Monday, March 4, 2013

Space

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.

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17010|

Injected Payload Ratio(?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 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

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