The Test Stand for ORVEAL Series of Combined Rocket Engines

Article Preview

Abstract:

As a part of the ORVEAL project, the brand new series of compound rocket engines MEC-80 is subjected to a line of restrictions imposed by the experiment plan, which add an extra weight to the definitely expensive phase of the experimental development of the new types of rocket engine. The direct way to reduce the development time and cost of the new powering systems was found in tediously defining the experimental plan, the variables involved, the nature of the pay-off polynomials and the technological solutions. For the specific case the technological and reliability related constraints are explored, that led to the definition of a reversed-vertical configuration of the thrust frame of the test stand and of the scale and support system of the thrust frame, with position-defined sensors for acquiring the thrust tensor value. Simplicity and reliability were the main requirements in designing and manufacturing the components of the test stand in the new environment of the recently enhanced CEZAR proving grounds of ADDA Ltd. in Fagaras, Transylvania. The ORVEAL research is granted by Romanian UEFISCDI financing authority.

You might also be interested in these eBooks

Info:

Periodical:

Pages:

10-17

Citation:

Online since:

October 2013

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2013 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] Ramohalli K, Yi J, Hybrids Revisited, 26th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 16-18 July, 1990, Orlando, FL.

DOI: 10.2514/6.1990-1962

Google Scholar

[2] Greiner B, Frederick Jr RA, Results of Labscale Hybrid Rocket Motor Investigation, 28th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 6-8 July, 1992, Nashville, TN.

DOI: 10.2514/6.1992-3301

Google Scholar

[3] Godon JC, Duterque J, Lengelle G, Solid-Propellant Erosive Burning, Journal of Propulsion and Power, Vol 8, No. 4, July-August (1992).

DOI: 10.2514/6.1987-2031

Google Scholar

[4] Grosse M, Development Work on A Small Experimental Hybrid Rocket, 33rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 6-9 July, 1997, Seattle, WA.

DOI: 10.2514/6.1997-2802

Google Scholar

[5] Rugescu, R. D., ADDA Rocket Engines Research Program: Principles and Thermo-chemical Data, Sc. Bulletin of U.P.B., series D, Mechanical Engineering, 61, 3-4(1999), pp.405-414.

Google Scholar

[6] Chiaverini MJ, Serin N, Johnson DK, Lu Yeu-Cherng, Kuo KK, Risha GA, Regression Rate Behavior of Hybrid Rocket Solid Fuels, Journal of Propulsion and Power, Vol 16, No. 1, January-February (2000).

DOI: 10.2514/2.5541

Google Scholar

[7] George P, Krishnan S, Varkey PM, Ravindran M, Ramachandran L, Fuel Regression Rate in Hydroxyl-Terminated-Polybutadiene/ Gaseous-Oxygen Hybrid Rocket Motors, Journal of Propulsion and Power, Vol. 17, No. 1, January-February (2001).

DOI: 10.2514/2.5704

Google Scholar

[8] Hartfield, R. J., Jenkins R. M., Burkhalter J. E., and Foster W., A review of Analytical Methods for Solid Rocket Motor Grain Analysis, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 20-23 July, 2003, Huntsville, AL.

DOI: 10.2514/6.2003-4506

Google Scholar

[9] Carmicino C, Sorge AR, Role of Injection in Hybrid Rockets Regression Rate Behavior, Journal of Propulsion and Power Vol 21, No. 4, July-August (2005).

DOI: 10.2514/1.9945

Google Scholar

[10] Karabeyoglu MA, De Zilwa S, Cantwell B, Zilliac G, Modeling of Hybrid Rocket Low Frequency Instabilities, Journal of Propulsion and Power, Vol 21, No. 6, November-December (2005).

DOI: 10.2514/1.7792

Google Scholar

[11] Rugescu, R. D., NERVA Romanian Non-Orbital Entry-Return Vehicle Assessor Project, Texas A&M University, USA, Paper IAC-06-B5. 5. 11, Proc. 57th IAC Congress, Valencia, Spain, Oct. 02-06, (2006).

DOI: 10.2514/6.iac-06-b5.5.11

Google Scholar

[12] Ziliac G, Karabeyoglu M A, Hybrid Rocket Fuel Regression Rate Data and Modeling, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 9-12 July, 2006, Sacramento, California.

DOI: 10.2514/6.2006-4504

Google Scholar

[13] Lohner, Kevin, Jonny Dyer, Eric Doran, and Zachary Dunn, Fuel Regression Rate Characterization Using a Laboratory Scale Nitrous Oxide Hybrid Propulsion System, AIAA 2006-4671, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 9-12 July, 2006, Sacramento, California.

DOI: 10.2514/6.2006-4671

Google Scholar

[14] Chiaverini, M. J., and K. K. Kuo, Fundamentals of Hybrid Rocket Combustion and Propulsion, Progress in Astronautics and Aeronautics, 218, ISBN 978-1-56347-703-4, AIAA Series, (2006).

DOI: 10.1017/s0001924000087443

Google Scholar

[15] Frederick Jr RA, Whitehead JJ, Knox LR, Moser MD, Regression Rates Study of Mixed Hybrid Propellants, AIAA J. Propulsion and Power, 23 (1), 2007, pp.175-180.

DOI: 10.2514/1.14327

Google Scholar

[16] Rugescu, R. D., Maximizing Chemical Information from Laboratory Statistics, Revista de Chimie, ISSN, 0034-7752, Publisher Chiminform Data S.A., Romania, 58, 6(2007), pp.579-581.

Google Scholar

[17] http: /www. nasa. gov/home/hqnews/2007/feb/HQ_0720_COTS_agreements. html, ** NASA Signes Agreement with t/Space, 02. 01. (2008).

Google Scholar

[18] Rugescu, R. D., The unit histogram concept for scarce statistical information, AECE Journal, Advances in Electrical and Computer Engineering-AECE Journal, ISSN 1582-7445, Vol. 9, No. 3, 2009, pp.68-74.

DOI: 10.4316/aece.2009.03013

Google Scholar

[19] Casalino L, Pastrone D, Optimal Design of Hybrid Rocket Mototrs for Launchers Upper Stages, Journal of Propulsion and Power, Vol 26, No. 3, May-June (2010).

DOI: 10.2514/1.41856

Google Scholar

[20] Rugescu, R. D., C. E. Constantinescu, D. R. Rugescu, B. Marcu, F. Ionescu, C. Dumitrache, M. O. Stanciu, E. Micu, S. P. Vataman, A. Ciocanea, S. Budea, I. Farcasan, Augmented Romanian Orbital Launcher Open for International Cooperation, Proceedings of the SASAC-2010, 1st South African Space Association Congress, 7-9 Oct. 2010, Cape Town, South Africa.

Google Scholar

[21] Pastrone Dario, Approaches to Low Fuel Regression Rate in Hybrid Rocket Engines, International Journal of Aerospace Engineering, Vol. (2012).

DOI: 10.1155/2012/649753

Google Scholar