Mission PHASE | Delta-V's |
a. Earth Orbit Plane Change Maneuver | 0.69 km/sec |
b. Trans-Lunar Injection | 1.67 km/sec |
c. Lunar Orbit Insertion | 0.54 km/sec |
d. De-Orbit Burn | 0.012 km/sec |
e. Lander Deceleration (to approx. 1000m) | 1.7 km/sec |
f. Landing Site Selection (approx. 200m x approx. 200m area) | unknown |
g. Final Lander Descent to MPS Cutoff | unknown |
Input Group | Interface/Information | Output Group |
Launch Vehicle | ||
Structures | Initial Spacecraft Mass Estimate | |
Launch Vehicle Payload Size Constraints | Structures | |
Refined Spacecraft Mass | Structures | |
Final Stage Orbital Trajectory | NGC | |
Main Propulsion System/Vernier System | ||
NGC | Landing Phase Requirements | |
NGC | Trajectory Design (Delta V) | |
Real Engine Performance | NGC | |
Propellant Tank Volume/Pressure | Structures | |
Pressurization Tank Volume/Pressure | Structures | |
Propellant Consumption | Structures | |
Power Requirements | Power | |
Computer Interfaces | Computer | |
Thermal Requirements | Thermal | |
Exhaust Products & Lunar Soil Interactions | Chemical | |
Reaction Control System | ||
NGC | Delta-V Requirements | |
NGC | Moment Requirements (thruster couples) | |
Real Thruster Performance | NGC | |
Thruster Placement | Structures | |
Thruster Propellant Consumption | Structures | |
Propellant Tank Volume/Pressure | Structures | |
Propellant Pressurization Tank Volume/Pressure | Structures | |
Power Requirements | Power | |
Computer Interfaces | Computer | |
Thermal Requirements | Thermal |
Last Modified:
CSR/TSGC Team Web