Validating a Novel Theoretical Expression for Burn time and
... [1]. The solid propellant charge is called the grain and it contains all the chemical elements for complete burning (i.e. oxidizer, fuel). Once ignited by the ignition system (which is usually an electrical fuse), the grain usually burns smoothly at a predetermined rate on all exposed surfaces of th ...
... [1]. The solid propellant charge is called the grain and it contains all the chemical elements for complete burning (i.e. oxidizer, fuel). Once ignited by the ignition system (which is usually an electrical fuse), the grain usually burns smoothly at a predetermined rate on all exposed surfaces of th ...
Electric Propulsion
... motors with a maximum Isp of roughly 450 s is approximately 20,000 m/s with a initial-to-final mass ratio of 150 Included in the final mass fraction, mf, are the vehicle inert mass (structure, tanks, engine, residual fuel, etc.), as well as the payload mass. The propellant mass fraction, expressed a ...
... motors with a maximum Isp of roughly 450 s is approximately 20,000 m/s with a initial-to-final mass ratio of 150 Included in the final mass fraction, mf, are the vehicle inert mass (structure, tanks, engine, residual fuel, etc.), as well as the payload mass. The propellant mass fraction, expressed a ...
Model Rocket Workshop
... world using these engines seem to indicate that this hypothesis is plausible. Finally, although the launch day was not meteorologically complicated, conditions such as wind could also have played a part in this inconsistency. If we consider a new simulation with other motor parameters we obtain othe ...
... world using these engines seem to indicate that this hypothesis is plausible. Finally, although the launch day was not meteorologically complicated, conditions such as wind could also have played a part in this inconsistency. If we consider a new simulation with other motor parameters we obtain othe ...
The Aerodynamic Forces code grew steadily over the course of the
... Fig. A.1.2.3.5.1, XCP vs angle of attack for a 3 stage vehicle at Mach 3 (Alex Woods) Figure A.1.2.3.5.1 shows that the center of pressure will move aft along the rocket body as angle of attack changes, which is what we expect for a launch vehicle.3 We have some issues with the validity of the resul ...
... Fig. A.1.2.3.5.1, XCP vs angle of attack for a 3 stage vehicle at Mach 3 (Alex Woods) Figure A.1.2.3.5.1 shows that the center of pressure will move aft along the rocket body as angle of attack changes, which is what we expect for a launch vehicle.3 We have some issues with the validity of the resul ...
Lecture2
... Impulse is the average force acting over a time period multiplied by the time period. It may also be written as an integral Note the difference between impulse J and work W. ...
... Impulse is the average force acting over a time period multiplied by the time period. It may also be written as an integral Note the difference between impulse J and work W. ...
Propulsion systems
... 3. Station/trajectory keeping (staying where it should be, or going in the correct direction). ...
... 3. Station/trajectory keeping (staying where it should be, or going in the correct direction). ...
AP Rocket Propulsion
... Upon exiting Earth’s atmosphere and reaching a distance where Earth’s gravitational field is negligible, the rocket moves at high speeds without slowing due to inertia! ...
... Upon exiting Earth’s atmosphere and reaching a distance where Earth’s gravitational field is negligible, the rocket moves at high speeds without slowing due to inertia! ...
Worksheet-ImpulseAndMomentum
... 15. A rocket takes off from the surface of Earth straight up. The total mass of the rocket is 5000 kg, 3500 kg of which is fuel. The exhaust gas velocity is 3000 m/s, and the rocket consumes 25 kg of fuel per second. For how long do the engines burn? What is the thrust of the engine? What are the in ...
... 15. A rocket takes off from the surface of Earth straight up. The total mass of the rocket is 5000 kg, 3500 kg of which is fuel. The exhaust gas velocity is 3000 m/s, and the rocket consumes 25 kg of fuel per second. For how long do the engines burn? What is the thrust of the engine? What are the in ...
Scramjet
A scramjet (supersonic combusting ramjet) is a variant of a ramjet airbreathing jet engine in which combustion takes place in supersonic airflow. As in ramjets, a scramjet relies on high vehicle speed to forcefully compress the incoming air before combustion (hence ramjet), but a ramjet decelerates the air to subsonic velocities before combustion, while airflow in a scramjet is supersonic throughout the entire engine. This allows the scramjet to operate efficiently at extremely high speeds: theoretical projections place the top speed of a scramjet between Mach 12 (8,400 mph; 14,000 km/h) and Mach 24 (16,000 mph; 25,000 km/h).