Download or read book Orbit Transfer Rocket Engine Technology Program Advanced Engine Study Task written by and published by . This book was released on 1992 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: In Task D.6 of the Advanced Engine Study, three primary subtasks were accomplished: 1) Design and Parametric Data, 2) Engine Requirement Variation Studies, and 3) Vehicle Study/Engine Study Coordination. Parametric data were generated for vacuum thrusts ranging from 7500 lbf to 50000 lbf, nozzle expansion ratios from 600 to 1200, and engine mixture ratios from 5:1 to 7:1. the Failure Modes and Effects Analysis (FMEA) driven baseline design generated in Tasks D.4 and D.5 was used as a departure point for these parametric analyses. These data are intended to assist in vehicle definition and trade studies. In the Engine Requirements Variation Studies, the individual effects of increasing the throttling ratio from 10:1 to 20:1 and requiring the engine to operate at a maximum mixture ratio of 12:1 were determined. Off-design engine balances were generated at these extreme conditions and individual component operating requirements analyzed in detail. Potential problems were identified and possible solutions generated. In the Vehicle Study/Engine Study coordination subtask, vehicle contractor support was provided as needed, addressing a variety of issues uncovered during vehicle trade studies. This support was primarily provided during Technical Interchange Meetings (TIM) in which Space Exploration Initiative (SEI) studies were addressed.

Download or read book Orbit Transfer Rocket Engine Technology Program written by National Aeronaut Administration (Nasa) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-10 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: In Task D.6 of the Advanced Engine Study, three primary subtasks were accomplished: (1) design of parametric data; (2) engine requirement variation studies; and (3) vehicle study/engine study coordination. Parametric data were generated for vacuum thrusts ranging from 7500 lbf to 50,000 lbf, nozzle expansion ratios from 600 to 1200, and engine mixture ratios from 5:1 to 7:1. Failure Modes and Effects Analysis (FMEA) was used as a departure point for these parametric analyses. These data are intended to assist in definition and trade studies. In the Engine Requirements Variation Studies, the individual effects of increasing the throttling ratio from 10:1 to 20:1 and requiring the engine to operate at a maximum mixture ratio of 12:1 were determined. Off design engine balances were generated at these extreme conditions and individual component operating requirements analyzed in detail. Potential problems were identified and possible solutions generated. In the Vehicle Study/Engine Study coordination subtask, vehicle contractor support was provided as needed, addressing a variety of issues uncovered during vehicle trade studies. This support was primarily provided during Technical Interchange Meetings (TIM) in which Space Exploration Initiative (SEI) studies were addressed. Erickson, C. M. Unspecified Center...

Download or read book Orbit Transfer Rocket Engine Technology Program written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-14 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: An advanced near term (1990's) space-based Orbit Transfer Vehicle Engine (OTVE) system was designed, and the technologies applicable to its construction, maintenance, and operations were developed under Tasks A through F of the Orbit Transfer Rocket Engine Technology Program. Task A was a reporting task. In Task B, promising OTV turbomachinery technologies were explored: two stage partial admission turbines, high velocity ratio diffusing crossovers, soft wear ring seals, advanced bearing concepts, and a rotordynamic analysis. In Task C, a ribbed combustor design was developed. Possible rib and channel geometries were chosen analytically. Rib candidates were hot air tested and laser velocimeter boundary layer analyses were conducted. A channel geometry was also chosen on the basis of laser velocimeter data. To verify the predicted heat enhancement effects, a ribbed calorimeter spool was hot fire tested. Under Task D, the optimum expander cycle engine thrust, performance and envelope were established for a set of OTV missions. Optimal nozzle contours and quick disconnects for modularity were developed. Failure Modes and Effects Analyses, maintenance and reliability studies and component study results were incorporated into the engine system. Parametric trades on engine thrust, mixture ratio, and area ratio were also generated. A control system and the health monitoring and maintenance operations necessary for a space-based engine were outlined in Task E. In addition, combustor wall thickness measuring devices and a fiberoptic shaft monitor were developed. These monitoring devices were incorporated into preflight engine readiness checkout procedures. In Task F, the Integrated Component Evaluator (I.C.E.) was used to demonstrate performance and operational characteristics of an advanced expander cycle engine system and its component technologies. Sub-system checkouts and a system blowdown were performed. Short transitions were then made into main combustor ignition and ...

Download or read book Orbit Transfer Rocket Engine Technology Program Advanced Engine Study written by and published by . This book was released on 1992 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program Phase 2 Advanced Engine Study written by and published by . This book was released on 1987 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program written by N. B. Gustafson and published by . This book was released on 1993 with total page 127 pages. Available in PDF, EPUB and Kindle. Book excerpt: An advanced near term (1990's) space-based Orbit Transfer Vehicle Engine (OTVE) system was designed, and the technologies applicable to its construction, maintenance, and operations were developed under Tasks A through F of the Orbit Transfer Rocket Engine Technology Program. Task A was a reporting task. In Task 8, promising OTV turbomachinery technologies were explored: two stage partial admission turbines, high velocity ratio diffusing crossovers, soft wear ring seals, advanced bearing concepts and a rotodynamic analysis. In Task C, a ribbed combustor design was developed. Possible rib and channel geometries were chosen analytically. Rib candidates were hot air tested and laser velocimeter boundary layer analyses were conducted. A channel geometry was also chosen on the basis of laser velocimeter data. To verify the predicted heat enhancement effects, a ribbed calorimeter spool was hot fire tested. Under Task D, the optimum expander cycle engine thrust, performance and envelope were established for a set of OTV missions. Optimal nozzle contours and quick disconnects for modularity were developed. Failure Modes and Effects Analyses, maintenance and reliability studies and component study results were incorporated into the engine system. Parametric trades on engine thrust, mixture ratio and area ratio were also generated. A control system and the health monitoring and maintenance operations necessary for a space-based engine were outlined in Task E.

Download or read book Orbital Transfer Rocket Engine Technology Advanced Engine Study Task D 6 Final Report written by and published by . This book was released on 1992 with total page 282 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents an advanced LOX/LH2 engine study for the use of NASA and vehicle prime contractors in developing concepts for manned missions to the Moon, Mars, and Phobos. Parametric design data was obtained at five engine thrusts from 7.5K lbf to 50K lbf. Also, a separate task evaluated engine throttling over a 20: 1 range and operation at a mixture ratio of 12 + or - 1 versus the 6 + or - 1 nominal. Cost data was also generated for DDT and E, first unit production, and factors in other life cycle costs. The major limitation of the study was lack of contact with vehicle prime contractors to resolve the issues in vehicle/engine interfaces. The baseline Aerojet dual propellant expander cycle was shown capable of meeting all performance requirements with an expected long operational life due to the high terminal margins. The basic engine design readily accommodated the 20:1 throttling requirement and operation up to a mixture ratio of 10 without change. By using platinum for baffled injector construction the increased thermal margin allowed operation up to mixture ratio 13. An initial engine modeling with an Aerojet transient simulation code (named MLETS) indicates stable engine operation with the baseline control system. A throttle rate of 4 to 5 seconds from 10% to 100% thrust is also predicted. Performance predictions are 483.1 sec at 7.5K lbf, 487.3 sec at 20K lbf, and 485.2 sec at 50k lbf with a mixture ratio of 6 and an area ratio of 1200. Engine envelopes varied+++om 120 in. length/53 in. exit diameter at 7.5K lbf to 305 in. length/136 in. exit diameter at 50K lbf. Packaging will be an important consideration. Continued work is recommended to include more vehicle prime contractor/engine contractor joint assessment of the interface issues.

Download or read book Orbital Transfer Rocket Engine Technology Advanced Engine Study written by and published by . This book was released on 1992 with total page 302 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program Automated Preflight Methods Concept Definition Task E 7 written by C. M. Erickson and published by . This book was released on 1991 with total page 109 pages. Available in PDF, EPUB and Kindle. Book excerpt: Orbit transfer engine preflight requirements were defined and a range of possible preflight methods were proposed. Critical issues and benefits were also identified for each method and technology readiness and development costs addressed. It would be advantageous in a space based setting to minimize or entirely eliminate preflight engine checkouts requiring manual/extravehicular interaction with the hardware. This study investigated the possibility of automating these checkouts. The minimum requirements in terms of information and processing necessary to assess the engine's integrity and readiness to perform its mission were first defined. A variety of ways of remotely obtaining that information, spanning a range of method sophistications were then generated. The sophistication of these approaches varied from a simple preliminary power up, where the engine is fired up for a short time, to the most advanced approach where the sensor and operational history data system alone indicates engine integrity. Critical issues and benefits of each of these methods were also identified, outlined, and prioritized. The technology readiness of these automated preflight methods were then rated on a NASA Office of Exploration Scale used for comparing technology options for future mission choices. Finally estimates were made of the remaining cost to advance the technology for each method to a level where the system validation models have been demonstrated in a simulated environment.

Download or read book Orbit Transfer Rocket Engine Technology Program Automated Preflight Methods Concept Definition written by and published by . This book was released on 1991 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program written by Leonard Schoenman and published by . This book was released on 1989 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Final Report Orbit Transfer Rocket Engine Technology Program written by C. M. Erickson and published by . This book was released on 1991 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Orbit Transfer Rocket Engine Technology Program Task C 5 Enhanced Heat Transfer Combustor Technology written by and published by . This book was released on 1991 with total page 171 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to increase the performance of a high performance, advanced expander-cycle engine combustor, higher chamber pressures are required. In order to increase chamber pressure, more heat energy is required to be transferred to the combustor coolant circuit fluid which drives the turbomachinery. This requirement was fulfilled by increasing the area exposed to the hot-gas by using combustor ribs. A previous technology task conducted 2-d hot air and cold flow tests to determine an optimum rib height and configuration. In task C.5 a combustor calorimeter was fabricated with the optimum rib configuration, 0.040 in. high ribs, in order to determine their enhancing capability. A secondary objective was to determine the effects of mixture ratio changers on the enhancement during hot-fire testing. The program used the Rocketdyne Integrated Component Evaluator (ICE) reconfigured into a thrust chamber only mode. The test results were extrapolated to give a projected enhancement from the ribs for a 16 in. long cylindrical combustor at 15Klb nominal thrust level. The hot-gas wall ribs resulted in a 58% increase in heat transfer. When projected to a full size 15K combustor, it becomes a 46% increase. The results of those tests, a comparison with previous 2-d results, the effects of mixture ratio and combustion gas flow on the ribs and the potential ramifications for expander cycle Combustors are detailed. Enhanced heat transfer combustor, Ribbed combustor, Hot-gas wall ribs, Heat transfer enhancement.

Download or read book NASA Orbit Transfer Rocket Engine Technology Program written by and published by . This book was released on 1984 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technology for Large Space Systems written by and published by . This book was released on 1987 with total page 508 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1994 with total page 956 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monthly Catalogue United States Public Documents written by and published by . This book was released on 1991 with total page 1690 pages. Available in PDF, EPUB and Kindle. Book excerpt: