DemoSat IIColorado Space Grant Consortium

Design (EPICS) DivisionColorado School of MinesGolden Colorado 80401303-273-3592rknecht@mines.edu

Critical Design Review

April 2, 2004

CSM Mission Landing site imaging

DescentSat Video mechanism

TXSat Radio transmission mechanism

LandSat Up-right mechanism

RoverSat Rover mechanism Video mechanism

Project Project GoalsGoals

to gather visual images and pictures as the satellite approaches the landing site.

to initiate research supporting future missions to the lunar surface.

to explore the design issues and imagery necessary to select a landing site.

Project Project DemographicsDemographics

SpecificationSpecification ValueValue

ProjectProjectStudentsStudents 1515

TeamsTeams 33

SystemSystemWeightWeight 1.5kg1.5kg

CostCost $1,500.00$1,500.00

TetherTether 2.5mm2.5mm

LaunchLaunch August 7August 7

Potential SatsDescentSat

LandSatRoverSat

Landing Site Satellites

The purpose of the Landing Site Sats is to gather data and

information support the selection of a landing site on other moons or

planets.

StorageStorage Transmission

Location

Impact

Visual Images

Orientation &Mobility

Power

data

conditions

conditions

conditions

conditions

energy

General Subsystem DiagramLanding Site Sat

Subsystem Subsystem ExamplesExamples Video cameraVideo camera Radio transmissionRadio transmission Orientation Orientation

mechanismmechanism Ramp deploymentRamp deployment RoverRover Remote controllerRemote controller BrainStem controllerBrainStem controller Power supplyPower supply

Up Down Crash

TEAM U. D. C.TEAM U. D. C.

-JACOB KIRKLEYJACOB KIRKLEY-DAN ALLENDAN ALLEN

-NATHAN SKITTNATHAN SKITT-ZAC SELFZAC SELF

Satellite Satellite SubsystemsSubsystems

MOTOR & GEARINGMOTOR & GEARING

TRACK SYSTEM & CHASSISTRACK SYSTEM & CHASSIS

COMMUNICATION SYSTEMSCOMMUNICATION SYSTEMS

SATELLITE HOUSINGSATELLITE HOUSING

Subsystem Subsystem DescriptionDescription

MOTOR & GEARINGMOTOR & GEARING– Two motors will be used to drive the rovor.Two motors will be used to drive the rovor.– Each motor will be connected directly by gears to the Each motor will be connected directly by gears to the

wheels.wheels.

COST & WEIGHTCOST & WEIGHTWeight of motor - 50 – 100 grams of weight.Weight of motor - 50 – 100 grams of weight.

Cost of each motor – $50.Cost of each motor – $50.

Weight of gears (total) – 20 grams.Weight of gears (total) – 20 grams.

Cost of gears (total) – $10.Cost of gears (total) – $10.

Track System & Track System & ChassisChassis

Made from Aluminum Channel, aluminum angle, and Made from Aluminum Channel, aluminum angle, and small nuts and bolts.small nuts and bolts.

Wheels for track system made from R/C car wheels.Wheels for track system made from R/C car wheels.

Track made from rubber.Track made from rubber.

““L” shaped brackets to hold motors.L” shaped brackets to hold motors.

Tracks in a Triangle shape.Tracks in a Triangle shape.

Chassis made from Al angle open on bottom.Chassis made from Al angle open on bottom.

Cost: $30-50Cost: $30-50

Weight: Approx. 350-400 gramsWeight: Approx. 350-400 grams

Tracks & ChassisTracks & Chassis

Tracks & ChassisTracks & Chassis

Communications SystemsCommunications Systems

Onboard video camera.Onboard video camera.

Transmitter for the video receiver from the camera.Transmitter for the video receiver from the camera.

Remote control receiver with a 3 – 5 mile range.Remote control receiver with a 3 – 5 mile range.

Remote control.Remote control.

Two onboard 12-v batteries to run electronics.Two onboard 12-v batteries to run electronics.

A third battery for the motors.A third battery for the motors.

Brainstem to control all communication functions.Brainstem to control all communication functions.

Estimated total cost: $900 - $1200Estimated total cost: $900 - $1200

Estimated total weight: 400 – 500 grams.Estimated total weight: 400 – 500 grams.

Satellite HousingSatellite Housing

Basic pyramid designBasic pyramid design

Landing possibilitiesLanding possibilities

Solutions to deploymentSolutions to deployment

Attaching to tetherAttaching to tether

Breaking the boxBreaking the box

Will cost between $10 - $50Will cost between $10 - $50

BudgetBudget

PROPOSED EXPENSES: PROPOSED EXPENSES: (Approx.)(Approx.)– Motor and gearing: $110Motor and gearing: $110– Track System & Chassis: $50Track System & Chassis: $50– Communication Systems: $1200Communication Systems: $1200– Satellite Housing: $50Satellite Housing: $50

Total Expenses: $1410Total Expenses: $1410

Team 2

Major Major SubsystemsSubsystems

RoverRover

CaseCase

CameraCamera

PowerPower

General Diagram

Rover• Front suspension• Rear Suspension

Main Chassis • All main electrical components are contained on the

chassis• Has a rolled arch for added stiffness• Solar plate mounted on hinge above chassis for

cooling and light purposes

Case• Rectangular, rounded edges• Durable & easy to build

Camera • Mounted on front of rover for maximum visibility

System Description

Level Arm MechanismOrientation

General Power Diagram

Components Mass (g)Mass (g)

Tires (12grams X4)ChassisVideo TX Video AntennaRear end w/ motor CameraLi-POH batterySolar CellR/C system(receiver) R/C micro servo 1(steering) R/C servo 2(lever arm)Suspension. A-Arms(8g X4) Shock Tower

4848 2828 300300 6060 170170 130130 538538 280280 99 1818 4141 4242 1010

Total Weight 1692

Mass Budget

Structure

Up-Dow n Crash Team 2

M ission D irectorCSM

B ob Knecht

M ission Contro lU niversity of Colorado

Chris Keohler

Dem oSat I ICSGC

DemoSat Project Schedule

Project Management ScheduleProject: DemoSat II (Landing Site Selection) Manager: R. D. KnechtNumber: 04es7csg Date: January, 2004

Time Jan Feb Mar Apr May Jun Jul AugActivityI. System Design and Selection A. Identify needs/develop specifications Problem Definition Design Specification

Project Plan B. Define subsystems Analyze feasibility Estimate costs

Subsystem Review C. Complete system Construct and Test Subsystems Assemble and Test System Prepare Design Presentation

Satellite Selection

II. Design Refinement A. Mission readiness Upgrade System Environmental Testing

MRR B. Launch readiness

LRR