Back to SC Design

Home

Progressive Evolution of Launcher Payloads

Gen

Type

Functions

Missions

0

Escape Test

Attached to Stage 3, Laser Link, H2O RCS

Performance tests, Burials

I

Link Test

H2O RCS, Temp Controls, Laser Link with Telescope

Data transmission tests

II

Stabilization

Type I + Radiation pressure stabilization

Longer term data transmissions

III

NEO Flyby

Type II + NH3 decomposition thrusters, delta V ~500 m/s

Develop navigation skills, NEO photography

IV

NEO Orbit

Type III + 1-2 km/s delta V, NH3 decomp or biprop rocket

Orbit NEO

V

Lunar Land

3 km/s delta V, 1 g acceleration

direct lunar landing

VI

NEO Land

Type IV + NEO lander with local RF link to orbiter

NEO landings

VII

Ion Test

Tests of 1 watt FEEP or colloid electrostatic thruster

High delta V with less propellant

Back to SC Design

Home


: 2007 Charles Pooley -- ckpooley@microlaunchers.com