Download or read book Orbital Transfer Vehicle Engine Technology written by and published by . This book was released on 1991 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: New technologies for space-based, reusable, throttleable, cryogenic orbit transfer propulsion are being evaluated. The supporting tasks for the design of a dual-expander cycle engine thrust chamber design are documented in this report. This supports plans for development of a new Orbit Transfer Vehicle (OTV) to be operational in the late 1990s. Critical to the economical operation of a space based OTV is a new H2/O2 rocket engine with capabilities superior to available engines. Available engine characteristics and those required of a new engine are summarized. In total, these requirements represent a substantial advance in the state-of-the-art technologies and a considerable challenge to rocket engine designers. OTV engine studies have identified a dual-propellant expander cycle as offering advantages over either staged combustion or gas generator cycles. The purpose of the studies documented in this report was to research the materials used in the thrust chamber design, the supporting fabrication methods necessary to complete the design, and the modification of the injector element for optimum injector/chamber compatibility.
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 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 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 Vehicle Engine Technology written by J. A. Schneider and published by . This book was released on 1991 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Future Orbital Transfer Vehicle Technology Study Volume 2 Technical Report written by Eldon E. Davis and published by . This book was released on 1982 with total page 260 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study has the objective of identifying missions for future orbit transfer vehicles (1995-2010) and defining the technology, operations and vehicle concepts that satisfy the transportation requirements. Several issues were examined. The first involved comparison of reusable space and ground based LO2/LH2 OTV's. Both vehicles used advanced space engines and aero assist capability. The SB OTV provided advantages in life cycle cost, performance and potential for improvement. The second issue was the comparison of an all LO2/LH2 OTV fleet with a fleet of LO2/LH2 OTVs and electric OTV's. The normal growth technology electric OTV used silicon cells with heavy shielding and argon ion thrusters. In this case, the LO2/LH2 OTV fleet provided a 23% advantage in total transportation cost. The third issue dealt with the impact of accelerated technology. An accelerated technology LF2/LH2 OTV provided improvements in performance relative to LO2/LH2 OTV but had higher DDT & E cost which negated its cost effectiveness. The accelerated technology electric vehicle used GaAs cells and annealing but still did not result in the mixed fleet being any cheaper than an all LO2/LH2 OTV fleet. The study conclusion is that reusable LO2/LH2 OTV's can serve all general purpose cargo roles between LEO and GEO for the foreseeable future. The most significant technology for the second generation vehicle would be space debris protection, on-orbit propellant storage and transfer and on-orbit maintenance capability.
Download or read book Orbit Transfer Vehicle Engine Technology Program written by P. T. Coleman 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 Orbital Transfer Rocket Engine Technology 7 5k LB Thrust Rocket Engine Preliminary Design written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-27 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary design of an advanced LOX/LH2 expander cycle rocket engine producing 7,500 lbf thrust for Orbital Transfer vehicle missions was completed. Engine system, component and turbomachinery analysis at both on design and off design conditions were completed. The preliminary design analysis results showed engine requirements and performance goals were met. Computer models are described and model outputs are presented. Engine system assembly layouts, component layouts and valve and control system analysis are presented. Major design technologies were identified and remaining issues and concerns were listed. Harmon, T. J. and Roschak, E. Unspecified Center AD-A276954, NASA-CR-190754, NAS 1.26:190754, RI/RD88-291 NAS3-23773...
Download or read book Orbital Transfer Vehicle Engine Technology Baffled Injector Design Fabrication and Verification written by J. A. Schneider and published by . This book was released on 1991 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Future Orbital Transfer Vehicle Technology Study Volume 1 Executive Summary written by Eldon E. Davis and published by . This book was released on 1982 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Definition Technology Readiness and Development Cost of the Orbit Transfer Vehicle Engine Integrated Control and Health Monitoring System Elements written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: An Integrated Control and Health Monitoring (ICHM) system was conceived for use on a 20 Klb thrust baseline Orbit Transfer Vehicle (OTV) engine. Considered for space used, the ICHM was defined for reusability requirements for an OTV engine service free life of 20 missions, with 100 starts and a total engine operational time of 4 hours. Functions were derived by flowing down requirements from NASA guidelines, previous OTV engine or ICHM documents, and related contracts. The elements of an ICHM were identified and listed, and these elements were described in sufficient detail to allow estimation of their technology readiness levels. These elements were assessed in terms of technology readiness level, and supporting rationale for these assessments presented. The remaining cost for development of a minimal ICHM system to technology readiness level 6 was estimated. The estimates are within an accuracy range of minus/plus 20 percent. The cost estimates cover what is needed to prepare an ICHM system for use on a focussed testbed for an expander cycle engine, excluding support to the actual test firings. Cannon, I. and Balcer, S. and Cochran, M. and Klop, J. and Peterson, S. Unspecified Center...
Download or read book Orbit transfer vehicle engine technology program combustor wall condition monitoring subtask II task E 5 written by B. L. Szemenyei and published by . This book was released on 1988 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Definition Technology Readiness and Development Cost of the Orbit Transfer Vehicle Engine Integrated Control and Health Monitoring System Elements written by and published by . This book was released on 1991 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Orbit Transfer Rocket Engine Technology 7 5K LB Thrust Rocket Engine Preliminary Design written by T. J. Harmon and published by . This book was released on 1993 with total page 233 pages. Available in PDF, EPUB and Kindle. Book excerpt: A preliminary design of an advanced LOX/ LH2 expander cycle rocket engine producing 7,500 lbf thrust for Orbital Transfer vehicle missions was completed. Engine system, component and turbomachinery analysis at both on design and off design conditions were completed. The preliminary design analysis results showed engine requirements and performance goals were met. Computer models are described and model outputs are presented. Engine system assembly layouts, component layouts and valve and control system analysis are presented. Major design technologies were identified and remaining issues and concerns were listed. Orbit Transfer Vehicle(OTV). Expander cycle, Hydrogen/oxygen rocket engine, Space based engine. High pressure fuel turbopump.
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 Orbit Transfer Vehicle Engine Technology Program Task B 6 High Speed Turbopump Bearings written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-13 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Bearing types were evaluated for use on the Orbit Transfer Vehicle (OTV) high pressure fuel pump. The high speed, high load, and long bearing life requirements dictated selection of hydrostatic bearings as the logical candidate for this engine. Design and fabrication of a bearing tester to evaluate these cryogenic hydrostatic bearings was then conducted. Detailed analysis, evaluation of bearing materials, and design of the hydrostatic bearings were completed resulting in fabrication of Carbon P5N and Kentanium hydrostatic bearings. Rotordynamic analyses determined the exact bearing geometry chosen. Instrumentation was evaluated and data acquisition methods were determined for monitoring shaft motion up to speeds in excess of 200,000 RPM in a cryogenic atmosphere. Fabrication of all hardware was completed, but assembly and testing was conducted outside of this contract. Unspecified Center...
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...
