MORIZUMI, S. J.
Most widely held works by S. J MORIZUMI
THERMAL RADIATION FROM THE EXHAUST PLUME OF AN ALUMINIZED COMPOSITE PROPELLANT ROCKET ( Book )
1 edition published in 1964 in English and held by 1 library worldwide
A technique is developed for calculating rocket base heating and spacecraft heating environments due to particle radiation from a single nozzle rocket exhaust plume. The technique has proved successful when applied to a single nozzle exhausting into a rarefied atmosphere on the basis of comparison of predictions with experimental results. The analysis treats radiation from a cloud of particles as that from an equivalent radiating surface. Thus, the problem is reduced to the determination of the proper values of the apparent surface emissivity and the effective temperature. In defining the apparent emissivity of the particle plume, an analogy with neutron scattering for a cylindrical cloud is adopted which shows the apparent emissivity to be dependent on particle emissivity and cloud optical thickness. Since the plume is non-uniform in particle size, concentration, and temperature, certain averaging techniques are used to define values of optical thickness and temperature.
Re-entry vehicle synthesis program calculation of structural weights ( Book )
1 edition published in 1961 in English and held by 1 library worldwide
The re-entry vehicle synthesis program is used for parametric studies of re-entry vehicles. It is intended to indicate generally the optimum (i.e., minimum weight) shapes for various missions, but is not used for detailed design calculations. The structural weights estimated by the existing program have been overly conservative, so a slightly more sophisticated method has been devised, using the same basic equations, which optimizes the design within the limitations of the program. The previous method assumed that each separate section of the body was a single conical shell stiffened at the end by a single stiffener ring. Each ring was presumed to support the pressure load acting on the rear half of the section which immediately preceded it. In the new program each section is divided up into a number of bays, each one stiffened by a ring. An iterative procedure is used to determine the number of bays which result in the minimum weight of structure. Both normal pressure and axial compression loads are considered. The resultant structure is checked against expected launch loads and peak normal re-entry loads (the basic design is made for peak axial deceleration). (Author).