THE ARTEMIS PROJECT
PRIVATE ENTERPRISE ON THE MOON
Access to Low Earth Orbit
Section 4.1.1.1.
Home Tour Join! Contents Team News Catalog Search Comm

Launcher Requirements Summary

Payload

Payload weight65,000 lbs would be nice
Orbit115 nmi @ 28.5 deg orbital inclination
Payload Envelope Diameter180 inches
Payload Envelope Length780 inches
Cryogenics in payloadyes
Keep-alive powersupplied by payload after launch
Telemetrynot required before payload deployment
Deployment Mechanismpyro bolts and springs

Orbital insertion tolerance

Flight 1+/- 30 nmi, +/- 2 deg inclination
Subsequent launch+/- 2 nmi, +/- 0.2 deg inclination
(Driven by rndz requirements)

Deployment stability

Rotation< 1 deg/sec, all axes
Relative Velocity< 25 ft/sec, all axes
Rndz ResponsibilityPayload

Vehicle control

Prior to Payload DeployLauncher
After Payload DeployPayload

Access to Low Earth Orbit

Home Tour Join! Contents Team News Catalog Search Comm
ASI W9600868r1.2. Copyright © 2007 Artemis Society International, for the contributors. All rights reserved.
This web site contains many trade names and copyrighted articles and images. Refer to the copyright page for terms of use.
Author: Gregory Bennett. Maintained by Jeremy Kraemer .
Submit update to this page. Maintained with WebSite Director. Updated Sun, Jul 5, 1998.