![]() The Brazilian Recoverable Satellite Platform (SARA) relies on a chemical propulsion system for orbital de-boost. For some specific missions, hybrid rocket technology may become a competitive choice due to its inherent advantages over more traditional chemical propulsion systems. This work presents a multidisciplinary optimization technique applied to the design of a hybrid rocket motor for the de-boost system of a small recoverable satellite. The tools developed as part of this thesis are Rocket design and sizing software, Rocket Optimization Software, Satellite Design Software, and Trajectory Analysis Software. A total of 39 performance plots were generated and presented. The simulation was carried out with the aid of OPEN ROCKET software. Simulation of the UAV launch from the rocket at an altitude of 100 m above sea level was presented. A detailed design of the surveillance UAV was carried out with the necessary features to facilitates its deployment from a 0.65m diameter rocket, launched into suborbital altitudes defined by the user. The Second Phase of the research work hinged on the design of an unconventional rocket-seated unmanned Aerial Vehicle capable of being launched from a rocket. The design software is robust enough to accommodate scaling and utility for a high-end reclusive satellite based on requirement and user input. A MATLAB program was written for the computation of the mathematical models used in the design of the nanosatellite. In addition, software was developed to perform trajectory analysis to determine if the vehicle designed would achieve the intended mission of placing a satellite into space. The software outputs, the number of rocket stages, required thrust, Characteristic Velocity “delta-V”, diameter and length of each stage of the rocket, and other pertinent data. The program is capable of sizing a rocket based on user input (target altitude or parking orbit, payload). The preliminary design software was developed based on the validated methodologies. The design was validated against three launch vehicles, VEGA, ARAINE, and FALCON rocket with the margin of error between the simulated result and the live launch well within less than 7%. The study provided for the preliminary design and sizing of a 3-stage rocket to launch a 30kg spy satellite into a low Earth orbit of 350 km. May not be able to use this as a flight simulator because it was made for pyro rockets.Ģ023 All rights reserved.The overarching goal of this research is to prove the feasibility of the application of hybrid rockets for space application in view of its numerous comparative advantages over the solid and liquid propellant rockets. Openrocket is an open source program that lets you calculate the CG and CP. Here you can find a lot of applied results on the parachutes inįlight simulation (structural, aerodynamic and aero elastic analysis). List of links to popular rocket simulation ![]() Windows, MACĪnd Linux versions available for download. The interface is designed to be easy to use and understand. ![]() The physics of water rockets and how to optimize their water rocket launches to obtain the highest apogees. This program can help students and rocketeers understand (works really well with WIN98 and older PC's) Links to websites containing water rocket mathematical formulas, parachute calculations, drag calculations, online or downloadable computer models.Ī Very accurate DOS based water rocket simulator If you would like a link to your site added to this page please post it to the link section in the ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |