↑ GROSS, F. (1965). “Buoyant Probes into the Venus Atmosphere”. Unmanned Spacecraft Meeting 1965. American Institute of Aeronautics and Astronautics. doi:10.2514/6.1965-1407.
↑ Goddard, Robert H. (tháng 3 năm 1920). “Report Concerning Further Developments”. The Smithsonian Institution Archives. Bản gốc lưu trữ ngày 26 tháng 6 năm 2009. Truy cập ngày 29 tháng 6 năm 2009.
↑ Boris Chertok, "Rockets and People", NASA History Series, 2006
↑ Graves, Claude A.; Harpold, Jon C. (tháng 3 năm 1972). Apollo Experience Report - Mission Planning for Apollo Entry (PDF). NASA Technical Note (TN) D-6725. The purpose of the Apollo entry maneuver is to dissipate the energy of a spacecraft traveling at high speed through the atmosphere of the earth so that the flight crew, their equipment, and their cargo are returned safely to a preselected location on the surface of the earth. This purpose must be accomplished while stresses on both the spacecraft and the flight crew are maintained within acceptable limits.
↑ Whittington, Kurt Thomas. “A Tool to Extrapolate Thermal Reentry Atmosphere Parameters Along a Body in Trajectory Space” (PDF). NCSU Libraries Technical Reports Repository. A thesis submitted to the Graduate Faculty of North Carolina State University in partial fulfillment of the requirements for the degree of Master of Science Aerospace Engineering Raleigh, North Carolina 2011, pp.5. Truy cập ngày 5 tháng 4 năm 2015.
↑ Regan, Frank J. and Anadakrishnan, Satya M., "Dynamics of Atmospheric Re-Entry", AIAA Education Series, American Institute of Aeronautics and Astronautics, Inc., New York, ISBN1-56347-048-9, (1993).
↑ Hogan, C. Michael, Parker, John and Winkler, Ernest, of NASA Ames Research Center, "An Analytical Method for Obtaining the Thermogravimetric Kinetics of Char-forming Ablative Materials from Thermogravimetric Measurements", AIAA/ASME Seventh Structures and Materials Conference, April, 1966
↑ Di Benedetto, A.T.; Nicolais, L.; Watanabe, R. (1992). Composite materials: proceedings of Symposium A4 on Composite Materials of the International Conference on Advanced Materials – ICAM 91, Strasbourg, France, 27–ngày 29 tháng 5 năm 1991. Amsterdam: North-Holland. tr. 111. ISBN978-0444893567.
↑ Tran, Huy K, et al., "Qualification of the forebody heat shield of the Stardust's Sample Return Capsule", AIAA, Thermophysics Conference, 32nd, Atlanta, GA; 23–ngày 25 tháng 6 năm 1997.
1 2 3 Chambers, Andrew; Dan Rasky (ngày 14 tháng 11 năm 2010). “NASA + SpaceX Work Together”. NASA. Bản gốc lưu trữ ngày 16 tháng 4 năm 2011. Truy cập ngày 16 tháng 2 năm 2011. SpaceX undertook the design and manufacture of the reentry heat shield; it brought speed and efficiency that allowed the heat shield to be designed, developed, and qualified in less than four years.'
↑ Chaikin, Andrew (tháng 1 năm 2012). “1 visionary + 3 launchers + 1,500 employees = ?: Is SpaceX changing the rocket equation?”. Air & Space Smithsonian. Truy cập ngày 3 tháng 6 năm 2016. SpaceX's material, called PICA-X, is 1/10th as expensive than the original [NASA PICA material and is better],... a single PICA-X heat shield could withstand hundreds of returns from low Earth orbit; it can also handle the much higher energy reentries from the Moon or Mars.
↑ Flight-Test Analysis Of Apollo Heat-Shield Material Using The Pacemaker Vehicle SystemNASA Technical Note D-4713, pp. 8, 1968–08, accessed 2010-12-26. "Avcoat 5026-39/HC-G is an epoxy novolac resin with special additives in a fiberglass honeycomb matrix. In fabrication, the empty honeycomb is bonded to the primary structure and the resin is gunned into each cell individually.... The overall density of the material is 32 lb/ft3 (512 kg/m3). The char of the material is composed mainly of silica and carbon. It is necessary to know the amounts of each in the char because in the ablation analysis the silica is considered to be inert, but the carbon is considered to enter into exothermic reactions with oxygen.... At 2160O R (12000 K), 54 percent by weight of the virgin material has volatilized and 46 percent has remained as char.... In the virgin material, 25 percent by weight is silica, and since the silica is considered to be inert the char-layer composition becomes 6.7 lb/ft3 (107.4 kg/m3) of carbon and 8 lb/ft3 (128.1 kg/m3) of silica."
