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This is a guidance document on how to use the compliance reporting tool under the US DOE's Energy Policy Act (EPAct).
This is a guidance document on submitting the standard compliance annual report under the US DOE's Energy Policy Act (EPAct).
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Modifications to automatic picture transmission systems ground stations to enable processing of high resolution infrared signals
Computer program for calculating initial values of trajectory and iterative program for running multiple cases with varied parameters
A programmer's manual is presented for the SEL 840MP multiprocessing control system MPCS. The topics discussed include task control; defining displays; MPCS calls for task control functions; MPCS calls and system interfaces for display functions; MPCS calls for input/output functions and services, file management, and utility services; and MPCS assembly language call sequence summary.
The generation and operational use of the SEL 840MP multiprocessing control system (MPCS) are considered. System initialization, job task table generation, the MPCS command language, display library generation, and system error summary are reviewed.
The mathematical models and computer program which are used to implement LASS are described. The computer program provides for a simulation of boost to orbit and abort capability from boost trajectories to a prescribed target. The abort target provides a decision point for engine shutdown from which the vehicle coasts to the vicinity of the selected abort recovery site. The simulation is a six degree of freedom simulation describing a rigid body. The vehicle is influenced by forces and moments from nondistributed aerodynamics. An adaptive autopilot is provided to control vehicle attitudes during powered and unpowered flight. A conventional autopilot is provided for study of vehicle during powered flight.
A computer program is described which is primarily designed to simulate the transient behavior of communications systems.
A guide to the high altitude imagery of Michigan outlines the areas of the state covered by selected recent high altitude aircraft and Earth Resources Technology Satellite flights. The types of remote sensing used are described. Maps of the flight coverage areas are included along with price lists of available imagery.
This manual details the input instructions to the data bank, and explanation of the program and its output. The data bank was developed in satisfaction of two of the study tasks, the equipment thermal requirement catalog and the equipment characteristics and constraints catalog. The data bank contains 109 components within space tug avionics system. Other systems were not included in the data bank due to the available information, however, with some program modification, other systems could be incorporated into the data bank program. The data bank was developed and checked out and is compatible with the Univac 1108, and the CDC 6500 operating systems. The data contained in the data bank is general in content with emphasis on the component thermal design. The data is applicable to any spacecraft program where the components contained in the data bank can be applied in satisfaction of the system and subsystem requirements.
The digital program ASTP Docking Dynamics as outlined is intended to aid the engineer using the program to determine the docking system loads and attendant vehicular motion resulting from docking two vehicles that have an androgynous, six-hydraulic-attenuator, guide ring, docking interface similar to that designed for the Apollo/Soyuz Test Project (ASTP). This program is set up to analyze two different vehicle combinations: the Apollo CSM docking to Soyuz and the shuttle orbiter docking to another orbiter. The subroutine modifies the vehicle control systems to describe one or the other vehicle combinations; the rest of the vehicle characteristics are changed by input data. To date, the program has been used to predict and correlate ASTP docking loads and performance with docking test program results from dynamic testing. The program modified for use on IBM 360 computers. Parts of the original docking system equations in the areas of hydraulic damping and capture latches are modified to better describe the detail design of the ASTP docking system.
Background information of detailed photo base maps produced from orbital and surface experiments data derived from Apollo missions 15, 16, and 17 is presented in outline form.
A set of programs developed for use on the JSC Univac 1100 series computers and designed to automate the collection and processing of data into the mass properties section of the shuttle operational data book is described.
A programmer guide for computing maximum likelihood estimates of mixture distributions from an unlabeled sample is presented. A subroutine provides graphic representation of mixture distributions.
Spacelab is an orbital facility that provides a pressurized, 'shirt-sleeve' laboratory (the module) and an unpressurized platform (the pallet), together with certain standard services. It is a reusable system, which is transported to and from orbit in the cargo bay of the space shuttle orbiter and remains there throughout the flight. Spacelab extends the shuttle capability, and the Orbiter/Spacelab combination can be regarded as a short-stay space station which can remain in orbit for up to 30 days (the nominal mission duration is 7 days). In orbit, the experiments carried by Spacelab are operated by a team of up to four payload specialists who normally work in the laboratory, but spend their off-duty time in the orbiter cabin. The purpose of Spacelab is to provide a ready access to space for a broad spectrum of experimenters in many fields and from many nations. Low-cost techniques are envisaged for experiment development, integration and operation. The aim of this document is to provide a brief summary of Spacelab design characteristics and its use potential for experimenters wishing to take advantage of the unique opportunities offered for space experimentation.
A FORTRAN IV computer program used to perform modal synthesis of structures by stiffness coupling, using the dynamic transformation method is described. The program was named SCAMP (Stiffness Coupling Approach Modal-Synthesis Program). The program begins with the entry of a substructure's physical mode shapes and eigenvalues or a substructure's mass and stiffness matrix. If the mass and stiffness matrices are entered, the eigen problem for the individual substructure is solved. Provisions are included for a maximum of 20 substructures which are coupled by stiffness matrix springs. Each substructure has a number degrees of freedom (DOF), except that for DOF greater than 100; vector sets having maximum row and column size of 100 were generated prior to entering SCAMP. The substructures are then coupled together via coupling springs, and the dynamic transformation is used to reduce the size of the eigen problem.
A 2-D boundary layer computer code developed to process data for an arbitrary number of streamlines is presented. Provisions are included for the computer code to determine either mass transfer rates necessary for an effective boundary layer displacement of zero thickness or the effective displacement thickness for a specified mass transfer-rate distribution. The computer code was developed to be compatible with other computer codes which are being modified and/or developed at the NASA-Langley Research Center in order to design the three dimensional, contoured, wind tunnel liner used in transonic testing of a laminar flow control system installed on a supercritical airfoil section. A brief discription of the liner design procedure, representative liner calculations, adaptive-wall design for a two dimensional wind tunnel test, and other applications are reported.