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This paper discusses several LOX/Hydrocarbon booster engines that are being considered for future launch vehicles. The various concepts are compared. ...Introducing liquid hydrogen to the liquid oxygen/hydrocarbon booster engine appears to offer many benefits.

With reusability accepted as a means of reducing operating costs, the size of the initial investment (research and development) is likely to determine the choice for the next generation boosters. High volume utilisation lifting bodies propelled by LH/LOX rockets in a vertical take-off mode are shown to be superior to several other concepts. ...Even lower costs can be shown for a modular concept (MUSTARD) in which basically identical lifting bodies units are utilised as both boosters and spacecraft. The concept is shown to be feasible, and progress on some aspects of the associated structural analysis is described.

Three critical aspects of implementing reusable booster concepts are discussed. These aspects center on requirements for economic justification, establishing the credibility of recurring cost characteristics, and means of minimizing development costs such that these nonrecurring costs are matched with the size of market which must amortize them. ...The impact of these factors on implementing a reusable booster development program is discussed. Approaches and possible programs are suggested that could make significant progress toward establishing our technological preparedness for reusable booster program implementation. ...Approaches and possible programs are suggested that could make significant progress toward establishing our technological preparedness for reusable booster program implementation.

The evolution of the booster system for the space shuttle is traced from the initial concepts employing liquid propellant,reusable boosters to the final selection of recoverable, solid rocket motors. ...The evolution of the booster system for the space shuttle is traced from the initial concepts employing liquid propellant,reusable boosters to the final selection of recoverable, solid rocket motors. The rationale associated with each of the several major decisions in the evolution process is discussed.

Control of contamination in rocket booster hydraulic systems is of paramount importance if these systems are to operate reliably. This paper presents a general summary of the problems associated with contamination control of rocket booster hydraulic systems and includes discussions of the nature of the contamination normally encountered in these systems, the results of the presence of this contamination, and the cleanliness criteria currently in use. ...This paper presents a general summary of the problems associated with contamination control of rocket booster hydraulic systems and includes discussions of the nature of the contamination normally encountered in these systems, the results of the presence of this contamination, and the cleanliness criteria currently in use.

Continuing evolutionary booster developments and improvements, in combination with space configured upper stages and strap-on solid motors, have provided the Air Force with this versatile family of small, medium and large launch vehicles.

In conclusion, possible applications for solid motors, either as prototype systems such as Titan III or intermediate type launch vehicles combining the solid booster first stage with a liquid fueled second stage for low earth orbit or lunar probes are outlined.

The Pegasus Air-Launched Space Booster is an innovative new space launch vehicle now under full-scale development in a privately-funded joint venture by Orbital Sciences Corporation (OSC) and Hercules Aerospace Company.

After burn out and separation of a conventional cylindrical booster configuration, the outer tank portions are discarded, leaving a lifting shaped center-body capable of re-entry, pull out, flyback and landing.

However, the descendants of the vehicle are still in production as an operational space booster after undergoing continuous improvement through such methods as uprating the main engine and electronics, addition of solid propellant thrust augmentation motors, extension of the propellant tanks, and adding the ability to mate with various upper stage vehicles.

Eight fixed-wing reusable horizontal landing booster point design concepts are presented and compared on the basis of weight, cost, technical difficulty, and availability date. ...The airbreathing first stage boosters, however, may offer more mission flexibility than the rocket first stages because of their capability to fly for longer periods within the earth's atmosphere.

In designing large booster structures, a major area requiring extensive stress analysis is the discontinuous region, such as the skirt intersection, the sculptured joint, and the reinforced opening.

This paper discusses the mechanical, hydraulic, and heat transfer aspects of designing a hydraulic system to gimbal the engine on the Saturn S-IVB Booster Stage. This stage requires restart capability after a moderate period of orbital coast.

A flow and ice particle trajectory analysis was performed for the booster of the Honeywell ALF502 engine. The analysis focused on two closely related conditions one of which produced an icing event and another which did not during testing of the ALF502 engine in the Propulsion Systems Lab (PSL) at NASA Glenn Research Center. ...This was attributed to the similar aerodynamic conditions in the booster for the two cases. The particle temperature and melt fraction were higher at the same location and particle size for the non-icing event than for the icing event case due to the higher incoming inflow temperature for the non-event case.

No wind tunnel testing was performed, despite the fact that in contrast to conventional boosters, aerodynamic forces have a major impact on both the performance and stability of Pegasus.

A significant part of the power reduction plan is to eliminate the use of the Orbiter's Booster Fan. To accomplish air exchange between the ISS and Orbiter, a series of fans are used which include the ISS U.S. ...Lab (USL)/Pressurized Mating Adaptor (PMA) Intermodule Ventilation (IMV) Fan, the Orbiter Booster Fan, and a portion of the capability provided by the Orbiter Cabin Fan. The elimination of the Booster Fan from the series was predicted to reduce the air exchange significantly, but to not cause any adverse Environmental Control and Life Support (ECLS) conditions in either the Orbiter or ISS. ...The elimination of the Booster Fan from the series was predicted to reduce the air exchange significantly, but to not cause any adverse Environmental Control and Life Support (ECLS) conditions in either the Orbiter or ISS.

These missions are interrelated in the paper with regard to booster and spacecraft capabilities. It is shown that a low-cost booster based largely on current expendable booster technology can meet these interrelated requirements. ...Although currently available booster technology could allow a major decrease in space-booster costs, hardware already built in the Saturn system has precluded any development efforts in this direction. ...This paper reviews the available alternatives and describes the characteristics and capabilities of a low-cost booster system which is both desirable and practically feasible for missions beginning as early as 1973.

In increasing development complexity, the vehicles evaluated include 1) existing developed equipment like the S-IC and S-IVB stages of Saturn V, 2) a new 260-inch diameter solid booster vehicle and 3) new pressure fed storable propellant booster vehicles. Comparisons are made evaluating the effort and cost required to implement the various systems and their individual operational costs. ...The low cost system selection changes with mission requirements and is further contingent on a booster stage recovery and reuse decision.