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.

Test Plan Update

The Test Plan has been updated. Click here to see the Test Plan Rev A.
(As formatting is not maintained within GoogleDocs please contact Alaina at alaina.reres@gmail.com for an original copy)

Pedestal and Platform Pictures

The constructed platform for the nose cone insert should coincide with the previously posted schematic.

Teague Middle School

The Analysis of Rocket Flight Parameters project will be presented to Teague Middle School on 2 December 2008 by invitation of Mr. Mark Imhoof. We appreciate the continuing support of Teague Middle School throughout the development of this project.

Test Launch

We will be performing a test launch tomorrow Sunday 16 November at approximately 2:00PM. The FAA has been left our launch information in a voicemail to the Florida FAA office. The integrated rocket and 9V battery weighs in at about 22.9 ounces. The test launches will test the transmissions of altitude, rotational acceleration, pitch, and roll. E motors will be used for these test launches.

Integration Status

The insert for the nose cone has been completed. The pedestal and platforms are assembled and are removeable from the nose cone of the rocket. Issues arose when aligning the fasteners to the railing that connects the platform to the nose cone. The fasteners and railing must be exactly line up and flush with the inner plastic.

A securing mount will be placed on top of the pedestal for the electronics board. Polyester fill is being investigated as a padding around the electronics board for protection in the event that the board becomes lose during flight or after landing.

Alternate battery sources are being investigated to minimize the weight of the rocket. Few FAA regulations apply to projectiles under one pound so if we are able to keep the weight of the rocket and payload under one pound we will have an easier time performing multiple launches.

The antenna is able to transmit through the plastic nose cone so creating a porthole for the antenna tip will not be necessary.

The pressure sensor will not need a large contact with outside atmosphere. Holes will be made in the rocket body to equalize pressure and allow the sensor to relay an accurate reading.

Programming Update

I've embedded a video demonstrating what coding we've done so far, how it all looks, and where we're going from here. It's a quick overview, so if you have any questions, feel free to ask!

Integration Progress/Final Presentation Date

The presentation for this project will be on 5 December 2008 at the University of Central Florida, Engineering Building 1, Room 388 at 3:00PM.

To Date:

The programming for transmitting roll and pitch data is complete and successful. Final steps are being taken to complete programming for the altimeter.

The platform that will hold the circuit board and battery is designed and almost finished. Remaining tasks are to secure the pedestal of the platform within the nose cone.

Click Photos to Enlarge

Updates!!

All electrical components have been soldered to the board, and retracting was required due to an unseen error in initial schematic design. Initial programming and testing has begun and the ADC and IMU appear to be in working order.

The corrected schematic can be seen here.

When programming began for the Transmitter and Receiver Modules, we encountered some issues when trying to get the devices to communicate. When looking at the data output through an oscilloscope, it appeared that the data was being transmitted but not received. However, this turned out to be a simple fix - we needed to pull the reset pin high and the sleep pin low. Now wireless communication is working as it should be.

Another slight issue we are having with the transmitter board, however, is that the program seems to be resetting itself every so often. Right now we are unsure what is causing this issue, but this will need to be fixed prior to initial launch.

Progress

To date:

The rocket has been assembled for preparation for integration. Rocket motor adaptor and body have been constructed. Integration is looking most feasible within the nose cone so the nose cone has not been connect to the parachute cord yet.

The circuit boards have been in-laid and are prepared to have the components soldered in place.

Electrical Componets Ordered

The final schematic for the board has been completed and the boards have been ordered for copper tracing. All other electrical components have also been ordered, and soldering will begin in the latter part of next week. Although we are behind our desired time line, we should be easily be able to catch up now that all parts have been ordered.

The Final Electrical Schematic can be seen here.

The Bill of Materials for all electrical components can be seen here.

Documentation

The Bill of Materials (BOM) for the circuitry and rocket components can be found at: http://spreadsheets.google.com/pub?key=pGCdyoA6O3hFCkT_2oISMIQ

The Pre-Test Plan (TPL) can be found at:
http://docs.google.com/Doc?id=dd5s54bp_45dvvt3dd7

The project overview can be found at:
http://docs.google.com/Doc?id=dd5s54bp_47q9n55df6

The above links are published through googledocs and have lost certain formatting features. For original document files please contact Alaina at alaina.reres@gmail.com.

Rocket Ordered

The rocket to be constructed has been ordered:
ARO-89011 Aerotech: Initiator Rocket Kit

Length 39 inches.
Diameter 2.6 inches.
Nose Cone 5-1.
Weight 14 oz.
3 fins, swept with cranked leading edge.
Motor Mount 29mm (includes 24mm adapter).
Parachute Recovery.

Recommended engines - RMS E18-4W, F24-4W, F40-7W, G64-7W or Single Use G40-7W or F20-4W Econojet.

Initial Schematic Design

Research for electrical components is almost complete and is being recorded in the project's "Bill of Materials" spreadsheet. Most components are available from Digi-Key. The initial schematic will be designed in PCB Express and will commence within the next couple of days. Hopefully the final design will be completed and ready to send out by Monday, September 22nd.

Rocket Search

The model rocket kit to be used must be able to accommodate the circuitry in some manner, whether it be integrated into the body, secured externally, or housed in the nosecone. J&B Hobby Center has a selection of model rocket kits. The available kits did not contain a body larger in diameter than about 1 1/2 inches (about the size of a paper towel roll). It is still undetermined whether or not we will have to integrate the circuitry into the body or not, which could pose the problem of our available kits to be spatially inadequate. J&B Hobby Center rocket kits range from about $14.99 to $20.00. Motors are available as large as a size "D" and are $12.99 for a pack of three (3) motors. The possibility of kits being available at the University of Central Florida is still being investigated.

Approval

The Senior Design Proposal for the analysis of rocket flight parameters submitted by Jessica and Alaina has been approved per Dr. Alfred Ducharme on behalf of the University of Central Florida College of Engineering and Computer Science Department of Engineering Technology.

Proposal Document

The published proposal can be found at the following link:
http://docs.google.com/Doc?id=dd5s54bp_42hpnw72cv

Proposal Submitted

We have submitted our proposal and are waiting to find out if it is approved.