Responsive Access Small Cargo Affordable Launch (RASCAL ...

the actual flight hardware (ejection seat, turbofans, etc.). The only major exception is the
TPS weight which was sized independently from the aeroheating data.
The major components of the first stage are the wing, body, main propulsion, and
landing gear. The weight breakdown of the first stage is included as Figure 18.
Gross Weight
Dry Weight
Wing Group
Tail Group
Body Group
TPS
Landing Gear
Main Propulsion
Electrical Conversion and Distribution
Hydraulic Systems
Surface Control and Actuators
Avionics
Environmental Control
Personnel Equipment
Dry Weight Margin
101,503 lb
56,565 lb
7,936 lb
1,432 lb
12,727 lb
865 lb
3,034 lb
16,992 lb
1,138 lb
660 lb
2,021 lb
1,964 lb
200 lb
218 lb
7,378 lb
Environmental Control
0%
Avionics
3%
Surface Control and
Actuators
4%
Hydraulic Systems
1%
Electrical Conversion
and Distribution
2%
Main Propulsion
30%
Figure 18: Weight Breakdown for 1st Stage Baseline.
Personnel Equipment
0%
Dry Weight Margin
13%
Wing Group
14% Tail Group
3%
Body Group
23%
TPS
2%
Landing Gear
5%
From this weight breakdown it can be seen that the body and main propulsion (including
MIPCC engines) are the main contributors to the dry weight. Weight growth margin is
also a significant portion of the dry weight (15% of pre-margin dry weight).
The second stage was modeled from MERs from both expendable rocket data
[10], as well as conceptual design equations [7]. The hybrid engine was modeled as a
pressurized oxidizer tank, a solid fuel casing, a feed system for the oxidizer, and a nozzle.
The fuel casing is sized as a seven port solid with a 48% volumetric efficiency [7]. A
weight breakdown of the second stage is included as Figure 19. It should be noted that
the structure includes both the fuel and oxidizer tanks, while the propulsion elements
include the engine nozzle and the feed system. The gross weight includes both the
payload and the gross mass of the third stage.
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