SpaceQuest, Ltd. 1 May 15, 2007 NanoSat Payload Accommodations Presented To: NSF Workshop on Small Satellite Missions for Space Weather

SpaceQuest, Ltd. 1 May 15, 2007

NanoSat Payload Accommodations

www.spacequest.com

Presented To:

NSF Workshop on Small Satellite Missionsfor

Space Weather and Atmospheric Research

Dr. Dino Lorenzini

SpaceQuest


Presentation Outline

• Brief Introduction to SpaceQuest products

• Experience with Microsatellite launches

• Describe auxiliary payload flight opportunities


SpaceQuest, Ltd.

• Founded 1994; Based in Fairfax, Virginia• Focused on microsat technologies.• Built and launched Microsats for Aprize and AMSAT.• Microsat subsystems to NASA, CSA, universities, others.• All avionics systems & software for Bigelow Aerospace.• Conducted several flight qualifications programs.

2002 2004 2006

1993


Full Range of Space-Qualified Components


Components Integrated into Stackable Trays

Battery Regulator Tray

Transmitter Tray Receiver Tray

Flight Computer Tray Experiment Trays

Torque Rod Tray


SpaceQuest NanoSat Stack

Tray Stack Without Solar Panels Complete NanoSat


Satellites

Launch campaigns

Payload Qualification

Payload Integration & Flight Experience


Satellite Programs

USAF Academy FalconSAT-3 SaudiComSat 1A AMSAT Echo

LatinSat-B USAF Academy FalconSAT-1 AprizeSat A and B


Microsatellite Experience

Participated in 37 Satellite Projects

Responsible for8 Satellites

Managed 5 Launch Campaigns

AMSAT MicrosatU of ArizonaEyeSatItamSatSaudiSat 1A, 1B, 1CUnamSat 1 and 2JawSatQuicksatCitizen ExplorerOPALASUSatSapphireMOSTChipSatAMSAT AO-40FalconSat 1& 2LatinSat A & BAprizeSat 1 & 2Genesis 1 & 2TacSat-3SaudiComSat 3, 4, 5, 6 and 7Morocco ComSat & ImageSatBigelow Aerospace Gen-1, 2, & 3

EyeSat

ItamSat

SaudiSat 1A

SaudiSat 1B

LatinSat A

LatinSat B

AprizeSat-1

AprizeSat-2

1993 Ariane-4 V59

2002 Dnepr-2

2004 Dnepr-3

2006 Dnepr-6

2007 Dnepr-8


Launch Campaign Experience

1993 Ariane ASAP launch of AO-27

2000 Dnepr launch of SaudiSat 1A and 1B

2002 Dnepr launch of LatinSat A and B

2004 Dnepr launch of AprizeSat 1 and 2

2006 Dnepr launch of Genesis-1

2007 Dnepr launch of Genesis-2


Dnepr Launch Advantages

• Four successful Dnepr missions to date.

• Short lead time and attractive pricing.

• Minimal documentation or reviews.

• ISC Kosmotras responsible for fit check & separation mechanism.


NanoSat Integration Activities

Baikonur, Kazakhstan


Bigelow Genesis-1 Integration & Encapsulation

Genesis Ready to Ship

Genesis 1 Integration

Encapsulation into Dnepr Space Head


Vehicle Assembly and Launch Sequence


Auxiliary Payload Activities

• Qualified two Canadian technology demonstration payloads on SpaceQuest satellites

• Xiphos payloads: Two Q-4 Networking Cards Attitude Control Sensors

• CSA payloads: Semi-permanent magnetic torque rod High-voltage drive electronics Two-Axis Digital Sun Sensor

Experiment Module

SpaceQuest, Xiphos, and Canadian Space AgencySpaceQuest, Xiphos, and Canadian Space Agency

Demonstrated SpaceQuest’s ability to integrate payloads quickly and economically.

Demonstrated SpaceQuest’s ability to integrate payloads quickly and economically.


Canadian Space Agency Experiments

Two months from Contract Award to Launch !Two months from Contract Award to Launch !

Experiment for 2002 Launch Experiment for 2004 Launch


Auxiliary Payload Flight Opportunities

NanoSat Auxiliary Payloads

Adaptable Microsat Design


Auxiliary Payload Launch Opportunities

• SpaceQuest plans to launch 1 or 2 NanoSats every year

• Next SpaceQuest NanoSat Launch is 4Q 2008

• Always some space available for auxiliary science payloads Interface requirements 6 to 12 months prior to launch Flight Article delivered 2 to 3 months prior to launch

10-kg NanoSat 75-kg MicroSat


NanoSat Accommodation

Volume: 22cm x 20cm x 6+cm

Mass: 2 Kg

Power: 1W average; 30W Peak

Supply: 8-Volt Unregulated Battery Bus

Interfaces: Serial, SPI, I2C, CAN, RS-232

Data Storage: 8+ Mbytes

Openings: Small Areas on all 6 sides of S/C

Cost: $0.5M to $1M, including launch

Volume: 22cm x 20cm x 6+cm

Mass: 2 Kg

Power: 1W average; 30W Peak

Supply: 8-Volt Unregulated Battery Bus

Interfaces: Serial, SPI, I2C, CAN, RS-232

Data Storage: 8+ Mbytes

Openings: Small Areas on all 6 sides of S/C

Cost: $0.5M to $1M, including launch

NanoSat Tray Stack

Experiment PackageAuxiliary Payload Tray


Nanosat Trays Simplify Payload Integration

Antenna, Filters & Sun SensorsIntegrated Flight Computer

Battery Charger and Pyro Circuits UHF Transmitters and Camera Computer VHF RX, S-Band TX, Modem & Switches


Microsat Payload Accommodations

Volume: 40 x 32 x 26 cmMass: 30 KgPower: 30W average; 100W PeakSupply: 28 Volt Unregulated Battery BusInterfaces: Ethernet, Serial, SPI, I2C, CAN, RS-485

Attitude: 0.1° Knowledge; 0.5° ControlData Storage: Up to 8 GBytesDownlink: 5 GBytes/day down; 6 Mbytes/day upOpenings: Visual to Zenith or NadirCost: $2M to $5M, including launch

Volume: 40 x 32 x 26 cmMass: 30 KgPower: 30W average; 100W PeakSupply: 28 Volt Unregulated Battery BusInterfaces: Ethernet, Serial, SPI, I2C, CAN, RS-485

Attitude: 0.1° Knowledge; 0.5° ControlData Storage: Up to 8 GBytesDownlink: 5 GBytes/day down; 6 Mbytes/day upOpenings: Visual to Zenith or NadirCost: $2M to $5M, including launch

Primary Payload

Secondary Payload

RF Unit Processing Unit

Antenna

TECSAS Capture Interface

Telescope/Camera/Cooler

Baffle/Door

Controller Board

CubeSats Dispenser

ABB Bomem Interferometer

Radar Altimeter Payload Space Surveillance Payload Instrument Payload


General Purpose Interface

Power Output:

Six Switched +28 Volt OutputsTwo DC/DC converters with adjustable output

Analog Inputs:

Four ±10 V analog channelsEight additional 3.3 V analog channels16-bit ADC with very high sample rate

Glue Free Interface:

A special multiplexer allows direct connection of: - YSI Thermistor beads - AD590 temperature sensors - RADFET radiation sensors - Potentiometers and micro switches

Analog Output:

One channel, 0 – 2.5 V, 12-bits

Digital I/O:

8 general-purpose digital I/OFour-wire SPI busTwo RS-485 serial connectionsFault-tolerant CAN bus

Telemetry:Internal voltages, currents, temperatureBuilt-in pressure sensor and microphone

Processor: 20 MIPS 8-bit microcontroller

Memory:8 kBytes boot ROM56 kBytes program/data flash; updatable on orbit512 kBytes data RAM

General Purpose Terminal


SpaceQuest Multi-Mission Bus Configuration

Radar Altimeter Mission


SpaceQuest Multi-Mission Bus Designs

Technology Demonstration Mission

Near Earth Orbit Surveillance Mission

Solar Sail Mission


Four Missions from Adaptable Bus Design

Generic Configuration

Near Earth Satellite

Surveillance

Radar Altimeter

TechnologyDemonstration

Solar Sail Mission


Summary

Flexible Requirements Quick response.

• Reproducible NanoSat Bus (6-month build)• Adaptable Microsat Bus (~1-year build)• Experience with integration and launch of secondary payloads• Long-term partnership with Russian Launch Company• Commercial UHF spectrum at 400 MHz• PI connectivity to payloads via the internet• Firm, fixed price contracts on commercial terms• Always on cost and schedule !

Easy to work with.

Documents

SpaceQuest, Ltd. 1 May 15, 2007 NanoSat Payload Accommodations Presented To: NSF Workshop on Small Satellite Missions for Space Weather