System for use of external secondary payloads

Abstract

An experiment system with six different re-entry experiment locations for testing high temperature re-entry materials, creating new thermal protection systems, proving innovative new concepts for spacecraft exterior surfaces and the incremental development of next generation aerospace materials. A commercial transportation system to and from orbit provides a 24-hour return cycle for the experiments on a surface actually re-entering the earth's atmosphere. Now using existing doors, hatches and other points on the reusable launch vehicle's exterior, the actual re-entry environment is experienced by test specimens with quick turn around for a wide variety of different re-entry temperatures ranges for broad testing and development purposes. The reusable launch vehicle launches, remains in orbit for 24 hours and returns to provide an actual test environment for the exterior experiment system.

1 . A system for introducing payloads into earth orbit, comprising:
 a reusable orbital vehicle capable of being placed in earth orbit, the orbital vehicle having an outer skin;   a thermal protection system attached to the outer skin of the orbital vehicle to thereby form an outermost layer of the orbital vehicle, the thermal protection system being formed by materials capable of withstanding environmental temperatures associated with re-entry of the orbital vehicle;   an internal payload coupled to an interior portion of the orbital vehicle; and   a first external payload package affixed to the orbital vehicle at a first attachment position on the outer surface of the outermost layer of the orbital vehicle wherein the first external payload package is exposed to the external atmosphere during launch and re-entry phases of a space mission and is further exposed to the environment of space while in orbit.   
   
   
       2 . The system of  claim 1 , further comprising a second external payload package affixed to the orbital vehicle at a second position on the outermost layer of the orbital vehicle wherein the second external payload package is exposed to the external atmosphere during launch and re-entry phases of the space mission and is further exposed to the environment of space while in orbit. 
   
   
       3 . The system of  claim 2  wherein the first and second external payload packages have uniform predetermined dimensions, the first and second attachment positions being configured to receive and retain the first and second external payload packages at the first and second attachment positions. 
   
   
       4 . The system of  claim 1 , further a carrier plate assembly positioned at the first attachment position to receive and retain the first external payload package. 
   
   
       5 . The system of  claim 1 , further comprising an access panel on the orbital vehicle wherein first attachment position is located on the access panel. 
   
   
       6 . The system of  claim 5  wherein the access panel on the reusable orbital vehicle is removable from the orbital vehicle. 
   
   
       7 . The system of  claim 1 , further comprising a carrier plate configured for attachment at the first attachment position and further configured for attachment to the first external payload package wherein the carrier plate is intermediate the outer skin surface of the orbital vehicle and the first package. 
   
   
       8 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the first attachment position being on the outermost layer of the orbital vehicle substantially at the first end. 
   
   
       9 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the first attachment position being on the outermost layer of the orbital vehicle forward of a midpoint between the first end and the second end. 
   
   
       10 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the first attachment position being on the outermost layer of the orbital vehicle rearward of a midpoint between the first end and the second end. 
   
   
       11 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the system further comprising an aft skirt proximate the second end wherein the first attachment position is on an exterior skin portion of the aft skirt. 
   
   
       12 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the system further comprising an aft skirt proximate the second end and a protected attachment position on an interior portion of the aft skirt. 
   
   
       13 . The system of  claim 1  wherein the orbital vehicle has an elongated shape with first and second ends with a rocket engine positioned proximate the second end of the orbital vehicle, the system further comprising an aft skirt proximate the second end and an attachment member mounted to an interior portion of the aft skirt. 
   
   
       14 . The system of  claim 1 , further comprising a sensor associated with the first experimental package, the sensor generating sensor data. 
   
   
       15 . The system of  claim 14 , further comprising a data storage unit electrically coupled to the orbital vehicle and electrically coupled to the sensor, the data storage unit receiving and storing the generated sensor data. 
   
   
       16 . The system of  claim 15  for use with an avionics data bus on the orbital vehicle to monitor operation of the orbital vehicle, the data storage unit being coupled to the avionics data bus on the orbital vehicle to store data related to the operation of the orbital vehicle in association with the generated sensor data. 
   
   
       17 . The system of  claim 14  wherein the first external payload package comprises a thermal protection system. 
   
   
       18 . The system of  claim 1 , further comprising an initial stage coupled to the orbital vehicle to boost the orbital vehicle from a position on earth to a predetermined altitude.