ISProgram
SketchUp Orbinaut
50mt to LEO!
Okay, so I've done it, the rocket now gets 50,000 kg to LEO!
The first stage still had some margin on its propellant mass, 0.03%, which is now gone. The LR-60 dry mass has been reduced to 500 kg. Since the LR-60 is smaller than either the L-1 and its future replacement engine, the interstage could lose weight. Payload fairing mass and jettison time is unchanged.
Here are the numbers:
First Stage
Empty Mass/Inert: 37,863 kg (83,474 lb)
Thrust: 12,040 kN (2,706,700 lbf), 70% of full thrust
Propellant Mass: 809,326 kg (1,784,258 lb)
Second Stage
Empty Mass/Inert: 8,894 kg (19,608 lb)
Thrust: 1,160 kN (260,700 lbf)
Propellant Mass: 79,296 kg (174,817 lb)
Interstage
Mass: 1,096 kg (2,416 lb)
Silverbird says the rocket can get 50,127 kg to a 160 km circular orbit with a inclination of 28.7, launching from Cape Canaveral. Admittedly, I would've preferred it to be 185 x 185, but I've exhausted practically all my margin, and rockets are tricky things.
The first stage has a delta-V of 5652.17 m/s and the second stage has one of 3931.08 m/s. This does not include payload fairing mass on the second stage, because the fairing will either be jettison during first stage burn or shortly after second stage ignition.
Complete delta-V is thus 9583.25 m/s, so this redundantly confirms that it has a 50,000 kg payload capacity.
Success!
Okay, so I've done it, the rocket now gets 50,000 kg to LEO!
The first stage still had some margin on its propellant mass, 0.03%, which is now gone. The LR-60 dry mass has been reduced to 500 kg. Since the LR-60 is smaller than either the L-1 and its future replacement engine, the interstage could lose weight. Payload fairing mass and jettison time is unchanged.
Here are the numbers:
First Stage
Empty Mass/Inert: 37,863 kg (83,474 lb)
Thrust: 12,040 kN (2,706,700 lbf), 70% of full thrust
Propellant Mass: 809,326 kg (1,784,258 lb)
Second Stage
Empty Mass/Inert: 8,894 kg (19,608 lb)
Thrust: 1,160 kN (260,700 lbf)
Propellant Mass: 79,296 kg (174,817 lb)
Interstage
Mass: 1,096 kg (2,416 lb)
Silverbird says the rocket can get 50,127 kg to a 160 km circular orbit with a inclination of 28.7, launching from Cape Canaveral. Admittedly, I would've preferred it to be 185 x 185, but I've exhausted practically all my margin, and rockets are tricky things.
The first stage has a delta-V of 5652.17 m/s and the second stage has one of 3931.08 m/s. This does not include payload fairing mass on the second stage, because the fairing will either be jettison during first stage burn or shortly after second stage ignition.
Complete delta-V is thus 9583.25 m/s, so this redundantly confirms that it has a 50,000 kg payload capacity.
Success!