System design thrust vector control via liquid injection within the nozzle and the numerical simulation of the corresponding flow

Transcription

1 6 9 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 mmemodaresacir * heidarimr@piauacir * 9 : 9 : 9 : System design thrust vector control via liquid injection within the nozzle and the numerical simulation of the corresponding flow MohammadReza Najjari, MohammadReza Heidari* Department of Mechanical Engineering, Islamic Azad University of Parand Branch, Tehran, Iran *POB Parand, Tehran, Iran, heidarimr@piauacir ARTICLE INFORMATION ABSTRACT Original Research Paper Received November 0 Accepted 0 January 0 Available Online 0 March 0 One way to control the position of a missile is to control thrust vector which moves with help of thrust due to exiting gas All thrust vector control TVC methods are independent of aerodynamic forces of atmosphere and until the engine has thrust, maintain their performance Secondary injection systems are one of the four major TVC methods In this study, first the components are identified and conceptual design of system is drawn and the preliminary design of manifold of a type of thrust vector control system using a liquid injection thrust vector control isdetermined Then the layouts of components on some parts such as injectors and reservoirs, as well as detailed design of the system are discussed The numerical simulation of flow and the design and study of the sprayers in systems will be discussed Also, numerical designing and simulation in two parts: injection system and the injector spray effects into the main flow are analyzed and the results are presented and validated The results of this study can be used as a model for the design and analysis of various kinds of TVC systems with lateral fluid method on a variety of missiles with different launchers Keywords: system designing thrust vector control liquid injection numerical simulation of flow manifold Please cite this article using: TVC : MR Najjari, MR Heidari, System design thrust vector control via liquid injection within the nozzle and the numerical simulation of the corresponding flow, Modares Mechanical Engineering Vol, No, pp 6, 0 in Persian

2 [6] [7] 009 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 [8] 00 TVC [9] TVC 0 [0] 0 [0] 0 96 [] 0 III [] 98 [] 007 [] [] 97 7 [] 0 0 [] [] TVC 8 0 9, NO CClF 8 Pressure Regulator Pressure Valve 9 Blade 0 Accumulator Flow Meter Manifold TVC Electrical Distribution Box ECU Injector [96] 7 9 SITVC Secondary Injection Thrust Vector Control NASA Solid Rocket Titan Shuttle SRB

3 Downloaded from mmemodaresacir at : IRST on Saturday February rd % 0 [] 98 Fig Authorized space for locating of system Table The nozzle flow properties in close situation to secondary flow injection A/A* K kg/m Bar

4 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 7 Fig The location of nitrogen and accumulator tanks on the nozzle 6 AlSl Fig Structural analysis of the nitrogen tank [] III 7 [] Fig The location of the components of system 9

5 9 8 Downloaded from mmemodaresacir at : IRST on Saturday February rd Fig Structural analysis of the Freon tank Fig 7 The longitudinal section of injector in fully open attitude 7 Fig 8 The crossing sectional variations of flow vs movement of the needle of injector Fig 6 The samples of initial designs of liquid injection thrust vector control system 6 8 9

6 % Downloaded from mmemodaresacir at : IRST on Saturday February rd T0 P K 000 T0 P [] 0 0 [,0] Fig 0 The first part simulation grid 0 Table The numerical results in output borders of the selected system injectors Fig 9 The passing flow rate variations vs movement of the needle of injector m/s kg/s % 60 80% 899 6% Table Chemical properties of the fluid injection Freon 7 0% 8 6 % kg/kmol J/kg_K kg/m 6 0%

7 000 Downloaded from mmemodaresacir at : IRST on Saturday February rd K 0 : 00% 80% 0% : : 6% % : 0% Fig The Freon flow stream lines in accumulators and injectors of the system = = + & = + Fig The second part simulation grid 60 Table The air properties %

8 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 Injector in 0% open situation Injector in 00% open situation Injector in 0% and 80% open situation Injector in % and 6% open situation Fig The temperature distribution on output nozzle section for four case injections Injector in 0% open situation Injector in 00% open situation Injector in % and 6% open situation Injector in 0% and 80% open situation Fig The speed contours in injection pages in four cases selected 8 7 Fig The study paths on surface of divergent nozzle Fig The static pressure distribution on the divergent nozzle wall, while that injector 00% open 00% Line Angle LA 9 8

9 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 Table The numerical results of second part simulation % and 6% 0% and 80% 6 0% and 0% 00% and 0% kg/s kg/s Pa m/s X m/s Y m/s Z Fig 7 The static pressure distribution on the divergent nozzle wall, while those two injectors 0% open % Fig 8 The static pressure distribution on the divergent nozzle wall, while that one injector 6% and another one % open % % 9 9

10 Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 0% 00% a: Injector in 00% open situation 7 00% b: Injector in 0% open situation [] Fs/Fm Ws/Wt c: Injector in 0% and 80% open situation % d: Injector in % and 6% open situation Fig 0 The temperature distribution on the four edges of divergent nozzle wall in four cases selected 0 Fig 9 The static pressure distribution on the divergent nozzle wall, while that one injector 0% and another one 80% open 0% 9 80% 9 60

11 6 Table 6 Geometric and boundary conditions of experimental model laboratory sample 98 Downloaded from mmemodaresacir at : IRST on Saturday February rd a: Injector in 00% open situation b: Injector in 0% open situation 06 c: Injector in 0% and 80% open situation % 68 d: Injector in % and 6% open situation Fig The density distribution on the four edges of divergent nozzle wall in four cases selected 7 6 9

12 [] Downloaded from mmemodaresacir at : IRST on Saturday February rd 09 7 Table 7 The comparing between simulation and experimental results [] 6 [] C J Green, F McCullough, Liquid Injection Thrust Vector Control, AIAA Journal, Vol, No, pp 778, 96 [] W Howard Duglass, NASA Space Vehicle Design Criteria, Solid Rocket Thrust Vector Control, pp700, December 97 [] C L Martin, L B Powers, Feasibility Study of for Shuttle SRB, NASATP9, Sep 98 [] J Tsohas, L J Droppers, E Glean, E M Dambash, S D Heister, Progress in Technology Demonstration for a Small Hybrid Launch Vehicle, Proceedings of th Responsive Space Conference, April 007 [] Sh R Subanesh, T R Aravindkkumar, K S Nareshkumar, S Ragothaman, R Riyana, V R Sanalkumar, Studies on Thrust Vector Control using Secondary Injection Sonic and Supersonic Jets, Proceedings of nd International Conference on Mechanical, Electronics and Mechatronics Engineering, June 78, 0 [6] M R Heidari, A Noorallahi, Liquid Injection Thrust Vector Control and Effective Parameters, Journal of Development and promotion of Energetic Materials, Vol, No, pp, 008 In Persian [7] M R Heidari, A Noorallahi, A Review of Liquid Injection Thrust Vector Control Usage in Different Missiles, Conference of Iranian Aerospace Society, Tehran, Iran, 008 In Persian [8] M R Heidari, A Pouramir, Analysis of the Interaction of Side Jet Injection into the Main Nozzle Flow Field, Journal of Energetic Materials, Vol, No, pp 768, 009 In Persian [9] M R Heidari, M Hashemabadi, Aerodynamic Design Algorithm of Liquid Injection Thrust Vector Control, Journal of Aerospace Systems Design, Vol, No, pp 7, 00 In Persian [0] M R Heidari, A Pouramir, Numerical Simulation of Liquid Single Injection Thrust Vector, Journal of Energetic Materials,Vol 6, No, pp, 0 In Persian Fs/Fm Ws/Wt % % kg/s kg/s [] M R Heidari, A Pouramir, Investigation and Comparison effects of Fluid Injection Type in Thrust Vector Control, Journal of Applied Fluid Mechanics JAFM, Vol 9, No, pp 96, Jan 0 9 Fig The diagram of comparing between simulation and experimental results [] [] 8 00% [] M R Heidari, A Pouramir, Injectors Arrangement and Injection Flow Distributions Analysis in Liquid Injection Method for Thrust Vector Control, Journal of Energetic Materials, Vol 9, No, pp9, 0 In Persian [] M R Najjari, M R Heidari, A Pouramir, System Design and Manifold of a Thrust Vector Control System with Liquid Injection inside a Nozzle, Conferences of Modern Achievement on Aerospace and Related Sciences, Tehran, Iran, summer 0 In Persian 7 00% 6