The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Sep. 18, 2001
Filed:
Oct. 26, 1999
Richard Vail DeMars, Lynchburg, VA (US);
Barry John Miles, Lynchburg, VA (US);
Barry Gene Miller, Goode, VA (US);
Kurt Ogg Westerman, Forest, VA (US);
BWX Technologies, Inc., Lynchburg, VA (US);
Abstract
A solar thermal rocket that includes a thermal energy storage section, a radiant inter-heater, a primary solar concentrator, and a propulsion nozzle. The primary solar concentrator is selectively movable to direct solar energy to either the thermal energy storage section or to the radiant inter-heater. The thermal energy storage section, along with insulation, is arranged to define a cavity such that a focused beam of solar rays can enter the cavity through an aperture in the insulation. The thermal energy storage section typically absorbs and stores solar energy during the non-propulsion portion of the orbital period. The solar rays are captured and absorbed and thereby heat the thermal energy storage section to very high temperatures. A radiant inter-heater directly receives concentrated solar rays and transfers the heat to the propellant during the propulsion phase. The propellant heated by the inter-heater is directed through the thermal energy storage section where it is further heated to its peak temperature and then expelled through the nozzle to produce thrust. With the inter-heater, the rate of heat extraction from the thermal energy storage section is reduced, prolonging the period of peak propellant temperature, resulting in an overall higher average specific impulse.