Digital Commons Network^™

The Origin Of Meteorites: Space Erosion And Cosmic Radiation Ages, David E. Fisher

Space Congress® Proceedings

particles in the asteroidal belt, coupled with the fact that there is a high mass cut-off for chondrites at about 1000 kg, is sufficient to explain the absence of chondrites with radiation ages greater than 55 x 10^ years. Then if one postulates continuous creation of meteorites by asteroidal collisions, the effect of space erosion is to shift the measured ages toward lower values and to destroy a certain portion of meteorites as a function of their time in space. The total effect, as estimated with several simple but plausible erosion rates, is to duplicate quite nicely the observed shape …

Precision Automatic Tracking Using A Cw Laser, E. L. Mcgann

Space Congress® Proceedings

This paper describes the design and performance of a precision CW laser tracker. When tracking low acceleration targets such as satellites and airplanes, this tracker has an accuracy of approximately 25 microradians rms. The accuracy under these conditions is set by the static friction, the background noise present in the equivalent noise bandwidth of the tracker and the scintillation of the atmosphere. When tracking high acceleration targets such as rockets, the tracker has a tracking error which is essentially proportional to the relative angular acceleration. If the rocket acceleration and the tracker-target geometry are such as to cause a relative …

S-1c Stage Instrumentation Systems Checkout At Ksc, J. S. Clements

Space Congress® Proceedings

This paper will identify the test philosophies, describe the S-1C instrumentation systems and associated GSE, and define the test and checkout methods used at KSC, for S-1C test and checkout operations.

Advanced Power Conditioning For An Ion Propulsion System, John J. Davis

Space Congress® Proceedings

Space programs proposed for the period 1970 to 1980 include plans for transporting large payloads to the near planets, such as Mars, and to even greater interplanetary distances. The accomplishment of these missions in a reasonable travel time will require» specially designed, continuous-thrusting propulsion systems. Three types of systems are envisioned: chemical, nuclear, and electrical. Of the three, the electric propulsion system is certainly the most advanced and by far the most attractive in terms of potential development. The electric systems, which have the highest specific impulse, provide a maximum payload in terms of propulsion system weight.

In any electric …

Cosmology And Organic Evolution, Minas Ensanian

Space Congress® Proceedings

In keeping with the Einstein concept of unified fields, a general cosmological problem (GCP) is proposed which requires not only a physical basis for the unification of gravitation and electromagnetism but the incorporation as well of the origin and dynamics of the phenomenon of organic evolution-for the case of a living system existing in Opik's oscillating universe.

To effect this unification, the assumption must be made that in its final analysis the universe consists of a single entity viz*, a subquanturn mechanical "ether" referred to as "cosmic entropy" and all events in the physical universe constitute perturbations in the local …

Application Of General Purpose Computer Techniques To The Design Of A Programmable Pcm Telemetry Decommutator, D. J. Hermen, J. O. Horsley

Space Congress® Proceedings

This paper describes design of a programmable decomrnutator for multi-format PCM telemetry data. The decommutator organization includes a program counter, instruction decoding registers, and an arithmetic unit, together with pattern comparison logic, and synchronization decision networks.

The various types of input formats are discussed and their implications on the organization are determined. The input data formats include (a) normal PCM commutation with frame synchronization and subcommutation synchronization, (b) mixes of different rate PCM commutation, (c) word synchronization and (d) data address tags with each data word.

The decommutator is organized around a coincident current memory which serves for both program …

Space Craft Electrical System -- New Concepts In Protection And Control, Thomas W. Butler Jr.

Space Congress® Proceedings

Increased demands for more reliable circuit protection and power control in manned space craft electrical systems have resulted in a vigorous exploratory research program to develop a totally new "systems concept" of protection and control using solid-state logic in conjunction with either solid-state or electromechanical power switching.

The electrical power system currently used in manned space craft is patterned after those used in aircraft. It should be noted that, in many cases, the electrical system, in even our most modern aircraft, could stand a critical re-evaluation.

Missile Explosion Simulation, Robert O. Harper

Space Congress® Proceedings

Missile propellant systems are not designed to explode. However, prototype missiles may require a range destruct command for safety reasons or even explode due to some malfunction. Digital computer simulations of missile explosions were run to provide an estimate of physical parameters which an Explosion Measurement System must measure. The computer simulations were run using the Naval Ordnance Laboratory "WUNDY" hydrodynamic computer code (program) reported on herein as well as with a two dimensional code. After an explosion the remotely measured data are used to determine inputs to the hydrodynamic computer code. Iterative methods are then used to fit data …

Calibration Of The Impact Errors Due To G&G Uncertainties In The Minuteman R&D Test Program At The Eastern Test Range, A. N. Drucher

Space Congress® Proceedings

It became evident a little over a year ago that errors in our knowledge of the force field acting on a ballistic missile in free flight and errors in our knowledge of target location, the so-called geodetic and geophysical (G & G) errors, constitute two of the principal error sources in the Minuteman R & D test program on the Eastern Test Range. We found that individually-measured subsystem miss contributions, when added together on a given flight, would not fully account for the weapon system impact miss derived from the splash net; in other words, we were always left with …

Optical Subcarrier Communications, J. H. Ward, M. L. Shechet

Space Congress® Proceedings

This paper discusses the use of rf subcarriers placed on optical beams for communication purposes. Through the use of advanced optical beam processing and post detection electronic processing, the advantages of optical frequency techniques can be combined with the mature background of the rf technology. These techniques are expected to find applications for long range wideband communication, spacecraft tracking and rendezvous, and altimetry, as well as for aircraft and spacecraft landing aids.

Rescue And Recovery In The Space Age (Search, Rescue And Recovery), Emil G. Beaudry, John L. Vandegrift

Space Congress® Proceedings

This paper will be presented by Colonel Emil G. Beaudry, Vice Commander, Aerospace Rescue and Recovery Service. It will include a statement of the present Aerospace Rescue and Recovery Service mission and how it relates specifically to our country's various space programs, past, present, and as far into the future as we can project.

It will cover the introduction of the HC-130's into the Aerospace Rescue and Recovery Service inventory, the Fulton System and its potential, the possibilities of air-to-air recovery and the entirely new concepts of air-to-air refueling of the HH-3 helicopter from the HC-130H aircraft and rnid-air recovery …

System Reliability Mathmatical Modeling, Lee R. Webster

Space Congress® Proceedings

The reliability mathematical model of a system is the basis of all reliability predictions, optimization, apportionment, and virtually all other system reliability analyses. Because of the importance of the math model, maximum care should be taken in its construction. A system reliability model is defined here as a probability expression which represents the actual system configuration such that when the reliabilities of the system elements are known along with certain other mission parameter values, the expression can be used to calculate the overall system mission reliability. The complexity of the model structure depends upon the complexity of the system it …

The Fine Guidance Sensor, An Electronic Scanning Star Tracker, R. A. Deters, D. F. Eisenhut, R. F. Gates

Space Congress® Proceedings

The advent of space exploration has placed hitherto unheard of requirements on accuracy and precision sensing devices for guidance and attitude control. The necessity for high reliability, due to non-repairability, required new approaches to this design problem. Rather than try to improve upon existing systems, components, and approaches, a totally new concept evolved which eliminates the mechanical rotors and reticles of yesterday. Instead, a totally new breed of electronic scanning star sensor resulted.

This paper describes one such device, a Boresighted Star and Planet Tracker developed for precise attitude sensing and control of an experimental sounding rocket.

Discussed are the …

The Evaluation And Calibration Of Range Instrumentation Systems At The Air Force Eastern Test Range, Charles L. Carroll Jr.

Space Congress® Proceedings

This paper gives a brief discussion of the status of work at the Air Force Eastern Test Range on the evaluation and calibration of range instrumentation systems whose accuracy specifications are a few parts per million. More emphasis will be placed on the STAFF project because of its current interest. The evaluation and calibration problems are distinct but they are intimately related. In the evaluation problem, one is asked to make estimates of the performance parameters of a range instrumentation system for purposes of understanding the system and its potential. This information is required to appraise system performance and to …

Test And Checkout Concept For Space Transportation Systems, John M. Miller

Space Congress® Proceedings

Current space vehicles and missions are characterized by almost complete dependence upon ground support equipment and facilities for determination of vehicle status. For the manned missions of the post Apollo era, this dependence will degrade the probability of mission success. Achievement of autonomous space vehicles is necessary for the successful accomplishment of advanced manned missions.

The development of an on-board test and checkout concept and the design, fabrication and test of a major hardware element of the concept is described.

The integration of functions into an overall data management system for future vehicles, with the flight crew assuming the role …

Navigation For Spin Stabilized Deep Space Planetary Spacecraft, R. A. Park, D. H. Newell

Space Congress® Proceedings

Navigation for planetary missions is well understood as shown by the successful flights to Venus and Mars by the JPL Mariner spacecraft. However, when we consider the farther planets, such as Jupiter and ultimately Pluto, the trip time requirements are so .long (on the order of 2 years to Jupiter and 8 to 1 0 years to Pluto) that spacecraft reliability becomes the paramount consideration.

A basic approach to achieving reliability is to simplify the spacecraft system as much as possible within the limits of mission objectives, which usually arise from the scientific payload. System simplicity and reliability can be …

Positioning And Aligning The 250 Ton Solid Rocket Motors For Titan Iiic, W. F. Vobejda, L. J. Rothermel

Space Congress® Proceedings

In the Integrate-Transfer-Launch concept of Titan IIIC, each 120-inch solid rocket motor is first assembled on a support frame and then lifted at the base and moved about 70 feet to a precise position adjacent to the core vehicle. The positioning of the completed motor presented several unique problems because this was the first attempt in any space program to transfer a vertical solid motor weighing 500,000 pounds, measuring 10 feet in diameter and 85 feet high, and having an eccentric center of gravity.

The physical size of the positioning sling components and the magnitude of their stresses presented a …

Automatic Chemical Processing Systems For Extraterrestrial Biochemical Investigations, Donald C. Garwood, Harry A. Taussig

Space Congress® Proceedings

Implementing the concept of planetary exploration is a formidable task. Laboratory procedures and techniques that are performed routinely by scientists and technicians must be performed remotely, automatically, and reliably for long periods of time without direct human intervention. The subtle and sophisticated reasoning, planning, and execution that lies behind well-conducted research in terrestrial laboratories must be incorporated into the careful original design and mechanization of extraterrestrial experiments.

Mechanisms capable of automation for use in batch chemical processing of surface samples for scientific payloads have been devised and tested. Elemental processing operations common to a wide variety of possible life detection …

Potential And Hazards Of The Oceanographic Market For The Aerospace Industry, Meryl C. Burns

Space Congress® Proceedings

The Oceanography market will provide a potential for diversification by the Aerospace industry. An analysis of this market and the correlation between oceanographic requirements and aerospace resources establishes the relative potentials and hazards for selected market sectors. A minimum risk entry into the potentially profitable and diverse Oceanography market is proposed.

Automation In Range Scheduling, John R. Norton

Space Congress® Proceedings

The imposing challenge of space for management is to direct the most complex and massive engineering effort ever attempted to attain obfectives of the highest national priority. And within the body of new management knowledge and experience produced in these tasks lie methodologies fundamental to the administration of any large project. The purpose of this paper is to present an operations research model for the range scheduling function. These techniques were derived from an analysis of the Eastern Test Range, but they are applicable to many cases of the general large project scheduling problem. The method is illustrated with test …

Testing The Man-Rated Launch Vehicle, Francis X. Carey

Space Congress® Proceedings

Although manned space flight is still in its infancy, testing of launch vehicles has progressed to a high degree of sophistication.

As of December 1965, the Martin-built Gemini launch vehicle has launched seven Gemini spacecraft successfully out of seven attempts. This remarkable record was made possible by two facts:

1. The basic reliability of the hardware

2. The test program.

This paper briefly describes the Gemini launch vehicle noting the major differences between it and the Titan II and discusses the test program. It is not proposed that this is the only method of testing a man-rated launch vehicle; however, …

A Manned Flyby Mission To Eros, Eugene A. Smith

Space Congress® Proceedings

Eros (433), the largest of the known close approach asteroids, will pass within 0.15 AU of the Earth during its 1975 opposition. This close approach, occurring near the asteroid's descending node and perihelion, offers an early opportunity for a relatively low energy manned interplanetary mission. Such a mission could provide data important to the space technologies, to the astro sciences, and to the utilization of extraterrestrial resources. Mars and Venus are the primary targets of early manned planetary flight, and therefore early manned planetary missions to other objects should support or complement the Mars and Venus programs. The model mission …

Application Of Titan Iii Guidance And Navigation System To Lunar Missions, Spencer M. Macy

Space Congress® Proceedings

The current series of Titan III R and D flights includes missions of considerable complexity. The mission profiles are designed to take full advantage of the combination of the Titan IIIC vehicle configuration and of the accuracy and flexibility provided by the AC Electronics Guidance and Navigation (G & N) System.

The fact that the Titan IIIC is capable of completing a synchronous equatorial mission from an ETR launch implies that a lunar impact mission could be flown with a payload having two to three times the synchronous payload weight. This paper discusses the changes which would be required in …

Time Correlated Data Retransmission Telemetry System, Edward L. Keohane

Space Congress® Proceedings

The paper describes techniques for the development of a time correlated burst retransmission telemetry system. The discussion covers the feasibility of a time correlated system and considerations for its implementation. The many dependent and independent parameters encountered and their effect on the overall system requirements are examined. Formatting techniques of the output link which provides the capability of extracting data and time events while maintaining a high bandwidth effeciency is presented. A three input link system (Gemini, Agena and Titan) having one output link will be examined. The advantages and disadvantages of the burst system will be evaluated resulting in …

Progress Report On Martin's Titan Iii Incentives (January 1963 To March 1966), Robert W. Chapman

Space Congress® Proceedings

Three years ago Martin started work on the Phase II contract for the development and test of the Titan III Space Booster. This was the first large aerospace system contract to incorporate multiple incentives for schedule, cost, and technical performance. Now, with the Titan III contract more than 90% complete, this report will evaluate the success of the incentives used and will compare incentive success with program results.

In consonance with the philosophy that the purpose of incentives is to motivate superior performance, this Martin/AFSSD contract contains definitive criteria for the determination of incentive success or failure. The contract also …

Reliability & Confidence For Serially Connected Systems, George J. Schick, Richard J. Prior

Space Congress® Proceedings

In most test programs component test results are available. It is in general a fairly easy task to find lower one-side confidence limits on the probability of failure of a chosen component. Either variable data or attribute (success-failure) data can be used. From a statistical point of view it is most often more desirable to use variable data (like pressure, temperature or specific impulse, etc.). From that information, upper one-sided confidence limits on the reliability of the component can be secured. It is true, in general, that different components are tested under varied conditions with an unequal sample size. A …

Spacecraft Communications System Design Steps, William Benner

Space Congress® Proceedings

A spacecraft communications system is defined as including not only two-way voice links, but also command channels from the earth, telemetry (and in some cases TV) to the earth, as well as tracking transmitters or transponders. These links have varying significance for the common vehicle phases of launch, orbit (either parking or mission) , objective trajectory adjustment and/or return; some of the features of these operational phases are illustrated for their effect on communications.

In the course of designing such communications systems for major spacecraft programs, certain fundamental areas inevitably appear, and lend themselves to a systematic approach. By applying …

Transient Thermal Study Of A Space Suit Clad Astronaut On The Moon, Robert J. Martin

Space Congress® Proceedings

A transient thermal analysis of a space suit clad man on the moon is presented. No refrigeration system is considered for his suit, and it is assumed that the only evaporative cooling is that achieved through the saturation of the occupant's exhalation. These restrictions are imposed because the primary concern is to determine -whether useful mission times are possible without recourse to special cooling devices. Practicable exposure times are demonstrated for the lunar day. The analysis also shows that extended mission times are easily feasible for the lunar night side.

The Range Safety Problem, "A Thorn In The Flesh", J. R. Duffett, J. N. Thilges

Space Congress® Proceedings

The range safety problem is truly "a thorn in the flesh" to the user of the missile test ranges. The range user has one objective in mind: to get his missile off the ground and successfully complete his test objectives. Any thing that interferes with that objective is, to him, an evil he can do without. Range Safety has often been considered such an evil - albeit a necessary one. Possibly a misunderstanding of the problem is the basis for this feeling. This paper endeavors to present the problem in its proper perspective by defining the problem and presenting the …

Mission Control Center - Houston, R. E. Driver, J. M. Satterfield

Space Congress® Proceedings

The Mission Control Center - Houston (MCC-H) was designed to control all NASA manned space flights from the first Gemini rendezvous through the Apollo program. The MCC-H is a three-story building which contains 112,000 square feet, and which required 30 months to implement. It has a capability to control a live mission and a simulation simultaneously, or two simulations simultaneously. This capability was provided by locating duplicate operational areas on separate floors. The facility layout is shown in Figures 1, 2, and 3.

The MCC-H is comprised of five basic systems: the Display/Control System, the Real Time Computer Complex (RTCC), …