 (en) | Wing-in-ground-effect craft | |
CN112549885B (en) | Folding wing submerged cross-domain marine robot capable of taking off and landing vertically | |
CN218786088U (en) | Water-air amphibious cross-medium aircraft | |
KR20070114703A (en) | Aircraft landing method and device | |
US7347154B2 (en) | Amphibious craft | |
US7631609B1 (en) | Versatile watercraft | |
CA2331944A1 (en) | Seaplane having main wing mounted beneath fuselage | |
JPS58218499A (en) | Air cushion vehicle | |
SI23103A (en) | Device for moving on water and/or air and/or ashore | |
CN106573668B (en) | High speed triangle hydroplaning single hull ship | |
US20050279878A1 (en) | Amphibian delta wing jet aircraft | |
CN203111502U (en) | Ship and submarine integrated airplane | |
US7281484B1 (en) | Multimission transonic hull and hydrofield | |
US20010045492A1 (en) | Triple hybrid water craft | |
GB2440320A (en) | Amphibious gyroplane | |
TWM578678U (en) | Water-surface flying boat with diving function | |
CN104002972A (en) | Triple warship submarine airplane | |
CN115649438B (en) | Multi-working-mode cross-medium aircraft | |
RU2776632C1 (en) | "tailless" flarecraft | |
CN102642597A (en) | Ship with hydrofoil wing | |
KR101785226B1 (en) | Air-Jet Propelled Ship has Hovercraft Function And The Composition Method |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: AEROART, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:APELOIG, JULIEN;DUMITRU, ALEXANDRU;GRIZEL, THOMAS;AND OTHERS;REEL/FRAME:020449/0609 Effective date: 20080104 Owner name: AEROART,FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:APELOIG, JULIEN;DUMITRU, ALEXANDRU;GRIZEL, THOMAS;AND OTHERS;REEL/FRAME:020449/0609 Effective date: 20080104 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |