Numerical Simulation and Test Research on Impact Force of Rocket to Seal Cap
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The seal cap design of rocket pod/container(RP/C) is one of the key technical problems in rocket launching device.The impacting force in the whole process of test during fire could not be acquired because of the specialty of this kind of rocket.Due to this reason,the impacting force of rocket to seal cap in a certain rocket pod/container(RP/C) were simulated and tested by use of LS-DYNA explicit center difference method.This method can solve the difficult problem that the instantaneous response of seal cap impacted by rocket can not be tested to obtain during rocket launcher was carrying out the live fire.The numerical simulation results was compared with the test results,and the relative error was less than 12%.The numerical simulation results can provide a correct theory method for proper design of seal cap.According to the numerical simulation results,the improved design of seal cap was verified by means of launching experiment,and it can meet the qualification requirements of rocket launcher system.Keywords:
Rocket (weapon)
Rocket engine
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Besides safety and low-cost,the start/shutdown/restarting and throttling ability are the other two significant advantages of hy-brid rocket motors(HRMs) compared with liquid and solid ones.In this study,a two-stage variable thrust and non-toxic 98%HP/HTPB hybrid rocket motor(VTHRM) is designed and applied in a sounding rocket,and the design parameters of the motor are analyzed and optimized.A computational program is developed to design the motor system structure,to predict the interior ballistics and the ballistic trajectory.A star grain and a wheel grain are compared.The design of experiment(DOE),variance analysis and the main effect analysis are employed to investigate the influence of the main design parameters on mo-tor performance.The multidiscipline feasible(MDF) approach is applied to establish the optimization procedure after analyz-ing the system design structure matrix.A modified differential evolution algorithm is employed to maximize the load mass.The results indicate that the wheel grain could obtain a larger load mass and a lower length to diameter ratio,and that throttling markedly meliorates the motor and rocket performance.The conclusions drawn from the analysis and optimization could pro-vide instructive guide and theoretical basis for engineering designs.
Sounding rocket
Internal ballistics
Rocket (weapon)
Bandwidth throttling
Solid-fuel rocket
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An Innovative Stabilizer Unit Design for Tube Launched Artillery Rocket to Improve Dynamic Stability
In this paper, stabilizer unit of the tube launched artillery rocket is designed with flat wrap around fins (WAF). A comparative study has been carried out to find out the aerodynamic behavior of same rocket with curved and flat WAF. Computational fluid dynamic (CFD) is used to find out aerodynamic coefficients of the rocket with both types of fins. It is found that with flat WAF chances of occurrence of out-of-plane moment reduced drastically. Hence, it is recommended to use Flat WAF for tube launch rocket to avoid any
Rocket (weapon)
Artillery
Stabilizer (aeronautics)
Launched
Aerodynamic force
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Specific impulse
Rocket (weapon)
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The nozzle geometry affects the performance achieved by a solid propellant rocket motor to a great extent. In order to improve the development of a small home made solid propellant rocket motor these effects on performance from the nozzle geometry need to be understood. This thesis project involves the design of a small solid propellant rocket motor with materials readily available to a hobby rocket enthusiast. A specific investigation is then carried out into the effects that nozzle geometry has on the thrust and impulse performance of the rocket motor. The thrust-time profiles of the rocket motors are achieved by conducting a static firing in a cantilever beam thrust measuring apparatus. A secondary study is also done on these different nozzle geometries using computation fluid dynamics simulations to determine the predicted thrust performance. This also gives the advantage of visualizing the entire flow field and assists in identifying the features that drive the differences in performance. Overall this project develops a high performance nozzle geometry for use on a small home made solid propellant rocket motor as well as outlining various engineering issues involved with the development of a solid propellant rocket motor.
Solid-fuel rocket
Specific impulse
Rocket engine nozzle
Rocket (weapon)
Rocket propellant
Liquid-propellant rocket
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Solid-fuel rocket
Sounding rocket
Specific impulse
Rocket (weapon)
Rocket engine
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Rocket Thruster is a reaction control system of liquid rocket propulsion system, used for the attitude control of missile. The reaction control system is employed in the missile to provide roll control to the second stage after separation of the first stage. The thruster is subjected to temperature and pressure loads during its operation. It is essential for a flight vehicle to have low weight and high velocity to overcome the gravity. In order to develop compact size thruster, it is required to carry out structural analysis for SS321 material. The present report deals with analysis of Rocket Thruster casing and flange joint. The Rocket Thruster casing is designed as per ASME pressure vessel code and NASA SP 125 design report. The proposed model is a modification from the conventional joint between L-dome and injector plate. Thermo-structural analysis is performed to evaluate the new design which eliminates use of welded joint. Analysis is carried out to estimate stresses especially in the modified region to ensure less stresses are developed compared to the original design. Analysis has been carried out considering the external injector pressure for shell and then the temperature loads are applied on the thruster to estimate the deformations and stresses. The Thruster is then subjected to a thermo-structural load and then von Mises stresses are estimated.
Rocket (weapon)
Flange
Rocket engine
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Rocket motor design is based on the use of maximum capability of each component. To fully realize this goal in the case of rocket nozzle,, a more precise structural analysis has to be performed. The finite element method provides one of the powerful and commonly used techniques for such type of analysis. In this work, the stress analysis on rocket nozzle is investigated. A finite element computer program was implemented for stress analysis of axisymmetric structures. The program would assist in therrno-structural verification of rocket nozzles made of composite materials with non-linear thermal and mechanical properties. For a case study on a submerged nozzle, exploration of critical loading zones was made possible, by the analysis of results from running this program. The efficiency of the program had been proved by the good agreement with results obtained from theory and other validated codes.
Rocket (weapon)
Rocket engine nozzle
Solid-fuel rocket
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Rocket engine
Liquid-propellant rocket
Solid-fuel rocket
Rocket engine nozzle
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During their operation, solid rocket boosters experience axial stresses caused among other things also by fluid mechanical loads from the internal flow. The accurate prediction of the flowfield is mandatory for an accurate prediction of axial stresses and strains during the mission. In the present Paper, a very efficient but still accurate approach is presented to simulate the internal flow featuring an erosive combustion process, which leads to a temporal variation of the fluid domain. The impact of the calculated fluid behavior on the calculation of axial strains is demonstrated using the example of a firing test, where it can be shown that by taking into account the fluid behavior a significant improvement on the axial strain prediction could be achieved compared to the previous method, in which the fluid mechanical impact partly had been neglected.
Internal ballistics
Booster (rocketry)
Solid-fuel rocket
Internal flow
Rocket (weapon)
Ballistics
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A solid rocket or a solid-fuel rocket is a rocket engine that uses solid propellants (fuel/oxidizer). The term "solid fuel" in this context is actually erroneous because solid propellant must contain both a fuel and an oxidizer to support combustion. All rockets used some form of solid or powdered propellant up until the 20th century, when liquid rockets and hybrid rockets offered more efficient and controllable alternatives. In this we consider a composite material Carbon/Epoxy and Kevlar/epoxy for a pole relevant in rocket parts. Its length as 10m, interior breadth as 1m, inside weight as 1000psi or 6.894Mpa, engine packaging is outlined and subjected to basic and modular examination. Fundamentally engine packaging is planned in ANSYS apparatus by considering outline contemplations, assist the model is subjected to stack imperatives and weight parameters as in the constant flight and reproduction examination will be completed and perceptions are made to know the basic functions, loads, stress, strain and proficiency of rocket engine packaging. For the Design and Analysis, Simulation Software ANSYS R 18.0 be utilized and results will be summoned. Layer as stress – strain Distribution is acquired, Static Structural Analysis, Modal Analysis will be done and comes about might be closed.
Rocket engine
Solid-fuel rocket
Rocket (weapon)
Liquid-propellant rocket
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