2009 Bridging the Gap to Space

forestevanescentElectronics - Devices

Nov 2, 2013 (3 years and 7 months ago)

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National Aeronautics and Space Administration


Balloon Program

2009 Bridging the Gap to
Space

The Micro
-
Instrumentation
Package: A Solution for
Lightweight Ballooning



Created by Jill Juneau

Presented
by Dwayne
Orr


Consolidated Instrumentation Package (CIP)


Used for systems in range of Line of Sight
(LOS) lasting hours up to a few days



Battery powered, lasting up to several days



TM Uplink



1200 Baud UHF Uplink


77 Discrete Relay Drivers


16 Bit Parallel Data Word


TM Downlinks


VCO’s IRIG 7, 8, 9, B, E, HH


GPS Position / Pressure Altitude


FAA Transponder


L/S Band Transmitters


NTSC Video


Up to 1Mbit Bi
-
phase Science Data



≈ 100 pounds with the termination system




Support Instrumentation Package (SIP)


Used for Long Duration flights needing Over the Horizon
Communications


Line Of Sight Communications


Telemetry Transmitter up to 1 Mbps


Over the Horizon Communications


NASA’s TDRSS


6 kbps Omni Antenna


NASA’s TDRSS


92 kbps High Gain Antenna


Iridium


2kbps through dialup


Solar Panel Power System and Backup Batteries


≈ 400 lbs with solar panel and termination system


What is the MIP?


The MIP is a lightweight Over the Horizon telemetry and
termination system that in its full up configuration can
provide safe operation of a balloon flight including data
downlink/uplink, termination, parachute cutaway, and
ballasting

Benefits of a Lightweight Cost Effective Telemetry System


The Micro Instrumentation Package (MIP) is great for scientists who:


Want to use a lightweight payload on small balloons for lower costs and/or
disposable flights


Want to use a lightweight payload on a large balloon for higher altitudes


Need a NASA approved Over the Horizon lightweight telemetry system to
safely operate the balloon flight











The MIP does have very limited data rates compared with CSBF’s other
telemetry systems
-

the trade off is weight and cost


History of the MIP development and test flights


Early 2006
-

First electronic development
started



During summer and fall of 2007


3
piggyback flights on CSBF flights and 7
test flights conducted using 3000 gram
balloons that burst at 100k feet



Spring 2008
-

Two full up test flights with
full flight trains



After the 2 successful full up test flights,
the MIP was qualified as a NASA flight
system


MIP Test Flights

Microcontroller PCB


The central unit of the MIP


Designed by CSBF


Uses Microchip Pic18F8722


Programmed in C


Features located on board


22 Analog inputs


16 digital inputs


30 digital outputs


6 serial ports


Line Of Sight port


Iridium port


GPS port


Cross over commanding or
external stack input


Diagnostics port


Science data port




Microcontroller PCB


The central unit of the MIP


Advantages of microcontroller board


Inexpensive parts (microcontroller costs
$10)


Low power


120
mA

at 9 V with GPS
unit running


Board footprint is small (4.25” x 4.25”)


Can be used for many different CSBF
applications


Many timers and parameters are
programmable during flight


Operates over wide range of
temperatures and performs well in a
vacuum environment





MIP Configurations


Antarctica Pathfinder


Used to verify satellite derived wind
data acting as an Over the Horizon
sonde




Provides basic GPS information and
temperature data



Consists of CSBF Microcontroller
PCB, Iridium SBD modem 9601, and
battery



System has been used successfully
the last 2 seasons in Antarctica



MIP Configurations


Antarctica Pathfinder


Steady State power = 1.2 Watts


The 9601 Iridium modem uses Short Burst Data only


To save power Iridium modem is put into power standby when not used


In Previous flights the system weighed 4 pounds and lasted for 5 days with
once every 30 minute transmission


New configuration will weigh less than 5 pounds and provide for 10 days of
flight with once every 30 minute transmission rates





Video of a Pathfinder Launch

MIP Configurations


Backup Navigation System


Used as the third redundant GPS system on long
duration flights with a Support Instrumentation
Package (SIP)


Provides basic GPS information and SIP critical
housekeeping parameters


Consists of CSBF Microcontroller PCB, Iridium
SBD modem, DC/DC Converter and is powered
from the SIP


MIP Configurations


Full Up System Functions



Redundant Microcontroller Boards with
crossover commanding


Redundant LOS Transceivers


Redundant SBD Iridium Units


Dial
-
Up capability on one modem


Redundant GPS receivers


Redundant DC/DC converter Boards


3 MKS Pressure Sensors


1 for each range


2 Science Interface Ports



MIP Configurations


Full Up System Functions


Burst Detect and Minimum Altitude Circuits


Ballast Valve Circuit controlled independent
of software


Each microcontroller board redundantly
monitors termination, parachute cutaway,
and valve information


Redundant termination firing circuits and
Helium Valve


Parachute Cutaway System


MIP Data Rates

LOS


LOS transceiver UHF frequency


MIP packet once every 15 seconds


Science packet up to 255 bytes once every 30
seconds


Commands can be received at any time


Science can add LOS telemetry transmitter
(up to 1 Mbps) with
tradeoff
of more batteries

OTH


Iridium Short Burst Data


MIP packet once a
minute


Commands received when packet is sent


Science packet up to 255 bytes once every few
minutes


Future capability to have dial up available for science data

Comparison of Data Rates for CSBF systems

Description (Data Types)

Consolidated

Instrumentation
Package (CIP)

Support

Instrumentation
Package (SIP)

Micro
-
Instrumentation

Package
(MIP)

LOS Data Rate

Up to 1 Mbps
(Continuous)

Up to 1 Mbps (Continuous)

255

bytes once every 30
secs
.

(Option

for
Up to 1 Mbps
-
Continuous)

Iridium Short Burst (OTH)

N/A


255 byte packe
t once every 15
minutes

255 byte packet once every few
minutes (programmable)

Iridium Dial Up (OTH)

N/A

Up to 2

kbps

(Continuous)

250 bytes per second


Development not completed

for
science data

TDRSS

Omni Antenna
(OTH)

N/A

Up to 6kbps

(Continuous)

750 bytes per

second


N/A

TDRSS High Gain Antenna

(OTH)

N/A

Up to 92kbps

(Continuous)

11,500 bytes per

second


N/A


MIP Power
Consumption and Weight


MIP
Enclosure
steady state power 28V
@.5A = 14W


When transmitting LOS Current spikes shortly above 1A


When Dialed
up Iridium
current spikes up to .75A


Can
achieve lower power consumption depending on the
configuration


Can operate on batteries or solar panel system


The MIP electronic enclosure weighs 20 pounds without
batteries


A 10 lb. 30 amp hour battery pack will last approximately 2
days


6 day flight


50 lbs. of electronics and batteries


Science Interface

Success with the Full Up MIP System
-

Summer 2008


Super Pressure Balloon Test Flight


Launched in Ft. Sumner, New Mexico


2 million cubic feet balloon


MIP provided telemetry of the balloon location and
termination of the flight

Success with the Full Up MIP System
-

Summer 2008


Flight from Sweden to Canada lasting 4 days 9 hours


11 million cubic feet balloon


MIP operated termination and parachute cutaway


System powered from batteries


Science Interface used to transmit science payload charge
controller information

Success with the Full Up MIP System
-

Winter 2008
-

2009


Super Pressure Balloon Test Flight


Launched from McMurdo Station, Antarctica


Flight Duration: over 54 days


7 million cubic feet balloon


MIP powered by small solar panel system


MIP operated flight including flight termination and parachute cutaway


Video of SPB launch

Success with the Full Up MIP System
-

Summer 2009


Flight from Sweden to Canada lasting 4 days 11 hours


39 million cubic feet balloon


MIP operated termination and parachute cutaway


System powered from batteries


Science Interface used to transmit science payload charge
controller information


Upcoming campaigns Antarctica 2009
-
2010


BARREL


MIP Pathfinder with terminate firing circuit used as a redundant method
of balloon communication and cut down


5 Test flights using .3 million cubic feet size balloon


Total payload weight 70 lbs.


MIP powered from BARREL solar panel system and backup battery


Hand launch system

Video of BARREL Test Launch



Thank you for
your attendance

Questions
and Comments?

Video Of LEE launch