Sanders was not finished with inlets, though. He retired later that year after 33 years at NASA. In 1996, Sanders was named chief of Inlet & Propulsion Airframe Integration Technology Branch. In 1991 NASA awarded Sanders the Exceptional Service Award “for outstanding personal dedication, engineering insight, and leadership in defining, conducting, and guiding high-speed inlet research.” Sanders received awards for his contributions to the VDC inlet, Mach 5 inlet, and NASP program. The inlet was successfully demonstrated during wind tunnel testing as part of the High-Speed Research program. The innovative system provided the required area variation while permitting inlet bleed without leakage and maintaining acceptable aerodynamics in the diffuser. He designed an inlet diffuser using a folding-leaf mechanism for the variable diameter centerbody, a configuration that offered high performance and stability. Sanders also initiated the center’s study of a variable diameter centerbody (VDC) inlet for supersonic propulsion. Sanders defined the parameters for the NASP inlet/combustor combination and led a series of research tests that provided definitive information on inlet performance and interaction issues. The branch was responsible for performing analysis and testing of hypersonic inlets, nozzles and combustors to support the National Aerospace Plane (NASP) program. In 1986, Sanders was named deputy chief of the Propulsion Systems Division’s Hypersonic Technology Branch. It was the first demonstration of a large-scale, high-performance, Mach 5 cruise inlet. Several agencies used data from testing of the vehicle’s ramjet engine inlet in the 10×10 to validate computations fluid dynamics (CFD) predictions. There he led a joint NASA and industry team that supported the design of a supersonic cruise demonstrator aircraft by investigating technological issues in the largely ignored Mach 3 to 6 range. The center reorganized in 1983, and Sanders became a member of the Aerodynamics and Engine Systems Division. Sanders’ inlet bleed stability research has been fundamental to the development of many subsequent high-speed inlet designs. Subsequent testing of this passive-bleed control system on an inlet from the SR–71 aircraft in the 10×10 demonstrated that the bleed system significantly increased inlet stability. Sanders and Glenn Mitchell patented a passive-bleed airflow control system in 1971. This reduces flow through the compressor to prevent stall and choking. It also mitigates disturbances in the incoming airflow and in engine airflow demand. The inlet bleed system, which draws small amounts of air from the inlet’s porous surfaces, stabilizes the supersonic shock wave system in order to maximize performance. This led to the development of bleed systems for supersonic inlets that improved performance and increased stability. Sanders helped prepare the center’s F-106 Delta Dart to support this research effort.ĭuring this period, Sanders developed and tested many inlet bleed geometries and bleed airflow control strategies in the center’s wind tunnels to increase the range of stable airflow in supersonic mixed-compression inlets. Initially, this group focused on issues related to supersonic transport propulsion systems. The tests determined the effect of the escape tower’s control flaps on its overall aerodynamic stability.Īs the center reorganized in the mid-1960s to increase its aeronautics research, Sanders became a member of the Inlets Section in the new Wind Tunnels and Flight Division. Sanders also performed wind tunnel testing of the Apollo Command Service Module and its escape tower. Sanders went on to compare the data with similar tests of the Agena/Lunar Orbiter shroud. The tests verified the dynamic performance of the oversized shroud and vehicle. One of Sanders’ first assignments was the aerodynamic shroud testing for the Mariner-C spacecraft and the Atlas-–Agena launch vehicle. At the time, the division was testing space vehicles in the 8- by 6-Foot Foot Supersonic Wind Tunnel (8×6) and the 10- by 10-Foot Foot supersonic Supersonic Wind Tunnel (10×10). Sanders joined the NASA Lewis Research Center in 1963 as part of the Advanced Development and Evaluation Division. He was engaged in the conceptualization, design, and testing of a diverse array of inlets for both military and commercial applications. Sanders was a nationally-recognized leader in the advancement of engine inlet technology for over 50 years. Home > Glenn History > Glenn Hall of Fame > Biographies Bobby Sandersīobby W.
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