Delta
Vehicle Design
Overall Vehicle Data
Stage 1: Three Common Booster Cores
Dimensions (per core) | ||
Length | 40.8 m (133.9 ft) | |
Diameter | 5.1 m (16.7 ft) | |
Mass (per core) | ||
Propellant Mass | 199.6 t (440.0 klbm) | |
Inert Mass | 26.76 t (59.0 klbm) | |
Gross Mass | 226.4 t (499.0 klbm) | |
Propellant Mass Fraction | 0.88 | |
Structure | ||
Type | Tanks: isogrid | |
Center body, interstage: skin-stringer | ||
Tanks: aluminum | ||
Material | Interstage: graphite–epoxy | |
Center body: graphite–epoxy | ||
Propulsion (per core) | ||
Engine Designation | RS-68A (Aerojet Rocketdyne) | |
Number of Engines | 1 | |
Propellant | LOX/LH2 | |
Average Thrust | Sea level: 3,135 kN (705 klbf) | |
Vacuum: 3,559 kN (800 klbf) | ||
Isp | Sea level: 362 s | |
Vacuum: 411 s | ||
Chamber Pressure | 109 bar (1,580 psi) | |
Nozzle Expansion Ratio | 21.5:1 | |
Propellant Feed System | Gas generator turbopump | |
Mixture Ratio (O/F) | 6.0:1 | |
Throttling Capability | 52% and 100% | |
Restart Capability | None | |
Tank Pressurization | High-pressure helium gas | |
Attitude Control | ||
Pitch, Yaw | Hydraulic nozzle gimbal | |
Roll | Vectoring of turbine exhaust gas | |
Staging | ||
Nominal Burn Time | 249 s | |
Shutdown Process | Propellant depletion | |
Stage Separation | Guided Springs | |
Upper Stage: Delta Cryogenic Second Stage (DCSS)
| Dimensions | ||
| Length | 12.0 m (39.5 ft) | |
| Diameter | 5.1 m (16.7 ft) | |
| Mass | ||
| Propellant Mass | 27,200 kg (60,000 lbm) | |
| Inert Mass | 3,490 kg (7,700 lbm) | |
| Gross Mass | 30,710 kg (67,700 lbm) | |
| Propellant Mass Fraction | 0.89 | |
| Structure | ||
| Type | Isogrid LH2 tanks, | |
| monocoque LOX tanks | ||
| Material | Aluminum | |
| Propulsion | ||
| Engine Designation | RL10B-2 (Pratt & Whitney) | |
| Number of Engines | 1 | |
| Propellant | LOX/LH2 | |
| Average Thrust (Total) | 110 kN (24,750 lbf) | |
| Isp | 462.4 s | |
| Chamber Pressure | 32.1 bar (465 psi) | |
| Nozzle Expansion Ratio | 285:1 | |
| Propellant Feed System | Split-expander turbopump | |
| Mixture Ratio (O/F) | 5.5:1 | |
| Throttling Capability | 100% only | |
| Restart Capability | Nominally 1 restart | |
| Tank Pressurization | Helium for LOX tank, warm | |
| hydrogen for LH2 tank | ||
| Attitude Control | Electromechanical gimbaling | |
| Pitch, Yaw, Roll, Settling | 40-N (9-lbf) hydrazine thrusters | |
| Staging | ||
| Nominal Burn Time | 1,125 s | |
| Shutdown Process | Guidance shutdown or burn to depletion | |
| Stage Separation | Payload separation system | |
Payload Fairing
