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Check Out UTOPIA

Thu Jan 24, 2013 4:31 am by Admin



Utopia Forum is almost complete and is now ready for all new members and visitors.

The forum is a little different to here as it uses a single page forum which puts all the topics on one page with important threads globally pinned at the top of the page.

Like i said we are ALMOST complete but we are still playing around and moving things about so please bare …

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Picture Evidence Inside a Chemtrail Plane

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Picture Evidence Inside a Chemtrail Plane

Post  Admin on Fri Apr 27, 2012 8:19 pm

Is this picture the first actual evidence of the highly controversial Chemtrail Planes? The number clearly shown here corresponds to this >> A method and apparatus for aerial fire suppression utilizing a potable fire retardant chemical dispensing system, readily adaptable, without extensive aircraft modification, to various makes of aircraft, for dispensing current types of forest and range fire fighting chemicals. The aerial delivery system is self contained and reusable. It enables cargo/utility aircraft to carry and dump a load, under control. The aerial delivery system is capable of attachment at the wing box, pressurized delivery from the nozzles, and nozzles directed straight downward.

Inventors: John C. Hale, Christopher B. Harris, Daniel A. Kottman
Original Assignee: Evergreen International Aviation, Inc.
Primary Examiner: Michael J. Carone
Secondary Examiner: Benjamin P Lee
Attorneys: Brian L. Johnson, George C. Rondeau, Jr., Davis Wright Tremaine LLP
Current U.S. Classification: 244/136; 137/899.2; 239/171; 244/118.1

View patent at USPTO
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Citations
Cited Patent Filing date Issue date Original Assignee Title
US1911431 14 May 1931 30 May 1933 IKEIGATION APPARATUS
US2242705 6 Feb 1939 20 May 1941 WATER SPRAYING AIRPLANE
US2493017 5 Aug 1946 3 Jan 1950 GRID SPRAY NOZZLE
US2926688 8 May 1956 1 Mar 1960 PRECISE CONTROL DISTRIBUTION OF AIRPLANE FUEL STORES
US3547000 1 Dec 1970 SYSTEM FOR DROPPING STORED MATERIAL FROM
US3995328 13 Dec 1974 7 Dec 1976 The Boeing Company Vacuum toilet system
US4172499 5 Dec 1977 30 Oct 1979 Canadair Limited Powder and water mixing and dropping system onboard an aircraft
US4202061 29 Dec 1978 13 May 1980 The Boeing Company Lavatory wastewater disposal system for aircraft
US4208949 3 May 1978 24 Jun 1980 Boeing Commercial Airplane Company Missile carrier airplane
US5261440 26 Jan 1993 16 Nov 1993 Deutsche Aerospace Airbus GmbH Water supply system for an aircraft
US5655732 9 Mar 1995 12 Aug 1997 Daimler-Benz Aerospace Airbus GmbH Apparatus for draining waste water from aircraft
US5769124 12 Mar 1997 23 Jun 1998 Daimler-Benz Aerospace Airbus GmbH Fresh water supply system for an aircraft
US6622966 23 Sep 2002 23 Sep 2003 System for extinguishing wild fires and method therefor
US20040016848 25 Jul 2002 The Boeing Company STORE EJECTION SYSTEM WITH REPLACEABLE PRESSURE VESSEL
Referenced by
Citing Patent Filing date Issue date Original Assignee Title
US7753314 5 Oct 2007 13 Jul 2010 L-3 Communications Integrated Systems, L.P. Systems and methods for aerial dispersion of materials
US7819362 1 Mar 2007 26 Oct 2010 Evergreen International Aviation, Inc. Enhanced aerial delivery system
US8066223 15 Jul 2010 29 Nov 2011 Evergreen International Aviation, Inc. Enhanced aerial delivery system
US8079551 24 Aug 2010 20 Dec 2011 Evergreen International Aviation, Inc. Enhanced aerial delivery system
Claims
1. A system for an aircraft having wings with flaps having trailing edges, the flaps having an extended position for relatively slow flight of the aircraft, the aircraft having a fuselage with a longitudinal dimension, the aircraft having a nose and a tail, the nose being forward along the longitudinal dimension of the tail and the tail being aft along the longitudinal dimension of the nose, the aircraft having a longitudinal center of gravity located with respect the longitudinal dimension of the fuselage, the fuselage having a forward most center of gravity point CGf at a particular location along the longitudinal dimension of the fuselage and having an aft most center of gravity point CGa at another particular location along the longitudinal dimension of the fuselage aft of the forward most center of gravity point, the aircraft having performance requirements that dictate that the longitudinal center of gravity remain at or aft of the forward most center of gravity limit point, CGf, and that the longitudinal center of gravity remain at or forward of the aft most center of gravity limit point CGa, the aircraft having a wheel system for ground support of the aircraft, the fuselage having a bottom side configured to be the side of the fuselage nearest to a runway when the aircraft is being supported on the runway by the wheel system, the aircraft having a plurality of seat tracks configured to be removably coupled to passenger seats to secure the passenger seats to the aircraft when the passenger seats are coupled to the seat tracks, the system comprising:

a plurality of material tanks configured to each contain material, the plurality of material tanks located inside the fuselage of the aircraft, at least one of the plurality of material tanks located aft along the longitudinal dimension of the fuselage of another one of the plurality of material tanks;
at least one pressurized tank configured to contain a gas under pressure of at least 50 pounds per square inch (p.s.i.), the at least one pressurized tank coupled to the plurality of material tanks such that the gas when released from the pressurized tank assists in releasing material from containment within each of the plurality of material tanks; and
a plurality of outlets coupled to the material tanks, the outlets extending from inside the fuselage and through the bottom side of the aircraft in a direction approximately perpendicular to the longitudinal dimension of the fuselage, the outlets configured to conduct material released from containment within the plurality of material tanks to be projected outside the fuselage of the aircraft in a direction approximately perpendicular to the longitudinal dimension of the fuselage, the outlets coupled to portions of at least some of the plurality of seat tracks of the aircraft to secure the outlets to the aircraft and sufficiently distributing thrust loads to the aircraft resulting from projection of the material through the outlets outside of the fuselage of the aircraft, the outlets approximately located along the longitudinal dimension of the fuselage immediately aft of the longitudinal location of the trailing edge of at least a pair of the flaps when the at least a pair of the flaps are in their extended position, the at least one pressurized tank and the material tanks so sized and positioned within the fuselage such that the longitudinal center of gravity is located at or between the forward most center of gravity limit point, CGf and the aft most center of gravity limit point CGa along the longitudinal dimension of the fuselage as the at least one pressurized tank releases the gas into the material tanks and as the material tanks empty in the predetermined order.
2. The system of claim 1 wherein the material tanks are configured to contain material selected from the group consisting of at least a water, gel, decontamination compound, weather modification compound, oil spill treatment compound, and a firefighting compound.

3. A system for an aircraft having wings, the aircraft having a fuselage with a longitudinal dimension, the aircraft having a nose and a tail, the nose being forward along the longitudinal dimension of the tail and the tail being aft along the longitudinal dimension of the nose, the aircraft having a wheel system for ground support of the aircraft, the fuselage having a bottom side configured to be the side of the fuselage nearest to a runway when the aircraft is being supported on the runway by the wheel system, the aircraft having a plurality of seat tracks configured to be removably coupled to passenger seats to secure the passenger seats to the aircraft when the passenger seats are coupled to the seat tracks, the system comprising:

a material tank configured to contain material and located inside the fuselage of the aircraft;
a pressurized tank configured to contain a pressurized gas, the pressurized tank so coupled to the material tank that the pressurized gas, when released from the pressurized tank, assists in releasing material from containment by the material tank; and
a plurality of outlets extending from inside the fuselage through the bottom side of the aircraft and so coupled to the material tank to receive material from containment by the material tank and to project the released material outside of the fuselage of the aircraft, the outlets coupled to portions of at least some of the plurality of seat tracks of the aircraft to secure the outlets to the aircraft and sufficiently distributing thrust loads to the aircraft resulting from projection of the material through the outlets outside of the fuselage of the aircraft.
4. A system comprising:

an aircraft having wings, the aircraft having a fuselage with a longitudinal dimension, the aircraft having a nose and a tail, the nose being forward along the longitudinal dimension of the tail and the tail being aft along the longitudinal dimension of the nose, the aircraft having a wheel system for ground support of the aircraft, the fuselage having a bottom side configured to be the side of the fuselage nearest to a runway when the aircraft is being supported on the runway by the wheel system, the aircraft having a plurality of seat tracks configured to be removably coupled to passenger seats to secure the passenger seats to the aircraft when the passenger seats are coupled to the seat tracks;
a material tank configured to contain material and located inside the fuselage of the aircraft;
a pressurized tank configured to contain a pressurized gas, the pressurized tank so coupled to the material tank that the pressurized gas, when released from the pressurized tank, assists in releasing material from containment by the material tank; and
a plurality of outlets extending from inside the fuselage through the bottom side of the aircraft and so coupled to the material tank to receive material from containment by the material tank and to project the released material outside of the fuselage of the aircraft, the outlets coupled to portions of at least some of the plurality of seat tracks of the aircraft to secure the outlets to the aircraft and sufficiently distributing thrust loads to the aircraft resulting from projection of the material through the outlets outside of the fuselage of the aircraft.
5. A system for an aircraft having wings, the aircraft having a fuselage with a longitudinal dimension, the aircraft having a nose and a tail, the nose being forward along the longitudinal dimension of the tail and the tail being aft along the longitudinal dimension of the nose, the aircraft having a wheel system for ground support of the aircraft, the fuselage having a bottom side configured to be the side of the fuselage nearest to a runway when the aircraft is being supported on the runway by the wheel system, the aircraft having a plurality of seat tracks configured to be removably coupled to passenger seats to secure the passenger seats to the aircraft when the passenger seats are coupled to the seat tracks, the system comprising:

a material tank configured to contain material and located inside the fuselage of the aircraft; and
a plurality of outlets extending from inside the fuselage through the bottom side of the aircraft and so coupled to the material tank to receive material from containment by the material tank and to project the released material outside of the fuselage of the aircraft, the outlets coupled to portions of at least some of the plurality of seat tracks of the aircraft to secure the outlets to the aircraft and distribute thrust loads to the aircraft resulting from projection of the material through the outlets outside of the fuselage of the aircraft.

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