2012CoDR

RocketSat 8 Preliminary Design

ReviewUniversity of Colorado

Boulder10/26/11

2012CoDR

Nomenclature

• RODEO – Roll Out De-Orbiting Device• VACA - Validation Assembly of

Communication Antennae• DONDE – Attitude Determination System

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2012CoDR

Mission Statement

• To design a system that deploys the Roll Out De-Orbiting Device (RODEO) developed by Composite Technology Development (CTD). This shall provide a possible means to de-orbit future small satellites.

• To eject VACA for the examination of communication capabilities between two differently located antennas.

• To validate the Attitude Determination System (ADS) developed for RockSatC.

2012CoDR

Theory and Background

• The aerospace market has been continually moving towards small satellites

• Approximately 23 small satellites (10kg-500kg) are launched every year by the United States alone

• The continual growth of small satellites in space increases the likelihood of collisions exponentially

• The rise in number of satellites in orbit has led to an increasing need for a cost effective and lightweight means to de-orbit small satellites.

2012CoDR

Theory and Background Continued

• Communication distance and capability is often increased by having line of sight between a transmitter and receiver.

• DONDE was a small, low-cost system designed by RocketSat VII to determine the orientation of the payload through a CMOS optical sensor and other various devices.

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2012CoDR

Mission Overview: Concept of Operations

Launch

Begin Telemetry

Splash Down

Apogee

Altitude: ≈160 kmDeploy RODEO

Deploy VACA

End of Orion Burn

Collect Data from VACA

Chute Deploys

Power off all systems

Pre-Launch

-G switch triggered

-All systems on

-Begin data collection

-Initialize Cameras

2012CoDR

Mission overview: Expected Results

• We expect that the RODEO system be extended whilst attached to the rocket

• We expect to capture images and video of the extended RODEO system

• We expect the VACA to be deployed from the main plate• We expect to measure signal quality between the

antennae • We expect the signal quality of the antenna on the

RODEO to be stronger than the one on the main plate• We expect to validate the attitude determined by

DONDE

2012CoDR

Main System Overview

8

2012CoDR

Main System Functions

• Houses other subsystems• Deploys RODEO• Validates RODEO • Ejects VACA• Processes Communication with VACA

2012CoDR

RequirementsProject Requirements

O1 Shall deploy the RODEO device Mission Objective

O2 Shall validate the deployment of the RODEO device Mission Objective

O3 Shall eject the VACA Device Mission Objective

O4 Shall validate that deployed antenna performs better than static antenna located on the main plate

Mission Objective

O5 Shall comply with all RockSat-X requirements Mission Objective

System Requirements

S1 Shall deploy the RODEO with an electro-mechanical release mechanism O1

S2 Shall capture image of deployed RODEO sail O2

S3 Shall eject VACA from the main plate through the use of deployment mechanism O3S4 Shall receive communications signals from VACA with both antennas and

compare signal strengthO4

S5 Shall meet all structural requirements as defined in the RockSat-X user guide O5S6 Shall meet all electrical requirements as defined in the RockSat-X user guide O5

2012CoDR

Requirements (cont.)

System Level 2 Requirements

S1.1 Shall deploy RODEO using an electromechanical actuator S1

S2.1 Shall deploy in a time sufficient for the needs of the mission S2

S2.1 Shall capture an images of RODEO while it is in the field of view of the camera S2

S2.2 Shall set a image frame rate and quality that confirms RODEO deployment S2

S2.3 Shall store the image data S2

S3.1 Shall detach from rocket at the determined time S3

S3.2 Shall detach from rocket without damaging equipment S3

S3.3 Shall generate acceleration upon detachment S3

S4.1 Shall communicate with antenna at end of RODEO and S4

S6.1 Shall have sufficient power to perform all required operations S6

2012CoDR

Structures Overview

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2012CoDR

BC

A

Basic Design Overview

13

Single middle plate design: the RODEO, the cube sat (VACA) and its ejection system are mounted on the bottom of the middle plate. The ADS and electronic boards will be on top of the middle plate incased in an air tight shell with a view port for the camera.

Front ViewA- air tight shellB- Cube Sat & ejection system

C- RODEOD- Camera

Bottom ViewB- Cube Sat & ejection system

C- RODEOD- Cameras

ED

C

B

Top View (without airtight shell)D- ADSE- electronics board

DD

D

2012CoDR

Design

2012CoDR

Structural Requirements

Structures Subsystem Requirements  

D1 The structure shall be made of materials that can withstand temperatures of re-entry S5

D2 The structure shall fit into the 12 inch diameter, 11 inch tall volume S5

D3The structure shall be able to withstand at least 25 g's sustained and impulses of up to 50 g’s and remain intact S5

D4 The entire RockSat X payload shall weigh 30±1 lb (13.607 kg) S5

D5The payload shall be designed to have a center of gravity (CG) that lies within a 1x1 inch envelope on the x-y plane of the structure. S5

D6The payload shall be designed such that it integrates on top and on bottom of a middle plate mounting system inside of the rocket. S5

D7 The structure shall insure that all electrical connections are secure throughout the entire flight. S1.1

D8 The structure shall maintain the position of each of the sensors during flight S1.1

D9 The structure and sensors shall not impact the canister during the vibrations of flight S1.1

D10 The structure shall allow for the correct degree of view for the sun sensor S1.1

2012CoDR

Structural Requirements

Structures Subsystem Requirements  

D11The structure shall integrate an ejection system that will eject the VACA Cube-Sat device given to us by Composite Technology Development. S5

D12 The ejection system shall not pre-maturely eject VACA or malfunction due to the forces of launch S5

D13The structure will mimic the RockSat C program by having an encasing over the attitude determination system S5

D14 The encasing over the ADS will be airtight and should keep all data intact through splashdown S5

2012CoDR

Trade Study for Stack Mounting

 MaterialStructural Integrity

(.50)

Chances of Image Captured

(.30)

Cost (.10)

Machine-ability (.05)

Flight Heritage (.05) Total

Middle Mount 8 7 5 8 10 7.5

Bottom Mount 6 7 5 8 9 6.45

2012CoDR

Stack Mounting• It has been decided to use the middle mount offered by

Wallops.• A middle mount will separate the two systems into airtight

and open to space• Open air hardware will be interfaced to electronics boards

via a sealed electrical feedthrough• The mount will also make sure the deployable is not in the

field of view of the camera.• The top and bottom mounts either connect to the top or

bottom, not both.– This is due to other projects being on either side of our

stack

2012CoDR

Preliminary Mass Budget

Mass Estimation Unit Weight (specified) Mass (lbs.)

Computer Boards na 1

Sensors 0.02425 lbs. 0.02425 lb

Sensor Enclosure .347 lb .347 lb

Middle Aluminum Plate .098 lb/in3 2.77088 lb

Makrolon Plate .043 lb/in3 .6838851 lb

ADS Canister .098 lb/in3 3.70413 lb

RODEO na ~ .25 lb

VACA na ~ 1 lb

Standoffs, other hardware na .5 lbs

Total na ~ 10.2801 lb

2012CoDR

Preliminary Testing

• Thermal analysis on metal components will be done to ensure hardware is safe upon reentry.

• SolidWorks Analysis– Our SolidWorks model will undergo structural testing in the SolidWorks

program.– SimulationXpress analysis will be used for load testing as well as

testing the torque of the design– This will also be used to determine the precise locations of sensors for

the best field of view. – Stress analysis in SolidWorks will show how forces on our model will be

distributed.

2012CoDR

Risk Analysis for Structural Failiures

5 Structure collapses

 Failure to photograph deployment

   

4 Standoffs failEjection system failure 

   

Risk 3 Plates crack

Sensor becomes detached from plate

Sail collapses after

deployment   

2  Sensors become

misaligned

1  

  1 2 3 4 5

Probability

2012CoDR

Current Progress and Goals

Current Progress• Current design in SolidWorks of the main plate.• Research and decide type of ejection system (spring).Goals• Complete Solidworks stress analysis on each of our plate materials• Complete torque testing on the stack• Complete torque spec for materials to be used• Identify points of failure for mechanical model• Complete thermal analysis at reentry and electronics protection• Make more detailed designs in relation to updated system requirements• Researching materials to be implemented for stack• Assessing materials and parts to be ordered

2012CoDR

Electrical System Overview

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2012CoDR

Functions

• Deploy RODEO using timed event• Image RODEO with HD and low resolution

cameras• Communicate with VACA using RF• Process images and data• Store images, and data in on-board memory• Send data and low resolution images through

telemetry lines

2012CoDR

RODEO Electrical System

MCU

RF chip

Antenna 1

RODEO release Antenna 2

Power Converters

Memory

HD Camera

Lo-Res Camera

FPGA

from RockSatpower

totelem

toCubeSat

RFComm

Imaging

2012CoDR

Main System Power

• Power for the main plate shall be delivered by 28 V lines from the rocket

• Total power consumption for the mission shall not exceed the limit of 1 A/hr

• 28 Volt power shall be reduced to 9 Volt power for distribution to subsystems

• Filtering techniques shall be employed to reduce noise on power lines for reduction of errors in signal transmission

2012CoDR

Power Distribution Diagram

Buck Converter

ADS Main System MCU COMM

RODEO

28V

Linear Regulators

9V

2012CoDR

Main Power Requirements

Subsystem Voltage Current PowerMain MCU 3.3 V 18 mA .0594 W

ADS 9V .55 A 5 W

RODEO <9V <50 mA .45W

VACA n/a n/a Self Powered

COMM 3.3 V 215 mA .7095 W

Total Power Required from 28V lines ≈ 6.22 W

2012CoDR

DC to DC Conversion

• 28V power will be reduced to 9V power through the use of switched mode converter for decreased power losses

• DC conversion for microcontroller and other electronics components will be performed using linear regulators

Type RF Noise (20%)

Cost(20%)

Reliability(20%)

integration factor(10%)

power capabilitie

s(10%)

electrical noise(10%)

efficiency(10%)

Weighted Average

Buck 4 3 5 5 5 4 4 4.2

Boost 2 3 5 5 5 3 3 3.6

Buck-Boost 2 3 5 5 5 2 3 3.5

Split-pi 1 1 5 5 5 4 5 3.3

2012CoDR

Electrical Component Selection

30

• We will be selecting components to use in the electrical system based on performance requirements and ease of interface with other components.

• Primary hardware considerations:– Low power consumption– Accommodate interface protocols employed– Withstand launch, reentry conditions

2012CoDR

Electrical Component Selection

Microcontroller• Requirements:

– Interface with RF Comm System– Process data (sent via RF Comm)– Store data to memory– Upload data to telemetry lines

2012CoDR

Electrical Component Selection

• We chose the XMEGA256A3 microprocessor.– Same one used on last year’s system: driver software

already written, tested, and proven– Capable of interfacing with XBEE RF protocol

2012CoDR

Electrical Component Selection

Memory• Requirements:

– Non-volatile storage– Sufficiently fast write speed– Easily interfaced to microcontroller– Heat, vibrations resistent

2012CoDR

Electrical Component Selection

• We decided to use digital (SD) cards– Cheap, compact, reliable data storage– Non-volatile– Many available software libraries– Light-weight and durable

2012CoDR

Electrical Component Selection

Cameras:• Provide visual confirmation of RODEO deploy• One low-resolution camera

– Images processed on-board, sent to telemetry lines– Same camera as in VACA

• One high-resolution camera– Data saved straight to internal memory card– Hardware implementation: GoPro HD Hero2

Outdoor Edition

2012CoDR

Electrical Component Selection

HD Video Camera Resolution(Pixels)   30%

Frames per Second (fps) 25%

Angle of View   20%

Power   15%

Cost    10%

Weighted Average

1. ContourROAM 5 4 3 5 4 4.251. Go Pro HD Hero2

Outdoor Edition5 5 5 5 5 5

1. Oregon Scientific ATC9K

5 5 4 5 3 4.6

1. Drift HD170 5 5 3 5 2 4.3

HD Camera Selection:

2012CoDR

System Software Overview

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2012CoDR

Software Overview

• Software for the main microcontroller will control all other non-deployable components of the main system

• Software will run efficiently and at a speed that will record and store all data

• Software will be programed as a state machine• Software will be redundant in order to prevent failures

moving from state to state• Redundancies include watchdog timers and secondary

signaling hardware to confirm timed events

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2012CoDR

Main Plate State Diagram

Off-Check State

Pre-Launch-Power Main MCU-Signal HD Camera-Signal ADS MCU-Power Low Res Camera-Start transmitting data through telem lines

Launch-Start Watchdog Timer

Deploy-Initialize mechatronics to deploy VACA

Apogee-Signal VACA-Deploy RODEO

Power Failure

User Power

Timed Event/G Switch

Timed Event/Watchdog Timer

Watchdog Time/Timed Event

2012CoDR

Language Trade Study

Language Speed(30%)

Efficiency(30%)

Versatility(20%)

Ease of Use

(10%)

Existing Code (10%)

Weighted Total

C 5 5 5 4 5 4.9

C++ 4 4 5 4 0 3.8

Assembly 4 4 2 1 0 2.9

2012CoDR

Software Concerns

• How to design the code for power failure survival • How to check the health system of the payload throughout

mission• How to mange component level failures• How to make code more robust and redundant • How to best integrate software functionality with hardware

41

2012CoDR

Subsystem A: RODEO

42

Courtesy of CTD

2012CoDR

Subsystem: RODEO

• RODEO is a drag inducing deployable boom developed by CTD for the deorbit of small satellites

• System shall electromechanically deploy RODEO device and validate deployment with deployment sensors and photo evidence

• HD video of the RODEO device will be recorded • A low resolution camera will capture images of the RODEO device and

transmit data to ground via the telemetry lines• The RODEO boom shall additionally house an antenna to increase

communication quality with VACA

2012CoDR

Structures: RODEO

• Rodeo shall be securely held in place on the bottom of the middle mount plate

• Rodeo will be mounted at the edge of the keep out zone so that sail deploys outside of rocket

2012CoDR

Structures: RODEO

Undeployed RODEOTwo camera angles-one HD camera-one low resolution camera

Deployed RODEO-three foot sail when fully extended

2012CoDR

RODEO Release Mechanism

• The RODEO is stored under potential within an aluminum structure

• The RODEO is contained with hinged door• The release of the hinged door produces an

extension of the rodeo sail in less than 1 second

2012CoDR

RODEO Release Mechanism Continued• The release of the RODEO containment door

will be executed using an electro-mechanical device

• The electro-mechanical device will be have sufficient holding torque for launch survival

• Testing will be done to ensure survivability and properly timed release of RODEO

2012CoDR

Rodeo Release Mechanism Continued

Possible Release Mechanisms• Frangibolt• Linear Actuator• Burn Wire

Release Mechanism Characteristics• Launch survivability• Size and weight constraints• Ease of integration with RODEO• Ease of electrical interfacing• Cost

Courtesy of WikipediaCourtesy of Tiniaerospace

2012CoDR

RODEO Electrical Interface

49

• A timer-controller power line will switch to high voltage at the time that we will want the RODEO to deploy.

• The signal will trigger power to be sent to the release latch

2012CoDR

VACA

50

2012CoDR

Subsystem: VACA

• Ejected from main system via deployment mechanism

• Houses antenna that communicates with antenna on the main plate and at end of RODEO

• Serves as basis upon which to test locations effect on signal strength

• Sends collected data to the main system to be stored and analyzed later

2012CoDR

Structures: VACA

• The structure shall deploy the Cube-Sat (VACA) out of the rocket at apogee.

• The deployment system thus far will be composed of springs and tracks that will push out VACA squarely to the structure.

• The deployment shall not interfere with any other operations in progress.

2012CoDR

Trade Study for VACA Ejection System

 MaterialOdds of Success

(.50)

Required Hardware

(.30)

Cost (.10)

Machine-ability (.05)

Flight Heritage (.05) Total

Springs 8 8 7 8 10 8

Compressed Air 2 6 6 8 2 3.9

Motor Driven 6 6 4 8 9 6.05

2012CoDR

Ejection System

• From the trade study a spring powered is the most logical option for powering the system.

• Compressed air cannot be easily flown with pressure differentials and safety in mind.

• The spring will need to be very well protected to avoid an accidental ejection therefore our release mechanism will provide sufficient holding stability.

2012CoDR

55

We are looking into options for the deployable mechanism that include a loaded spring and electronic releasing switch that will be triggered at the ideal time of release, and will be secure throughout the launch and flight.

- We are currently looking into software developed by Sierra Nevada that is meant to eject objects from rockets into a space environment. The one pictured is called a Hold Down Release Mechanism, and is characterized by low shock and reusability.

Other options include a frangibolt system and a linear actuator.

2012CoDR

Vaca Power Requirements

Component Voltage Current PowerXbee Transceiver 3.3 V 215 mA .7095 W

Sensors 3.3 V < 1 mA < 1 mW

Xmega Microcontroller

3.3 V 18 mA 54 mW

Power Source Options• Rechargeable Batteries• Nonrechargeable Batteries

• Alkaline Long Life• Nickel Cadmium• Nickel Metal Hydride

Power Conversion Options• Linear Regulator• Switch Mode Converters

2012CoDR

Vaca Power

• The VACA structure shall be powered separately from the main structure using 9 volt long life alkaline batteries

• Hardware voltage requirements will be met using linear regulators to reduce battery voltage

• Batteries shall provide sufficient power for all operational tasks of the VACA structure while meeting weight constraints

2012CoDR

CubeSat Electrical Subsystem

MCU

Power

Memory

RF Chip

AntennatoRODEO

Sensors

Temp

Mag

2012CoDR

VACA Hardware

• Same microcontroller and memory as main board: easiest RF interface with RODEO subsystem

• Temperature sensor and accelerometer provide data to be sent over RF Comm

2012CoDR

VACA State Diagram

OFF/PRE-APOGEE

VACA Operating

Signal Initia

tion

-Turn on VACA-Initialize sensors-Initialize comm -Begin transmitting all data

Power failure

2012CoDR

Subsystem: Communications

• Consists of antennae in BRONCO, on RODEO boom, and in VACA

• Measuring signal strength of these communications part of mission

2012CoDR

Communication

Communication between main payload and CUBESAT involves :

• Two antennas on the RODEO (one each on the base and tip)

• A transmitter on VACA

• VACA shall transmit data received from the sensors to the main payload.

• Data will be received through both the antennas on the main payload and compared to measure the quality of reception .

• All the received data will then be stored onboard and if possible sent through telemetry lines to the ground station.

2012CoDR

RF Communication Layout

RF Chip

AntennaRF chip

Antenna 1

Antenna 2

to Power to Power

to MCU

to MCU

CubeSatRODEO

2012CoDR

XBEE Overview

• Xbee is a low-cost, low-power over-the-counter radio communications system designed for easy short-range data transmission.

• It is available in various configurations to suit the user’s needs.

• It can be used for wireless point-to-point communication ranging from 30m to 24000m which should facilitate ample communication time.

• It supports data transfer rates up to 250kbps which is enough to transfer the sensor data from VACA to main payload.

2012CoDR

How Xbee works?• Xbee Modules interface with a host device like a microcontroller

through a logic-level asynchronous port.

• Through this serial port it can communicate with any logic and voltage compatible UART.

Source: XBEE Datasheet

2012CoDR

How does Xbee work?

XBee uses the IEEE 802.15.4 networking protocol:

• Clear Channel Assessment (CCA): Before transmitting it checks to see if the selected frequency is busy. • Addressing: It has both a fixed 64-bit serial number (MAC address) which may be used for addressing, or a 16-bit assignable address

• Error Checking and Acknowledgements: It uses a checksum to help ensure received data contains no errors. Acknowledgements are sent to the transmitting node to indicate proper reception.

2012CoDR

XBEE Specifications

XBEE Pro 900 U.FL Device:• 900 MHz operating frequency• 156 Kbps data rate• 6 mile range• -40 to 85 OC operational temperature• 3.3 V, 210 mA operating power

2012CoDR

Antenna Specifications

Description: This connector cable interfaces UFL RF connectors to RP-SMA antennas. It can be used to attach any standard RP-SMA 2.4GHz antenna to the DPAC 802.11 modules.Dimensions: 4" Length

Description: 2.4GHz Duck Antenna 2.2dBi with Reverse Polarized - SMA RF connector. 50 ohm impedance. Dimensions: 4" Length

2012CoDR

DONDE

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2012CoDR

Subsystem: DONDE

• Housed within BRONCO• Consists of modified ADS from last year• Employs an optical CMOS and magnetometer to

obtain two absolute vectors as well as gyroscopes to update the payloads position

2012CoDR

Structures: DONDE

• This year we are re-designing the ADS to become smaller and more efficient.

• Structurally it will be shorter and designed so that the electronics board can be mounted horizontally.

• It is also being designed so that the camera will be on a separate board standing vertically in the bracket shown

2012CoDR

Structures: ACC

• The Airtight Covering Canister is a protective incasing that will cover all of the electronics boards and the ADS

• The canister will have a viewport so that the ADS can see into the space environment, as well as a conical object that will go from the viewport to the lens on the ADS

2012CoDR

Structures: ACC

Cone which blocks all reflection from camera to viewport

Mimic of RockSat C viewport

ACC Canister

ADS

Middle Plate

New Field of View

RocketSat VII Field of View

Camera Lens

2012CoDR

Attitude Determination System

Functions• Receives data from sensors• Processes and stores data in on-board memory• Upon, payload retrieval, data will be processed to

create attitude profile for flight

2012CoDR

DONDE Electrical System Schematic

MCUXMEGA256A3

Gyroscope

MagnetometerHoneywell HMC5883L

CameraToshiba TCM 8230 MD

MemorySD card

FPGA

Power In

2012CoDR

Modifications on Previous ADS

• Use of an FPGA for the low resolution camera instead of the CPLD increases the efficiency of the ADS

• FPGAs have a better processing speed than CPLDs.

• Camera can be more fully utilized .• Reduces complexity and footprint optical

circuitry.

• Use power from wallops instead of 9V batteries.• Cheaper, no weight penalty, more reliable.

2012CoDR

DONDE Hardware

Microcontroller• Requirements:

– Collect data from magnetometer, gyroscopes.– Supply these sensors with operation power.– Format sensor data.– Save sensor data to on-board memory.

• Most probable hardware implementation: XMEGA256D3 (same as last year)

2012CoDR

A

Vector determination methods:

Sensor Vector Producedsun position absolute

magnetometer absolute

gyroscope relative

DONDE Hardware

2012CoDR

Camera:• Activated by microcontroller• Takes pictures out payload opening• Pictures sent to FPGA to be processed• Processed data saved straight to memory card

from FPGA• Same hardware as in previous version: Toshiba

TCM8230MD (A)

DONDE Hardware

2012CoDR

ADS: Risk Matrix

80

Consequence

Magnetometer Failure

Gyroscope Failure

Sun Sensor Failure

Possibility

2012CoDR

DONDE State Diagram

OFF STATE

OPERATING STATE

Receive SignalMain MCUInitialize all

Devices-CMOS Camera-Gyroscopes-MagnetometersBegin Storing all Data

Power Failure

2012CoDR

Project ManagementAndrew Broucek

82

2012CoDR

Organizational Chart

83

Andrew BroucekProject Manager

Wheeler GansSystems Lead

Nate Keyek-Franssen

Structures Lead

Emma YoungScience Lead

Andrew ThomasElectrical Lead

Ethan LongSoftware Lead

Devin MackenzieStructures

Kameron MedinaStructures

Eric LobatoScience

Aram PodolskiScience

Shreyank AmartyaElectrical

Brendan LeeElectrical

Long TatSoftware

Shawn CarrollProgram Manager

Mentor from CTDPhil Keller

Lia MatthewsAdvisor (COSGC)

2012CoDR

Schedule: First Semester

84

Task Start Date Completion Date

Preliminary Design Review - Oct 27

Software: ADS code Oct 27 Nov 15

Science/Electrical: 2 Antennae 1transmitter project Oct 27 Nov 9

Software: HD Camera & Low Res. Camera Outline Nov 15 Nov 25

Electrical: Hardware mapped out Oct 30 Nov 30

Electrical/Software: Sending images through telemetry Oct 30 Nov 30

Conceptual Design Review Nov 3 Nov 29

Software: Memory & Mechatronics Outline Nov 15 Nov 30

Software: Main MCU, VACA MCU, & COMM Outline Nov 20 Dec 5

Structures: Design completed (SolidWorks) Oct 30 Dec 5

Structures: Thermal analysis Nov 9 Dec 5

Order Hardware Dec 5 -

2012CoDR

Schedule: Second Semester

85

Task Start Date Completion Date

Electrical: 1st rev. Altium board designs & ordering Jan 1 Jan 30

Electrical: Fabrication of PCB’s (all revisions) Jan 1 Feb 15

Science: Testing Documentation Jan 1 Feb 25

Software: Testing code(all systems) Jan 1 March 9

Structures: Fabrication of structure Jan 1 March 9

Software: Flight Code March 9 April 13

VACA and COMM Integration & Testing March 9 March 16

RODEO Integration & Testing March 16 March 30

ADS Integration & Testing March 30 April 13

Full system checkout April 13 April 27

Launch Readiness Review - Jun 5

Testing and Environmental w/Wallops Jun 15 Jun 21

Launch! Jul 19 -

2012CoDR

Budget

86

Margin: 0.25 Budget:$5,000.00 Last Update:10/26/2011RocketSat 8

Item Supplier Estimated Cost Number Required Total Cost NotesStructures

Aluminum OnlineMetals $600.00 1 $600.00 Materials (nuts, bolts, etc.) mcmaster carr $200.00 1 $200.00 Misc. $100.00 1 $100.00 RODEO CTD $0.00 1 $0.00 Ejection System SNC $0.00 1 $0.00 Currently in the talks

Electrical/SoftwarePCB's Advanced Circuits $116.67 3 $350.01 3 board revisionsMicrocontrollers DigiKey $15.00 12 $180.00 Sensors (Cameras, gyros, magnetometer) DigiKey/SparkFun $200.00 1 $200.00 COMM DigiKey/ SparkFun $400.00 1 $400.00 ADCs, Regulators, etc. DigiKey $400.00 1 $400.00 Misc. $50.00 1 $50.00 HD Camera $300 1 $300.00

ScienceTesting Materials $300.00 1 $300.00 Misc. $100.00 1 $100.00

Total(no margin) $3,180.01 Total(with margin) $4,430.01

2012CoDR

Questions?

87

2012CoDR

References

88

• http://www.tiniaerospace.com/ca/caimages/1cafc12.jpg\• http://upload.wikimedia.org/wikipedia/en/thumb/c/c3/Linear_ac

tuator_photo.jpg/220px-Linear_actuator_photo.jpg