SPACE FLIGHT DYNAMICS
AE 713
ASSIGNMENT-2
Submitted by N. ARVIND10301002|
entry Vehicle and armorial bearing:
Launch Vehicle: FALCON 9
Mission: NASA COTS DEMO 1
Launch Vehicle and Mission Specifications:
mo| 315|
mf| 10.45|
D| 5.2|
mp| 289.147|
ms| 15.403|
hook-off Thrust| 4400 KN|
Fuel| LOX/RP-1|
mo extreme Lift off stilt (in tons)
mf Payload can (in tons)
mp Total 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:
Stage| First| Second|
Propellant Mass (Tons)| 243.431 (mp1)| 45.716 (mp2)|
geomorphological Mass(Tons)| 10.1343 (ms1)| 5.268 (ms2)|
Specific Impulse (Sec)| 304 (Isp1)| 342 (Isp2)|
Question 1:
Calculation of stage ratios, payload 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 Ratio(?f) : i=0n?i
?f=?1Ã?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 values 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 Mass mf=10.45 Tons
New payload Mass mf=1.2 Ã mf...If you want to get a full essay, order it on our website: Ordercustompaper.com
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