US3913704A - Air cushion vehicle cell having rigid base - Google Patents

Air cushion vehicle cell having rigid base Download PDF

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Publication number
US3913704A
US3913704A US355510A US35551073A US3913704A US 3913704 A US3913704 A US 3913704A US 355510 A US355510 A US 355510A US 35551073 A US35551073 A US 35551073A US 3913704 A US3913704 A US 3913704A
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US
United States
Prior art keywords
vessel
air cushion
cell
rigid base
air
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.)
Expired - Lifetime
Application number
US355510A
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English (en)
Inventor
Wilfred James Eggington
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ingalls Shipbuilding Inc
Original Assignee
Litton Systems Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Litton Systems Inc filed Critical Litton Systems Inc
Priority to US355510A priority Critical patent/US3913704A/en
Publication of USB355510I5 publication Critical patent/USB355510I5/en
Application granted granted Critical
Publication of US3913704A publication Critical patent/US3913704A/en
Assigned to INGALLS SHIPBUILDING, INC. reassignment INGALLS SHIPBUILDING, INC. ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: LITTON SYSTEMS, INC. A CORP. OF DE
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion

Definitions

  • FIG. 1 Illustrates a perspective view of the invention in its normal environment
  • FIG. 2 Illustrates a fragmentary side elevational view of the preferred embodiment of the invention
  • FIG. 3 Illustrates a plan fragmentary view of the invention in the preferred embodiment.
  • FIG. 4 Illustrates an alternative embodiment of the invention.
  • skirt 12 DESCRIPTION OF THE PREFERRED EMBODIMENT To achieve the desired end, a new construction of a skirt 12 has been discovered for placement about the lower periphery of the conventional Hovercraft vessel 10, reference being had to FIG. 1.
  • the air cushion 18 is surrounded on the periphery of the vessel by skirt 12.
  • this skirt 12 will be constructed, at least on its forward bow and stern peripheral sections, with cells to be described in more detail below.
  • Such new construction is explained and understood more clearly when the view along line 22 in FIG. 1, shown in detail in FIG. 2, is understood.
  • an air-seal cell 20 is shown depending below the outside edge or periphery of the raft 16 of the vessel 10.
  • the cell 20 consists of flexible walls 22 which enclose the cell 20.
  • the cells 20 are thus freely capable of vertical compression and extension.
  • the walls 22 are disposed in airtight relationship with the underside of the raft 16.
  • the lower end of the cell is comprised of a rigid seal base 30 which is in airtight coupling with the flexible walls 22.
  • the forward end of wall 22 extends to a distance shorter than the rearward end of wall 22 so that when the forward cells 24"are extended, the forward edge of the rigid seal base 30 maintains a higher altitude relative to the water level 28 than does the rear edge of the rigid base 30.
  • the orifice 32 is constructed so that the orifice lip of the rear section of the rigid base 30 overlaps the orifice lip of the forward section of the rigid base 30, for reasons to be described in more detail below.
  • FIGS. land 3 While in FIGS. land 3 the side skirts 12 of the vessel 10 are shown as being solid, it is understood that the cellular construction of the bow peripheral portions can be substitutedtherefor.
  • the same rigid base as described above and in FIG. 2 could be provided, i.e., having a higher forward; edgerelative to the rearward edge.
  • Design considerations should dictate that there be slightly higher altitude on the forward edge of rigid base 30 than on the following edge.
  • a cell system having direct pneumatic contact between adjacent cells is preferred.
  • the individual cells 20 may be pneumatically separate from each other, and individually supplied with air under pressure.
  • Air to the cells 20 would be supplied through conduits 52 from air coinpressor 50, as shown in FIG. 3.
  • Thecells would then be provided with inter-pneumatic contact for air pressure equalization among the cells, if that is desired.
  • the cells 20 are in airtight relationship to each other, such that no air from the central air cushion 18 will escape therebetween.
  • air cells 20 having adjacent cell direct pneumatic contact could be arranged to receive, additionally, air under pressure from conduits 52 individually at the same time.
  • a skirt 34 which depends downwardly from the forward edge of the rigid base 30.
  • This skirt 34 can be flexible, but should be allowed to pivot rearwardly from its connection with the rigid seal base 30.
  • a connection 35 such as a wire perforated plane, or the like may be provided to restrain the skirt 34 from pivoting forwardly.
  • a control tie 36 extends from the rigid seal base 30 to power control means within the vessel 10, not shown.
  • the operator or captain of the surface effect ship can either manually, or by remote automatic powered means, control the vertical movement of the control tie 36, and consequently the vertical disposition of rigid seal base 30.
  • the control tie 36 is optional to the performance and practice of this invention, as will be shown.
  • FIG. 4 An optional alternative to the configuration of rigid seal base 30 is shown in FIG. 4. As shown, the base sections 31 and 33 can be progressively canted so as to ensure good planing characteristics in all anticipated water surface conditions.
  • the new skirt cell operates in thefollowing manner.
  • Compressed air from an air source 50 is conveyed throughair ducts 52 into a cell 20, as
  • the air pressure acts against the inside of walls 22 and against the upper side of base so to extend thewalls 22 and the base 30 to their optimum extension, asshown by arrows 44.
  • the water 28 provides an upward force against base 30 at the bases rearward end, as indicated by arrow 46.
  • the air withincell 20, indicated generally by arrows 42, 44, acts against the air pressure from the air cushion 18 on the rearward flexible wall 22, against the water pressure on rigid base 30, indicated by arrow 46, and, against the normal, inertial atmospheric air resistance in the forward flexible wall 22 by the forward movement of the vessel 10, indicated generally by arrows 48.
  • the rigid base 30 skims or planes across the water surface 28 when the vessel 10 is in transport.
  • Air pressure 42, 44 maintains the base 30 extended from the vessel 10 and in contact at its rearward end with the water surface 28.
  • skirt 34 retreats inwardly to accommodate the wave.
  • Air pressure normally found between the water level 28 and the forward edge of the base 30 increases so as to form a natural, upward.
  • An air cushion vessel having a periphery about a.
  • each said cell including a flexible wall and capable. 4 of vertical compression, and fixed at its upper end to said periphery of said vessel, said cell being; pneumatically connected to a source of air pres sure;
  • each said cellfurther including a rigid base oriv ented at a planing angle relative to the desired di rection of movement of the vehicle, said rigid base having an orifice therein for allowing air to escape to below said base and d. at least a portion of said rigid base disposed in substantial contact with a surface over which said vessel transports.
  • said cell further comprising a rigid, selectively controllable tie rod fixed at one end of said rigid base, said tie rod disposed at a.
  • the vessel as claimed in claim 1 further including atleast a second said air cushion cell disposed depending from at least a stern section of said periphery forming'a stern seal for said larger, centralair cushion.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Vibration Prevention Devices (AREA)
US355510A 1973-04-30 1973-04-30 Air cushion vehicle cell having rigid base Expired - Lifetime US3913704A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US355510A US3913704A (en) 1973-04-30 1973-04-30 Air cushion vehicle cell having rigid base

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US355510A US3913704A (en) 1973-04-30 1973-04-30 Air cushion vehicle cell having rigid base

Publications (2)

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USB355510I5 USB355510I5 (enrdf_load_stackoverflow) 1975-01-28
US3913704A true US3913704A (en) 1975-10-21

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4658926A (en) * 1985-02-11 1987-04-21 The United States Of America As Represented By The Secretary Of The Navy Seal for air cushion vehicle

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3267882A (en) * 1963-07-31 1966-08-23 Hovercraft Dev Ltd Load carrying unit
US3272272A (en) * 1963-06-21 1966-09-13 Hovercraft Dev Ltd Air cushion vehicles having vertical collapsible walls
US3363718A (en) * 1964-12-01 1968-01-16 Hovercraft Dev Ltd Skirts for gas-cushion vehicles
US3473503A (en) * 1968-02-07 1969-10-21 Fred C Gunther Air-supported marine vehicle
US3504755A (en) * 1967-07-19 1970-04-07 Hovercraft Dev Ltd Gas-cushion vehicles
US3631938A (en) * 1968-05-01 1972-01-04 Aerojet General Co Fluid cushion cells for fluid cushion vehicles
US3700065A (en) * 1971-08-30 1972-10-24 Aerojet General Co Fluid cushion cells for fluid cushion vehicles
US3752253A (en) * 1970-04-23 1973-08-14 Air Cushion Equip Flexible skirts for gas-cushion supported equipment

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3272272A (en) * 1963-06-21 1966-09-13 Hovercraft Dev Ltd Air cushion vehicles having vertical collapsible walls
US3267882A (en) * 1963-07-31 1966-08-23 Hovercraft Dev Ltd Load carrying unit
US3363718A (en) * 1964-12-01 1968-01-16 Hovercraft Dev Ltd Skirts for gas-cushion vehicles
US3504755A (en) * 1967-07-19 1970-04-07 Hovercraft Dev Ltd Gas-cushion vehicles
US3473503A (en) * 1968-02-07 1969-10-21 Fred C Gunther Air-supported marine vehicle
US3631938A (en) * 1968-05-01 1972-01-04 Aerojet General Co Fluid cushion cells for fluid cushion vehicles
US3752253A (en) * 1970-04-23 1973-08-14 Air Cushion Equip Flexible skirts for gas-cushion supported equipment
US3700065A (en) * 1971-08-30 1972-10-24 Aerojet General Co Fluid cushion cells for fluid cushion vehicles

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4658926A (en) * 1985-02-11 1987-04-21 The United States Of America As Represented By The Secretary Of The Navy Seal for air cushion vehicle

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Publication number Publication date
USB355510I5 (enrdf_load_stackoverflow) 1975-01-28

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AS Assignment

Owner name: INGALLS SHIPBUILDING, INC., 360 NORTH CRESCENT DRI

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:LITTON SYSTEMS, INC. A CORP. OF DE;REEL/FRAME:004741/0178

Effective date: 19870717

Owner name: INGALLS SHIPBUILDING, INC.,CALIFORNIA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:LITTON SYSTEMS, INC. A CORP. OF DE;REEL/FRAME:004741/0178

Effective date: 19870717

STCF Information on status: patent grant

Free format text: PATENTED FILE - (OLD CASE ADDED FOR FILE TRACKING PURPOSES)