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Scientific investigations which can be performed with a Lunar Exploration System for Apollo (LESA) base system are briefly described. Operational and logistics requirements for support of the scientific investigations and missions are discussed. Desirable lunar base deployment and typical installations are presented and are summarized in an illustration showing the concept of an alternate base configuration. Also summarized are logistics support requirements based upon scientific investigation and requirements support.

Practical considerations for an efficient ferry-resupply system are emphasized in this paper. Titan III performance capabilities are briefly reviewed, and the influence orbit characteristics have on ferry-resupply rendezvous is discussed. Logistic mission sensitivity to orbit altitude and inclination parameters as they affect payload, frequency of launch opportunity and phasing requirements is evaluated. The capability of launching on time and the ability to respond rapidly to a supply mission abort or scrub was found to be a prime system prerequisite. Advantages of a mobile launch system with back-up capability are clearly established.

Studies concerning advanced container design are necessary for two reasons: Prolonged storage time of cryogenic liquids, and the need for improved container configurations. Anticipated storage times range from a few weeks to many months. Both the effect of low temperatures as well as stringent insulation requirements influence the design of the tank and its support structure. Necessary protection against micrometeoroids and reusability requirements add complications which are in need of solutions. Improvement of container configurations is necessary, essentially, for economical reasons. Shorter tanks, e.g., mean shorter vehicles, reduced bending moments, higher vehicle frequencies--advantages which go far beyond the tanks themselves. Even if no length or weight reductions are achieved, reduced manufacturing costs are certainly also a desirable result. Other containers, such as crew compartments, can be designed to offer more volume without increased stage length.

The requirements for on-board checkout for advanced space missions are identified and an on-board checkout system capable of meeting the requirements is defined. The development of a major hardware element of the defined system is discussed. Application of advanced design technology to the developed hardware has permitted substantial capability to be incorporated on board advanced mission vehicles with very little weight, volume and power consumption penalty. The on-board checkout system software development and application are described.

The development of a unique micro quenched age formed (MQAF) process for producing titanium alloys of shallow hardening composition with deep hardening characteristics is described. Also, in line with the desire to improve the elevated temperature strength of titanium alloys, an alternate approach has been devised for producing titanium alloys with useful strength above 1000 F. Data are presented on the development of composites of two titanium alloys, each constituent possessing complementary properties. It is believed that this bi-alloy concept offers great potential for titanium alloys in the high-temperature range.

MAN AND COMPUTER can work together on the design of complex components and systems using graphic input/output devices. Man-oriented I/O devices such as light pens, keyboards and displays extend the capabilities of man and computer in evolving a design. Typical design problems include a large volume of data, a profusion of calculations, interrelated decisions, and iterative operations - all readily processed by a computer. These problems also contain creative analytical or job coordination tasks which can be performed best by skilled human specialists. The graphic interface permits “conversational” communication between the specialist (frequently an engineer) and the computing equipment, in the form or a symbolic language having both pictorial and alphameric elements. Such a language is currently the medium for engineering thought, expression and documentation.

Objectives of the Saturn Program have necessitated a more accurate knowledge of the vehicle mass and lift-off weight. Since propellants constitute the major portion of the vehicle mass, a method of accurately determining and regulating the quantity of propellants on board the vehicle is a primary requirement. Several elements are involved in providing accurate on-board quantities of vehicle propellants. Of most significance are the vehicle propellants sensors, storage and transfer facilities, and a system to monitor the sensors and control the transfer facilities. The purpose of this paper is to describe the functions and operation of the Propellant Tanking Computer System (PTCS) which performs this propellant monitor and control function for Saturn IB and Saturn V vehicles. The PTCS was developed for NASA KSC by G.E., KSCSO.

During the F-1 rocket engine program, turbine exhaust gases have been successfully used to film cool large thrust chamber nozzle extensions. This design concept provides the engine with a detachable nozzle of low weight, simple construction, and a service life equivalent to that of the basic engine. Several nozzle extension concepts are reviewed, and a comparison is made in terms of operational advantages and engine application as defined by required nozzle geometry, heat flux, and available coolant. The particular application for which the gas-cooled concept is the most desirable engineering choice is discussed in detail. Experimental data obtained during development are presented, with particular emphasis given to thermal analysis considerations. The correlation observed between predicted and measured temperatures is also discussed.

The Douglas Aircraft Co. has developed a concept known as the Fixed Service Tower (FST) to increase the efficiency of medium space vehicle buildup and servicing operations. Advantages of the concept are presented in this paper by first discussing present flight preparation procedures for the National Aeronautics and Space Administration Improved Delta vehicle and then discussing how these procedures would be improved by utilizing the FST techniques. Aspects of the FST, which are covered in detail, include location, configuration, flexibility, growth potential, launch environment, cost, and implementation status.

In the past testing of airborne electronics equipment has for the most part fallen into the category of either completely manual or fully automatic. While manual test equipment is relatively simple and inexpensive, it is too slow for testing many of today's multiple-output electronic packages. To reduce checkout time, more sophisticated automatic test systems have been built. However, the automated equipment requires elaborate programming and storage facilities, and the overall cost of this equipment tends to be astronomical. This paper presents an examination of current maintenance problems in the Tactical Air Command and investigates problems associated with some of the automatic test systems in use today. The merits of semiautomatic test equipment are discussed as a possible optimum solution to many of these problems. As an illustration, a design problem is presented along with a practical approach and solution.

Some insights into problems associated with the design and use of ground vehicles for tactical missile and electronic systems are presented. The problems of shock and vibration, operating deflections, and range of payloads are treated briefly. Some guidelines are provided in selection and design of ground vehicles, and descriptions are provided of some vehicles currently in use.

On-board test systems are reviewed from the initial establishment of a need through the technical and economic trades of implementation. The varying needs of different users are considered along with the assistance that can be effected in operations and maintenance activities. Systems within the state-of-the-art are discussed along with idealized future possibilities.

In order to efficiently maintain an operational aircraft in its intended environment, adequate and timely aerospace ground equipment (AGE) must be made available for the first flight test phase of the aircraft development program. This demands that a systematic approach to defining AGE be instigated early in the conceptual design phase and that a program considering the following disciplines be established: intended aircraft mission and utilization, maintenance goals, and reliability of the aircraft in terms of individual subsystems and their interface functions. These primary variables are combined to establish the basic requirements for AGE. The detailed requirements for AGE must be obtained through aircraft subsystem analysis designating to what extent each subsystem requires support and then how this support is to be implemented.

Spark plug thermal characteristcs were investigated for both propane and butane at various altitudes. These tests show that under ordinary conditions, if the correct spark plug heat range is installed at sea level, the selection does not need to be changed for higher altitude operation. Operating spark plug temperatures were lower with butane as compared with propane and may warrant, in some instances, a hotter heat range. Knock-limited spark advance increased with altitude, but decreased with increasing compression ratios. There is no significant spark plug voltage requirement change under running conditions, as altitude is increased from roughly sea level to 8000 ft.

Accident statistics indicate that postcrash fire is one of the most serious threats to human life in aircraft crashes. It is also a serious threat in automotive crashes. Several methods are available to reduce this hazard. The simplest and most effective method is through control of the fuel spillage. Aircraft crash testing has shown that fuel systems incorporating tough, flexible fuel tanks that are smooth in contour, free from rigid attachments, and mated with flexible fluid lines are capable of preventing fuel spillage during crashes involving decelerative loading above the human survival range.

A working system of peak to valley surface roughness control has been developed and is in use on selected aerospace production hardware. The system, while similar to the Swedish H system, has additional flexibility for the design engineer. A test in which seven companies participated proved the compatibility of roughness values obtained.

This paper defines system effectiveness and identifies the framework within which such a program operates. The objectives of a system effectiveness program are covered, along with the tasks in the program. An example of the use of the model during system life is given. The role of the modeler is outlined, especially his responsibility for good communications with the system effectiveness team. No detailed mathematical terminology is used.

This paper briefly describes systems effectiveness work currently under way at the Army Missile Command. Two basic types of systems effectiveness analyses performed on Army missile systems are described together with their time phasing during the life cycle of the weapon. The Command conducts major operations research studies at the outset of each major development program and at points where significant changes in system characteristics occur. All system performance parameters are analyzed in the context of a “mix” of weapons in a dynamic battlefield environment. Factors such as mobility, survivability, kill probability, and firepower are considered. Normally, these studies are used to demonstrate the cost effectiveness of proposed systems and to conduct initial parametric design trade-off studies. The second type is that of mission reliability assessment.

Frequently, a choice between system concepts must be made on the basis of something other than a detailed evaluation of the design effectiveness of these systems. This paper develops a rudimentary analysis process for use in addressing this problem.

This paper discusses general and specific requirements of AFSCM 375-5 as applied to control and surveillance systems. The ingredients of the total design concept to achieve operational effectiveness includes specifications, analyses, engineering reviews, and tests. The concepts of utility, acquisition time, effectiveness, and cost are discussed. Model and trade-off considerations are presented. Applications of WSEIAC and AFSCM 375-5 principles and procedures to three complex electronic systems are illustrated.