Method for producing lateral ejection apparattii for helicopter or plane

The method for producing lateral ejection bed apparattii for helicopter or plane comprising, a bed for sleeping, rest, or emergencies attached to long, perpendicularly arranged track, guide rail or apparattii rocket catapulted propelled laterally out of an aircraft fuselage interior by a rocket catapult system;

• a monorail supporting track;
• an outer track, guide rail box to which any bed chassis or chassis' can be mounted, and ejected laterally, perpendicular to the horizontal longitudinal axis of an aircraft, and guided out of the path of a failed aircraft during ejection flight by two bottom rotor positioning tail fins slotted within an ejection monorails launcher platform legs mold, which fins or rudders at angle theta exit launcher platform leg slots, which is the maximum angle bottom-mounted tail fins can be turned and still exit the launcher platform leg slots;
• laterally ejectable bed apparattii which are aerodynamically able to navigate a life threatening aircraft debris field, by employing a track and guide rail construction of a monorail or monorails type, which uses a tubular airfoil form of monorail working as an airfoil or airfoils, i.e. wings, yaws, fins, flaps, rudders rotary positioned on the underside or underside and back of a lateral ejection bed apparattii, with air current flowing through the empty monorail track tube or tubes, insuring a steady and reliable emergence flight from said aircraft debris field;
• an ejection guide rail monorail roller truck and roller truck wheels construction, which is a self ventilating grid formation for ducting heat caused by fire or enemy fire, thereby said ventilating preventing or minimizing track freezing or similar failure of a guide track and rail system due to severe friction of metallic or alloy tracks, a track and guide rail expanding against one another from exposure to very high temperatures;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel or door, which design is prevented from recoiling into the path of the ejecting occupant and bed device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck and chest of the ejecting occupant, necessary for safe lateral equal access emergency exit ejection;
• three compartments for altitude appropriate parachutes;
• a hermetically sealed fuse box with a rip cord attached to a blast shield in which altitude sensitive sensors and fuses for opening the desired altitude appropriate parachutes are contained;
• with a gas powered rotor motor harness which is useful and effective, not just at moderate and/or high or tolerable altitudes, but during onboard fires, runway overshooting, very low or zero altitudes, or when over a body of water at a very low or tolerable altitude;
• whenever a motor harness sequencing completes;
• laterally ejecting bed apparattii at very low or zero altitudes, during aircraft fires, or water escape flotation, escapes that utilize a delayed bed apparattii separation from an occupant, using a gas powered rotor motor harness, so that the bed apparattii optionally controlled by a sequencing motor harness provides protective surfaces of a bed apparattii, flotation device located in a bed apparattii frame bottom or panel and/or airbags for the occupant as the laterally ejecting bed apparattii impacts the ground, water, air or other surface;
• minimizing the lateral force on a spine, neck, head and organs of an occupant by using side mounted pressure sensitive airbags or other concave, convex or bucket like restraints to create a rigid restraint and confine for the body, head, neck, spine and organs;
• or using any other bucket, convex or concave forms to restrain a human body during lateral ejection;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and bed device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck, spine and organs of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• a anterior side mounted ceramic and alloy or metallic backed blast shield and track support to which a pair of ejection catapult rockets are sealed with collar seals around rocket nozzle ends, until ignited and bursting collar seals with rocket exhaust pressure, thereby preventing a track and seat chassis from moving along an inner and/or supporting track and guide rail, failsafe main-lock and ignition release key nozzle collar;
• with a plane pneumatic rocket or other explosive charge method for a drop-down emergency panel or emergency door, and wing strut or support pneumatic removal or other said explosive charge means of wing strut, object or instrument removal from the emergency exit lateral ejection trajectory or pathway;
• a track support launcher platform, column, columns or center console support the lateral ejection bed apparattii at a functional and comfortable level and height for the occupant or occupants;
• with a single and/or double track, track and guide rail system arranged perpendicular to the horizontal longitudinal axis of an aircraft interior;
• in a single or double track construction, a number of rocket catapult chambers are used, which are correspondingly rocket catapult chambers, 1bb, 2bb and/or 3bb. Moreover the lateral ejection tool is sight-able by utilizing an aiming mechanism FIG. 1B, directed by a mechanized gear console handle 13B, and swing arm barrel sight bed swivel 14B for rotor positioning the occupant;
• only when existing fuselage area allows;
• actuated by cylindrical telescoping hydraulic arms 15B, and 16B, capable of realizing near perfect, or, perfect theoretical, lateral ejection respective of the real time forward motion (pressure) from velocity and position of a failed aircraft, by targeting preferred bed trajectories 9B, 10B, 11B, 12B, towards any quadrant within a sphere when right and left bipolar bed pairs (or optional opposite directions of lateral ejection) FIG. 1B, are configured in a commercial, medical/emergency, combat or high performance helicopter or plane;
• if said aiming mechanism operates independent of a robotic arm, which costs would perhaps become prohibitive except in commercial, medical/emergency, luxury aircraft or military designs in an exemplary embodiment;
• the aiming mechanism can work by pushing and pulling rotor positions on the lateral ejection track and guide rail with attached bed chassis, swinging from a center console 13B, containing a ceramic tile with alloy or metallic backing blast shield, and a swivel plate 14B, on which a single track, double track or triple monorail track are attached without overburdening the aircraft with additional weight;
• including attached simply to an aircraft floor or wall without a center console, riser or launcher platforms;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck, spine and organs of the ejecting occupant, necessary for safe lateral equal access emergency exit ejection;
• three compartments for altitude appropriate parachutes, inside ejection rigid framework back;
• a hermetically sealed fuse box with a rip cord attached to a blast shield in which altitude sensitive sensors and fuses for opening the desired altitude appropriate parachutes are contained;
• with a gas powered rotor motor harness which is useful and effective, not just at moderate and/or high or tolerable altitudes, but during onboard fires, runway overshooting, very low or zero altitudes, or when over a body of water at a very low or tolerable altitude;
• whenever a motor harness sequencing completes;
• laterally ejecting apparattii at very low or zero altitudes, during aircraft fires, or water escape flotation, escapes that utilize a delayed bed apparattii separation from an occupant, using a gas powered rotor motor harness, so that the bed apparattii optionally controlled by a sequencing motor harness provides protective surfaces of a bed apparattii, flotation device located in a bed apparattii frame bottom or panel and/or airbags for the occupant as the laterally ejecting apparattii impacts the ground, water, air or other surface;
• minimizing the lateral force on a spine, neck, head and organs of an occupant by either turning a bed apparattii using side mounted pressure sensitive airbags or other concave, convex or bucket like restraints to create a rigid restraint and confine for the body, head, neck, spine and organs;
• or using any other bucket, convex or concave forms to restrain a human body during lateral ejection;
• laterally ejectable bed apparattii which are aerodynamically able to navigate a life threatening aircraft debris field, by employing a track and guide rail construction of a monorail or monorails type, which uses a tubular airfoil form of monorail working as an airfoil or airfoils, i.e. wings, yaws, fins, flaps, rudders rotary positioned on the underside or underside and back of a lateral ejection bed apparattii, with air current flowing through the empty monorail track tube or tubes, insuring a steady and reliable emergence flight from said aircraft debris field;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck, spine and organs of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• a anterior side mounted ceramic and alloy or metallic backed blast shield and track support to which a pair of ejection catapult rockets are sealed with collar seals around rocket nozzle ends, until ignited and bursting collar seals with rocket exhaust pressure, thereby preventing a track and bed chassis from moving along an inner and/or supporting track and guide rail, failsafe main-lock and ignition release key nozzle collar;
• with a plane pneumatic rocket or other explosive charge method for a drop-down emergency panel or emergency door, and wing strut or support pneumatic removal or other said explosive charge means of wing strut, object or instrument removal from the emergency exit lateral ejection trajectory or pathway;
• a track support launcher platform, column, columns or center console support the lateral ejection bed apparattii at a functional and comfortable level and height for the occupant or occupants;
• an aircraft fuselage, with a, or, a set of bed chassis' mounted on triple monorails, and covered along the guide track end by a teflon mesh or teflon coated metallic mesh end cover;
• a monorail supporting track;
• an outer track, guide rail box to which any bed chassis or chassis' can be mounted, and ejected laterally, perpendicular to the horizontal longitudinal axis of an aircraft, and guided out of the path of a failed aircraft during ejection flight by two bottom rotor positioning tail fins slotted within an ejection monorails launcher platform legs mold, which fins or rudders at angle theta exit launcher platform leg slots, which is the maximum angle bottom-mounted tail fins can be turned and still exit a launcher platform leg slots;
• laterally ejectable bed apparattii which are aerodynamically able to navigate a life threatening aircraft debris field, by employing a track and guide rail construction of a monorail or monorails type, which uses a tubular airfoil form of monorail working as an airfoil or airfoils, i.e. wings, yaws, fins, flaps, rudders rotary positioned on the underside or underside and back of a lateral ejection apparattii, with air current flowing through the empty monorail track tube or tubes, insuring a steady and reliable emergence flight from said aircraft debris field;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck and chest of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• three compartments for altitude appropriate parachutes inside ejection rigid framework back;
• a hermetically sealed fuse box with a rip cord attached to a blast shield in which altitude sensitive sensors and fuses for opening the desired altitude appropriate parachutes are contained;
• with a gas powered rotor motor harness which is useful and effective, not just at moderate and/or high or tolerable altitudes, but during onboard fires, runway overshooting, very low or zero altitudes, or when over a body of water at a very low or tolerable altitude;
• whenever a motor harness sequencing completes;
• laterally ejecting bed apparattii at very low or zero altitudes, during aircraft fires, or water escape flotation, escapes that utilize a delayed seat, bed or apparattii separation from an occupant, using a gas powered rotor motor harness, so that the apparattii optionally controlled by a sequencing motor harness provides protective surfaces of a bed apparattii, flotation device located in a bed apparattii frame bottom or panel and/or airbags for the occupant as the laterally ejecting bed apparattii impacts the ground, water, air or other surface;
• minimizing the lateral force on a spine, neck, head and organs of an occupant by either turning apparattii using side mounted pressure sensitive airbags or other concave, convex or bucket like restraints to create a rigid restraint and confine for the body, head, neck, spine and organs;
• or using any other bucket, convex or concave forms to restrain a human body during lateral ejection;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck, spine and organs of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• a anterior side mounted ceramic and alloy or metallic backed blast shield and track support to which a pair of ejection catapult rockets are sealed with collar seals around rocket nozzle ends, until ignited and bursting collar seals with rocket exhaust pressure, thereby preventing a track and seat chassis from moving along an inner and/or supporting track and guide rail, failsafe main-lock and ignition release key nozzle collar;
• with a plane pneumatic rocket or other explosive charge method for a drop-down emergency panel or emergency door, and wing strut or support pneumatic removal or other said explosive charge means of wing strut, object or instrument removal from the emergency exit lateral ejection trajectory or pathway;
• a track support launcher platform, column, columns or center console support the lateral ejection bed apparattii at a functional and comfortable level and height for the occupant or occupants;
• an aircraft fuselage, with a, or, a bed chassis or set of bed chassis'mounted on triple monorails, load bearing triple monorails with two-hundred fifty-two roller trucks and three-hundred and four (or other number) of teflon or other fire resistant material coated, circumventing roller truck wheels attached to the inner rails monorail roller trucks grid, and a supporting track grid with eighty-four roller trucks and one-hundred-sixty-eight roller truck wheels (or other number);
• a monorail supporting track;
• an outer track, guide rail box to which any bed chassis or chassis' can be mounted, and ejected laterally, perpendicular to the horizontal longitudinal axis of an aircraft, and guided out of the path of a failed aircraft during ejection flight by two bottom rotor positioning tail fins slotted within an ejection monorails launcher platform legs mold, which fins or rudders at angle theta exit launcher platform leg slots, which is the maximum angle bottom-mounted tail fins can be turned and still exit the launcher platform leg slots;
• laterally ejectable bed apparattii which are aerodynamically able to navigate a life threatening aircraft debris field, by employing a track and guide rail construction of a monorail or monorails type, which uses a tubular airfoil form of monorail working as an airfoil or airfoils, i.e. wings, yaws, fins, flaps, rudders rotary positioned on the underside or underside and back of a lateral ejection bed apparattii, with air current flowing through the empty monorail track tube or tubes, insuring a steady and reliable emergence flight from said aircraft debris field;
• an ejection guide rail monorail roller truck and roller truck wheels construction, which is a self ventilating grid formation for ducting heat caused by fire or enemy fire, thereby said ventilating preventing or minimizing track freezing or similar failure of a guide track and rail system due to severe friction of metallic or alloy tracks, a track and guide rail expanding against one another from exposure to very high temperatures;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck and chest of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• three compartments for altitude appropriate parachutes;
• a hermetically sealed fuse box with a rip cord attached to a blast shield in which altitude sensitive sensors and fuses for opening the desired altitude appropriate parachutes are contained;
• with a gas powered rotor motor harness which is useful and effective, not just at moderate and/or high or tolerable altitudes, but during onboard fires, runway overshooting, very low or zero altitudes, or when over a body of water at a very low or tolerable altitude;
• whenever a motor harness sequencing completes;
• laterally ejecting bed apparattii at very low or zero altitudes, during aircraft fires, or water escape flotation, escapes that utilize a delayed bed apparattii separation from an occupant, using a gas powered rotor motor harness, so that the bed apparattii optionally controlled by a sequencing motor harness provides protective surfaces of a bed apparattii, flotation device located in a bed apparattii frame bottom or panel and/or airbags for the occupant as the laterally ejecting bed apparattii impacts the ground, water, air or other surface;
• minimizing the lateral force on a spine, neck, head and organs of an occupant by either turning a seat or apparattii using side mounted pressure sensitive airbags or other concave, convex or bucket like restraints to create a rigid restraint and confine for the body, head, neck, spine and organs;
• or using any other bucket, convex or concave forms to restrain a human body during lateral ejection;
• a bed chassis able to eject laterally by the opening of an emergency pneumatic rocket propelled fixed greater sliding door panel, in which, a operational conventional hinged door is housed;
• an emergency fixed greater sliding door panel with pneumatic rockets located at the top and bottom of the sliding panel, which door or panel is prevented from recoiling into the path of the ejecting occupant and bed device by spring loaded latch catches attached to the aircraft frame on the outside of a fuselage and pushed into a locked and rigid position by the pneumatic rocket propelled sliding emergency door or panel;
• two sets of dual airbags for positioning the legs and torso and protecting the head, neck, spine and organs of the ejecting occupant, and which are mandatory for safe lateral equal access emergency exit ejection;
• a anterior side mounted ceramic and alloy or metallic backed blast shield and track support to which a pair of ejection catapult rockets are sealed with collar seals around rocket nozzle ends, until ignited and bursting collar seals with rocket exhaust pressure, thereby preventing a track and seat chassis from moving along an inner and/or supporting track and guide rail, failsafe main-lock and ignition release key nozzle collar;
• with a plane pneumatic rocket or other explosive charge method for a drop-down emergency panel or emergency door, and wing strut or support pneumatic removal or other said explosive charge means of wing strut, object or instrument removal from the emergency exit lateral ejection trajectory or pathway;
• a track support launcher platform, column, columns or center console support the lateral ejection bed apparattii at a functional and comfortable level and height for the occupant or occupants.

An aircraft fuselage for lateral ejection apparattii which is enlarged and has additional supporting aircraft fuselage struts and structural supports installed in the fuselage frame structure with slender tempered glass panes inserted between the reinforcing struts and structural supports added to the fuselage frame in order to accommodate the lateral ejection apparattii with the same near number of aircraft seats, and improved or near same field of view for the aircraft pilots, crew, passengers or other occupants;

• which safe, stable and efficient process, methodology, devices and apparattii, may eject all occupants of aircraft, be they ejected from helicopters or planes, or, like action crossovers, such as gyroplanes or spacecraft designed to fly like planes, and are laterally ejected from an imperiled and life threatening said aircraft;
• providing laterally aligned escape devices for all types of private, business, commercial, government and general aviation aircraft, which lateral ejection apparattii are stable, reliable, simple, efficient, safe and effective at extracting aircraft occupants from life threatening aircraft, whether they are sitting in a seat or lying down in a bed, or in an aircraft cabin or cockpit;
• which method and process of escaping life threatening aircraft by lateral rocket catapult propulsion and a unique advanced triple (or number larger than 2) parachute configuration to extract pilots, passengers, emergency and medical patients in seats, beds or apparattii from life threatening aircraft by configuring rigid ejection apparattii framework perpendicular to aircraft longitudinal horizontal axis and propelling said occupant or occupants out the side of said aircraft by a rocket catapult system, past an emergency pneumatic rocket actuated sliding aircraft door or panel, wing strut, support or other propelled object in the lateral ejection pathway, so then an automatic parachute system can deploy, and lower or recover the laterally ejected occupant or occupants to the ground or surface;
• with teflon or other fire resistant material, primarily on the outer surface, but not limited to the outer surfaces of a seat or bed or apparattii right and left side mounted, pressure sensitive airbags, and roller truck wheels, and track mesh end cover to prevent fire or enemy fire from burning or hitting the ejected occupant or occupants, or igniting the guide track or igniting the roller truck wheels;
• such that an advantageous arrangement combining the advantages of conventional jet aircraft vertically seeking ejection apparatus with the advantages of lateral ejection apparattii and process is made possible;
• such that rotor positioning apparattii and aircraft occupants for lateral ejection from an upright, rolled or rolling aircraft fuselage is possible;
• when aircraft seats and their occupants can be aligned and usually are in commercial and private aircraft, along the edge of the planes right and left latitudes, and ejected laterally through the side wall, door, canopy openings or opening or space;
• thereby, when an aircraft is in an upright posture minimizing both the applied force of gravity pulling down on the seat and seat occupant and distance, angle and altitude of recovery and time interval between rocket power ignition and rocket power off during the apparatus transversing from point A to point B;
• so to be removed by the lateral ejection apparattii powered by a rocket catapult and moving from point A to point B along the same or near same gravitational plane along a preferred angle of descent and recovery when ejected laterally from a plane in a dangerous or life threatening descent;
• so that an automatic, individual parachute system can be automatically activated and deployed to break and stabilize the plane occupant(s) descent to a surface, after ejecting laterally from a plane;
• with separately falling seats and parachutists in aircraft that are laterally ejected perpendicular to the horizontal longitudinal axis of an aircraft fuselage in seat rows aligned in aisles on a reloading chain and gas engine powered track and guide rail lateral ejection apparattii are also constructed for laterally ejecting aircraft occupants who are arranged in rows and aisles.