Task 12 data dump (phase 2) OME integrated thrust chamber test report

The characteristics and performance of the orbit maneuvering engine for the space shuttle are discussed. Emphasis is placed on the regeneratively cooled thrust chamber of the engine. Tests were conducted to determine engine operating parameters during the start, shutdown, and restart. Characteristics of the integrated thrust chamber and the performance and thermal conditions for blowdown operation without supplementary boundary layer cooling were investigated. The results of the test program are presented

Tank 12 data dump OME integrated thrust chamber test report, phase 1

The test program conducted to characterize the steady state stability, thermal, and performance characteristics of the integrated thrust chamber assembly, as well as limited tests to investigate transient characteristics are described

Space shuttle orbit maneuvering engine reusable thrust chamber program

Analyses and preliminary designs of candidate OME propellant combinations and corresponding engine designs were conducted and evaluated in terms of performance, operating limits, program cost, risk, inherent life and maintainability. For the Rocketdyne recommended and NASA approved propellant combination and cooling concept (NTO/MMH regeneratively cooled engine), a demonstration thrust chamber was designed, fabricated, and experimentally evaluated to define operating characteristics and limits. Alternate fuel (50-50) operating characteristics were also investigated with the demonstration chamber. Adverse operating effects on regenerative cooled operation were evaluated using subscale electrically heated tubes and channels. An investigation of like doublet element characteristics using subscale tests was performed. Full scale 8- and 10-inch diameter like-doublet injectors for the OME were designed, fabricated, and tested. Injector stability was evaluated analytically and experimentally

Integral Glass Encapsulation for Solar Arrays

Work reported was performed during the period from August 1977 to December 1978. The program objective was to continue the development of electrostatic bonding (ESB) as an encapsulation technique for terrestrial cells. Economic analyses shows that this process can be a cost-effective method of producing reliable, long lifetime solar modules. When considered in sufficient volume, both material and equipment costs are competitive with conventional encapsulation systems. In addition, the possibility of integrating cell fabrication into the encapsulation process, as in the case of the preformed cell contacts discussed in this report, offers the potential of significant overall systems cost reduction

Supply Chain Resilience: Assessing USAF Weapon System Life Cycle

The Air Force Global Logistics Support Center (AFGLSC) is responsible for the United States Air Force’s supply chain. One of the AFGLSC’s responsibilities is to improve AF supply chain processes. This thesis investigates the subject of supply chain resilience and its potential impact for improving supply chain management. Through literature a supply chain resilience framework and measurement tool was identified for potential benefit to Air Force supply chain management. Air Force weapon systems were identified and segmented into two phases of the weapon system life cycle. This research analyzes data collected on supply chain resilience factors, vulnerabilities and capabilities, for each individual weapon system to determine if differences exist as weapon systems progress through the weapon system life cycle. The results indicate that the supply chain resilience framework and measurement tool provides Air Force leadership with beneficial information to improve and assist in the strategic management of their supply chain

Space shuttle orbit maneuvering engine reusable thrust chamber program

Tests were conducted on the regenerative cooled thrust chamber of the space shuttle orbit maneuvering engine. The conditions for the tests and the durations obtained are presented. The tests demonstrated thrust chamber operation over the nominal ranges of chamber pressure mixture ratio. Variations in auxiliary film coolant flowrate were also demonstrated. High pressure tests were conducted to demonstrate the thrust chamber operation at conditions approaching the design chamber pressure for the derivative space tug application