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Review of the orbit maneuvering system, i.e. the propulsion system which is to provide the thrust for all major maneuvers while the shuttle orbiter is functioning as a spacecraft. The design and operational philosophy of the shuttle vehicle and orbital maneuvering system are discussed, along with the selection rationale for the current baseline orbit maneuvering system. Critical development issues and potential design alternatives are examined.

Supersonic performance of logistics spacecraft, giving special attention to return from orbit to continental U.S.

Gemini spacecraft and launch vehicle interface design, development and configuration control

Mission objectives and design requirements of unmanned spacecraft for deep space investigations through 1980

Reliability and maintainability analysis of two year spacecraft mission combining earth orbits and Mars program, using computerized mathematical model

Mission and planetary vehicles characteristics affecting design of solid propellant motors and thrust vector control systems in planetary orbiters and landers

Effects of space station logistic requirements on design of spacecraft configurations with various hypersonic lift/drag ratios, comparing payload, cost, etc

This paper discusses the organization of a special supplementary channel in the UV spectrometer of the apparatus of the Solar Patrol space experiment, which is to be installed for experimental operation on the outer surface of the service module of the Russian segment of the International Space Station. It is assumed that the optical axes of the apparatus will be aimed at the center of the sun's disk by means of a solar-oriented platform to within ±1.8°. A channel will be created to estimate the correctness of the orientation of the device toward the sun, and its readings will be used when processing the data of the measurements of the main spectrophotometric channels of the UV spectrometer. It is proposed to use a photocathode mounted in zeroth order of the spectrum of the diffraction grating of the spectrometer as a detector. © 2005 Optical Society of America

The results of experimental simulation in vacuum chamber of full-scale process of SM refueling lines purge are reported. The descriptions of the experimental setup, measurement methods and results of videoshooting of liquid ejection into vacuum are given. The measured angular spatial distribution of liquid phase, pressure fluctuations in the line are given as well. The data about influence on flow structure of the protective screens assembled around the output pipe are presented. It is shown that the mounting of the similar device allows to reduce essentially the amount of backflow of drops and therefore ISS surface contamination.

OLAR powered spacecraft are currently being developed for the Global Positioning System (GPS). The development of nuclear power supplies and related technologies have proceeded to the point where nuclear powered spacecraft alternatives are possible and need to receive serious consideration for application to the GPS mission. An analysis was performed, and is herein reported, of the economic benefits which may result from developing and utilizing nuclear powered spacecraft in place of solar powered spacecraft for the GPS mission. The analysis considers cost uncertainties, launch system and spacecraft subsystem reliability, time phasing of nuclear spacecraft into a system consisting of solar powered spacecraft, a nuclear demonstration experiment, and the likelihood of nuclear operational spacecraft implementation in terms of the successful duration of the experiment, and single and multiple payload launches. It also develops the probability distributions of all pertinent events, annual costs, and present values of costs and benefits. Contents Since the early 1960's, both the Navy and the Air Force have actively pursued the idea that navigation and positioning could be performed using radio signals transmitted from space vehicles. This has led to the Global Positioning System (GPS),l which is a space-based radio positioning navigation system that will provide extremely accurate three-dimensional position and velocity information together with system time to suitably equipped users anywhere on or near the Earth. The space segment of the system will ultimately consist of 24 spacecraft deployed in circular 10,900-n. mi. orbits, having 12-hr periods and located in three orbital planes inclined at approximately 63 deg.

The feasibility of a tandem launch of a mother/daughter spacecraft pair with a single launch vehicle for a 1981 Mariner Jupiter Orbiter mission is described. The mother is a close derivative of the three-axis stabilized Mariner Jupiter Saturn 1977 spacecraft with the addition of a Viking-type propulsion module for orbit capture; it concentrates on the planetology and satellite science objectives. The daughter is a small, simple spin-stabilized spacecraft taking advantage of the mother's transit and delivery capabilities; it obtains in-situ measurements of the surrounding planetary environment. A conceptual design of the daughter spacecraft is presented.

Communication satellite models are developed so as to indicate the proper number of spacecraft per launch vehicle and the proper spacecraft weight fraction which should be assigned to spacecraft housekeeping.

During 1970 the USA remained the major centre of world space activity, despite the cutback in funds made available to NASA and the resulting reduction in manpower and facilities. Any thoughts that moon flights were becoming a matter of routine, inspired by the relatively little-publicized successful mission of Apollo 12 in November 1969, were dispelled by the flight of Apollo 13 in April 1970, which became a near disaster due to an explosion in the service module.

The UoSAT-2 spacecraft incorporates two ground-programmable computers. The primary computer is based around an RCA 1802 microprocessor and is intended for general-purpose management and data collection purposes within the spacecraft, whilst the secondary computer, based on the National Semiconductor NSC-800 microprocessor, controls the Digital Communications Experiment and has a more limited interface to the rest of the spacecraft. This paper describes how the experience gained from operating the UoSAT-1 spacecraft led to an enhanced primary computer design on UoSAT-2.