Changes

== Propulsion System ==

== Propulsion System ==

The Cesaroni M1450 was chosen because it is commercially available, reloadable, complies with the Tripoli and California restrictions, keeps our rocket sub Mach-1, and should achieve a maximum height of 16,300 ft with the current mass estimates. Thus even if our mass budget increases, there will still be ample altitude to test the parafoil system.

The Cesaroni M1450 was chosen because it is commercially available, reloadable, complies with the Tripoli and California restrictions, keeps our rocket sub Mach-1, and should achieve a maximum height to a safe margin below the maximum ceiling. Thus even if our mass budget increases, there will still be ample altitude to test the parafoil system.

The M1450 has an average thrust of 1500 N, a total impulse of 10000 N-s, a specific impulse of 210 s, a burn time of 6.9 s, and a maximum velocity of 300 m/s (Mach 0.9).

The M1450 has an average thrust of 1500 N, a total impulse of 10000 N-s, a specific impulse of 210 s, and a burn time of 6.9 s.

=== Flight Characteristics ===

=== Flight Characteristics ===

[[File:Pegasus_Performance_Altitude_Speed.png|thumb|frame|center|800px|Altitude and Mach variation throughout the flight]]<br />

With current mass budget considerations, the M1450 motor is projected to boost the rocket to a peak of roughly Mach 0.78 and an apogee of roughly 11000 ft after 27 s.

[[File:CM1450_S_Stabil.png|image]]

 

 

 

[[File:Pegasus_Performance_Mass_Stability.png|thumb|frame|center|1000px|Mass decrease and change in static stability during the motor firing]]

== Structural Design ==

== Structural Design ==