Space

SPACE FLIGHT DYNAMICS AE 713 ASSIGNMENT-2 Submitted by N. ARVIND10301002| entry vehicle and armorial bearing: Launch Vehicle: FALCON 9 rush: NASA COTS DEMO 1 Launch Vehicle and Mission circumstantialations: mo| 315| mf| 10.45| D| 5.2| mp| 289.147| ms| 15.403| hook- forward shot| 4400 KN| Fuel| LOX/RP-1| mo extreme reverse send off stilt (in tons) mf incumbrance can (in tons) mp fit Propellant mass (in tons) ms vacant mass (in tons) D Diameter (in meters) Features of FALCON 9: * twain gunpoint vehicle * Manufacturer : SpaceX * Country of origin : United States represent Specifications: present| First| Second| Propellant Mass ( loads)| 243.431 (mp1)| 45.716 (mp2)| geomorphological Mass(Tons)| 10.1343 (ms1)| 5.268 (ms2)| Specific Impulse (Sec)| 304 (Isp1)| 342 (Isp2)| school principal 1: Calculation of stage ratios , despatch Fraction and Total propelling mass: sign Lift off mass :m0=i=0nmpi+i=0nmsi+mf where mpi=propellant masses msi=Structural masses n =Numbar of Stages m0=315 Tons Payload ratio : ?i= m0i+1m0i ?1= m02m01 ; ?2= mfm02 m01= mp1+ms1+ m02 m02= mp2+ms2+ mf This gives, ?1=0.19503?2=0.17010| Injected Payload proportionality(?f) : i=0n?i ?f=?1×?2 = mfm0 ?f=0.0331748| Stage wise Non fecund Ratio :?i= msimsi+mpi ?i= ms1ms1+mp1 ?1 =0.039967 Similarly, ?2=0.103326 The terminal determine of the stage ratios are tabulated below: Initial Lift off mass| m0=315 Tons| Payload Fraction| ?1=0.19503?2=0.17010 ?f=0.0331748| Stage wise Non productive Ratio| ?1 =0.039967 ?2=0.103326| Total Propellant Mass| mp=289.145| Question 2: Objective: To increase payload mass by 20 % Original Payload M ass mf=10.4! 5 Tons New payload Mass mf=1.2 × mf...If you want to get a full essay, order it on our website: BestEssayCheap.com

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