Technology of missile science.

"Contract no. AF 33(608)-642."

Structural design of missiles and spacecraft

Mode of access: Internet.

Antiproton annihilation propulsion /

Mode of access: Internet.

Maintenance instructions direct support : launcher, rocket, armored vehicle mounted, M270, (1055-01-092-0596) : multiple launch rocket system.

Includes index.

Maintenance instructions direct support launcher, rocket, armored vehicle mounted, M270 (1055-01-092-0596) : multiple launch rocket system.

Includes index.

Maintenance instructions, general support launcher, rocket, armored vehicle mounted, M270, (1055-01-092-0596) : Multiple Launch Rocket System.

Includes index.

Operator's manual : launcher, rocket, armored vehicle mounted, M270, (1055-01-092-0596), Multiple Launch Rocket System.

Includes index.

Operator's manual for 66mm light antitank weapon system M72A1, M72A2 with coupler, M72A3 and practice rocket launcher M190 with M73 practice rocket.

"January 1986."

J-P fundamentals ...

Reproduced from type-written copy.

Supersonic aerodynamics and rocket propulsion,

Includes bibliographical references.

Freezing rain experiments, Project Freeze; final report. Contract no. Nonr-2250(00)

Mode of access: Internet.

Pressurization systems for liquid rockets.

Cover title.

Total heat transfer measurements on a flight investigation of reentry environment model

Stagnation-point total heat transfer was measured on a 1:27.7 model of the Flight Investigation of Reentry Environment II flight vehicle. Experiments were performed in the X1 expansion tube at an equivalent flight velocity and static enthalpy of 11 km/s and 12.7 MJ/kg, respectively. Conditions were chosen to replicate the flight condition at a total flight time of 1639.5 s, where radiation contributed an estimated 17-36% of the total heat transfer. This contribution is theorized to reduce to <2% in the scaled experiments, and the heating environment on the test model was expected to be dominated by convection. A correlation between reported flight heating rates and expected experimental heating, referred to as the reduced flight value, was developed to predict the level of heating expected on the test model. At the given flow conditions, the reduced flight value was calculated to be 150 MW/m2. Average stagnation-point total heat transfer was measured to be 140 ± 7% W/m2, showing good agreement with the predicted value. Experimentally measured heat transfer was found to have good agreement of between 5 and 15% with a number of convective heating correlations, confirming that convection dominates the tunnel heating environment, and that useful experimental measurements could be made in weakly coupled radiating flow

Visible and near infrared spectroscopy of hayabusa reentry using semi-autonomous tracking

Aground-based tracking camera and coaligned slitless spectrograph were used to measure the spectral signature of visible radiation emitted from the Hayabusa capsule as it entered into the Earth’s atmosphere in June 2010. Good quality spectra were obtained, which showed the presence of radiation from the heat shield of the vehicle and the shock-heated air in front of the vehicle. An analysis of the blackbody nature of the radiation concluded that the peak average temperature of the surface was about (3100± 100)K. Line spectra from oxygen and nitrogen atoms were used to infer a peak average shock-heated gas temperature of around((7000±400))K.