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Academic literature on the topic 'Aerospike engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "Aerospike engines"

1

Meiss, Jan-Hendrik, and Eric Besnard. "Numerical Analysis of Curved Thrusters for Multichamber Aerospike Engines in Flight Conditions." Journal of Propulsion and Power 33, no. 4 (July 2017): 1002–19. http://dx.doi.org/10.2514/1.b36332.

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Ashley, Steven. "Bringing Launch Costs Down to Earth." Mechanical Engineering 120, no. 10 (October 1, 1998): 62–68. http://dx.doi.org/10.1115/1.1998-oct-1.

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This article discusses the three federally funded projects that are underway to develop new rocket engines that can make it more affordable to send payloads into orbits. The new RS-68 propulsion system is Rocketdyne's entry in competition to power the US Air Force's new heavy-lift booster. The most ambitious of the new propulsion system designs is Rocketdyne's XRS-2200 linear aerospike engine, a seemingly nozzle-less oxygen/hydrogen powerplant that is designed to send the autonomously controlled NASA X-33 lifting body into orbit. The X-33 is being developed by Lockheed Martin Skunk Works, Palmdale, CA. The key for new launch vehicles, whether they're expendable or reusable, is to get the costs down. The article also highlights that the payload that can be lofted by a launch vehicle depends in large part on engine performance and the ratio of propellant to structural weight. Bell nozzles are designed to offer the best compromise of shape and length for a vehicle and flight path. Rocketdyne's R-68 engine is to be 17 feet tall and 8 feet wide at the base. The key to the R-68 engine design was the selection of hydrogen as the propellant rather than kerosene.

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Lewitowicz, Jerzy, Mirosław Kowalski, and Andrzej Żyluk. "Modern Diagnostics of Aircraft Gas Turbine Engines – Some Selected Issues / Nowoczesna Diagnostyka Lotniczych Silników Turbinowych - Wybrane Zagadnienia." Journal of KONBiN 29, no. 1 (December 1, 2014): 33–40. http://dx.doi.org/10.2478/jok-2014-0004.

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Abstract In aeronautics, the question of maintaining the highest possible level of flight safety is the most crucial issue. This is the reason why the scientists, engineers, and aerospace/aviation engineering staff keep searching for ever newer and more reliable methods of increasing the safety level. Therefore, new methods - primarily nondestructive ones - to diagnose aircraft turbine engines are looked for. These methods are expected to prove useful for the real-time monitoring of actual health of the engine and its assemblies. The paper has been intended to outline the most recent methods of diagnosing aircraft turbine engines, including the computed tomography methods as applied to assess health/maintenance status of turbine blades, for the phase mapping of increments in the engine’s rotational speed, to diagnose health/maintenance status of the compressor’s 1st stage rotor blades in pure jets. Other methods discussed are, e.g. vibroacoustic and tribological ones

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Zhou, P. L., and Y. Q. Qian. "Development of a modified diesel engine cycle." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 212, no. 2 (February 1, 1998): 145–50. http://dx.doi.org/10.1243/0954407981525867.

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This paper presents an investigation of a novel type of diesel engine cycle, an approximate constant pressure cycle. The prototype engine is called the diesel engine with oil cushioned piston (DEOCP). In contrast to conventional engines, the DEOCP has a variable cylinder volume which is controlled automatically by the engine's cylinder pressure. The variable cylinder pressure is achieved by inserting a hydraulic cylinder into the engine's piston rod. The engine cylinder pressure is thus self-controlled and an ideal constant pressure cycle can theoretically be achieved. Computer simulations and engine tests have shown that the DEOCP distinguishes itself with high cycle efficiency, improved low-load performance and good starting ability. A detailed theoretical analysis and test results are presented in the paper, as well as a discussion of existing problems and possible further developments. Development of the diesel engine with oil cushioned piston could break the limit of cycle efficiency of conventional engines, hence opening a new avenue for diesel engine development.

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Glowacki, Pawel Jan. "Aircraft piston engines on-condition exploitation." Aircraft Engineering and Aerospace Technology 90, no. 7 (October 1, 2018): 1095–103. http://dx.doi.org/10.1108/aeat-01-2017-0042.

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Purpose Currently, in many countries, aviation safety regulations allow piston engines exploitation above Time Between Overhaul (TBO) recommended by manufacturers. Upon fulfillment of certain requirements, which are already included in the manufacturers’ documentation, TBO extension is granted. National Aviation Authority has approved exploitation of piston engines to something like quasi on-condition maintenance, which has no technical proof behind. This leads to the conclusion that the current, simple way of the engine’s life extension is not the best solution for maintaining flight safety. Aircraft piston engines TBO extension requires changes in the current exploitation system. Design/methodology/approach The paper provides methodology for aircraft piston engines on-condition exploitation based on engine flight parameters (from cruise and takeoff) and engine oil particles analysis. The paper describes a method of diagnostic limits for certain engine parameters and elements in the oil assignation assuming that they come under rules of normal distribution. Findings It has been found that piston engines installed on maximum takeoff mass <5,700 kg class aircraft are the second biggest contributor as a source of aviation events, thereby having a significant impact on aviation safety. Engine flight parameters and elements content in the oil meet Gaussian rules. Practical implications Introduction of the engine on-condition exploitation into operation practices reduces the operator’s engine direct maintenance cost and increases technical knowledge of the employees and has a positive impact on flight safety. Originality/value It is the first scientific description in Poland, which proposes an empirically proved methodology of the aviation piston engines on-condition exploitation.

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Clifton, David A., Peter R. Bannister, and Lionel Tarassenko. "A Framework for Novelty Detection in Jet Engine Vibration Data." Key Engineering Materials 347 (September 2007): 305–10. http://dx.doi.org/10.4028/www.scientific.net/kem.347.305.

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A novelty detection approach to condition monitoring of aerospace gas-turbine engines is presented, providing a consistent framework for on- and off-line analysis, each with differing typical implementation constraints. On-line techniques are introduced for observing abnormality in engine behaviour during aircraft flights, and are shown to provide early warning of engine events in real-time. Off-line techniques within the same analysis framework are shown to allow the tracking of single engines and fleets of engines from ground-based monitoring stations on a flight-by-flight basis. Results are validated by comparison to conventional techniques, in application to aerospace engines and other industrial high-integrity systems.

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Bhasha, Sanjeev Gautam, Parul Malik, and Purnima Jain. "Ceramic Composites for Aerospace Applications." Diffusion Foundations 23 (August 2019): 31–39. http://dx.doi.org/10.4028/www.scientific.net/df.23.31.

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Ceramic composites is playing crucial role to accomplish highly efficiently and cost effective equipment for aerospace industry. The instigation of ceramics into aircraft industry is a promising step towards virtuous future. Ceramics has a key role in innovation of highly competent material for space travel which is highly economical and environmentally sustainable. Advancement in making fuel efficient engines are necessity in present scenario due to the harmful emissions releases in the environment by burning of fuel to power up engine. The high temperature application of composites makes it very attractive for aerospace applications. This light weight material has potential to thrust spacecraft upto ten times quicker with the identical fuel consumption, therefore significantly depreciating size of vehicle and increasing travel distance. The implementation of ceramics into jet engines and turbines increase the efficiency of engine due to its lighter weight and better thermal capabilities. A jet engine employing ceramic composites has manifest 15% more fuel saving when compared to the simple nickel based alloys. Hence, ceramic composites can replace nickel based alloys which has been a promising candidate for the engines of commercial aircrafts. Some disadvantages has been also discussed that is brittle failure and limited thermal and shock resistance.

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Skliros, Christos. "A CASE STUDY OF VIBRATION FAULT DIAGNOSIS APPLIED AT ROLLS-ROYCE T-56 TURBOPROP ENGINE." Aviation 23, no. 3 (January 17, 2020): 78–82. http://dx.doi.org/10.3846/aviation.2019.11900.

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Gas turbine engines include a plethora of rotating modules, and each module consists of numerous components. A component’s mechanical fault can result in excessive engine vibrations. Identification of the root cause of a vibration fault is a significant challenge for both engine manufacturers and operators. This paper presents a case study of vibration fault detection and isolation applied at a Rolls-Royce T-56 turboprop engine. In this paper, the end-to-end fault diagnosis process from starting system faults to the isolation of the engine’s shaft that caused excessive vibrations is described. This work contributes to enhancing the understanding of turboprop engine behaviour under vibration conditions and highlights the merit of combing information from technical logs, maintenance manuals and engineering judgment in successful fault diagnosis.

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Gosala, Dheeraj B., Cody M. Allen, Aswin K. Ramesh, Gregory M. Shaver, James McCarthy, Dale Stretch, Edward Koeberlein, and Lisa Farrell. "Cylinder deactivation during dynamic diesel engine operation." International Journal of Engine Research 18, no. 10 (February 1, 2017): 991–1004. http://dx.doi.org/10.1177/1468087417694000.

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Cylinder deactivation can be implemented at low loads in diesel engines to improve efficiency and aftertreatment thermal management through reductions in pumping work and airflow, respectively. The rate of increase of torque/power during diesel engine transients is limited by the engine’s ability to increase the airflow quickly enough to allow sufficient fuel addition to meet the desired torque/power. The reduced airflow during cylinder deactivation needs to be managed properly so as to not slow the torque/power response. This paper demonstrates that it is possible to operate a diesel engine at low loads in cylinder deactivation without compromising its transient torque/power capabilities, a key finding in enabling the practical implementation of cylinder deactivation in diesel engines.

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Yu, Bing, Wenjun Shu, and Can Cao. "A Novel Modeling Method for Aircraft Engine Using Nonlinear Autoregressive Exogenous (NARX) Models Based on Wavelet Neural Networks." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 161–69. http://dx.doi.org/10.1515/tjj-2017-0005.

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Abstract A novel modeling method for aircraft engine using nonlinear autoregressive exogenous (NARX) models based on wavelet neural networks is proposed. The identification principle and process based on wavelet neural networks are studied, and the modeling scheme based on NARX is proposed. Then, the time series data sets from three types of aircraft engines are utilized to build the corresponding NARX models, and these NARX models are validated by the simulation. The results show that all the best NARX models can capture the original aircraft engine’s dynamic characteristic well with the high accuracy. For every type of engine, the relative identification errors of its best NARX model and the component level model are no more than 3.5 % and most of them are within 1 %.

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Dissertations / Theses on the topic "Aerospike engines"

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Korak, Ghosh. "Model predictive control for civil aerospace gas turbine engines." Thesis, University of Sheffield, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.595827.

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Kiker, Adam Paul. "Experimental Investigations of Mini-Pulsejet Engines." NCSU, 2005. http://www.lib.ncsu.edu/theses/available/etd-08112005-134914/.

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An experimental 8 cm pulsejet was developed using scaling laws from research on both 50 and 15 cm pulsejets. The 8 cm jet operates in three different inlet configurations?conventional, perpendicular, and rearward. The rearward configuration features inlets facing in the opposite direction of the flight path and develops the maximum net thrust. Using a high frequency pressure transducer, the operational frequency of the pulsejet was obtained by monitoring the combustion chamber pressure. It was found that in the rearward configuration, the operational frequency of the jet decreases with increasing inlet length. In addition, the combustion chamber peak pressure rise per cycle increases significantly if the exhaust diameter is reduced. Using information from the 8 cm pulsejet, a 4.5 cm pulsejet was developed and is operational.

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Schoen, Michael Alexander. "Experimental Investigations in 15 Centimeter Class Pulsejet Engines." NCSU, 2005. http://www.lib.ncsu.edu/theses/available/etd-08082005-095911/.

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Testing is performed on the 15 centimeter class pulsejet engine in order to develop, study, and explore the operational characteristics. Valved and valveless operation, hydrogen and propane fuels, various fuel injection methods, and a range of geometric configurations are investigated for operational feasibility. The scaling capabilities of a valveless 15 centimeter class pulsejet of conventional design are studied by methodically varying inlet length, exit length, exit geometry, and inlet area to combustor area ratio (Ai/Ac). Engine performance is defined by measuring chamber pressure, internal gas temperatures, time-resolved thrust, operational frequency, and fuel flow rate. The scaling capability is characterized by the success of self-sustained combustion for each corresponding geometric configuration. Tail pipe length is found to be a function of valveless inlet length and may be further minimized by the addition of a diverging exit nozzle. Chemical kinetic times and Ai/Ac prove to be the two prominent controlling parameters in determining scaling behavior.

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OVERMAN, NICHOLAS. "FLAMELESS COMBUSTION APPLICATION FOR GAS TURBINE ENGINES IN THE AEROSPACE INDUSTRY." University of Cincinnati / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1163776616.

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Siddiqi, Majid. "Turbine Engine Control and Diagnostics." The Ohio State University, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=osu1420210543.

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Reichel, Jonathan R. "Parametric study of liquid fuel jet in crossflow at conditions typical of aerospace applications." Thesis, Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/22590.

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Nilamdeen, Mohamed Shezad. "An uncoupled multiphase approach towards modeling ice crystals in jet engines." Thesis, McGill University, 2010. http://digitool.Library.McGill.CA:8881/R/?func=dbin-jump-full&object_id=92185.

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Pietroniro, Asuka Gabriele. "Modelling coaxial jets relevant to turbofan jet engines." Thesis, KTH, Mekanik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-200909.

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Simulations of subsonic turbulent coaxial hot jets were conducted on two types ofunstructured grids within the framework of STAR-CCM+. The study case is based on atypical airliner turbofan engine model with a core nozzle and a fan nozzle, having a bypassratio of five. The two meshes used are a polyhedral one, suitable for complex surfaces, and atrimmed one mainly made of hexahedral cells. The sensitivity of the study case to variousinputs is attested using second and third order upwind schemes, modelling turbulence with aSST k-omega model. The project proves to be a valid feasibility study for a steady-statesolution on which an aeroacoustic analysis could be based in future works.

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Cosher, Christopher R. "Detailed Analysis of Previous Data Relevant to Foreign Particle Ingestion by GasTurbine Engines and Application to Modern Engines." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1461152408.

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Bulut, Jane. "Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basis of decided design characteristics, Angelino's method is used to design the nozzle contour through MATLAB. The flow field over the aerospike analyzed using commercial CFD program FLUENT for sea level, optimum expansion and vacuum conditions. Flow simulations are carried out for air (specific heat ratio, gamma= 1.4), and afterwards based on the obtained thrust values at each altitude for air, expected thrust values for the real propellant, LOX/LCH4 (specific heat ratio, gamma = 1.1664), are calculated. Finally, the study is concluded with the comparison of trend in thrust and specific impulse for conventional bell nozzle and aerospike. For the conventional bell engine the values obtained in commercial computational simulation of chemical rocket propulsion and combustion software RPA for bell nozzle with same characteristics with aerospike, Po = 30 bar and expansion ratio = 15, are taken as reference for sea level, optimum expansion level and vacuum condition performance. Due to its ability to adopt the altitude, aerospike delivers higher performance at the low altitudes with respect to the conventional bell nozzle which has the same expansion ratio and combustion chamber pressure. Last in order but not in importance, after obtaining the flow field on plug of the aerospike, the shock wave impingement on the nozzle surface at sea level has been investigated.

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Books on the topic "Aerospike engines"

1

Rieckhoff, T. J. High-speed observer: Automated streak detection for the aerospike engine. Marshall Space Flight Center, Ala: National Aeronautics and Space Administration, George C. Marshall Space Flight Center, 2001.

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Larson, Richard R. Automated testing experience of the linear aerospike SR-71 experiment (LASRE) controller. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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Aerospace propulsion systems. Singapore: Wiley, 2010.

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Rajamani, Ravi. Diagnostics and Prognostics of Aerospace Engines. Warrendale, PA: SAE International, 2018. http://dx.doi.org/10.4271/0768093082.

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Thompson, William Murry. Aerospace flight test engineer. Charleston, SC (809 Burnett Dr., Charleston 29412): W.M. Thompson, 1998.

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A shortage of engineers. New York: St. Martin's Press, 2001.

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Decôme, Guy. Joseph Szydlowski et son temps, ou, L'aventure de Turboméca. Tarbes: Conseil imprim, 1999.

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Decôme, Guy. Joseph Szydlowski et son temps, ou, L'aventure de Turboméca. Tarbes: Conseil imprim, 1999.

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American Institute of Aeronautics and Astronautics. AIAA aerospace design engineers guide. 6th ed. Reston, VA: American Institute of Aeronautics and Astronautics, 2012.

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Building aircraft and spacecraft: Aerospace engineers. New York: PowerKids Press, 2016.

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Book chapters on the topic "Aerospike engines"

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Gialanella, Stefano, and Alessio Malandruccolo. "Gas Turbine Aero-Engines." In Aerospace Alloys, 17–39. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-24440-8_2.

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Rezunkov, Yuri A. "Aerospace Laser-Propulsion Engine." In High Power Laser Propulsion, 133–70. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79693-8_4.

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Trinh, Diep V. "Materials for Solid Rocket Engines." In Aerospace Materials and Applications, 609–40. Reston ,VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624104893.0609.0640.

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Vishwanatha Rao, A. N., T. N. Satish, Anagha S. Nambiar, Soumemndu Jana, V. P. S. Naidu, G. Uma, and M. Umapathy. "Challenges in Engine Health Monitoring Instrumentation During Developmental Testing of Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 275–95. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_16.

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Williams, James C. "Aero Engine Materials." In Aerospace Materials and Applications, 579–608. Reston ,VA: American Institute of Aeronautics and Astronautics, Inc., 2018. http://dx.doi.org/10.2514/5.9781624104893.0579.0608.

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Nagappa, Rajaram, Sankarkumar Jeyaraman, and C. Kishore Kumar. "Design and Structures of Aircraft Engines." In Aerospace Materials and Material Technologies, 279–303. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2143-5_14.

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Devi Priya, T., Sunil Kumar, Devendra Pratap, S. Shylaja, T. N. Satish, and A. N. Vishwanatha Rao. "Rotor Blade Vibration Measurement on Aero Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 263–73. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_15.

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Jagadish Babu, Chinni, Mathews P. Samuel, and Antonio Davis. "In-Depth Analysis of the Starting Process of Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 219–42. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_13.

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Johnston, Peter. "The Aero-Engine Business Model: Rolls-Royce’s Perspective." In Supply Chain Integration Challenges in Commercial Aerospace, 237–48. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-46155-7_16.

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Kumar, Dilip, and Sanjay G. Barad. "Structural Health Assessment of Gas Turbine Engine Carcass." In Proceedings of the National Aerospace Propulsion Conference, 479–89. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_29.

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Conference papers on the topic "Aerospike engines"

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Kumakawa, A., T. Onodera, M. Yoshida, M. Atsumi, and I. Igarashi. "A study of aerospike-nozzle engines." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3526.

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Erickson, Chris, and Chris Erickson. "Thrust vector control selection in aerospike engines." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3307.

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Besnard, Eric, and John Garvey. "Development and Flight-Testing of Liquid Propellant Aerospike Engines." In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-3354.

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Besnard, Eric, and John Garvey. "Aerospike Engines for Nanosat and Small Launch Vehicles (NLV/SLV)." In Space 2004 Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-6005.

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Schnabel, Mark C., and Christopher M. Brophy. "Pressure Distribution and Performance Impacts of Aerospike Nozzles on Rotating Detonation Engines." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1626.

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Erickson, Chris, and Chris Erickson. "Power cycle selection in aerospike engines for single-stage-to-orbit (SSTO) applications." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3316.

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Lengade, Rohin. "A Prototype Aerospike: Another Fish in the Sea." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-23852.

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Abstract Exploration is in our DNA! It is this spark of curiosity that has taken us to the moon and beyond. It is not easy to get into orbit. The rockets that we build today are quite sophisticated. Although technology will improve, these massive machines will increasingly be complicated to play with. One big reason being the ‘tyranny of rocket equation.’ As of now, we do not have any technology that will propel us out into space without using rockets. We are constantly finding ways to make rockets more efficient and launch more meaningful payloads into orbit. This is done by intelligently choosing the propellants, radical change in the design of rocket nozzles, applying different rocket engine cycles and improving the manufacturing process. Quite recently, we find a range of rockets being developed. The most commonly used engine cycle is the gas generator cycle (open cycle). Another way is to use electric powered turbo pumps. This cycle is far simpler than a gas generator cycle as it uses batteries to directly power the pumps. However, unlike propellant tanks with fuel, these energy powerhouses (batteries), do not reduce their weight during flight. Hence they represent dead weight. This technology is preferred for smaller rockets. There is another, not so often used engine cycle, called the full flow combustion stage or closed cycle. This cycle is the most complicated cycle and was considered almost impossible to build. Here, the exhaust from the turbine is fed into the combustion chamber, turning it into useful thrust. Apart from engine cycles, various engine nozzles have also been researched on. The conventional bell shaped nozzle, although widely used, is designed for a specific altitude. This means that the rocket needs to be multi-staged. The aerospike nozzle however, is an altitude compensatory nozzle. Although an aerospike has never flown to space, it has been rigorously tested. Here in, is a concept design of a prototype aerospike rocket engine. The intention of the design is to solve the engineering complexity involved in making efficient rocket engines. From the research carried out over a period of time, the following problems were noticed in an aerospike: • Near full combustion of propellant was not observed. • Overall heating of the spike increased. • Thrust Vector Control was difficult. The suggested design concept aims to tackle the above mentioned problems. The key technology used here is additive manufacturing. Additive manufacturing provides great flexibility in design and manufacturing. The complexity involved in manufacturing the aerospike can be tackled with this. The exhaust from the turbine can be used to create additional thrust by letting it out from the bottom of the toroidal spike. Near full combustion of the fuel-oxidizer mixture can be achieved by a dedicated combustion chamber rotated around the exhaust pipe of the turbine; unlike previous aerospikes which didn’t. The outer shape of the combustion chamber will be cylindrical, which will house traditional thrust vector control assembly. The heating of the nozzle can be reduced by using high grade graphite, tungsten and aluminum alloys with composite and ceramic materials. Also, for the rocket to be fuel efficient, the initial momentum to the turbines used will be given by permanent magnets mounted on the shaft, surrounded by windings and powered by supercapacitors. Once a desired rpm is achieved, a very small amount of fuel is used to maintain the same.

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Kim, Sangwon, Charles Mitchell, and Allan Kirkpatrick. "Design and Evaluation of High Pressure Fuel Valve Nozzles Using the Method of Characteristics and CFD." In ASME 2003 Internal Combustion Engine and Rail Transportation Divisions Fall Technical Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/icef2003-0742.

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The topic of this paper is the design of fuel valve nozzles for natural gas engines that maximize the kinetic energy and momentum of the injected fuel and maintain a required mass flow rate. The nozzle design used both the method of characteristics and computational fluid dynamics (CFD). Three types of nozzles were designed: a converging-diverging nozzle, three conical nozzles and an aerospike nozzle. The evaluation of the performance of the nozzle designs was conducted using Computational Fluid Dynamics. CFD simulations were used to calculate the average axial momentum per unit fuel mass and the average kinetic energy per unit fuel mass in the jets emanating from each nozzle. The performance was computed in off-design conditions (2.9MPa, 3.1MPa) as well as for the nominal design supply pressure of 3 MPa. Results showed that for the new nozzle designs, the average axial momentum per unit mass was improved by 17 to 24% and the average kinetic energy per unit fuel mass was improved by 30 to 80% compared with a standard shrouded poppet valve. Of the candidate designs, the converging-diverging nozzle gave the best performance, and the simple 15 degree conical nozzle also performed very well.

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McRoberts, Bradley J., and Charles T. Walejewski. "Lightweight, Opto-Electronic Engine Control System for Aerospace Turbine Engines." In Aerospace Atlantic Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931442.

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Fick, Michael, Robert Schmucker, Michael Fick, and Robert Schmucker. "Linear aerospike engine performance evaluation." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3305.

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Reports on the topic "Aerospike engines"

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Barclay, Rebecca O., Thomas E. Pinelli, David Elazar, and John M. Kennedy. NASA/DoD Aerospace Knowledge Diffusion Research Project, Paper Fourteen: An Analysis of the Technical Communications Practices Reported by Israeli and U.S. Aerospace Engineers and Scientists. Fort Belvoir, VA: Defense Technical Information Center, November 1991. http://dx.doi.org/10.21236/ada252564.

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Pinelli, Thomas E., Rebecca O. Barclay, Myron Glassman, and Walter E. Oliu. NASA/DoD Aerospace Knowledge Diffusion Research Project, Paper One: The Value of Scientific and Technical Information (STI), Its Relationship to Research and Development (R and D), and Its Use by U.S. Aerospace Engineers and Scientists. Fort Belvoir, VA: Defense Technical Information Center, January 1990. http://dx.doi.org/10.21236/ada252565.

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