Lab+Report+(Yingchao+Kyle+Ji)

__//**Lab Report**//__

Purpose Materials Procedure Data Analysis Conclusion Sources of Error

Purpose Return to top

The purpose of this activity was to build and launch a model rocket and apply concepts learned in class during the entire process.

Materials Return to top


 * Styrofoam
 * Estes rocket engines (B6-4 and C6-4) and igniter/ igniter plug
 * Old binder
 * Utility knife
 * 18" elastic
 * Hot glue and glue-gun
 * White glue
 * Scissors
 * Spray paint
 * Plastic bag
 * Wadding
 * Scotch tape
 * String
 * Paper clip
 * Dime roll
 * Cardboard
 * Plastic tube
 * Paper
 * Launch pad and launch controller
 * Estes altitude finder
 * Talcum powder
 * Straw

Procedure Return to top

Building Procedure:

Pieces resembling fins were cut out from an old binder and hot glued equidistant to each other and parallel to the plastic tube. The engine mount was covered with glue and stuffed inside the plastic tube. The one end of the elastic was glued inside the plastic tube and the other end was attached to a nose cone shaped from a block of styrofoam. A parachute cut from a plastic bag and tied with strings was glued to the elastic. A straw was then glued onto the body tube to accommodate the launching device. The parachute was powered with talcum, and then stuffed into the body tube. The entire rocket was then spray-painted.

Launch Procedure:

An engine was placed into the engine mount. An igniter was placed into the clay nozzle and held in place by an igniter plug. Alligator clips were attached to the igniter. The rocket was placed on the launchpad, the launch button was then pressed.

Data Return to top

Launch Attempt 1: (Estes) || 4s || Launch Attempt 2:
 * Mass of rocket with B6-4 engine || 0.0768kg ||
 * Time Up || 4.57s ||
 * Time Down || 13.4s ||
 * Angle || 39° ||
 * Force of rocket engine (Estes) || 6N ||
 * Time delay between the end of the thrust phase and ignition of the ejection charge
 * Takeoff success || Yes ||
 * Controlled Takeoff || Yes ||
 * Recovery System Deploys || Yes ||
 * Broken Parts || No ||


 * Takeoff success || Yes ||
 * Controlled Takeoff || Yes ||
 * Recovery System Deploys || Yes ||
 * Broken Parts || N/A (rocket could not be retrieved) ||

Analysis Return to top

5.25N(0.57s) = 0.0768kg(∆v) 2.993Ns = 0.0768∆v ∆v = 38.97 m/s || 39.0 m/s = 0 +a (0.57s) a = 68.42 m/s² || 40.5 = 6. 625 V₂ V₂ = 6.02 m/s || a = 0.44m/s || (0.44)(0.0768) – (0.0768)(9.8) = F air (0.0338)-(0.753)=F air F air = 0.7188N F net = 0.034N ||
 * Force of gravity || 0.0768kg * 9.8m/s² = 0.753N ||
 * Net force on rocket || 6N – 0.75N = 5.25 N ||
 * Distance travelled by rocket || 50tan39° = 40.5 meters ||
 * Duration of thrust phase || 4.57s – 4s = 0.57 seconds ||
 * Maximum velocity reached by rocket || F (∆t) = m (∆v)
 * Acceleration reached during thrust phase || V₂ = V₁ + at
 * Velocity before hitting ground || 40.5 = (V₂+0)/2 x (13.4)
 * Acceleration after parachute deployment || 6.02 = 0 + 13.4a
 * Force of air resistance after parachute deployment || F net – F gravity = F air

Conclusion Return to top

Our rocket preformed well. It reached a maximum velocity of 39 m/s with an acceleration of 68.42 m/s² and the parachute deployed successfully on both trials, slowing it down to 0.44m/s ². Since the parachute was so effective, the rocket stayed intact for the first trial, and it was likely it would stay intact for the second trial. However, since the second trial ended when the rocket landed on the roof of a tall building, its condition is still unknown.

Sources of Error Return to top

The main source of error was the fact that the rocket did not launch perpendicular to the ground but launched at an angle instead. This means the calculated distance will not be entirely accurate. Another major source of error was air resistance and wind velocity; simply because it cannot be calculated with the data we have. This means the values for acceleration during thrust phase, maximum velocity, and net force on rocket will be higher than what they actually should be.

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