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The functions performed by pyrotechnic systems and devices in the Apollo spacecraft during a lunar exploration mission and in aborts are presented. The devices and systems are described. ...The modular cartridge concept and the standard electroexplosive device used throughout the spacecraft are innovations and are discussed in detail. Some of the techniques used to attain the high levels of reliability, to assure crew safety, to control quality, and to eliminate human errors are briefly presented.

These neutrons are produced from several sources: from the terrestrial albedo and as secondary particles produced by the interaction of cosmic rays, solar protons and trapped protons with the material of the spacecraft. Recently, neutrons have also been observed originating in solar flares, at the solar surface. ...Theoretical estimates and experimental measurements of the neutron fluxes inside manned spacecraft in near-Earth orbit are reviewed and discussed. The anticipated neutron fluxes and their resulting dose-equivalents, as a function of shielding depth for exploration class missions, are presented and discussed.

The performance of the Paraglider spacecraft recovery system is described in terms of wing aerodynamic characteristics, glide range, maneuver capabilities, and landing trajectories.

Vacuum and radiation conditions in space are discussed, as these appear to cause the major limitations on lubrication for spacecraft equipment. While many lubricants suffer a drastic loss in lifetime as a result of these environments, experimental studies have demonstrated that certain oils and greases can lubricate lightly loaded ball bearings without replenishment for periods of two years and more under the following conditions of operation: speeds of 8000 rpm, temperatures of 160 to 200 F, and vacuum of 10−8 torr.

In recent years, with the advent of large spacecraft, thermal balance testing techniques using infrared lamp sources have become increasingly attractive. ...In addition to cost savings, the IR technique is more versatile in terms of spacecraft orientation and supplied flux conditions. Because of the differences between solar illumination and IR simulation the IR lamp flux characteristics must be accurately determined. ...The radiation absorbed by spacecraft surfaces under test conditions can be obtained from a computer code incorporating lamp arrays, specular baffles and surface property variations with lamp power level and radiation angle of incidence.

Followed by brief discussions of the primary natural particle radiation sources and the operational sensitivities imposed by them on crew and spacecraft, the analytical system and methods are described. The use of this automated analytical tool called Brem (Boeing radiation exposure model), is then addressed regarding spacecraft design and the optimization of radiation shielding. ...The use of this automated analytical tool called Brem (Boeing radiation exposure model), is then addressed regarding spacecraft design and the optimization of radiation shielding.

Experience with free-flying space payloads in the current era of reduced budgets has led to a continuing need for an easier-to-use and more cost-effective capability for spacecraft thermal analyses. Preliminary thermal design of the MSX spacecraft has been developed using an 80386-based MS-DOS microcomputer. ...These programs provide both an interactive geometry editor and a graphical representation of the current spacecraft geometry. The output of VIEWI is converted to a SSPTA2 geometry input file. SSPTA, a software package that simplifies the procedures for conducting sophisticated thermal analyses of orbiting payloads, consists of CONSHAD, a view factor calculation program, SCRIPTF, a radiation conductance calculation program, ORBITAL, a satellite orbital heat flux program, and ABSORB, a program to calculate absorbed power.

To provide spacecraft thermal design engineers with the data needed to define the earth albedo and emission, we have analyzed data from the Earth Radiation Balance Experiment (ERBE) over a period of 36 months, covering orbital inclinations of 57 and 99 degrees.

Thermal conductances are computed for relatively simple node geometries that are typical of analytical models of spacecraft. Heat-transfer rates computed with these conductances are compared to heat-transfer rates computed from exact, closed-form mathematical formulas.

Studies indicate that paragliders may provide lightweight, controllable re-entry vehicles suitable for spacecraft recovery. During entry, the light wing loadings available with this concept result in peak radiation-equilibrium temperatures below the temperature limits of existing materials, thus eliminating the need for heavy ablative heat protection systems.

Using the presently available technologies in the fiber composite rotors and in magnetic bearings, it is feasible to design the flywheel energy storage to replace the battery in the spacecraft power system. The potential benefits are reductions in weight, size and cost. The fundamental design considerations in designing the photovoltaic/flywheel power system are investigated in this paper.

Heat dissipated in conduction cooled spacecraft components must be transported across the component base plate/spacecraft mounting plate interface preparatory to final radiation to the space sink.

Former maintainability concepts for weapon systems are reviewed briefly, pointing out their inadequacies for manned spacecraft. The reliability concepts for manned spacecraft which require that all systems function during a mission are examined. ...This paper discusses a concept of reliability, which includes the relationship of man to total system reliability, and the techniques and controls used to insure spacecraft mission success through reliability. Former maintainability concepts for weapon systems are reviewed briefly, pointing out their inadequacies for manned spacecraft. ...Examples of man's contribution to the reliability of aircraft and spacecraft systems are discussed. These concepts will permit achievement of mission success that approaches 100 percent, using hardware with a reliability of 80 percent.

The Spacecraft Radiative Thermal Model Exchange System is a technology developed for the bi-directional exchange of spacecraft radiative thermal models via the TMG thermal software package. ...The Spacecraft Radiative Thermal Model Exchange System is a technology developed for the bi-directional exchange of spacecraft radiative thermal models via the TMG thermal software package. It provides a means for quickly and accurately transferring models between TMG and theree of the major thermal radiation codes used in the spacecraft industry, particularly the ESARAD and Thermica packages, which are widely used by contractors to the European Space Agency, and the TSS code which is prevalent in the United States space industry. ...It provides a means for quickly and accurately transferring models between TMG and theree of the major thermal radiation codes used in the spacecraft industry, particularly the ESARAD and Thermica packages, which are widely used by contractors to the European Space Agency, and the TSS code which is prevalent in the United States space industry.

The technological requirements and the development program required in producing a spacecraft have significant effects on the manufacturing operations of an aerospace corporation, particularly when there is no prospect of follow-on production. ...The technological requirements and the development program required in producing a spacecraft have significant effects on the manufacturing operations of an aerospace corporation, particularly when there is no prospect of follow-on production. The spacecraft’s internal and external environment considerations, weight controls, reliability, traceability, and limited production are reviewed with respect to their influence on manufacturing costs, schedules, operations, skill levels, and training requirements.

The thermal design of a spacecraft is a time consuming and tedious process. As more graphical tools are becoming available, this process is becoming more efficient, and changes to the thermal design are more quickly implemented. ...This paper discusses the THERMICA-SINDA/G software system, where the entire spacecraft thermal design process in integrated in one interactive graphical environment.

This paper presents application of multi-objective optimization to the design of spacecraft power subsystem. The selection of optimum design can be achieved by having a comparative trade study among different alternatives available. ...The paper provides a methodology to optimize the SEPS (Spacecraft Electrical Power Subsystem) design process taking into account both the technology trades and initial sizing in a constrained environment. ...Then it presents spacecraft power system sizing, which is derived by the mission requirements and design constraints imposed by technology available.

The most, often utilized method of thermal design verification for past and current types of spacecraft has been by Solar Thermal Vacuum (STV) tests at system level. This approach, however, will require fundamental modifications for future large and complex spacecraft, three types of which are defined; a large communication satellite, a modular earth observation satellite and a large infrared telescope, all exceeding the capabilities of existing STV test facilities. ...This approach, however, will require fundamental modifications for future large and complex spacecraft, three types of which are defined; a large communication satellite, a modular earth observation satellite and a large infrared telescope, all exceeding the capabilities of existing STV test facilities. ...Alternative test methods - STV testing in parts, infrared radiation tests, thermal canister method, skin heater application - are also discussed with regard to their advantages and disadvantages of applying them to the large types of spacecraft. The thermal design considerations to be regarded and the critical parameters to be verified by test are highlighted, in order to enable the alternative verification test concept at an acceptable level of confidence.

Not only the detectors are cooled, but also major subsystems and systems of the spacecraft’s. The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. ...The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. ...The Centre Spatial de Liège (CSL) is involved in the testing of several parts of the spacecraft’s, starting from optical tests on the mirrors or on the telescopes, going on with cryogenic vibration testing of scientific focal plane instruments, ending with the full Planck spacecraft testing. Each test requires temperature lower than 20 [K], in volumes ranging from 1 [m3] to 60 [m3], cooling down several kilograms to more than one ton, and withstanding heat load up to 150 [W] in stabilization.