Indian Missile News And Discussion

[Arun_S]

[quote name='gagan111' date='09 February 2010 - 01:00 AM' timestamp='1265656938' post='104007']

Arun_S are there configuration files for the Agni-3, Agni-5, and Shaurya missiles for Rockism? Can you post the links Pl? The version I have don't have these.



How can I plot a graph as suggested by Ramana? Is it possible to do this with any of MS office tools?



Thanks in advance.

[/quote]



I have not put on web the Rocksim configuration files for these rockets.



You can transcribe following configs:



Agni-3

Payload = 2,000.0 Kg, Number of Stages = 3, Simulation Time Granularity = 0.150 Second

Launch Direction = 50 degrees-North, Launch Latitude = 22.00 degrees



Segment-Name ISP(Vac) ISP(SL) Stage-Mass Fuel-Fract Burn-Time Thrust-Direction Diameter Length ThrustOverdrive OverdrivePeriod

Stage1 269.0 237.0, 34,000.0 0.900 090.0 Sec 51.0 Degree 2.00 Meter 07.00 Meter 25.00 % 20.00 %

Stage2 290.0 190.0, 15,000.0 0.870 110.0 Sec 22.0 Degree 2.00 Meter 03.50 Meter 10.00 % 10.00 %

PayloadAdaptor 000.0 000.0, 00,150.0 0.700 001.0 Sec 00.0 Degree 1.00 Meter 03.30 Meter 00.00 % 00.00 %

=============================================



Configuration file: Agni-3 SL for IDR article 29Dec08 R1.cfg

Payload = 550.0 Kg, Number of Stages = 4, Simulation Time Granularity = 0.250 Second

Launch Direction = 0 degrees-North, Launch Latitude = 22.00 degrees



Segment-Name ISP(Vac) ISP(SL) Stage-Mass Fuel-Fract Burn-Time Thrust-Direction Diameter Length ThrustOverdrive OverdrivePeriod

Stage1 269.0 237.0, 27,000.0 0.905 075.0 Sec 52.0 Degree 2.00 Meter 06.60 Meter 15.00 % 25.00 %

Stage2 294.0 190.0, 04,300.0 0.860 065.0 Sec 36.0 Degree 2.00 Meter 02.90 Meter 10.00 % 10.00 %

SUM 294.0 190.0, 01,150.0 0.800 050.0 Sec 35.0 Degree 2.00 Meter 03.30 Meter 00.00 % 00.00 %

Dummy 000.0 000.0, 00,000.1 0.880 001.0 Sec 15.0 Degree 0.01 Meter 02.00 Meter 00.00 % 00.00 %



==================================



Path up from Agni-3 is via addition of another 2 meter dia motor of ~ 8 tonne mass or a Small Upper Motor (SUM) that is inside the nose cone. (See figure "L" in my article "[url="http://www.indiaresearch.org/WayToACredibleDeterrent.pdf"]WayToACredibleDeterrent[/url]" ). Following

is based on SUM based configuration.



Configuration file: Agni-5 add 3rd stage to -A3 29T+11T+2.6T r1.cfg

Payload = 1,000.0 Kg, Number of Stages = 5, Simulation Time Granularity = 0.250 Second

Launch Direction = 42 degrees-North, Launch Latitude = 22.00 degrees



Segment-Name ISP(Vac) ISP(SL) Stage-Mass Fuel-Fract Burn-Time Thrust-Direction Diameter Length ThrustOverdrive OverdrivePeriod

Stage1 264.0 237.0, 29,000.0 0.910 065.0 Sec 50.0 Degree 2.00 Meter 07.00 Meter 10.00 % 25.00 %

Stage2 294.0 190.0, 11,000.0 0.880 055.0 Sec 28.0 Degree 2.00 Meter 03.50 Meter 05.00 % 10.00 %

Stage3 294.0 190.0, 02,700.0 0.830 040.0 Sec 20.0 Degree 2.00 Meter 00.00 Meter 00.00 % 00.00 %

Isolator 000.0 000.0, 00,050.0 1.000 001.0 Sec 01.0 Degree 0.00 Meter 00.00 Meter 00.00 % 00.00 %

RV-fuel 294.0 200.0, 00,000.0 0.990 001.0 Sec 00.0 Degree 0.00 Meter 00.00 Meter 00.00 % 00.00 %



===========================================



Shourya



Configuration file: Shourya rev1B for IDR article.cfg

Payload = 1,000.0 Kg, Number of Stages = 3, Simulation Time Granularity = 0.100 Second

Launch Direction = 90 degrees-North, Launch Latitude = 22.00 degrees



Segment-Name ISP(Vac) ISP(SL) Stage-Mass Fuel-Fract Burn-Time Thrust-Direction Diameter Length ThrustOverdrive OverdrivePeriod

SolidBooster 265.0 230.0, 01,275.0 0.780 010.0 Sec 70.0 Degree 0.75 Meter 02.00 Meter 40.00 % 30.00 %

Interstage 000.0 000.0, 00,020.0 0.100 015.0 Sec 70.0 Degree 0.75 Meter 00.50 Meter 00.00 % 10.00 %

Stage2 275.0 245.0, 03,625.0 0.820 038.0 Sec 47.9 Degree 0.74 Meter 06.00 Meter 00.00 % 00.00 %