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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Enabling a Solar System Escape Mission via the NASA Space Launch System
No abstract available
A Comparison of Boundary Layer Wind Profiling Systems for Use with Space Launch Vehicles
No abstract available
Microbial Ecology of the Osiris-Rex Assembly Test and Launch Environment.
No abstract available
Enhanced Feasibility Assessment of Payload Adapters for NASA’s Space Launch System
No abstract available
Enhanced Feasibility Assessment of Payload Adapters for NASA’s Space Launch System
No abstract available
The History of Worksite Design in Rockets: Design of Systems for Safe Launch Operations
No abstract available
Making Space Launch System Safer Through Worksite Design: Design of Systems for Safe Launch Operations; The Launch Vehicle
No abstract available
Enabling a Near-Term Interstellar Probe with the NASA's Space Launch System
No abstract available
Overview of the System Integration Lab and Its Role in the Space Launch System
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Status of InSight Entry, Descent, and Landing for 2018 Launch Opportunity
No abstract available
StarBooster Demonstrator Cluster Configuration Analysis/Verification Program
In order to study the flight dynamics of the cluster configuration of two first stage boosters and upper-stage, flight-testing of subsonic sub-scale models has been undertaken using two glideback boosters launched on a center upper-stage. Three high power rockets clustered together were built and flown to demonstrate vertical launch, separation and horizontal recovery of the boosters. Although the boosters fly to conventional aircraft landing, the centerstage comes down separately under its own parachute. The goal of the project has been to collect data during separation and flight for comparison with a six degree of freedom simulation. The configuration for the delta wing canard boosters comes from a design by Starcraft Boosters, Inc. The subscale rockets were constructed of foam covered in carbon or fiberglass and were launched with commercially available solid rocket motors. The first set of boosters built were 3-ft tall with a 4-ft tall centerstage, and two additional sets of boosters were made that were each over 5-ft tall with a 7.5 ft centerstage. The rocket cluster is launched vertically, then after motor bum out the boosters are separated and flown to a horizontal landing under radio-control. An on-board data acquisition system recorded data during both the launch and glide phases of flight.
Computational Prediction of Pressure and Thermal Environments in the Flame Trench With Launch Vehicles
One of the key objectives for the development of the 21st Century Space Launch Com- plex is to provide the exibility needed to support evolving launch vehicles and spacecrafts with enhanced range capacity. The launch complex needs to support various proprietary and commercial vehicles with widely di erent needs. The design of a multi-purpose main ame de ector supporting many di erent launch vehicles becomes a very challenging task when considering that even small geometric changes may have a strong impact on the pressure and thermal environment. The physical and geometric complexity encountered at the launch site require the use of state-of-the-art Computational Fluid Dynamics (CFD) tools to predict the pressure and thermal environments. Due to harsh conditions encountered in the launch environment, currently available CFD methods which are frequently employed for aerodynamic and ther- mal load predictions in aerospace applications, reach their limits of validity. This paper provides an in-depth discussion on the computational and physical challenges encountered when attempting to provide a detailed description of the ow eld in the launch environ- ment. Several modeling aspects, such as viscous versus inviscid calculations, single-species versus multiple-species ow models, and calorically perfect gas versus thermally perfect gas, are discussed. The Space Shuttle and the Falcon Heavy launch vehicles are used to study di erent engine and geometric con gurations. Finally, we provide a discussion on traditional analytical tools which have been used to provide estimates on the expected pressure and thermal loads.
Project ELaNa and NASA's CubeSat Initiative
This slide presentation reviews the NASA program to use expendable lift vehicles (ELVs) to launch nanosatellites for the purpose of enhancing educational research. The Education Launch of Nanosatellite (ELaNa) project, run out of the Launch Services Program is requesting proposals for CubeSat type payload to provide information that will aid or verify NASA Projects designs while providing opportunities for higher educational research. Some of the challenges involved with the program are discussed, and there is brief discussion about requirements for participation in the program, and the number of flight opportunities available for the launch of the Poly Picosatellite Orbital Deployer (PPOD).