Revised three degree of freedom particle trajectory program CO3E for the IBM 7094 computer
IBM 7094 computer program for simulated spacecraft motion
SEARCH · Search NASA
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
IBM 7094 computer program for simulated spacecraft motion
Accuracy of double-precision arithmetic operations on IBM 7094 computer
Double precision numerical fitting program for IBM 7094 for computation of gravitational position and accurate velocity ephemeris for planet
Fortran II IBM 7094 computer program for analytical development of planetary disturbing function
Digital computer program for IBM 7094 computer to generate spacecraft tracking station calculations
Cloud pattern recognition system - IBM 7094 computer simulation program
Flow fields about axisymmetric blunt bodies at large angles of attack calculated by IBM 7094 computer program
Input and operating instructions, and sample problems for IBM 7094 computer programs - interplanetary trajectory program, n-body trajectory program, and sensitivity coefficients
IBM 7094 computer program written in Fortran IV FOR prediction of neutron induced activation
SEDAN series of IBM 7094 computer programs for analyzing steady state data from SNAP-8 test loops
Open-shop remote computing terminal system using direct coupled system of IBM 7094 and 7040 computers for core-to-core transmission, discussing experience gained from using and managing it
Temperature prediction of spacecraft orbiting the moon, earth or other planets is an essential Manned Spacecraft Center capability. Existing methods was found, however, were either too simplified or specialized for Mod requirements. A contract was, therefore, let with Midwest Research Institute in Kansas City, Missouri, to develop a computer program to spacecraft heat, loads and/or thin skin transient temperature while orbiting the moon, earth or other planets. It is this computer program, which has recently been completed, that I'd like to introduce. The computer program is written for the IBM 7094 computer and is in the Fortran II language.
IBM 7094 computer program for theoretical calculation of outgoing infrared radiances from atmospheres of Earth and Mars as aid in satellite measurement interpretations
Three IBM 7094 computer. program used in the thermal design of spacecraft will be discussed. The first program is one used for integrating spectral reflectance or emittance. The second program calculates the percent time a satellite spends in the earth's shadow during a revolution about the earth. And the third program is called our General Space Thermal Program and is used to calculate satellite temperatures throughout a revolution about the earth.
IBM 7094 computer program for simulating atmospheric entry aided-inertial guidance systems
FORTRAN 4 program for use on IBM 7094 computer for calculating temperature field of shaft seals is described. Shaft seals are composed of basically axisymmetric bodies. Cylindrical coordinate system is used as basis for analysis. Program is quite general and can be applied to variety of axisymmetric body problems.
PLOTAN, a generalized plot analysis routine written for the IBM 7094 computer, minimizes the difficulties in adding plot capabilities to large existing programs. PLOTAN is used in conjunction with a binary tape writing routine and has the ability to plot any variable on the intermediate binary tape as a function of any other.
The General Electric Company, Missiles and Space Division, submitted/a proposal to NASA for the development of an IBM 7094 computer program which would select the exterior surface coatings for passively controlling spacecraft temperatures. G. E. claims that the "trial and error" procedures currently used can be accomplished more rationally and can therefore be programmed for a digital computer. In the ASME paper, 63-HT-41, which was presented at the ASME-AIChE Heat Transfer Conference at Boston in August, 1963, Costello, Harper, and Cline, described the procedures that have been used at G. E. to develop a coating selection program subject to the following restrictions: 1. Steady-state conditions prevail, 2. Heat transfer occurs by radiation only, 3. Temperatures are optimized at only one interior point in the spacecraft, an d 4. Only the solar absorptance of the external coatings is varied to optimize temperature. The emittance must remain constant at initially specified values. General Electric proposes to develop a generalized program in three steps: 1. The program would vary both solar absorptance and hemispherical emittance to obtain the optimum coating patterns; 2. Temperatures would be optimized at more than one interior point; and 3. The equations would be modified to account for both conduction and radiation heat transfer. In the development of the general program, the scope would be restricted to steady-state heat transfer. Since the thermal designs of most spacecraft are based primarily on nearly equilibrium conditions, the proposed program could have wide application. An obvious extension of the proposed program would be to account for transient temperatures.