I was comparing rocket systems via
Comparison of orbital launch systems - Wikipedia, the free encyclopedia and I noticed GSLV MK III and Atlas V 501 performance is roughly the same but, GSLV MKIII weights 304 tonnes more. why is that? is GLSV a inefficient design
GSLV Mk III
Mass 640,000KG
LEO 8,000KG
GTO 4,000KG
Atlas V 501
Mass 337,000KG
LEO 8,250KG
GTO 3,970
the math just doesn't add up.
Because you are comparing Mig 21 with Mig 29. Ie You need to compare Atlas 3 with Gslv 3 .
Atlas 3
Height 52.8 m (173.2 ft)
Diameter 3.05 m (10 ft)
Mass 214,338 kg (472,338 lb)
Stages 2
Capacity
Payload to LEO IIIA: 8,640 kg (19,040 lb)
IIIB: 10,218 kg (23,630 lb)
Payload to
GTO IIIA: 4,055 kg (8,939 lb)
IIIB: 4,500 kg (9,900 lb)
Associated rockets
Family Atlas
Launch history
Status Retired
Launch sites SLC-36B, CCAFS
Total launches 6
(IIIA: 2, IIIB: 4)
Successes 6
(IIIA: 2, IIIB: 4)[1]
First flight IIIA: 24 May 2000
IIIB: 21 February 2002
Last flight IIIA: 13 March 2004
III
First stage
Engines 1 RD-180
Thrust 4,148.7 kN (932,670 lbf)
Specific impulse 311 sec
Burn time 132 seconds
Fuel RP-1/LOX
Second stage (Atlas IIIA) - Centaur (SEC)
Engines 1 RL-10A
Thrust 99.2 kN (22,290 lbf)
Specific impulse 451 sec
Burn time 738 seconds
Fuel LH2/LOX
Second stage (Atlas IIIB) - Centaur (DEC)
Engines 2 RL-10A
Thrust 147 kN (41,592 lbf)
Specific impulse 449 sec
Burn time 392 seconds
Fuel LH2/LOX
GSLV MK3
Height 43.43 m (142.5 ft)[1]
Diameter 4.0 m (13.1 ft)
Mass 640,000 kg (1,410,000 lb)[1]
Stages 3
Capacity
Payload to
LEO (600 km) 8,000 kg (18,000 lb)[1]
Payload to
GTO 4,000 kg (8,800 lb)[1]
Launch history
Status Development
Launch sites Satish Dhawan Space Centre SLP, Andhra Pradesh, India
Total launches 1 (2 stage version)
Successes 1 (2 stage version)
First flight 18 December 2014 (2 stage version; sub-orbital flight)
Booster Stage - S200
Length 25 m (82 ft)[1]
Diameter 3.2 m (10 ft)[1]
Propellant mass 207,000 kg (456,000 lb)[1]
Engines 2 Solid
Thrust 5,150 kN (525 tf) each[3][4][5]
Specific impulse 274.5 (vacuum)[1]
Burn time 130 sec[1]
Fuel HTPB[1]
Core Stage - L110
Length 17 m (56 ft)[1]
Diameter 4.0 m (13.1 ft)[1]
Propellant mass 110,000 kg (240,000 lb)[1]
Engines 2 Vikas engines
Thrust 1,598 kN (163.0 tf)[1][6][7]
Specific impulse 293 sec[1]
Burn time 200 sec[1]
Fuel UDMH/N2O4
Upper Stage - C25
Length 13.5 m (44 ft)[1]
Diameter 4.0 m (13.1 ft)[1]
Propellant mass 27,000 kg (60,000 lb)[1]
Engines 1 CE-20
Thrust 186 kN (19.0 tf)[1]
Specific impulse 450 sec
Fuel LOX/LH2