Farklı Tip Burun Konilerinde Çentikli Delta Kanat Roketlerin Uçuş Performansının İncelenmesi

Year 2023, Volume: 18 Issue: 2, 435 - 447, 01.09.2023

Cihan Özel Cevher Kürşat Macit Meral Özel

https://doi.org/10.55525/tjst.1245275

Abstract

Bu çalışmada, konik, parabolik, power ve haack serisi burun konilerine sahip ortalama 3 km irtifaya 4 kg yükü taşıyabilen katı yakıtlı dört adet model roket OpenRocket programında tasarlandı. Daha sonra, tasarlanan bu model roketlerin üzerine çentikli delta kanat modeli monte edildi. Bu kanat modelinin roketlerin hızında, stabilitesinde, ivmesinde, ağırlığında ve irtifasındaki değişimlere etkileri OpenRocket programında sayısal olarak analiz edildi. Yapılan analizler sonucunda, en kötü uçuş performansını konik burunlu roketin en iyi performansı ise Haack serisi burun konisine sahip roket modelinin gösterdiği belirlendi. Haack serisi modelin çentikli delta kanat profiliyle birlikte kullanıldığında roketin irtifasında %7,67, hızında %1,83 artışın oluştuğu ancak mach sayısında %1.2, ağırlığında %0.6, ivmesinde %0.3, stabilitesinde ise %4.5 oranında azalmaların olduğu belirlendi. Sonuç olarak, roketin uçuş performansı değerlendirilirken burun konisi ve kanat profilinin birlikte ele alınmasının faydalı olacağı görüldü. Çalışmada elde edilen sonuçlar çentikli delta kanat modelinin deneysel olarak savunma sanayisi ve model roket uygulamalarında kullanılabileceğini ve çalışmaların ilerletilebileceğini göstermiştir.

Keywords

OpenRocket program, Burun konileri, Çentikli delta kanat, Roket uçuş performansı

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

Abstract

In this study, four solid fuel model rockets with conical, parabolic, power and haack series nose cones that can carry 4 kg payload at an average altitude of 3 km were designed in the OpenRocket program. Later, the notched delta fin model was mounted on these designed model rockets. The effects of this fin model on the changes in the speed, stability, acceleration, weight and altitude of the rockets were analyzed numerically in the OpenRocket program. As a result of the analysis, it was determined that the conical nose rocket showed the worst flight performance and the Haack series nose cone rocket model showed the best performance. When used with the notched delta fin of the Haack series model, it was determined that the rocket's altitude increased by 7.67%, and its speed increased by 1.83%, but decreased by 1.2% in mach number, 0.6% in weight, 0.3% in acceleration, and 4.5% in stability. As a result, it was seen that it would be beneficial to consider the nose cone and fin together when evaluating the flight performance of the rocket. The results obtained in the study have shown that the notched delta fin model can be used experimentally in defense industry and model rocket applications and the studies can be advanced.

Keywords

OpenRocket program, Nose cones, Notched delta fin, Rocket flight performance, OpenRocket programı, Burun konileri, Çentikli delta kanat, Roket uçuş performansı

References

• Barbosa AN, Guimarães LNF, Multidisciplinary design optimization of sounding rocket fins shape using a tool called mdo-sonda. J Aerosp Technol Manag 2012; 4: 431-442.
• Priyadarshi P, Alam M, Saroha K, Multi-disciplinary multi-objective design optimization of sounding rocket fins. Int J Adv Eng Sci Appl Math 2014;6(3): 166-182.
• Baloda Y, Jaiswal A, He X, Datye A. Theoretical and experimental performance evaluation of shark-caved, sounder, and trapezoidal fins. NCUR Proceedings, 2020.
• Bilgic HH, Coban S, Yapici A. Designing, Modeling and Simulation of Solid Fuel Rocket ALP-01,2019.
• Rohini D, Sasikumar C, Samiyappan P, Dakshinamurthy B, Koppula N. Design & analysis of solid rocket using open rocket software. Mater Today Proc 2022; 64: 425-430.
• Azevedo FS, Knowing the stability of model rockets: A study of learning in interest-based practices, Cognition and Instruction, 2013; 31(3): 345-374.
• Niskanen S, Development of an Open Source model rocket simulation software, MSc. Dissertation, Helsinki University of Technology, Faculty of Information and Natural Sciences, 2009.
• Campbell TA, Seufert ST, Reis RC, Brewer JC, Limberger Tomiozzo R., Whelan C. E., Okutsu M. Model rocket projects for aerospace engineering course: Simulation of flight trajectories. In 54th AIAA Aerospace Sciences Meeting 2016; 1577.
• Varma AS, Sathyanarayana GS, Sandeep J. CFD analysis of various nose profiles. Int. J. Aerosp. Mech. Eng.,2016; 3(3): 26-29.
• Ledu J, Pollak C. Flight testing results on a hypersonic reentry nose cone. J. Spacecraft Rockets 1969; 6 (9): 1044–1047.
• Ericsson RA, Guenther WR, Stake, Olmsted GS. Combined effects of nose bluntness and cone angle on unsteady aerodynamics. AIAA J 1974; 12(5): 729–732.
• Mari VA, Maharaj PN, Muthuraman ES. Design and analysis of spherically blunted conic and spherically blunted tangent ogive nose section of the aircrafts using CFD. Int. J. Adv. Res. Manag. Arch. Tech. Eng., 2019; 5(4): 61–70.
• Pandey PK, Rajput B, Narayan A, Narayanan S. Numerical simulation of supersonic flow past a biconic nose cone. Int. J. Adv. Res. Sci. Eng., 2017; 6(3): 604–610.
• Milligan A., “Drag of nose cones,” apogeerockets.com. https://www.apogeerockets.com/education/downloads/Newsletter346. pdf (accessed Sep. 22, 2021).
• Chalia S, Bharti MK. Mathematical modeling of ogive forebodies and nose cones. Int Res J Eng Tech 2016; 3(3):744–747.
• Parvez D, Chalia S. Investigation on aerodynamic performance of elliptical and secant give nose cones. Int J Sci Res Eng Tren 2019; 5(4): 1291–1300.
• Narayan A, Narayanan S, Kumar R, Kumar R. Hypersonic flow past parabolic and elliptic nose cone configurations: a comparative study. Simulation 2018; 94(8): 665–680.
• Varma AS, Sathyanarayana GS, Sandeep J. CFD analysis of various nose profiles. Int J Aerosp Mech Eng 2016; 3(3):26–29.
• Lim S, Kim SD, Song DJ. The influence of Chine nose shapes on a slender body flight vehicle at high angles of attack. J Aerosp Eng 2012; 226(2): 182–196.
• Yeshwanth A, Senthiil PV. Nose cone design and analysis of an avion. Int J Pure Appl Math 2018; 119(12): 15581– 15589.
• Ozel C, Macit CK, Ozel M. Investigation of the Effects of the New Type Notched Delta Wing Model on the Flight Performance of the Rocket. Fırat University Journal of Engineering Sciences, 2023; 35(1): 175-193.
• Hernandez RN, Singh H, Messimer SL, Patterson AE. Design and performance of modular 3-D printed solid-propellant rocket airframes. J Aerosp 2017; 4(2): 17.
• Rocketsschools. Rocket Stability.http://www.rockets4schools.org/images/Basic.Rocket.Stability.pdf. Accessed on January 20, 2023.
• Nasa. Determining center of pressure-cp. On 14 Jan 03 Accessed on January 16, 2023. https://www.grc.nasa.gov/www/k12/VirtualAero/BottleRocket/airplane/rktcp.html
• Rocketsan model rocketry. https://www.roketsan.com.tr/uploads/docs/1628594512_20.03.2020model-roketcilik-master-dokumanv04.pdf. Published on 20.03. 2020.Accessed on January 18, 2023.
• Crowell GA. (1996). The descriptive geometry of nose cones. URL: http://www. myweb. cableone. net/cjcrowell/NCEQN2. doc.
• Datye A. Effects of Shark Caved Fins on Altitude Performance of a High-Powered Rocket. 2019 NCUR, 2019.
• Shah S, Tanwani N, Singh SK, Makwana MM. Drag analysis for sounding rocket nose cone. Int Res J Eng Technol 2020; 7(07).
• Fraley ER. Design, Manufacturing, and Integration of Fins for 2017-2018 OSU ESRA 30k Rocket 2018.
• Neutrium. Mach Number, Neutrium, https://neutrium.net/fluid_flow/mach-number/ Published October 2014. Accessed on January 20, 2023.
• Zhang GQ, Ji LC, Xu Y, Schlüter J. Parametric study of different fins for a rocket at supersonic flow. Proc Inst Mech Eng Part C, 2015; 229(18): 3392-3404, 2015.
• Negahban S, Design of a Model Rocket Flight Logging System and In-Air Deployable Rover, 2019.
• Bar-Haim B, Seginer A. Aerodynamics of wraparound fins. J Spacecr Rockets 1983; 20(4): 339-345.
• Yarce A, Rodríguez JS, Galvez J, Gómez A, García MJ. Simple-1: Development stage of the data transmission system for a solid propellant mid-power rocket model. J Phys Conf Ser. 2017; 850(1): 012019
• Nakka, R., Fins for Rocket Stability, Experimental Rocketry Accessed on January 18, 2023.