Embed Size (px)
Citation preview
1
NASA Student Launch Initiative
Infrared and Visual Light Vegetation Imaging Analysis Preliminary Design Review
Educators
Principal Lead Educator
Ms. Christine Hager, Biology Instructor Madison West High School, 30 Ash St., Madison, WI 53726
Phone: (608) 204-3181 Fax: (608) 204-0529
Email: [email protected]
Co-Lead Educators Dr. Pavel Pinkas, Ph.D., Senior Software Engineer for DNASTAR, Inc.
1763 Norman Way, Madison, WI, 53705 Home Phone: (608) 238-5933 Work Phone: (608) 237-3068 Email: [email protected]
Prof. Dan McCammon, Ph.D., Professor of Physics at UW-Madison Work Address: 6207 Chamberlain Hall 1150 University Ave 53706
Home Phone: (608) 233-7757 Work Phone: (608) 262-5916
Fax: (608) 263-0361 Email: [email protected]
Ed Burdett, Technology Education Instructor
Madison West High School, 30 Ash Street, Madison, WI, 53726 Phone: (608) 204-3078
Email: [email protected]
NAR Mentor Mr. Scott T. Goebel
3423 Pierce Boulevard, Racine, WI 53405-4515 Home Phone: (262) 634-3971
Email: [email protected]
2
Students Participating
Vehicle Team
Tom Hanzlik (Key Manager): Duties: Labor division to vehicle team, lead vehicle design, vehicle construction.
Email: [email protected]
Rehan Quraishi (Key Technical Manager): Vehicle team Duties: Payload integration, assistant vehicle design, vehicle construction.
Email: [email protected]
Justin Balantekin: Vehicle team Duties: Vehicle safety manager, vehicle construction.
Email: [email protected]
Payload Team
Peter Culviner (Key Manager): Payload team Duties: Labor division to payload team, lead payload design, payload construction.
Email: [email protected]
Thomas Ostby (Key Technical Manager): Payload team Duties: Payload integration, assistant payload design, payload construction.
Email: [email protected]
Mengdi “Dennis” Zuo: (Key Technical Manager): Payload team Duties: Payload experiment manager, payload construction.
Email: [email protected]
Casey Petrashek: Payload team Duties: Payload feasibility manager, payload construction.
Email: [email protected] .
Andrei Pinchuk: Payload team Duties: Payload safety manager, payload construction.
Email: [email protected]
Wolfgang Schmaltz: Payload team Duties: Payload analysis manager, payload construction.
Email: [email protected]
3
Table of Contents: I) Vehicle Criteria 4
A. Selection, Design, and Verification 4
B. Recovery Subsystem 7
C. Mission Performance Predictions 9
D. Payload Integration 12
E. Launch Operation Procedures 12
F. Safety and Experimental Risk 13
II) Payload Criteria 15
A. Selection, Design, and Verification of Payload Experiment 15
B. Payload Concept Features and Definition 17
C. Science Value 18
D. Payload Risk and Safety 21
III) Outreach and Project Plans 21
IV) Summary 23
4
I) Vehicle Criteria
A. Selection, Design, and Verification
1. Mission Statement, Requirements, and Success Criteria:
The mission of this project is to successfully launch a payload-bearing vehicle to the altitude of 5,280 feet for the purpose of capturing multiple simultaneous images (standard and infrared) of vegetation on the Earth’s surface at varying altitudes. Two synchronized cameras will be used to obtain the pictures (camera 1 (VL) operating in visible spectrum, camera 2 (IR) capturing in IR spectrum). The IR pictures will be used to determine general health of the vegetation as well as the concentration of different plants (different foliage reflects different amounts of IR light). A comparison of amount/detail of information gained from the IR and the VL pictures will be made to demonstrate the importance and advantages of IR imaging.
This experimental goal requires a rocket capable of reaching the target height of one mile. It also requires the electronic payload to be integrated into the rocket. The flight will be considered successful if the rocket reaches the mile high altitude, deploys the payload and recovery systems, and the payload captures a sufficient number of properly synchronized pictures allowing us to extract functional environmental data for later computer analysis against samples taken before the experiment of "stressed" vegetation and also vegetation of varying species. 2. Vehicle Milestone Schedule: December 2005. 7th Preliminary Design Review due. Filter/Camera design choice finalized. 11th Scale model design finalized. 19th Construction of scale model finished.. 23rd Scale model test launch. Cameras obtained, testing/modifications begin. 30th 2nd Scale model test with ballast to render CG/CP relationship that of proposed full
scale model. Camera durability test begins. Compact Flash memory card purchased. January 2006 6th 3rd scale model test launch with mock payload Vehicle payload bay construction started. Digital Image Analysis Program testing begins. Engine selection finalized. 13th Work on the CDR begins. Requests for sponsorship go out. 15th Web presence finalized. 20th. Camera synchronization scheme construction completed. Testing begins. 27th Vehicle construction started. RDAS/Perfectflite Altimiters purchased. Deployment
electronics testing begins. February 2006 7th Critical Design Review due. 14th Vehicle component tests. Begin Digital Image Analysis Program testing. 23rd Vehicle construction continues.
5
March 2006 4th Begin working on Flight Readiness Review. Complete vehicle. Vehicle deployment
tests. 11th First test flight without payload components. 18th Test flight analysis, repair. Final payload testing. 25th Second test flight, all systems running. Digital Image Analysis Program testing finished. April 2006 1st Test flight analysis, repair. Final design analysis. 7th Flight Readiness Review due. 14th Final design preparations. Final test launch if necessary. May 2006 3rd to 7th SLI Launch at Huntsville. 7th to 24th Data analysis and compilation. 26th Final report submitted. 3. Design Systems/Subsystems Structural System
The structural subsystem's main purpose will be to keep the rocket together and going in the desired direction (straight up). The body will consist of two 4 inch diameter tubes coupled together (to provide a sufficient length), a transition to 9" diameter payload bay, which will be custom-made either by us or ordered, followed by a shoulder back to 4” diameter tube and a nosecone. The fins will use TTW (Through the Wall) construction, being attached to the rocket both at the motor mount and at the body tube.
We will be using a phenolic paper tube coated with a fiberglass and epoxy composite in order to ensure the strength of the rocket. The maximum acceleration of the rocket will be approximately 7 gees, so more strength will not be necessary. We chose these materials because they are all inexpensive, we have the needed supplies and equipment to use them, and they have worked well in the past for our group.
The structural system will be made to withstand the acceleration (10g), velocity, temperature and impact of the landing. Testing will commence once materials are obtained to determine exact performance characteristics, but judging from previous experience the integrity of the structural system should be adequate.
Propulsion System
The Contrail M711-12, our primary motor, is composed of three chief components: an oxidizer tank; a combustion chamber and a nozzle.
The purpose of an oxidizer tank is to provide N2O as an oxidizer in the combustion for the propulsion of the rocket. Various sizes of the oxidizer tank produce different impulse classes. All M-Level Contrail motors use 3200cc oxidizer tanks.
The combustion chamber is where the reaction between the oxidizer and the fuel occurs, creating thrust for the rocket. The combustion chamber is available in four different sizes (eighteen (18), twelve (12), ten (10) and eight (8) inches.), which produce varying levels of thrust. The motor that we intend to use (Contrail M711) uses a twelve-inch combustion
6
chamber. The nozzle is a very precision-based piece of equipment. It directly affects the thrust of the
rocket. The nozzle is fitted with one of three different graphite inserts, which determine the “speed” of the nozzle, which are labeled slow, medium and fast. The motor also uses fuel grains, which are used to combust with the N2O in the oxidizer tank. The fuel grain we will be using is PVC plastic grains. Recovery Subsystem
The recovery system can be divided into two independent portions, the vehicle recovery and the payload recovery. The details of the recovery subsystem are in the Section B: Recovery Subsystem. 4. Verification Plan
Verification Matrix:
Key T1-Scale Model Launch Test. T2- Drop Test from 20 ft. T3- Acceleration Test (using centrifuge). T4- Vacuum Test (to simulate pressure/altitude changes). T5- Ground Test (to test proper sending and reception of data). T6- Ignition Test. T7- Tension Test. T8- Drag Test. T9- Test Flight
System T1 T2 T3 T4 T5 T6 T7 T8 T9 Main Parachute
♦ ♦ ♦
Drogue Parachute
♦ ♦ ♦
Payload Parachute
♦ ♦ ♦
RDAS ♦ ♦ ♦ ♦ Telemetry System
♦ ♦ ♦
GPS System
♦ ♦ ♦
Altimeter ♦ ♦ ♦ Couplers ♦ ♦ ♦ Shock Cords
♦ ♦ ♦
Fins ♦ ♦ ♦ Engine/ Engine Retention
♦ ♦ ♦ ♦ ♦
7
5. System Risks/Mitigation: See Section F: Safety and Experimental Risk 6. Planning of Manufacturing, Integration, and Operations The time schedule for manufacturing the vehicle, the payload and their integration is outlined in our time plan (Vehicle Milestone Schedule section). Both the vehicle and the payload will be constructed in the workshop in school under supervision of a material science teacher and NAR mentors.
7. Confidence and Maturity of Design
Our rocket was designed using the RockSIM CAD software that allows us to determine the stability of our rocket. The software also allows us to simulate the flight under varying conditions (wind speed, temperature, location etc). A test vehicle will be built to evaluate the stability of the design, as well as the hybrid motor subsystem and the deployment/recovery subsystem. We will work with the NAR HPR certified rocketry mentors to integrate a hybrid motor subsystem to our rocket. A model of the payload will also be integrated into the vehicle to test the security of the payload during a launch.
All members of this SLI team have had prior experience in rocketry, and have qualified within top 25 ranking participants of TARC. Students experienced with model rocket design designed all planned vehicles. A Level-2 HPR certified mentor (Mr. Goebel) will review the final rocket design.
B. Recovery Subsystem
1. Design/Testing/Projected Specifications
The vehicle recovery subsystem will consist of two Perfectflite altimeters which will trigger FFFF black powder charges of previously tested quantities to deploy a drogue chute at apogee and a main body parachute at a preset altitude, most likely being 500 or 300 feet, depending on the wind velocity. Both altimeters will fire the same charges both at the apogee and the preset altitude (firing redundancy).
The payload parachute will be deployed at apogee by the RDAS and a Perfectflite altimeter located in the payload bay. Both the RDAS and the altimeter will activate the same charge (firing redundancy).
Recommended parachute sizes are tabulated below:
Parachute Descent Mass [oz]
Descent Rate [fps]
Parachute Size [in]
Booster Drogue 395 67 24Booster Drogue + Main 395 21 24 + 72Payload Main 177 15 72
8
The configuration of the vehicle/payload and the flight sequence are depicted on Figure 1 and Figure 2 below.
Figure 1. Vehicle/Payload subsystems configuration and deployment events
Figure 2. Flight sequence
9
The size of ejection charges will be based on the formula
Wp = dP * V / R * T
where:
dP is the ejection charge pressure in psi. R is the combustion constant, 22.16 (ft- lbf/lbm R for FFFF black powder) T is the combustion gas temperature (3307 degrees farenheit). V is the free volume in cubic inches Wp is the charge weight (pounds)
These numbers will be applied and tested during ejection charge tests. The rocket body and its respective recovery sub-systems will be held together by a nylon
shock cord attached to the engine, and running through the (4inch) body tube and attaching to he main body parachute. The shock cord will be of suitable strenght as determined by tension calculations when the final masses of the rocket components have been established, and will be physically verified. The shockcord linking the payload capsule to the payload chute will be anchored on a U-bolt installed into the payload capsule, and will be likewise choosen and verified.
C. Mission Performance Predictions
1. Mission Performance Criteria In order for the mission to be considered a "success" the following criteria must be met:
• Rocket must launch successfully at a desired angle (based upon wind speed and other on-site conditions).
• The altitude reached must be as close to one mile as possible. • To ensure the safety of the rocket, payload, and personal, recovery systems must
deploy at apogee. • The two cameras must capture synchronized photographs in their respective light
ranges at specific times from apogee to payload landing. • Photographs must be properly analyzed through use of computer imaging software
as to extract conclusions from data. • The payload must return to the ground undamaged as to allow for proper data
transfer/acquisition.
10
2. Simulated Data/Vehicle Specifications Experimental Performance/Specifications
Figure 3. Rocket Design (with CP and CG marked)
Figure 4. A 3D Model of the Vehicle
Results of the flight simulations with the M711 motor under various wind conditions are tabulated below. From the simulations is clear that the apogee is not significantly affected by the wind speed and only small amount of ballast will be needed to adjust for various wind speeds within the NAR allowed wind speed range (0—20mph).
Motor
Wind Speed [mph]
Ballast [lbs]
Max. Speed [mph]
Max. Acceleration
[g] Altitude
[ft]
Static Margin
[in] Contrail M711 0 11.75 380 4.62 5290 11.8Contrail M711 5 11.75 380 4.62 5276 11.8Contrail M711 10 11.25 384 4.69 5286 11.7Contrail M711 15 10.75 388 4.75 5272 11.7Contrail M711 20 9.75 395 4.88 5284 11.76
Note: The coefficient of drag (Cd) has been changed from the Rocksim calculated value of ~0.25 to 0.40. We have done this because past experience in flying rockets designed in Rocksim has led us to believe that the software is overly optimistic in altitude predictions, and using 0.40
11
Cd has been shown to provide more realistic simulations. Our scale model will be used to verify this. We will simulate it in Rocksim, and then fly it. We will average repeated flights, and then compare the Rocksim results to the actual results. From this, we will be able to determine the actual Cd of the rocket design, and our simulations will be much more accurate. The thrust curve for the Contrail M711 motor is shown on Figure 5.
Figure 5. Contrail M711 Thrust Curve
A typical altitude profile is depicted on Figure 6.
Figure 6. Altitude vs. Time
12
D. Payload Integration
1. Vehicle—Payload Integration
There are several concerns that present themselves in association with the issue of integrating the payload module into the vehicle structure. The first of these concerns is the exact positioning of the payload in relation to the rest of the rocket. After much thought and research, we have decided upon placing the payload bay below the payload parachute (which is in turn directly below the nosecone) and above the body drogue parachute (see Figure 1.). The reasoning behind this particular placement of the payload amounts to the fact that this design is most convenient due to experimental considerations (this type of positioning will enable the two cameras to point downwards and collect photographs at the necessary point in time). This design is also most convenient in terms of payload safety as it will ensure that the other sections of the rocket will not interfere with the payload at apogee (when both the payload parachute and body drogue parachute open).
Our second main concern relating to payload integration is the presence of possible hazards and risks that could damage our payload during launch, flight or recovery. One of these is the possible damage due to acceleration. As our vehicle will only experience 6g acceleration we predict that our payload will be easily able to sustain these forces.
Another possible hazard comes from the hot gases, emitted as a result of firing the ejection charge. The Nomex cloth and a plexiglas bottom of the payload bay will protect the cameras from possible contact with the ejection gases.
Finally, the dimensions of our rocket will be accommodated to the necessities of our payload system. So as to properly accommodate both of the 5.2’’ by 4.0’’ Nikon D50 Single Lens Reflection cameras (side by side) the section of the rocket which will hold the payload system has been increased from the original 4’’ (approx.) body size to approximately 10’’. This transition of sizes presents an interesting challenge. In order to allow the vehicle to reach the proper altitude with optimum fuel efficiency we had to work towards making our design more aerodynamic in addition to watching weight of the rocket as a whole.
E. Launch Operation Procedures
1. Launch System Final assembly checklist 1. Check functionality of altimeter 1, 2 and 3, RDAS and GPS/Telemetry systems 2. Verify functionality of cameras. 3. Inspect structural subsystems, looking for travel damage, weakened stress points, etc. 4. Prepare payload black powder deployment charges 5. Attach shock cords, parachutes, and sub-assemblies in correct order. 6. Fully assembly payload section, insert in vehicle. 7. Prepare vehicle black powder charges. 8. Insert altimeters in electronics bay, connect wires to ejection points. 9. Assemble rocket body. 10. Assemble and insert hybrid motor (empty). 11. Secure the motor.
13
Pre-Launch Checklist 1. Ensure integrity of rocket (check for any cracks, parts being loose, etc.). 2. Mount rocket on launch guide. 3. Activate recovery electronics (altimeter 1, altimeter2, RDAS). 4. Check GPS signal reception. 5. Connect ignition systems. 6. Ensure that ground-side teams are ready for launch. 7. Fill hybrid motor with N2O. 8. Check continuity 9. Arm ignition systems. 10. Check sky for aircraft. 11. Countdown. 12. Launch. Disarming Procedure (in Case of Ignition Failure) 1. Wait 1 minute, as designated by HPR safety code. 2. Disarm ignition systems. 3. Release fuel from rocket via remote. 4. Attempt launch another time (see pre-launch checklist). Post-Launch Checklist (Assuming Successful Recovery) 1. Download all data to ground computers. 2. Check and record calibration of all electronics. 3. Store data to hard copy.
F. Safety and Experimental Risk
Problem Result Mitigation Faulty Design- Improper
Integration of Engine Failure to ignite; possible
loss of fuel. Hybrid engine system will
be integrated into the rocket under proper supervision
and used in the accordance with manufacturers
conditions. Faulty Design- Structural
Failure
Rocket begins to disintegrate during flight
(fins rip off, nosecone tilts etc).
Rocket will be constructed under professional
supervision using sturdy materials such as fiberglass
and epoxy. Faulty Design- Unstable
Rocket
Rocket will not reach intended altitude; pictures
may not be of optimal quality.
Rocket design will be extensively reviewed
through RockSim program to ensure stability. Scale model will be built and
flown to test design. Launch Failure-
Catastrophic Failure of Propellant
Loss of rocket, payload and data.
Engines will be thoroughly researched and handled
under professional
14
supervision.
Launch Failure- Ignition/ Engine Malfunction
Inactivity of rocket on launch pad.
Proper launch procedure will be followed. If the motors do not ignite, a
checklist disarming procedure will be followed.
Launch Failure- Over-pressurization of Tanks
Explosion of engine during fueling or ignition.
Engines will be fueled under professional supervision.
Launch Failure- Launch Rod Malfunction
Rocket will be launched at incorrect angle; intended
altitude will (probably) not be reached.
Launch rod will be leveled, lubricated and secured to a
stable surface.
Recovery Failure- Parachutes
Fail to Deploy or Become Tangled
Ballistic fall of rocket and/or payload.
Parachutes will be prepared and installed shortly before launch. Deployment charges
will be inspected before launch.
Payload Integration- Structural Failure
Payload integration setup will fall apart; cameras will
not be able to capture photos and may receive possible
damage.
Payload will be carefully secured into a rocket using two metal rods to stabilize
payload as well as allow for easy removal and insertion
of payload into rocket.
Recovery Failure- Rocket Does Not Separate at
Correct Joint
Parachutes and payload do not deploy properly.
Separation joints will be properly prepared and
inspected before launch. All other joints will be fastened
securely.
Recovery Failure- Payload Ejection Charge Does Not
Ignite.
Payload and its parachute do not deploy.
Two different altimeters will fire the ejecting charge.
Recovery Failure- Shock Cord
Ripping/Tanglement
Separation of rocket body/payload from
parachute, ballistic descent.
The shock cord will be made of tubular nylon and
rated at or above 2,000 pounds. They will be tested during the ejection charge
tests. The parachutes will be in parachute bags as to
avoid entanglement with shock cords.
15
Transportation- Rocket is Damaged During
Transportation
Possible aberrations in launch, flight and recovery.
Rocket will be properly packaged for transportation and inspected carefully prior
to launch.
2. Environmental Concerns
The hybrid engine is one of the most environmentally safe engines on the market, due to it being made of rubber/plastic and N2O, both commonly accepted as very safe.
PVC has been rated by the Vandenberg range as a 0 lb of TNT equivalent. It has to be vaporized in the presence of an atomized oxidizer with a high temperature igniter in order for it to burn.
N2O is benign, non-toxic, storable, and self-pressurizing to 700psi at room temperature. A hybrid engine is extremely clean because the major combustion products are carbon
dioxide and water. The exhaust causes less environmental damage then the malignant mixtures produced by traditional rocket engines.
II) Payload Criteria
A. Selection, Design, and Verification of Payload Experiment
1. Payload Systems/Subsystems Camera System
The two cameras will be mounted in parallel alignment to maximize the portion of the two images that will overlap and to minimize the percent of each picture that will not overlap between the IR and visual light images. The two cameras will be held in parallel lock just inside the bottom section of the payload body. The cameras will also be supported and cushioned by semi-dense foam. The cameras will be protected from the necessary blast of the ejection charge (in the upper part of the payload) by a solid wood bulkhead coated with epoxy. The lenses of the cameras will be protected from below by a hard, clear plastic covering in addition to several layers of Nomex cloth beneath the plexiglass payload bay bottom (it is not expected that the hot ejection gasses and black powder particles will reach the plexiglass (we hope they will be adsorbed and cooled by the Nomex cloth).
Camera Selection Rationale
• No IR Blocking Filter (modified to remove) • Maximum shutter speed at least 1/1000s • 4MP or better resolution • Within SLI budget parameters • Feasible size for 12 inch payload section • Compatible with high capacity memory cards • ISO range of 200-400-800-1600 • Capable of repeated exposures • Sufficient battery life for flight • Filter rings on lense (for IR filter) • RAW image format compatible
16
Payload Electronics The payload electronics and data retention systems will be stored above the cameras
(separated by the aforementioned bulkhead). The upper section of the payload will be divided between electronics and the payload parachute (including the payload parachute ejection charge). The divider be constructed of reinforced (and generously epoxied) rocket wood; this part will have to be able to withstand the force/heat of the ejection charge.
Figure 7. Payload Configuration
2. Performance Characteristics
1. Rocket must successfully launch off launch pad at directed angle. 2. The altitude reached must be approximately one mile. 3. The Recovery systems must deploy at apogee. 4. The two cameras must capture synchronized photographs at specified times from
17
apogee to landing. These photos must overlap the same photo taken at the same altitude. 5. The payload must return to ground undamaged, as to allow safe recovery of data. 6. The pictures from the cameras must be successfully transferred to a computer for further processing.
3. Verification Plan
• The camera with the Hoya R-72 IR filter will be tested with the filter on to ensure that sufficiently detailed photographs can be obtained.
• The payload module, once constructed, will be dropped from a test height of 50 feet with the parachute to ensure that the module descends vertically.
• For other specific tests, see verification matrix in the vehicle part.
4. Preliminary Integration Plan
The payload module will be designed to be attached to the payload parachute. The payload will be situated so that the cameras are facing downward during ignition and launch. Once the payload has separated from the booster the payload will be allowed to fall vertically with the cameras still facing the down and the parachute attached to the top. The payload bay will be self-contained (including the payload deployment/recovery/tracking subsystems) and will be mounted on the top of the booster (using a simple tube coupling). See Figure 7 for further details. 5. Precision of Instrumentation and Repeatability of Measurement
The two cameras are rated to a 6.1 megapixel resolution. The Nikon ML-L3 Infrared Remote has a range of 5 meters and will be used to repeatedly trigger both cameras in the very same moment (camera synchronization). It will be connected to a specialized control circuit to allow for repeat automatic firing. The Hoya R-72 filter is rated from 690 to 710 nm. The images recorded by the cameras will be reproducible at other times baring extreme weather.
B. Payload Concept Features and Definition
1. Creativity and Originality
Our payload is creative and original because we are using the altitude gained by a high-power model rocket in a novel way. To use a rocket as a survey tool for forest health is certainly a rather under-researched if not completely unused method and our solution for determining this (using IR photography) is a effective and creative way of completing this problem. 2. Uniqueness and Significance
Our payload design is unique because it is a new and interesting use for the altitude gained by the rocket-- one that, so far as we know, has not been used extensively in the past. Our experiment has real world applications. The method we use in our experiment
18
could be used in the future to determine the general health of forests: a useful tool for assessing environmental impacts of various industries. 3. Level of Challenge Our payload experiment and design provides a suitable level of challenge because of the many things that need to be controlled inside the rocket for our experiment to proceed properly.
• Cameras must be safe and secure inside of payload. • There must be a clean and clear view from the camera's lenses through to the
image below, and this must not compromise the safety of the payload. • The payload must not become tangled with the other sections of the rocket, nor
can the other sections appear too largely in the photographs taken by the payload. • The rocket is fairly large (M-class) • The propulsion is a hybrid motor • Complex electronics will be used in the payload (GPS, telemetry, altimeters,
accelerometer, synchronized digital cameras) C. Science Value
1. Science Payload Objectives Our payload will have three different experiments designed to assist in analyzing forest vegetation. The two Nikon D-50 cameras will be mounted with the lenses facing the transparent bottom of the payload module. One camera will be equipped with a Hoya R-72 filter which is designed to block out all wavelengths of light below 720nm. The other camera will remain unmodified. The two cameras will be mounted in parallel position so that they record as near to the same image as possible. Both cameras will be triggered by the same circuit to ensure the perfect synchronization. The photographs will then be analyzed after the flight to identify:
a) Overall Forest Health: healthy foliage reflects significant portion of incoming IR light while the sick foliage does not reflect it almost at all. Thus, the sick foliage (while possibly still green in color and difficult to recognize by naked eye) will show as distinctive dark areas on infrared photographs. Drawing on Figure 8 demonstrates this phenomenon.
b) Forest Species Concentrations: different plant species reflect different amount of IR light. Most of the foliage is green in color and thus different species of trees can be difficult to distinguish on a standard color aerial photograph. However, because of the significant differences in IR reflectivity, different types of foliage show as distinctive shades of gray color on infrared photographs. See Figure 9.
c) The Ideal Altitude For Such Photography: pictures taken from the high altitude will cover large area but may not have enough detail for the desired purposes. On the other hand, low altitude pictures will carry a lot of detail but may not cover a sufficient area. We want to compare the pictures taken at different altitudes to find the optimal compromise between level detail and the area covered.
19
Figure 8. Different type of foliage reflects different amount of IR light and thus each type of foliage appears as a distinctive shade of gray on an IR photograph (as opposed to visually similar shades of green on a standard color picture). Sick anddead foliage appears as a very dark shade of gray.
Figure 9. A real world example of IR photography. The picture on the left is a standard color photograph of a landscape. The trees on the far shore all appear to be of the same type (or the type cannot be indetified). In contrast, the IR picture on the right hand side shows that the tree on the far left far are definitely of a different type than the trees on the far right. 2. Payload Success Criteria Experimental Risks
Not all risks are to specific to people's health. There is also a risk of the experiment failing due to unsynchronized camera photographs. It is very important that the cameras
20
take similar pictures so that they can be analyzed against each other. Thus, the cameras will be tested against each other multiple times before launch in conditions as similar to those it will be facing during the experiment as possible.
3. Experimental Logic, Approach, and Method of Investigation
The payload module contains one modified Single Lens Reflection (SLR) camera with Infrared filter taking IR pictures and a regular SLR camera taking Visible Light (VL) images. The aerial images obtained by the payload cameras will give sufficient information about the health of the forest and concentration of certain species according to the different infrared reflection rates in the pictures. The IR reflection rates are usually determined by the cellular structure and the amount of healthy chloroplasts in the vegetation (cf. Figure 8, 9).
Thus through comparing contrasts in the IR photos, we might be able to identify zones of unhealthy vegetation which we fail to see in the regular VL. At the same time, comparing the frequencies/color levels in both IR and VL images will create a chance to discover the concentration of one species in a certain region images (cf. Figure 8).
In order to accomplish this, we need to set up a basic IR scale for diversities of plantation. The major goal for the IR scale is to separate one species from the others. If the weather condition allows the camera to record images with ideal resolutions, the colors in both IR and VL photos should not change significantly despite the distance since there is not enough particles in the air blocking or refracting IR and VL light. With this fact in hand, we can first set up standard frequency levels by taking IR and VL images on plantation from ground level. Though the pictures are taken from a relatively short distance, they will still effectively fulfill their job as scales. After comparing with scale levels, we will be able to determine which region is suffering plantation disease or overwhelmed by one kind of species which might be invasive to the local ecological balance. 4. Measurement, Variables, and Controls
The dual Nikon D-50 SLR cameras will capture synchronized photographs of the ground during descent. The cameras will both be manually focused to infinity for the flight. This will allow for a continuous stream of in-focus photographs as the range at which the photographs will be taken will be distant enough to be in-focus with an infinity setting. To allow for comparison between photographs taken in different conditions, a Light Emitting Diode (LED) will be mounted in front of the cameras. This LED will allow for a continuous, consistent base point from which the overall darkness of the image can be adjusted using Microsoft Photoshop. This will allow for more consistent analysis of images gathered. Prior to the final flight, images of the tree species deemed most likely to exist in the area around the launch site. These photographs will then be compared to one another to determine what the average color shade captured for each tree species in IR is. This will be used to determine the concentrations of different species. 5. Relevance of Expected Data and Accuracy/Error Analysis The study of forest health based upon tree health and species concentration along with an analysis of the ideal altitude for air based photography will greatly enhance the ability of environmentalists to determine which forest areas are under stress. This will allow for a more economical distribution of the limited resources available to assist in rehabilitating stressed forest locals.
21
6. Experiment Process Procedures
Before the final flight, several tests will be undertaken in order to ensure that quality data is gathered during the flight. These tests include, but are not limited to, camera synchronization tests, scale model flight tests, and vehicle deployment tests as described previously.
D. Payload Risk and Safety
1. Preliminary Payload Risk Assessment and Mitigations/Risk Levels
There are several hazards that need to be addressed with a great care. One such hazard would be a lack of deployment of the payload parachute. This would create an object weighing approximately 15 pounds falling at a high velocity. There is also the possibility of the payload retention system failing, ejecting the payload from the encapsulating payload bay. There is the possibility of electric shock due to the use of electronic components. Also, with the use of batteries, there is also a possibility of hazardous chemical leakage if battery casings were to rupture.
The falling object hazards can easily be mitigated by the implementation of redundant systems. The payload parachute will have 3 separate ejection charges, two of which will be triggered upon reaching apogee by the payload altimeter. The third will be triggered by altimeter in the electronics bay, as a backup if other payload electronics suffer a malfunction.
To prevent payload separation (as in actual separation of components), an adequate retention system will be used. See payload integration for more information.
The risk of the payload electronics shocking personnel is negligible because the batteries used by our electronics do not hold enough charge to cause any serious injury. Nevertheless, all electrified and chemical components will be handled with the utmost in competence and care. 2. Environmental Concerns
The payload will have little or no environmental impact due to the environmentally sound components. The cameras and complete payload section will be recovered after every launch. There will be minimal littering due to careful trash collection after every launch.
III) Outreach and Project Plans
A. Outreach/Project Plans
1. Community Support:
Considerable progress has been made in the soliciting of community support and the realization of outreach projects. Our media relations representative was able to contact the local school district and submit a statement to be published in the school district staff bulletin announcing the many accomplishments of Madison West Rocket Club. We have also contacted the local affiliate of ABC, which plans on producing a series of news segments on the subject of our team and its progress through the SLI project. A Grant Application has been completed and submitted to the Rotary Foundation for the purpose of soliciting support.
22
2. Budget for Proposed Activities Launch System
Hypertek GSE $583 Hypertek M Fill Stem $137 Hypertek/Contrail Adapter Kit TBD Contrail 75mm 3200cc Engine Set $550.00 Shipping $50
On board Electronics
Perfect Flight altimeters (2) $210 Woven copper wire for wiring $20 Batteries $40
Vehicle Construction
Phenolic tubing/Transitions $300 G10 Fins $90 Misc. consumables $100 West Systems epoxy $0* Fiberglass cloth $200* Carbon fiber $0* Nosecone $0**
Scale Model Construction
Supplies $0** Tracking System
Adept Transmitter $0** Adept Antenna $0** Active Antenna $60 High Volume beepers $0**
Payload Supplies
Nikon ML-L3 IR Remote Control $20 Nikon D50 Camera (2) $0**** 1GB Secure Digital (SD) Memory Card (2) $0**** Hoya R72 Filter (1) $0** RDAS System $250 Telemetry transmitter $170
Total $2,780 *: school supplied **: already obtained ***: one/some already obtained ****Donated/Lent Should be impossible to follow this budget because of a withdrawal of sponsorship or other unexpected hardships, we are prepared to procure funding on our own by means of selling candy at our school, raking leaves or doing other fund raising activities.
23
3. Web Presence
Our web presence is still at early stages of development. We have a domain and name chosen and have begun work on templates for our end website design. As far as content goes, it will be added as it becomes available, at such early stages in the experiment there is not that much content which would be necessary to post. Our actual presence will most likely go live January 15th with all applicable content.
IV) Summary
The vehicle was designed to carry a payload of two Nikon D50 cameras to the altitude of one mile and provide them with the maximum reasonable data. The vehicle consists of two sections, he payload section and the body section.
The body section will be made out of 4inch fiberglass/carbon fiber reinforced tubing, and will most likely house a Contrail Hybrid engine in the L/M range. It will loft the vehicle up to the specified altitude and will then employ dual recovery procedures to return back to earth.
The payload section will consist of an approximately 9 inch tube, most likely custom made, and will house the payload. Fiberglass transitions will couple the 4inch and 9 inch tubes. The payload section will be recovered using a approximately 70 inch nylon parachute, the optimum descent rate being 15feet per second.
The vehicle, using the optimum engine (Contrail M711) will create an acceleration of less than 6 G’s, a survivable acceleration for the payload and slow enough for the GPS not to loose the signal during boost. The Ground Support Equipment will be Hypertek, adapted to fire Contrail engines.
All the payload equipment onboard the rocket is specifically designed to fulfill its function of acquiring IR aerial photography. The analysis of forest vegetation will be executed through the utilization of the payload. Namely, this objective will be achieved by the major component of the payload, two Nikon D-50 cameras. Their lenses will face toward the transparent bottom of the rocket. One camera will be equipped with a Hoya R-72 filter, which is designed to block out all wavelengths of light below 720nm. The other one will remain unmodified. Through comparing the IR photos and regular VL photos, we will be able to identify the overall health of the local forest and the concentration of certain plant species.
The two cameras will be mounted in a parallel position so that they can focus on the same area, to the largest possible extent. In order to gurantee the reliability of the obtained images, both cameras will be synchronized and triggered by the same electronic circuit. With 1GB memory onboard, the two cameras can record a sufficient amount of photographs through the entire flight. Thus we can determine the ideal altitude, which ensures that the onboard cameras will be capable of taking pictures with desirable resolution but simultaneously covering enough ground area. All the payload equipment will be connected to the Rocket Data-Acquisition System (RDAS), which fulfills the essential role as the rocket’s flight computer. The RDAS is located directly above the cameras and is connected to them via cable.
At the same time, we will conjoin the Global Positioning System (GPS) and telemetry transmitter with the RDAS. During each flight, the GPS records precise satellite coordinates for the area photographed by the cameras. The coordinates will then be sent to the ground staff by the telemetry transmitter. Hence we can easily pinpoint the position of the payload module and later retrieve the rocket successfully. Moreover, the GPS data will improve the image analysis
24
to a considerable amount. The body will located and recovered easily because of it’s dual deployment recovery that
allows for a landing close to the launch point. An additional 140dB screamer will aid the booster location.
The payload is expected to drift far away, as it deploys a large parachute in the apogee. The location of the payload will be periodically reported by an onboard GPS system broadcasting via 900Mhz telemetry transmitter. In addition to the GPS, an AM radio beacon (434MHz) and two 140dB screamers will be in the payload bay.
