Olin Corporation

Kistler Aerospace Corporation

Steven C Knowles

George E Mueller

William W Smith

Thomas G Johnson

Walter P Kistler

Thomas C Taylor

George W Butler

David B Cochran

Adam P Bruckner

Richard A Bailey

Charles D Limerick

Dale D Myers

Henry O Pohl

Aaron Cohen

Richard H Kohrs

Alan E Kull

Jason E Andrews

Chris McLain

Richard Warwick

Joseph W Cuzzupoli

Allan S Hill

David O King

An orbital vehicle ( ) having a propulsion module ( ) and a logistics module ( ). The logistics module includes a generally cylindrical outer shell ( ) with first and second ends. An openable cover ( ) is coupled with the outer shell at the first end, thereby providing access to the interior of the logistics module. The second end is adapted to couple to the propulsion module. A cargo container ( ) is disposed generally within the outer shell, the cargo container including a berthing mechanism ( ) disposed to be accessible when the cover is opened. A retractable grapple fixture ( ) is provided on the logistics module, selectively positionable between an extended position and a retracted position. When the grapple fixture is in the extended position a grapple shaft ( ) can be accessed to secure the orbital vehicle. When the grapple fixture is retracted, it is enclosed within the orbital vehicle.

Logistics module system and method

A two-stage wingless reusable aerospace vehicle having upper and lower stages that take off from a take-off area and separate at a separation point along a first trajectory. The separation forces are generated by air retained between the upper and lower stages, which is at a pressure higher than ambient pressure at the separation point. The lower stage is then propelled along a return trajectory to a landing area. After separation from the lower stage, the upper stage continues to an Earth orbit for deployment of a payload. After deploying the payload, the upper stage moves out of the Earth orbit, re-enters the Earth's atmosphere, and returns to the take-off and landing area. The upper and lower stages are powered by liquid oxygen and kerosene engines. The aerospace vehicle is transported to a take-off area by a transport vehicle having a first fixed carriage and a second translatable carriage that is adapted to move the upper stage relative to the lower stage for assembly of the aerospace vehicle while in the horizontal position. The transport vehicle then pivots the aerospace vehicle from the horizontal to the vertical position for launching.

Two-stage reusable earth-to-orbit aerospace vehicle and transport system

There is provided a system for the manufacture of a diamond film. A plasma generator generates a hydrogen atom containing plasma stream into which a hydrocarbon containing gas is fed. The plasma dissociates the hydrocarbon to carbon radicals and carbon which are deposited on a substrate where the carbon crystallizes to a diamond film. The efficiency of the system is increased by heating the hydrogen source gas prior to generation of the plasma. Other means to increase the effectiveness of the system include using a plurality of plasma streams and shaping the plasma stream, A low internal strain, high quality optical film is generated by depositing the carbon on a substrate supported by a heat sink having nonuniform thermal conductivity such that the thermal gradient across the surface of the heat sink is less than about 8.degree. C./centimeter.

Apparatus for synthesizing diamond films utilizing an arc plasma

An arcjet thruster has a constrictor and nozzle defining an arc chamber. The constrictor has an insulator and an anode. The constrictor defines a subsonic-to-supersonic transition zone axially coextensive with the inculator and anode. The anode is disposed side-by-side with the insulator and located upstream therefrom. A rod defines a cathode spaced from the anode by a gap. An electrical potential is applied to the anode and cathode to generate an electrical arc in the chamber which produces thermal heating of propellant gases flowing through the chamber and expansion thereof through the nozzle. Location of the insulator downstream from the anode causes diffusion and attachment of the arc to occur at the region of the anode in the constrictor and prevents movement of the arc diffusion and attachment region downstream past the insulator to the nozzle in response to propellant gas mass flow variations through the constrictor. The thruster can also include an expansion and compression cavity in the arc chamber to provide a low pressure region at the anode for arc attachment and diffusion. Further, a zone of thermal and mechanical isolation can be provided between the anode and insulator to reduce the temperature at the insulator and displace its location farther away from the region of arc attachment and diffusion at the anode. Still further, a passage is defined through the insulator to provide a path for secondary flow of propellant gas into the chamber downstream of the arc attachment and diffusion region in order to reclaim frozen flow losses.

Arcjet thruster with improved arc attachment for enhancement of

A non-erosive arcjet starting control system and method are provided in combination with an arcjet thruster which includes an anode, a cathode and a gap defined therebetween. The starting control system and method include the operative steps of, first, actuating a valve in a propellant gas feed path to an opened position thereby permitting flow of propellant gas at a predetermined pressure into the thruster past the gap therein, second, applying to the anode and cathode an electrical potential of a predetermined magnitude being less than that required to generate an electrical arc across the gap through propellant gas at the predetermined flow pressure and, concurrently, actuating the valve to its closed position thereby preventing flow of propellant gas into the thruster past the gap and thereby lowering the flow pressure of the propellant gas in the thruster below the predetermined pressure such that an electrical arc is now generated in the thruster across the gap and, finally, actuating the valve to its opened position thereby permitting propellant gas to flow again at the predetermined pressure into the thruster past the gap and force the electrical arc to move downstream within the thruster so as to minimize erosion in the constrictor. The flow of propellant into the thruster is prevented for only a short period of time.

Non-erosive arcjet starting control system and method

An improved efficiency arcjet thruster has a constrictor and electrically-conductive nozzle anode defining an arc chamber, and an electrically-conductive rod having a tip spaced upstream from the constrictor and defining a cathode spaced from the anode by a gap generally coextensive with the arc chamber. An electrical potential is applied to the anode and cathode to generate an electrical arc in the arc chamber from the cathode to anode. Catalytically decomposed hydrazine is supplied to the arc chamber with generation of the arc so as to produce thermal heating and expansion thereof through the nozzle. The constrictor can have a electrically insulative portion disposed between the cathode tip and the nozzle anode, and an electrically-conductive anode extension disposed along the insulative portion so as to define an auxiliary gap with the cathode tip substantially smaller than the gap defined between the cathode and nozzle anode for facilitating startup of arc generation. The constrictor can also include an electrically-conductive electrode with a variable electrical potential to vary the shape of the arc generated in the arc chamber. Also, the cathode is mounted for axial movement such that the gap between its tip and the nozzle anode can be varied to facilitate a generally nonerosive generation of the electrical arc at startup and reliable steady state operation. Further, the arc chamber can have a nonparallel subsonic-to-supersonic transition configuration, or alternatively solely a nonparallel supersonic configuration, for improved arc attachment.

Efficiency arcjet thruster with controlled arc startup and steady state

Growing community of inventors

Seattle, WA, United States of America

Steven C Knowles