Abstract: The reusable space launch system has a first stage vehicle or aerospacecraft, a second stage vehicle or reusable spacecraft and a third stage vehicle or reusable orbit transfercraft. All the stages have the basic aerodynamic vehicle elements of a fuselage, wings, and tail, with the incorporation of control surfaces to supply lift, stability and control. The aerospacecraft is configured to use ejector ramjet engines for powered flight and includes equipment to capture air to supplement oxidizer for the ejector ramjet engine during take-off and extreme high altitude In order to optimize aerospacecraft performance in a pull up movement to exit the sensible atmosphere, the aerospacecraft may include auxiliary ascent rocket engines. The aerospacecraft payload bay is accessed by nose load re-closable payload fairings. The reusable spacecraft is mounted on tracks on each lower side of the aerospacecraft payload bay.

Abstract: The orbital launch system is a three stage vehicle to launch orbital payloads. The system uses a turbofan powered aircraft as the first stage with an aerospacecraft attached by an underling aerospacecraft pylon at an aircraft engine mount for carriage. The aerospacecraft is the second stage and is powered by an ejector ramjet engine. The aerospacecraft has a cargo bay with cargo bay doors in its midsection. A booster rocket with payload is launched from the cargo bay by use of an ejection system. Normally the payload is mounted on a rocket booster to be placed in the proper orbit. The orbital launch system may also have a parachute drop recovery system to recover the booster rocket after it deorbits.

Abstract: A projectile which includes multiple warheads separated one from another within a casing, each warhead having its own independent detonator. The warheads are arranged in spaced relationship along the longitudinal axis of the casing, and the detonators are linked with a fuzing mechanism located at the forward region of the casing. Upon reaching the target, the rearmost warhead in the projectile is detonated and the remaining warheads are then detonated sequentially forwardly, ad seriatim, by the fuzing mechanism.

Abstract: A novel, high-altitude, solar powered aircraft, capable of staying aloft at high altitudes for many months or even years to conduct around the clock surveillance and/or reconnaisance, includes a forward wing with solar energy capturing cells, a rear wing, inflated pontoons for keeping the aircraft aloft, suspension wires attached to the pontoons, a gondola suspended from and connected to the wires, control apparatus for moving the gondola along the wires, shifting the weight of the aircraft and thereby enabling banking to optimize exposure of the solar cells to the rays of the sun. The gondola preferably contains a sensor suite, power generating and storage apparatus, and synthetic aperture radar imaging apparatus.

Abstract: A crew protection system designed to isolate an aircraft crew and provide a means for safely evacuating an aircraft, particularly hypersonic vehicles, in emergency situations. The crew compartment is designed within the forebody of the main vehicle. The forebody is designed so as to separate cleanly from the main vehicle as by generation of a circumferential structural break, in the event of a catastrophic failure or explosion of the main vehicle fuel tank. In the event of such an uncommanded failure of the main tank and propellant combustion, resulting in the above noted structural failure, the resultant pressure impulse thrusts the forebody containing the crew compartment clear from the remainder of the vehicle. The provision of a system of baffles in the forebody between the crew compartment and the fuel tank, and the shape of the forebody and the materials used in its construction mitigate the effects of the blast pressure impulse on the crew.

Abstract: An array of plane mirrors allows forward view of space volumes normally obscured by craft structure without the use of forward facing transparencies. In submerged cockpit aerospace craft, such a system may utilize a deployable upper mirror to reflect such space volumes onto a control mirror for the pilot's use in takeoff and landing operations, allowing the pilot the same visual cues as would be available through a forward facing transparency in front of an apaprent eye position external to the cockpit.

Abstract: A method and apparatus for maintaining useful conciousness and reducing the risk of injury for a subject exposed to high levels of acceleration while in a vehicle. A buoyancy force suit is provided for supporting the subject with a buoyancy force. The buoyancy force suit includes at least two layers of flexible material, each layer being relatively impermeable to a substantially incompressible fluid locatable in a space between the layers. The suit fits over substantially the entire subject, including the subject's neck. A fluid reservoir is provided for maintaining a constant fluid level within the buoyancy force suit during acceleration. The fluid reservoir is supported at substantially the subject's eye level for maintaining an optimal fluid pressure gradient for ensuring an efficient blood supply to the subject's brain. Means are provided for securely suspending the buoyancy suit within the vehicle.

Abstract: A high "g" protection system for a crewmember of an aircraft includes a seat and an upper torso support. The upper torso support is preferably secured to the crewmember's suit and to the seat. The torso support has a support plate and a support member which allow the crewmember to be supported and restrained while in a leaned forward or crouched position while enhancing the crewmember's tolerance to "g" forces. Another embodiment of the invention uses a pair of approximately positioned armrests to provide torso support. The seat is provided with a repositionable seat pan which allows the crewmember's knees to be raised bringing him into a more crouched position or, conversely, allows the crewmember's knees to be lowered reducing the crewmember's angle of crouch, as may be desired.

Abstract: A seat system for a crewmember of an aircraft is disclosed which provides support and restraint to the crewmember while in a crouched as well as an erect position. The crewmember is secured by means of a strap harness to an insert which is positioned behind and in contact with the crewmember's back. The insert is rotatably connected to the seat providing multi-axis rotation to the insert relative to the seat. The insert's multi-axis rotation allows the crewmember to turn in the seat while secured to the insert. The insert also has a limited degree of translational movement toward as well as away from its connection to the seat; this allows the crewmember to lean forward, backward and laterally in the seat while still secured to the insert. A mechanism locks the insert into a desired forwardly inclined position. Instead of an insert, however, the crewmember's upper torso may be directly connected, at the crewmember's back, to the seat by means of a strap system or a rigid extendable support member.