Paper Session III-A - The Advanced Solid Rocket Motor Project

On April 21, 1989, NASA informed Lockheed CEO Dan Tellep that Lockheed Missiles & Space Company had been selected for negotiations of the Advanced Solid Rocket Motor (ASRM). Lockheed Missiles & Space Company, specifically the Missile Systems Division, is the prime contractor to the Marshall Space Flight Center for the ASRM. Teamed with Lockheed as major subcontractors are Aerojet Space Boosters and Rust International as shown in Figure 1. Lockheed Missiles Systems Division\u27s primary function for more than thirty years has been the systems management of major Fleet Ballistic Missile programs for the United States Navy. In those projects, Lockheed subcontractors have been all of the major solid propellant contractors in the United States. Lockheed\u27s role resulting from this experience base is that of project manager, where Lockheed provides systems engineering and integration of the entire project. Lockheed\u27s association with Aerojet as subcontractor on the Polaris program, dates back to the mid-1950\u27s; thus the ASRM project represents a continuation of a long and productive association between the two major corporations. Aerojet, the major participant in the project, is responsible for the design, analysis and engineering of the rocket motor, as well as the manufacturing, quality assurance and testing. The other major subcontractor to Lockheed is Rust International, headquartered in Birmingham, Alabama. Rust is one of the largest domestic construction companies in the United States and will be responsible for the design and engineering of the facility, procurement and installation of equipment, and managing the construction activities

A digital control system for high level acoustic noise generation

As part of the modernization of the Acoustic Test Facility at Lockheed Missiles and Space Company, Sunnyvale, a digital acoustic control system was designed and built. The requirements imposed by Lockheed on the control system and the degree to which those requirements were met are discussed. Acceptance test results as well as some of the features of the digital control system not found in traditional manual control systems are discussed

Spacecraft Redundancy and Environmental Tests: An Historic Evaluation

The necessity of providing highly redundant spacecraft in the shuttle era was evaluated. Environmental and acceptance tests were done. Histories of 67 spacecraft over a 12 year period were analyzed. The final result of this study is that LMSC (Lockheed Missiles and Space Co., Inc.) is convinced of the significant value of redundancy in spacecraft and systems environmental testing and such techniques should be carried forward into the shuttle era

Unsteady aerodynamic analysis of space shuttle vehicles. Part 2: Steady and unsteady aerodynamics of sharp-edged delta wings

An analysis of the steady and unsteady aerodynamics of sharp-edged slender wings has been performed. The results show that slender wing theory can be modified to give the potential flow static and dynamic characteristics in incompressible flow. A semiempirical approximation is developed for the vortex-induced loads, and it is shown that the analytic approximation for sharp-edged slender wings gives good prediction of experimentally determined steady and unsteady aerodynamics at M = 0 and M = 1. The predictions are good not only for delta wings but also for so-called arrow and diamond wings. The results indicate that the effects of delta planform lifting surfaces can be included in a simple manner when determining elastic launch vehicle dynamic characteristics. For Part 1 see (N73-32763)

A 928 sq m (10000 sq ft) solar array

As the power requirements for space vehicles increases, the area of solar arrays that convert solar energy to usable electrical power increases. The requirements for a 928 sq m (10,000 sq ft) array, its design, and a full-scale demonstration of one quadrant (232 sq m (2500 sq ft)) deployed in a one-g field are described

The aeroelastic characteristics of the Saturn IB SA-203 launch vehicle

Aeroelastic properties, and effects of boundary layer-terminal shock wave interaction on Saturn IB SA-203 launch vehicl

Summary of solid rocket motor plume flow field and radiation analyses

The inclusion of solid propellant plume flow field effects in analyses and design of the space vehicle was investigated. Results of these analyses are summarized

Engineers handbook - Low-G propellant behavior

Engineers handbook applicable in prediction of low gravity behavior of liquids in rocket propellant tank

Thermal performance of multilayer insulations Interim report

Heat flux and optical property measurement for multilayer insulatio

Gust penetration loads and elastic vehicle response for Saturn 5 launch vehicles

Analysis of gust penetration loads and associated elastic vehicle response of Saturn 5 launch vehicles AS-505 through AS-508 penetrating sinusoidal gust