Finished

The final report is completed and has been printed and bound. This project is considered a success. The transmitter was able to relay values for each parameter and those values were able to be graphed to depict the motions of the rocket in relation to time.

Launch Video/Final Report Status

A video containing three of the launches can be found at:
http://www.youtube.com/watch?v=yLij_U_aZEw

The final report is finished, save for the complete hours of labor, which will be the last thing updated before submission.

Test Flight

Another test was performed on 26 November 2008.

The first flight launched an almost perfect profile launching straight up and falling straight down. X and Y axis acceleration values were transmitted through the entire launch and descent and the rocket was recovered safely.

The second launch was unsuccessful. A faulty igniter in one of the motors failed to ignite causing only one motor to burn. The rocket launch upward about 30ft and traveled horizontally about 200ft before crashing to the ground. When the rocket touched down the motor was still burning. The nose cone was not able to deploy because the payload section was lodged in the body tube. The payload section was torn by the battery being force out of the side wall. There was no damage to the electronic chips, but the antenna was damaged at the base. All components are still deemed functionable.

The second launch was programmed to record pressure values to be converted to altitude. Values were reported for the flight and did show a slight decrease in pressure when the rocket was flying horizontally. The transmission was not entirely justifiable because the rocket did not perform as expected.

Teague Middle School

Our presentation to Teague Middle School has been rescheduled for Tuesday 9 December 2008.

Launch Results

Test launching was performed today using the Estes 36 D-Squared rocket with D12-7 motors.

The electronics board was programmed to report pitch and roll angles. Transmission failed to report data just after launch. It was learned that the 9V battery placed inside the payload bay was shorting the back of the board. Polyster fill was packed around the battery to prevent this from happening.

The second launch reported pitch and roll values through ascent and descent. Transmission halted at apogee. It is suspected that the transmitter might be out of reach. Exact height restriction will become more apparent when the electronics board is programmed and launched to report altitude. Successfully recorded through the hyperterminal and values will be saved and presented in the report.

Due to minimal cogs we are only able to successfully transmit two parameters per launch. Rotational acceleration uses 2 cogs, which calls for its own launch. One complete data collect will require six launches.

Second Rocket/Second Flight Test

Length 36 in. (91.4 cm)
Diameter 2.21 in. (56 mm)
Weight 5.7 oz. (162 g)

A second rocket was constructed to remain within the time restraint. The 36 D-Squared Estes model rocket was constructed. This rocket contains a payload bay and does not use an ejection baffle, rather it uses the ejection blast directly buffered with wadding. It is also much lighter than the Initiator rocket used previously.

Rocket2 was launched and recovered two time successfully using two D12-5 Estes motors for each flight. The payload in the first launch contained only the battery source and polyester fill for padding. The second launch contained the circuitry, battery, and polyester fill, all recovered nicely. The second launch did melt a portion of the parachute rendering it unusable. A new, heavier parachute will be attached for future flights. The circuitry did transmit while the rocket was on the launch pad but failed to continue working through the flight. The transmitter did relay an accurate reading while the rocket was on the launch pad. The rocket was manually shaken to simulate take-off and values were reported at that time.

First Flight Test

Preliminary flight testing was performed without integrated circuitry. Testing was a failure due to an unsuccessful detachment of the nose cone. The ejection force proved inadequate to separate the nose cone containing the pedestal and 9V battery. Alternate, lighter battery sources are being investigated. Payload bays are also being considered as another placement for electronics. The nose cone and inner body tube have been sanded to minimize their tight attachment, but this is not showing much improvement in allowing for an easier detachment.