Launch vehicles have many compartments which are vented to the local external environment. local high pressure areas can cause high enthalpy flows into compartments at one location which are vented at other locations during ascent. during reentry, high enthalpy gases are entrained and expelled from… More

The low earth orbit space station will produce a local gas cloud and resulting contamination generated by (1) outgassing from nonmetallic materials, (2) early desorption from external surfaces, (3) leakage of the cabin atmosphere,(4) venting of condesnates, and (5) reaction control plumes.this very… More

The current space shuttle gas temperature probe designs have not provided adequate data for evaluation of the base heating process during the ascent flight stages in which heating is most severe. these designs have inadequate thermal responsiveness as well as insufficient accountability for gage… More

Current aircraft transparency material and systems are inadequate to cope with a number of present and future operational threats. these include: aeroheating at high mach numbers; high cockpit temperatures in stagnant, sunny ground conditions; condensation; flash blindness from nuclear bursts at… More

Manned spacecraft on long missions or permanently in orbit (e.g. space station) will require hot water for housekeepingchores such as clothes and dish washing and bathing. the ecls system will also require significant amounts of hot water. if this water is electrically heated, many additional square… More

This effort will enhance the capability of the air force parabolized navier stokes code (afwal pns code) to predict skin friction and heat transfer to high speed flight vehicles. the current prediction techniques require extremely accurate calculations of velocity and temperature in the vicinity of… More

Aeromaneuvering and aerobraking vehicles, such as the aeroassisted orbital transfer vehicle (aotv), will maneuver and decelerate in the upper rarefied regime of the atmosphere. in the case of the aotv, hypersonic rarefied flow in the shear layer from the forepart of the vehicle mayimpinge on the… More

An inexpensive, programmable, 3-d thermal target which simulates the ir signature of various vehicles is needed to assist in designing missile seekers, tailoring ir signatures to improve stealth characteristics of vehicles, and for developing ir imagery devices. the purpose of this phase i study is… More

Laminar flow offers significant payoff to undersea vehicles by providing drag reduction and reduced radiated noise. it has been shown that small particles can cause laminar flow to become turbulent. a technique is needed to measure the trajectory a particle takes as it moves past an underwater… More

The current inventory of instruments to measure aerodynamic heating during supersonic and hypersonic flight of a space vehicle is extremely limited. the evaluation of much of theheat transfer data measured by schmidt - boelter and gordon calorimeters has pointed out the large errors inherent to… More

Some of the proposed engines such as those being considered for space operations use regeneratively-cooled nozzles for enhancing their performance. the expanding gas in the nozzle loses heat through the wall to the coolant flowing outside the nozzle in a direction opposite to the nozzle flow. in… More

During the tests of some intrusion detection systems (ids), various spurious alarms have been produced, the origins of which are not known. these interfering signals are classified as either nuisance alarms or false alarms. this proposed phase i investigation will obtain data about the personnel… More

The development of a hypersonic merged layer (hml) program is proposed to investigate the near-wake flow on the aotv inthe rarefied and transitional flow regimes. due to the low density, high energy viscous flow impingement on the payload bay, it is necessary to assess the thermal environment,… More

The next generation of spaceflight vehicles, such as the afecurrently being designed, will require more precise predictions of the vehicle aerodynamics in the transitional flow regime than was achieved with the space transportation system. this is necessitated by the need to reduce onboard guidance… More

As the orbital maneuvering vehicle or astronauts seated in the man maneuvering unit move externally about the space station to perform assembly, maintenance, payload servicing,and other eva activities, their rcs micro-thruster plumes may impinge on various structures/payloads creating locally severe… More

The shock layer flow field around hypersonic vehicles maneuvering in the upper atmosphere such as afe, aotv and nasp is characterized by chemical and thermal nonequilibrium due to significant dissociation and ionization. electric fields are induced as a consequence of charge separation due to… More

Remtech, inc. proposes to develop a standardized computer code to analyze the venting of components for which pressuretransients exist, ranging from pressurized to free-molecularvacuum conditions. this code will eliminate the necessity that its user be a specialist in venting methodologies and will… More

An innovative computational technique is required to couple a compressible time-accurate cfd code with a structural analysis code to simulate fluids-structures interaction. a literature survey shows that some investigations have been made for fluids-structures coupling in transonic flow, but almost… More

The lack of the capability to accurately measure flow conditions in the arc jet facilities makes the data gathered in these facilities questionable. presently, arc jet flow conditions are derived. a discrepancy of 20 to 50 percent exists between theoretical derivations of free-stream enthalpy and… More

An automated vibration and thermal assessment of electronic devices using closed form procedures is proposed. it will address mechanical design that is consistant with simplified analysis. designs that depend on fundamental large feature will pass the assessment. problem features can quickly be… More

Aerobraking vehicles (aotv, astv and vehicles to mars) are going to make several passes and dip low in the transitional regime in order to achieve the desired reduction in velocity. even at the lowest point of the trajectory, surface-slip effects persist and real-gas effects due to nonequilibrium… More

A cost efficient aerothermal design tool is required for redesign for the Holloman rocket sled TPS for operating conditions in excess of Mach 10. Current hardware was designed with peak velocities at Mach 8. The proposed program is to develop a set of analytical software products which will both… More