User Manual

Antares
®
OSP-3 User’s Guide Appendix A – Payload Questionnaire
Release 1.1 July 2013 A-6
ASCENT TRAJECTORY REQUIREMENTS
Free Molecular Heating at Fairing Separation:
FMH =  W/m
2
 Btu/ft
2
/hr
Fairing Internal Wall Temperature
T =  deg C  deg F
Dynamic Pressure at Fairing Separation:
q =  N/m
2
 lb
f
/ft
2
Ambient Pressure at Fairing Separation:
P =  N/m
2
 lb
f
/in
2
Maximum Pressure Decay During Ascent:
Δ P =  N/m
2
/sec  lb
f
/in
2
/sec
Thermal Maneuvers During Coast Periods:
SPACECRAFT ENVIRONMENTS
THERMAL
DISSIPATION
Spacecraft Thermal Dissipation, Pre-Launch Encapsulated: Watts
Approximate Location of Heat Source:
TEMPERATURE
Temperature Limits During Max  deg F  deg C
Ground/Launch Operations: Min  deg F  deg C
Component(s) Driving Temperature Constraint:
Approximate Location(s):
HUMIDITY
Relative Humidity: or, Dew Point:
Max % Max  deg F  deg C
Min % Min  deg F  deg C
GAS PURGE
Specify Any Gas Purge Requirements (e.g.; Nitrogen), Including Component Description,
Location, and Required Flow Rate:
(Nitrogen Purge is a Non-Standard Service)
CLEANLINESS
Volumetric Requirements (e.g. Class 100,000):
Surface Cleanliness (e.g. Visually Clean):
Other:
LOAD LIMITS
Ground Transportation Load Limits:
Axial = g’s
Lateral = g’s