NASA's space science and applications program : a statement presented to the Committee on Aeronautical and Space Sciences, United States Senate, April 20, 1967 /

"The material in this booklet is a reprint of a portion of that which was prepared by NASA's Office of Space Science and Applications for presentation to the Congress."

NASA technical report.

Description based on: R-180; title from cover.

Motion devices for linear and angular oscillation and for abrupt acceleration studies on human subjects (impact), a description of facilities in use and proposed;

Includes bibliographies.

International cooperation and competition in civilian space activities.

Item 1070-M.

Reference Earth orbital research and applications investigations (Bluebook)

Cover title.

A chronology of missile and astronautic events;

"Serial b."

Delamination Arrestment in Bonded-Bolted Composite Structures by Fasteners

Thesis (Ph.D.)--University of Washington, 2016-06

Modeling collisional processes in plasmas using discontinuous numerical methods

Thesis (Ph.D.)--University of Washington, 2016-06

A Kinetic Vlasov Model for Plasma Simulation Using Discontinuous Galerkin Method on Many-Core Architectures

Thesis (Ph.D.)--University of Washington, 2016-03

Contributions to Physics-Based Aeroservoelastic Uncertainty Analysis

Thesis (Ph.D.)--University of Washington, 2016-06

Projectile Combustion Effects on Ram Accelerator Performance

Thesis (Master's)--University of Washington, 2016-06

Effects of Shallow Bi-Angle, Thin-Ply Laminates on the Structural Performance of Composite Wings

Thesis (Master's)--University of Washington, 2016-06

Two NextGen Air Safety Tools: An ADS-B Equipped UAV and a Wake Turbulence Estimator

Thesis (Master's)--University of Washington, 2016-06

Parametric Optimization of Inductively Driven Liner Compression Driver System

Thesis (Master's)--University of Washington, 2016-06

Three-component force measurements on a large scramjet in a shock tunnel

A stress-wave force balance for measurement of thrust, lift, and pitching moment on a large scramjet model (40 kg in mass, 1.165 in in length) in a reflected shock tunnel has been designed, calibrated, and tested. Transient finite element analysis was used to model the performance of the balance. This modeling indicates that good decoupling of signals and low sensitivity of the balance to the distribution of. the load can be achieved with a three-bar balance. The balance was constructed and calibrated by applying a series of point loads to the model. A good comparison between finite element analysis and experimental results was obtained with finite element analysis aiding in the interpretation of some experimental results. Force measurements were made in a shock tunnel both with and without fuel injection, and measurements were compared with predictions using simple models of the scramjet and combustion. Results indicate that the balance is capable of resolving lift, thrust, and pitching moments with and without combustion. However vibrations associated with tunnel operation interfered with the signals indicating the importance of vibration isolation for accurate measurements.