A NEW METHOD FOR DESIGN AND SIMULATION OF SPACE VEHICLE

Abstract

The Design of the space vehicle systems present a wide range of problems to engineers in numerous disciplines which range through propulsion, aerodynamic, structure, guidance, and control This thesis present a preliminary design for the Space vehicles which include Ballistic Missiles and Space launch Vehicles with fully 3D Rotating Ellipsoid earth model, Full Propulsion Model (Solid / Liquid) , Complete Guidance rules in all phases ( In-flight, guided, lift-guided), Aerodynamic model in both supersonic-hypersonic flow , and Re¬entry Conditions Calculations for ballistic missiles and re-useable space vehicle. As start point, studying the rigid body dynamics in 3D to get out the techniques of launching and firing of missiles and SLVs. Also multistage/Parallel staging rockets are an important point and covered in this thesis. Solid, liquid, Gas, and Hybrid Propellant are the main fuel kinds that used in any propulsion systems of the SVs. For this thesis, the solid and liquid propellant are chosen to study in details because the high percentage of the SVs that use those types in its engine. Propulsion system model covered those types from the fuel chemical properties to the chamber-nozzle Design and the resultant force during the time of the SVs. Supersonic and hypersonic flow modeling, these are the main problems in any aerodynamic modeling. By using the Supersonic Characteristics theory with build-up theory and made some reliable simplifications on it, Some preliminary equations For Lift and drag coefficients that make a good enough aerodynamic modeling subroutine that can be used for any SV shape configurations including the interfacing factors between body, wing, and tail units. And for flypersonic Flow, The main theories like Newton flow theory, modified Newton theory, Pardee Method and Some incompressible methods are helpful to get some formulas that calculate the aerodynamic characteristics in hypersonic flow region Finally, a full database for Launchers and ballistic missiles implemented to achieve the relations between the space vehicle parameters and using it in a preliminary design of the space vehicle. After this, building up a program that have Payload and desired range or altitude for inputs and gives the outline shape of the space vehicle and the optimal fuel for this mission, number of stages and design of each stage in details.