Table 31
|
Viking Project Orbiter
System: Baseline Conceptual Design Changes, Expected
Weights, 1969
|
|
Item Changed
|
Baseline
Weight (kg)
|
Expected
Weight (kg)
|
Cause
|
|
Orbiter (less propulsion)
|
627
|
606
|
1. Design to "flight loads"
analysis
|
|
|
|
2. Use of lightweight solar
cells
|
|
|
|
3. Reevaluation of expected subsystem
weights
|
Propulsion (inerts and
residuals)
|
385
|
302
|
1. Substitution of helium for
nitrogen as pressurant
|
|
|
|
2. Reduction of required Delta V =
1575 mps to Delta V = 1420 mps
|
|
|
|
3. Increase in nozzIe expansion ratio
frmn 40:1 to 60:1
|
Usable propcellant
|
1420
|
1263
|
4. Use of selected injectors for
Isp = 289 sec.
|
Lander capsule adapter
|
22
|
21
|
1. Design to "flight loads"
analysis
|
Lander capsule
|
816
|
995
|
|
Spacecraft adapter (includes destruct
package and transition adapter)
|
149
|
130
|
1. Design to "flight loads"
analysis
|
|
Viking spacecraft launch
weight
|
3419
|
3317
|
|