Award Data

Small and micro-spacecrafts require the efficient, micro-propulsion systems. Chemical micro-propulsion is best suited for use as primary thrust, orbital insertion and attitude control because of its high energy density. When grouped into arrays for larger thrust applications, micro-propulsion devices provide high propulsive flexibility or can be used as igniters. The proposed effort will focus ...

This proposal offers to provide NASA with an automatic mesh generator for the simulation of aerodynamic flows using Reynolds-Averages Navier-Stokes (RANS) models. The tools will be capable of generating high-quality, highly-stretched (anisotropic) grids in boundary layer regions and transition smoothly to inviscid flow regions even in an adaptive context. The objective of the work is to offer a un ...

The ability to restore large amounts of vented gaseous helium (GHe) at rocket test sites preserves the GHe and reduces operating cost. The used GHe is vented into the atmosphere, is non-recoverable, and costs NASA millions dollars per year. Helium, which is non-renewable and irreplaceable once released into the atmosphere, is continuously consumed by rocket test facilities at NASA centers such a ...

The proposed innovation utilizes carbon nanotubes (CNTs) coated with pseudo-capacitive MnO2 material as nano-composite electrode and ionic electrolyte for the construction of ultracapacitors. This novel approach of using nano-structured CNTs architectures provides high surface area of attachment of MnO2 nano-particles to maximize the charge efficiency and power capacity and to reduce series resist ...

Computational tools that accurately predict the performance of electric propulsion devices are highly desirable by NASA and the broader electric propulsion community. Large investments in running the long duration test programs (> 20 kHrs) at NASA GRC can be reduced with computer models and allow more focus on exploring the NEXT ion thruster design for future space missions. The current state of e ...

The innovation proposed here is a high performance, high fidelity simulation capability to enable accurate, fast and robust simulation of unsteady turbulent, reacting flows involving cryogenic propellants (such as LOX/LH2 and LOX/LCH4). The key features of this proposed capability are: (a) Hybrid RANS-LES (HRLES) methodology, and (b) flamelet modeling for turbulent combustion incorporated in a pr ...

TSRCo and CU are developing a framework to quantify and predict crew performance in various spacecraft designs in the context of the design process. The framework utilizes an elemental resource breakdown approach to relate the crew, the spacecraft design, and operations. The elements identified in the breakdown correspond to existing measures currently used in the physiological, cognitive, and ps ...