Design and Analysis of Aerospike Nozzle to Produce More Thrust in Hybrid Rocket Engine

Design and Analysis of Aerospike Nozzle to Produce More Thrust in Hybrid Rocket Engine

1. Pravin

   Dept of AERO-PITS

   R. Vishva

   Dept of AERO-PITS

   T. Anbarasan

   M.Tech

   HOD of AERO-PITS

2. Vairamuthu

M.Tech Assistant Professor Dept of AERO-PITS

Abstract:- The development of momentum distribution of the high temperature exhaust in rocket engine through modified in profile of aero spike nozzle by computational analysis. Due to modified of design we can develop improve thrust and mass flow rate of exhaust gas. This analysis was done by using fluent ANSYS on change of profile of aero spike nozzle. The comparison has been done with respect to vector, velocity streamline and mass flow rate between modified and unmodified Profile. Profile CAD model profile was designed by CATIA. The modification in the exit nozzle area of hybrid rocket engine. The new has developed in the reduction of non- uniform exhaust flow and Improved in mass flow rate of exhaust gas.

INTRODUCTION

Rocket propulsion systems are often classified per the kind of energy source(chemical, nuclear, solar), the essential function(booster stage, sustainer, perspective management, orbit), the kind of car, size, style of propellant, style of construction, or range of reaction propulsion units utilized in a given vehicle. in our own way is to classify by the strategy of manufacturing thrust. A physical science growth of a gas is employed within the majority of sensible reaction propulsion ideas. The internal energy of the gas is regenerate into the K.E. of the exhaust flow and thrust is made by the pressure on the surfaces exposed to the gas. Active development of reaction propulsion system is presently below method in additional than thirty totally different countries. a number of them have created important and original contribution to the state of the art of the technology.

Nozzles have a viscous physical phenomenon next to the walls, wherever the gas velocities area unit a lot of under the free stream velocities within the in gummy flow regions. The gaseous physical phenomenon contains a profound result on the general heat transfer to nozzle and chamber walls. It conjointly has an impression on the rocket performance, notably in applications with comparatively long nozzles with high nozzle space ratios, wherever a comparatively high proportion of the overall mass flow (2 to 25%) are often within the lower speed region of the physical phenomenon.

CAD MODEL DESIGN

CATIA is the most powerful and widely used CAD software of its kind in the world. CATIA V5 was created by Dassault System.

Using the CATIA V5 software, constructed a solid Aero spike nozzle and the isometric view and the dimension of the nozzle used are given:

TABLE I: DIMENSIONS OF THE AERO SPIKE NOZZLE

ROCKET NOZZLE

A number of various tried nozzle configurations area unit out there these days. Nozzle and chamber area unit sometimes of circular cross section and have a converging section, a throat at the narrowest location, and a oblique section. The converging nozzle section between the chamber and therefore the nozzle throat has ne'er been vital in achieving performance. The subsonic flow during this section will simply be turned at terribly low drop and any radius.

FIG 1: DRAFTING IMAGE

Now the below figure 2 reveals that the detail design of the Aero spike nozzle. Which was designed by using CATIA V5.

FIG 4: WIREFRAME VIEW OF AERO SPIKE NOZZLE I FLOW ANALYSIS

After completing the design the next step is analysis. The process of analysis starts with the meshing. Meshing is the process of sub dividing a structure into a convenient number of smaller elements (mesh density)

V. MESH OF AERO SPIKE NOZZLE

FIG 2: DETAIL DESIGN OF AERO SPIKE NOZZLE

The cross section view of the nozzle can be seen in figure three

FIG 3: CROSS SECTION VIEW

FIG 5: VIEW OF NOZZLE IN MESH TABLE II: DETAILS OF MESH

For this nozzle to get the convenient values a triangular prism is used.

FIG 6: AEROSPIKE NOZZLE WITH CONTROL VOLUME

FIG 7: ANSYS PHYSICS PRE-PROCESS VIEW TABLE III: DOMAIN PHYSICS FOR CFX

The ensuing step of the analysis of nozzle after finished by CAD. Its typically necessary to positive concerning if the mesh is pure mathematics is correct. At a similar time we've got to make sure that whether or not we tend to are having correct operative conditions and boundary conditions and

material choice for analysis. During this case there are main

3 major equations are resolved by convergent thinker particularly (continuity, energy, momentum) if the flow is viscous. Weve got chosen coupled convergent thinker, second implicit, absolute speed formulation, cell primarily based gradient possibility, superficial speed porous formulation. As our flow is restricted continuity, momentum, energy equation therefore is important to ascertain them up.the density as perfect gas to form the answer less complicated. Once if the answer is achieved then it may be planned in graphical format. The figure may be planned between position in coordinate axis and the other operates in coordinate axis from plot command. quadcopter surface speed has been chosen by with in the speed, vector and static pressure.

VI .RESULT AND DISCUSSION

1. FLOW ANALYSIS

   From the analysis of this nozzle, it is clearly visualized the pressure and velocity and temperature streamlines during the flow.

   TABLE IV: BOUNDARY CONDITIONS

   Boundary condition is usually necessary to analysis the item. It ought to lean into software system as associate degree recess condition of the matter.Extremely necessary parameter attributable to presence of management volume by hydraulic diameter.During this case we have a tendency to took recess condition as per our survey and convenient moreover.

2. VELOCITY STREAMLINE OFNOZZLE

   FIG 8: VELOCITY STREAMLINE

   The on top of result clearly reveals that the utmost speed at initial stage that has accumulated linear manner throughout the nozzle.

   The prandlt Meyer enlargement has been occurred at spike of nozzle. Owing to this reason the flow of gas is hooked up to the surface of the spike. This method ends up in will increase the flow speed.

3. PRESSURE STREAMLINEOF NOZZLE

   FIG 9: PRESSURE STRAMLINE

   The pressure vary is a smaller amount throughout nozzle whereas it has attained its maximum (3.527e^006). From this we {are able to} determine that the pressure and speed are reciprocally proportional.

4. TEMPERATURE STEAMLINE OF NOZZLE

FIG 10: TEMPERATURE STREAMLINE

Rise in temperature level may be seen in on top of image during this case the amount of temperature is high at half portion of the nozzle that is been variable in step with nozzle diameter. Raise in temperature cause the high speed at exit of nozzle. .

TABLE V: RESULT OF AEROSPIKE NOZZLE

SOLUTION

At the guts of ANSYS CFX package is its advanced convergent thinker technology victimization coupled pure mathematics multigrain, the key to achieving reliable and correct solutions quickly and robustly.

Its designed measurability ensures a linear increase in computer hardware time with downside size and parallel performance that's second to none. Users will follow convergence progress and dynamically monitor numerical and physical answer quantities. convergent thinker parameters, boundary conditions different parameters are often adjusted on the fly, no end the convergent thinker. The ANSYS CFX convergent thinker uses second order numeric by default, making certain users forever gets the

foremost correct predictions doable. for nearly a Kerala, India 2Assistant Professor, MES College of thousand iterations we tend to offer the convergent thinker to unravel the context, however the result's extracted most likely once the answer converges. the answer was taken on four grounds and supported this the result was extracted.

CONCLUSION

Flight research of an aero spike rocket nozzle was conducted using high power solid rockets. The lower aero spike chamber pressures and thrusts were likely to be caused by a larger actual aero spike nozzle throat area than the designed throat area. The design work on an aero spike nozzle design and associated testing hardware has been completed in preparation for a series of cold-flow tests on a truncated aero spike nozzle. the system will allow thrust vectoring and thrust augmentation through truncated aero spike base bleed of evaluation of aerodynamics. This series of tests will facilitate calibration of analytical prediction tools which include computational fluid dynamics results. Completion of cold gas testing should provide an adequate knowledge base before the project advances to hot flow testing.

ACKNOWLEDGEMENT

The authors acknowledge the valuable suggestion from the faculty of aeronautical engineering in Parisutham institute of technology and science.

REFERENCE

1. Aerospike nozzle contour design and itsperformance validation Chang-Hui Wang , Yu Liu, Li-Zi Qin403 Teaching and Research Section, Beijing University of Aeronautics and Astronautics, 100083 Beijing, Peoples Republic of China

2. MULTIDISCIPLINARY APPROACH TO LINEAR AEROSPIKE NOZZLE OPTIMIZATION J. J. Korte*, A.O. Salast, H.J. Dunn?, and N.M. Alexandrov P NASA Langley Research Center, Hampton, Virginia 23681

3. Development of a Reusable Aerospike Nozzlefor Hybrid Rocket Motors Patrick Lemieux1 California Polytechnic State University, San Luis Obispo, CA, 93407

4. Flight Research of an Aerospike Nozzle Using High Power

   Solid Rockets Trong T. Bui* and James E. Murray NASA Dryden Flight Research Center, Edwards, CA, 93523 Charles E. Rogers Air Force Flight Test Center, Edwards Air Force Base, CA, 93523

5. Scott Bartel§ blacksky Corporation, Carlsbad, CA, 92008 NUMERICAL ANALYSIS OF AERO-SPIKE NOZZLE FOR SPIKE LENGTH OPTIMIZATION

SANOOB S N1, PRINCE MG2 & SUNDAR B3

1Research Scholar, MES College of Engineering, Kuttipuram, Malappurm