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Aviation History
1963
1963 - 1776.PDF
GHT International, 3 October 1963 585 ount of radiobiological experimental and clinical facts about the ning effect of ionizing radiation under terrestrial conditions. parently transfer of these data to cosmic radiation is inadmissible hout reservations. Therefore the recommendation on per- sible dose of 25 rem should be regarded as temporary. With the iuisition of experimental data on the biological effect of individual nponents of cosmic radiation, on the effectiveness of radio- itective compounds, this dose will be altered." I/IERICAN AND SOVIET SPACE SUITS Bioastro- itics Review, 1963, by Dr Eugene B. Konecci US National ronautics and Space Administration) The present US state-of- i-art in full-pressure space suits has evolved to the Gemini and lollo space suits using the 51b/sq in, 100 per cent oxygen system. mini suits will have removable boots and gauntlets to provide a iximum degree of comfort to the astronaut during the long- ration nights. In addition, the Gemini spacecraft is designed to rmit the astronaut to open a hatch and pass from the craft into »space environment, protected only by his space suit. The new Apollo suit will carry its own portable life-support stem and power requirements, have pressure-compensating joints d greater provisions for increasing "extra-vehicular monceuvr- ility." The concept of utilizing a full-pressure anthropometric it goes back to a requirement for mobility and dexterity of military ots in the early development of such protective gear. The Soviets began at a very early date in the development of full- essure suits. As early as 1948 they had a regenerative type of full- essure suit, which was probably the forerunner of the present ace suit used in Vostok. Although on the surface it appears that B Russians and Americans have used two different applications the design of full-pressure suits there is no evidence to prove this, i the USA there have also been some discussions as to the utiliza- MI of a single-gas environment system, that is 100 per cent oxygen 51b/sq in, for Mercury, Gemini and Apollo areas; however, the acing of man in 100 per cent oxygen for a prolonged period of time :yond 14 days introduces another unknown variable, in the Soviet spacecraft Vostok, air is utilized as the mixed gas, ith oxygen varying normally from 21 to 29 per cent. This is luivalent to roughly one atmosphere or sea-level conditions. The wiets have apparently been afcle to maintain a hermetically sealed )mpartment, since they report no loss of cabin pressurization r nitrogen. It is interesting that the Soviet full-pressure suit, in case [an emergency, is pressurized to 7|lb/sq in (£ atmosphere) instead f 3-51b/sq in as is commonly done in the USA. The reasons for lis appear to be (1) that with a lesser pressure the Soviet cosmonaut light suffer from bends (even at 51b/sq in) if he experienced a udden loss of cabin pressurization, (2) that one of the most logical leans of providing proper counter-pressure is in a garment inflated ith air. However, such a garment restricts mobility. The Soviet pressure suit is pressurized with air, while the helmet pressurized with oxygen. In this way, at 7£lb/sq in, or approxi mately 18,000ft equivalent, the cosmonaut is protected against compression sickness but as a consequence his mobility would be verely restricted, owing to the higher pressurization. It is quite *ly that the cosmonaut is not able to move more than certain Sited parts of his body. It is very likely that the Soviets denitrogate ir one or more hours under the 7£lb/sq in condition, and that the SSR full-pressure suit could be reduced from 7£lb/sq in to 51b/sq 1 or less, thereby permitting the cosmonaut to become more mobile w, in fact, able to leave the spacecraft if required. This philosophy points up a basic difference of approach, and !t leads to the same alternate results that the cosmonaut has the ^doin and the equivalency of the Earth atmosphere environment M> when required, is afforded decompression protection with a 'tv-high-pressure suit. Substantial denitrogenation of a few hours al so afforded, which means that the suit can be utilized for mul- P'e purposes. It appears that the Russians have mastered the art moulding the regenerative system into a back-back assembly ™cn fits the contour of the body. Duration of the Soviet extra-e !^larsVi.t is estimated to be limited to less than one hour. This initial capability, however, would appear to be adequate accomplish the proposed rendezvous, docking and transfer ordures, as well as the back-up techniques involved in an early jL^1'01? of the lunar surface. It must also be assumed that the an K• 'S v'£oroUsty working to obtain an extended extra-vehicular Pabtliiy to perform some of the space station assembly tasks and ' r exPloration that they have disclosed verballv as well as in the Mn literature." GUIDANCE AND CONTROL Survey Observations 1963 (Guidance and Control), by George H. Webber General Electric Co) During the past year the field of guidance and control has seen notable advances in components and techniques, but the accent has been on reliability and integration of systems for pro jected missions. Such emphasis on reliability is related to the signi ficant rise in manned spaceflight work during the same period. The recent experience of Maj Gordon Cooper in having two autopilot inverters fail in orbital flight has provided fresh evidence of the need for reliability design. Towards the effective integration of techniques into useful guidance systems, progress is reported in the development of flight computers employing microminiaturization. One firm has achieved a producible high-speed digital computer having a 4,000-word memory, weighing 171b and capable of 20,000hr mean time before failure. The modular use of such units with available sensors, including man, is being vigorously pursued. lnertial component areas showing advances in the past year include both gyros and accelerometers. Methods of suspension avoiding contact bearings are receiving continued attention. Beryllium is being used increasingly because of such factors as its strength-density ratio and thermal coefficient of expansion. Several companies have developed operating units of electrically suspended gyros. Work continues on cryogenic gyros employing magnetic suspension. The "Flimbal" being developed by Massa chusetts Institute of Technology is a completely floated inertial measuring unit with high expected performance and simplicity derived by avoidance of gimbals and shafts. Many other forms of sensors, potentially useful for guidance, are being developed. Typical of these are lightweight radars for use in rendezvous and docking as well as on-board measurement of orbital parameters. Recently tested in a flight of the Saturn vehicle was a radar altimeter. Theoretical work to date shows a potential capability to determine each of the in-plane components of orbital velocity to a standard deviation accuracy of about one foot per second using altimeter techniques. The engineering of lunar landing systems is proceeding, based upon both optics and radar. Attitude control continues to receive much attention. Spin stabilization, a relatively convenient technique for early space pay- loads, is being largely supplanted by highly accurate control as necessary for orientation of optical or radio sensors. The Orbiting Astronomical Observatory is expected to have the ability to acquire reference stars within a circle of 0.5° radius and to have a fine orientation accuracy of better than one second of arc. Rocket Research Corporation's development of the subliming solid micro-rocket offers the prospect of long-term attitude control with very low weight. Providing thrust levels from 0.001 to ten pounds, it employs a form of solid propeliant capable of intermit tent operation, and performs on the basis of sublimation, rather than ignition, of the propeliant. Weighing approximately half as much as a comparable cold nitrogen system for attitude control, the small unit is capable of pulsing on and off millions of times over a period of months or years. SYNCOM 2 DETAILS Syncom, by F. P. Adler Hughes Aircraft Company) The Syncom 2 advanced technological de velopment studies in progress at Hughes for NASA's Goddard Space Flight Center include consideration of the techniques re quired to demonstrate the stationary or equatorial synchronous orbit, continuous wideband communications, new multiple access communications, an electronically steerable aerial beam and achievement of long life in orbit. The Syncom 2 spacecraft will utilize spin stabilization, and will be launched from Cape Can averal by Atlas Agena launch vehicles. Atlas Agena will permit a large increase in the weight injected on to the transfer ellipse. Slightly more than half of the weight injected on to the trans fer orbit is associated with the solid-propellant apogee injection rocket motor which is used both to circularize the elliptical trans fer orbit at the synchronous radius (as in Syncom 1) and simul taneously to remove the inclination of the transfer orbit so that the resulting orbit is both synchronous and equatorial. A possible configuration of the Syncom 2 spacecraft is 58in in diameter and 50in in length at the solar panels. Syncom 2 will employ redundant bipropellant rocket reaction jet control systems for the initial correction of orbital injection errors, orientation of the spin axis and periodic station-keeping throughout the orbital lifetime of the craft. Each of the two inde pendent systems will provide sufficient capacity to accomplish the mission objectives.
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