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Propulsion Engineering Innovations Thermal Protection Systems Propulsion Engineering Innovations Thermal Protection Systems Materials and Manufacturing Aerodynamics and Flight Dynamics Avionics, Navigation, and Instrumentation Software Structural Design Robotics and Automation Systems Engineering for Life Cycle of Complex Systems Engineering Innovations 157 Propulsion The launch of the Space Shuttle was probably the most visible event of the entire mission cycle. The image of the Main Propulsion System— the Space Shuttle Main Engine and the Solid Rocket Boosters (SRBs)— Introduction powering the Orbiter into space captured the attention and the Yolanda Harris imagination of people around the globe. Even by 2010 standards, Space Shuttle Main Engine these main engine s’ performance was unsurpassed compared to any Fred Jue other engines. They were a quantum leap from previous rocket engines. Chemochromic Hydrogen Leak Detectors The main engines were the most reliable and extensively tested rocket Luke Roberson engine before and during the shuttle era. Janine Captain Martha Williams The shuttl e’s SRBs were the largest ever used, the first reusable rocket, Mary Whitten and the only solid fuel certified for human spaceflight. This technology, The First Human-Rated engineering, and manufacturing may remain unsurpassed for decades Reuseable Solid Rocket Motor Fred Perkins to come. Holly Lamb But the shuttl e’s propulsion capabilities also encompassed the Orbite r’s Orbital Propulsion Systems Cecil Gibson equally important array of rockets—the Orbital Maneuvering System Willard Castner and the Reaction Control System—which were used to fine-tune orbits Robert Cort and perform the delicate adjustments needed to dock the Orbiter Samuel Jones with the International Space Station. The design and maintenance of Pioneering Inspection Tool the first reusable space vehicle—the Orbiter—presented a unique set Mike Lingbloom of challenges. In fact, the Space Shuttle Program developed the worl d’s Propulsion Systems and Hazardous Gas Detection most extensive materials database for propulsion. In all, the shuttl e’s Bill Helms propulsion systems achieved unprecedented engineering milestones and David Collins launched a 30-year era of American space exploration. Ozzie Fish Richard Mizell 158 Engineering Innovations Space Shuttle Main Engine S Spa ce Shu ttle M ain En gine Prop ellan t Flow NASA faced a unique challenge at Hydrydrogenogen Oxygen the beginning of the Space Shuttle Inlet Inlet Low-pressureLow-pressure LLow-pressureow-preessurssure Program: to design and fly a Fuel TTurbopumpurbopump Oxidizer TTurbopumpurbopump human-rated reusable liquid propulsion Main Oxidizer Oxidizer rocket engine to launch the shuttle. VValvealve VValvealvealv It was the first and only liquid-fueled rocket engine to be reused from Oxidizer VValvealve Oxidizer one mission to the next during the PPreburnerreburner shuttle era. The improvement of the Fuel Main Space Shuttle Main Engine (SSME) PPreburnerreburner Injector was a continuous undertaking, Powerhead with the objectives being to increase safety, reliability, and operational Main margins; reduce maintenance; and Fuel VValvealve Main improve the life of the engine’s Combustion High-prigh-pressureessure Chamber Oxidizer TTurbopumpurbopump high-pressure turbopumps. Nozzle HHigh-pressureigh-pressure FFueluel TTurbopumpurbopump The reusable SSME was a staged . d e v r combustion cycle engine. Using a e s Chamber e r s mixture of liquid oxygen and liquid Coolant VValvealvalve t h g i r l hydrogen, the main engine could attain l A . e n a maximum thrust level (in vacuum) y d t e of 232,375 kg (512,300 pounds), k c o R The Space Shuttle Main Engine used a two-stage combustion process. Liquid hydrogen which is equivalent to greater than y e n t and liquid oxygen were pumped from the External Tank and burned in two preburners. i 12,000,000 horsepower (hp). The h W The hot gases from the preburners drove two high-pressure turbopumps—one for liquid & t engine also featured high-performance t a hydrogen (fuel) and one for liquid oxygen (oxidizer). r P fuel and oxidizer turbopumps that © developed 69,000 hp and 25,000 hp, respectively. Ultra-high-pressure by the new Space Transportation The design team chose a dual-preburner operation of the pumps and combustion System (STS). powerhead configuration to provide chamber allowed expansion of hot precise mixture ratio and throttling In 1971 , the Rocketdyne division of gases through the exhaust nozzle to control. A low- and high-pressure Rockwell International was awarded a achieve efficiencies never previously turbopump, placed in series for each of contract to design, develop, and attained in a rocket engine. the liquid hydrogen and liquid oxygen produce the main engine. loops, generated high pressures across a Requirements established for Space The main engine would be the first wide range of power levels. Shuttle design and development began production-staged combustion in the mid 1960s. These requirements A weight target of 2,857 kg (6,300 cycle engine for the United States. called for a two-stage-to-orbit vehicle pounds) and tight Orbiter ascent (The Soviet Union had previously configuration with liquid oxygen envelope requirements yielded a demonstrated the viability of staged (oxidizer) and liquid hydrogen (fuel) compact design capable of generating combustion cycle in the Proton vehicle for the Orbiter’s main engines. By a nominal chamber pressure of in 1965.) The staged combustion 1969, NASA awarded advanced engine 211 kg/cm 2 (3,000 pounds/in 2)—about cycle yielded high efficiency in a studies to three contractor firms to four times that of the Apollo/Saturn technologically advanced and complex further define designs necessary to J-2 engine. engine that operated at pressures meet the leap in performance demanded beyond known experience. Engineering Innovations 159 For the first time in a boost-to-orbit rocket engine application, an on-board digital main engine controller continuously monitored and controlled all engine functions. The controller Michael Coats Pilot on STS-41D (1984). initiated and monitored engine Commander on STS-29 (1989) parameters and adjusted control and STS-39 (1991). valves to maintain the performance parameters required by the mission. When detecting a malfunction, it also commanded the engine into a safe A Balky Hydrogen Valve lockup mode or engine shutdown. Halts Discovery Liftoff “I had the privilege of being the pilot on the maiden flight of the Orbiter Design Challenges Discovery, a hugely successful mission. We deployed three large communications Emphasis on fatigue capability, satellites and tested the dynamic response characteristics of an extendable strength, ease of assembly and solar array wing, which was a precursor to the much-larger solar array wings disassembly, maintainability, and materials compatibility were all major on the International Space Station. considerations in achieving a fully “But the first launch attempt did not go quite as we expected. Our pulses were reusable design. racing as the three main engines sequentially began to roar to life, but as we Specialized materials needed to be rocked forward on the launch pad it suddenly got deathly quiet and all motion incorporated into the design to meet the severe operating environments. NASA stopped abruptly. With the seagulls screaming in protest outside our windows, successfully adapted advanced alloys, it dawned on us we weren’t going into space that day. The first comment including cast titanium, Inconel ® 718 came from Mission Specialist Steve Hawley, who broke the stunned silence (a high-strength, nickel-based superalloy by calmly saying ‘I thought we’d be a lot higher at MECO (main engine cutoff).’ used in the main combustion chamber So we soon started cracking lousy jokes while waiting for the ground crew support jacket and powerhead), and to return to the pad and open the hatch. The joking was short-lived when NARloy-Z (a high-conductivity, copper-based alloy used as the liner in we realized there was a residual fire coming up the left side of the Orbiter, fed the main combustion chamber). NASA from the same balky hydrogen valve that had caused the abort. The Launch also oversaw the development of Control Center team was quick to identify the problem and initiated the water single-crystal turbine blades for the deluge system designed for just such a contingency. We had to exit the pad high-pressure turbopumps. This elevator through a virtual wall of water . We wore thin, blue cotton flight suits innovation essentially eliminated the grain boundary separation failure back then and were soaked to the bone as we entered the air-conditioned mechanism (blade cracking) that had astronaut van for the ride back to crew quarters. Our drenched crew shivered limited the service life of the pumps. and huddled together as we watched the Discovery recede through the rear Nonmetallic materials such as Kel-F ® window of the van, and as Mike Mullane wryly observed, ‘This isn’t exactly (a plastic used in turbopump seals), ® what I expected spaceflight to be like.’ The entire crew, including Commander Armalon fabric (turbopump bearing cage material), and P5N carbon-graphite Henry Hartsfield, the other Mission Specialists Mike Mullane and Judy Resnik, seal material were also incorporated and Payload Specialist Charlie Walker, contributed to an easy camaraderie that into the design. made the long hours of training for the mission truly enjoyable.” Material sensitivity to oxygen environment was a major concern for compatibility due to reaction and 160 Engineering Innovations ignition under the high pressures. Mechanical impact testing had vastly expanded in the 1970s to accommodate the shuttle engine’s varied operating conditions. This led to a new class of liquid oxygen reaction testing up to 703 kg/cm 2 (1 0,000 pounds/in 2). d e v r e Engineers also needed to understand s e r s t long-term reaction to hydrogen effects h g i r l l to achieve full reusability. Thus, a A . e n whole field of materials testing evolved y d t e k to evaluate the behavior of hydrogen c o R y charging on all affected materials.
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