Leo lb-1a satellite launch system

Abstract

The present invention, LB-1A, is a system for launching satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, sub-orbital, orbital, and other aerospace payloads, which includes a modified existing carrier aircraft and a streamlined, unmanned rocket propelled lifting body spacecraft, air-launched from said carrier aircraft.

The inventors claim: 
     
         1 . The present invention is a system for launching small satellites, including small-sats, mini-sats, nano-sats, medical and scientific experiments, suborbital, orbital and other aerospace payloads, including a modified and optimized existing carrier aircraft, a streamlined, unmanned rocket-propelled lifting body spacecraft, air launched from said carrier aircraft and containing in addition to its own propulsion, the payload, staging, propulsion and insertion rocketry necessary to the mission and the provisions for protecting said payload during loading, fueling, transit to and mating with the said carrier aircraft, taxiing, conventional takeoff from the runway, climb and cruise to the selected launch point (LP) and high altitude release, as well as the tracking, navigation and control hardware, software and other equipment to effect a safe, reliable and affordable delivery, including: 
     
     
         2 . LB-1, an unmanned, rocket-powered, wingless lifting body spacecraft, assembled of commercially available composite rocket boosters, complete with solid or hybrid fueled motors and strapping hardware, employed to improve the efficiency and lower the gross weight and costs of air launched commercial payloads. Said spacecraft's lifting body characteristics are designed to mitigate lift and altitude losses during the horizontal release maneuver (HRM) and its wingless profile allows attachment between engines/landing gear of said carrier aircraft. Joined at the chine lines, streamlined airfoils of high-temp carbon/composite form the nose cone and main body upper and lower fairings to create a strong, light covering and provide a lift factor of approximately 65#/sq. ft. Said spacecraft's body cross section may be described as a flattened ellipse with a longitudinally placed, laterally centered conventional ⅔-stage rocket booster flanked by symmetrical pairs of propellant boosters of decreasing diameters and a wide, tapering nose cone to establish the desired cross sectional airfoil. 
     
     
         2 . Mid-body horizontal upper and lower chines on each side gradually widen aft of the nose cone from 2 to 3 feet, terminating in upper and lower “wye” stabilizers canted outboard 60 degrees from the horizontal and fitted with split elevons to maintain roll control in the atmosphere. In addition, the aft chines are fitted with split horizontal elevons for pitch control and use as speed brakes.
 Four thrusters have been provided near the forward end of the upper and lower outboard boosters to increase stability following release. To avoid waste of Stage 1 thrust, small outboard boosters designated “Stage 01” will be ignited to accomplish the pitch-up maneuver prior to Stage 1 ignition. It is foreseen that this combination along with the aforesaid improvement in lift will result in a considerably smoother, more controlled and economical spacecraft rotation. 
 To allow maximum opportunity to accommodate various loading options and combinations of payload types, the preferred embodiment provides that the rocket casings may be truncated at the firewall and the entire spacecraft nose or selected portions thereof may be utilized in place of the usual payload booster nose cone/s. To enable and control the cost of this “quick-change” facility it is planned that several firewall/payload plate options will be made available at loading sites. 
 A plan view showing a positioning and attachment diagram of the LB-1 utilizing the carrier aircraft hard point connections. An outline of the transport dolly chassis illustrates lead-in guidance and critical component clearances. 
 
     
     
         3 . Another embodiment of the LB-1 will be its use as a flying “Launch Laboratory” for the flight testing and optimizing of other new light-sat vehicles to speed their development, particularly in the field of small-sat constellation building.