ISS Ham Radioskaf V / ARISSat-1

ISS Ham Radioskaf V / ARISSat-1
Payload Safety Review Panel Phase II Flight Safety Review October 13-14, 2010 October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Radioskaf-V/ARISSat-1 Phase II Flight Safety Review
Project Personnel Mark Severance – ISS Ham National Laboratory Education Projects Manager Mark Steiner – ISS Ham Technical Liaison Kenneth Ransom – - ISS Ham Payload Developer Stephen Ponder - ISS Ham Payload Developer Support Barry Baines - AMSAT Gould Smith - AMSAT Lou McFadin - AMSAT Bob Davis – AMSAT Jerry Zdenek – AMSAT Tony Monteiro - AMSAT Claire Fredlund – Safety And many more…. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Agenda Overview Hardware Experiment Subsystems Structure Solar Panels and Covers Thermal Power/Battery/PSU Cameras Antennas Cables Transponder/Transmissions IHU MPPT Safety Circuit Hazard Reports October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat Overview ARISSat-1 is the first of a planned series of small experimental amateur satellites which can host educational payloads or experiments ARISSat is designed and built by AMSAT, a non-profit volunteer organization that designs, builds, and controls amateur radio spacecraft ARISSat will be operated in conjunction with the Amateur Radio on ISS (ARISS) working group Volunteer network of amateur radio operators around the world which support ISS contact with schools The ISS National Lab Education Project of the NASA Education Office has provided funding and in-kind support for the ARISSat development due to it’s potential for hosting student built payloads ARISSat-1 is seen as a flight test of the overall avionics package of the ARISSat series October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat Overview (cont’d)
ARISSat-1 leverages designs from the Suitsat-1 satellite (deployed via RS EVA February 2006) Safety interlock system Crew control panel All ARISSat series are currently planned to be Russian Segment EVA deployed but options for deployment from COTS cargo vehicles/booster will be explored Radioskaf V is Russian nomenclature for ARISSat-1 Progress Flight 41P (currently January 28, 2011) EVA RS 28 (currently February 21, 2011) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSAT-1 Diagram October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat Block Diagram October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat-1 Planned Mission and Capabilities
Commemorative and Educational Voice Messages. Includes audio greetings from around the world Kursk University Experiment Testbed for systems planned for future Amateur radio satellites Amateur operations CW ID ARISS Callsigns Transponder SSTV Images of Earth and Station October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

SSTV Slow Scan Television Video image is captured and digitized Four video ports No power until switched on just before data take. Four U.S. Supplied No blank video Processor examines video and skips if no image present October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Kursk Experiment Russian Experiment to measure the amount of vacuum as the satellite de-orbits Experiment developed at the Kursk State Technical University Experiment to be installed in the spacecraft in Russia Power the unit for 100 minutes once per day (10 minutes warm-up, 90 minutes data collection 5V maximum current 100 mA 30 minutes after the satellite is powered take the first data sample Transfer the data to the IHU and send to Earth via the BPSK signal Use a simple attachment scheme and interface Use a 9 pin cable to carry power, data and control signal between the IHU and the Experiment Keep the installation simple, since we cannot test it in the US October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Kursk Experiment October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Experiment Operations
30 minutes after the satellite is powered the first sample of the day will be taken The experiment will be powered for 100 minutes 2k of data will be transferred to the IHU, assembled into 5 packets with headers Transferred to the SDX and sent via the 1kBPSK data stream (or 400bps BPSK) The five data packets will alternate with the telemetry data October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat-1 Flight Structure
October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Top Exterior View October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Bottom Exterior View October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Interior View October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Flight Structure Mechanical subsystem includes structure and electronics boxes. Simple structure that can be implemented quickly Provide attachment for: SMEX solar panels Electronics boxes (IHU, Rx/Tx, MPPT, Control Panel) Orlan-M battery (integration on ISS) Kursk experiment (integration in Russia) Spare experiment box 4 cameras 2 whip antennas Handles Survive Progress loads (“CargoTransReqP103.doc”) Low outgassing Venting of volumes October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Design Methodology For conservative structure, we want low stresses, small deflections, and high frequencies (or at least >>50 Hz) All “masses” are attached to the Top & Bottom Plates, which are ¼” thick aluminum Thick enough for helical thread inserts Much faster to process than honeycomb sandwich panels Easy to over-design (which also lessens analysis burden) Given schedule, the above advantages outweigh the mass penalty The Plates are separated by custom machined angles in the four corners, also 1/4” thick Side Panels (with SMEX Solar Panels) act only as shear planes Small angle extrusion joins edges of Side Panels to Top & Bottom Plates Added flanges to die cast aluminum electronics boxes October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Margins Summary Simultaneous 10g vertical and 6g horizontal Material Factors of Safety Yield, FSy = 1.2 Ultimate, FSu = 1.5 Threaded fastener Factor of Safety FS = 2.0 All structural margins are positive October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Mass, CG & Inertia Masses Measured Avionics, harness, antennas, cameras Mass from CAD model Structure CAD model contains 97% of total mass Raw inertia matrix from CAD model is scaled for remaining 3% of mass Observatory Mass will be measured But not CG or inertia Add Battery, Remove Covers October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Verification Pre & Post Sine 0.25g from Hz at 4 Oct/min Ascent Qualification Random Orbital Qualification Random Observatory level vibration testing Mil-Spec Qual Test Facility Kursk experiment mass mockup No Orlan-M battery (not installed for launch either) Covers (installed for launch also) Levels from “CargoTransReqP103.doc,” Requirements for International Partner Cargo Transported on Russian Progress and Soyuz Vehicles, П October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Vibration Photos October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Vibration Results Satellite vibration tested per P103, but Sequence
Ascent Random extended to 4 minutes Shock extended to 7 events per from Samburov Sequence Z Random – completed but Mirror screws backed out (too short), replaced Z Shock – completed but Tx dummy load loosened radio functional failure, replaced radio S/N 1001 with 1003. Y Random - completed Y Shock – completed X Random – completed but Loose Helicoil identified as unused box mounting location X Shock - completed Z Random – completed Z Shock – completed Repeated Z axis so radio S/N 1003 was included October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Radio Details S/N 1001 had unknown failure after first Z axis Random S/N 1003 installed instead, tests repeated Days later, S/N 1003 experienced similar failure as S/N 1001 Both failures found to be RF filter component on Rx board Previously same RF filter component failed during prototyping Suspected batch issue (5 total), reported to component manufacturer October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Vibration Action Items
Included Proper length screws (Mirror) for engagement of locking feature of Helicoils Radio swap, then change RF filter components of both units Remove or capture unused Helicoils (spare box positions) RF dummy loads receive Vibra-tite and safety-wire All action items have been completed and closed for both Flight and Spare units October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Fracture Control All structural fasteners purchased as MS or NAS with Certifications, except Helicoils ordered as manufacturer’s P/Ns A few self-locking all-metal nuts were replaced with nylon-insert Metric screws for Kursk and Battery All structural aluminum purchased with Certifications Cells are touch sensitive Lexan Covers (hard but transparent) for launch and storage IVA: Cells can be visually inspected prior to removing Lexan Covers in favor of Energia-provided soft covers Energia-provided procedures Entire rear of cells is bonded to panel Entire rear of coverglass is bonded to cell October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Kick Off Section of P106 “Technical Requirements for Hardware to be Stored or Operated on the ISS Russian Segment” Inertial loading not examined Inside RS inadvertent cosmonaut contact load = 556 N (125 lbf) Outside RS inadvertent cosmonaut contact load = N (110 lbf) Susceptible surfaces to 125 lbf and FS = 2 Handles – Aluminum column bending – MSy<0, Msu=+0 Antenna Collar – Delrin column bending – MSy=3 Lexan Covers – Lexan plate bending – MS>>0 but gap closes to contact cells Quick-Release Pins – Lateral bending - hole of aluminum Side Sheet and/or Lexan Cover Solar Cells w/ or w/o soft covers – MS<0 (this is a no touch zone) Mirror – brass plate bending – MSy<0, Msu=+0 October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Camera Mirror Top and Bottom of spacecraft Mirror is .032” thick chrome plated brass Edge receives RTV bead for radius Brackets are machined aluminum Edges of mirror captured in slot Set screwed then RTV 1.73” October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Vented Volumes Structure and all electronics boxes have vent holes Gap between Solar Panels & Covers can vent via small harness holes in SMEX, and “through” perimeter Velcro Used at least twice the vent hole cross-sectional area suggested by AIAA Payload Venting in Worst Case Shuttle Environments Rule of thumb: 0.050” in2 unrounded hole for each 1.0 ft3 generates 0.5 psi pressure (box bloating) during ascent Always sought redundant holes in the event paint, tape, or potting caused a plugging event P103 requirements met. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Progress Interface Payloads in Progress weighing more than 10 kg must be positively secured (not just strapped) Provide attachment points to satellite (weighs 21.7 kg), used for vibration testing and launch Provide mass, center of gravity, and inertia matrix in coordinate system that can be applied to mounting configuration within Progress launch vehicle Energia will provide interface structure between spacecraft and Progress launch vehicle Energia Safety agrees to either hard mount or PSIP PSIP (container with foam) is being re-designed as alternative to 4x M6 thread inserts on bottom of spacecraft JSC / Energia to document mounting of PSIP within Progress October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Interface ICD – Bottom/Top
Draft drawing has been provided Satellite has M6x1 thread at each corner of Top Plate and each corner of Bottom Plate Can be mounted Right-side Up Up-side Down Threads not used if packed in foam inside PSIP October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Interface ICD - Side Whether right-side up or upside down, there are protrusions below interface plane From Side, about 26.5” diameter Progress hatch is 80cm (31.5”) diameter 2.5” radial clearance October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Coordinate System X & Y are geometrically centered
Bottom interface plane is Z=0 October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Solar Panels and Covers
SMEX-Lite modular solar panels provided by NASA GSFC, mounted 1 per satellite face (6 total). Design of satellite shall use these available solar panels Survive launch environment Vibration frequency Stresses Survive orbital environment Low Outgassing Flammability UV exposure Atomic oxygen Venting Facilitate handling and removal (covers) size of panels actually drove size of structure October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Panel Design 19.1 Watts 17.2” x 8.24” x .14” Composite 0.015” graphite facesheets aluminum core 1 string of 50 single-junction GaAs/Ge solar cells October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Panel Mounting Each face of spacecraft (4 sides, top, bottom) has one SMEX-Lite solar panel. As-received from GSFC, provisions for spacecraft mounting via perimeter bond line (originally to a composite frame). Perimeter Velcro line to aluminum sheetmetal “frame” which then bolts to structure around perimeter. Radioskaf-V/ARISSat-1 Phase II Flight Safety Review October 13-14, 2010

Panel Mounting SMEX Velcro’ed to 0.062” AL Side Sheet Solves CTE mismatch 36x small perimeter screws on Side Sheet All panels & covers are interchangeable Ass’y Front Ass’y Back Side Sheet SMEX October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Covers 3 independent inhibits for Covers 4x quick-release pins Energia-provided Velcro straps (like belt thru belt loops) Kapton tape perimeter Lexan cover allows visual inspection for damaged solar cells prior to removal October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety Considerations
Panels added to protect fragile solar cells during handling Started as aluminum sheetmetal - now clear Lexan Designed to be removed during IVA or EVA, but planned to be removed IVA Individual panel cover to be left on if visible damage to any solar cell is detected All exposed edges are rounded Quick-release pin was selected to eliminate threaded fastener & tool during EVA T-handle quick-release pin was selected for compatibility with EVA glove Quick-release pin is tethered to Cover If adjacent covers are removed, then Velcro strap (Energia –provided) can act as tether between Covers October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

SMEX Cross-Section October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Operations Steps for Cover removal provided to Energia Energia to provide procedure and training Option for leaving Covers on handled in procedure In operation, each panels’ voltage and current is available in telemetry October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Thermal Analysis October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Thermal Analysis Thermal analysis of 30th orbit (allowing time to settle from room temp) However, the touch surfaces will start the EVA at the ambient temperature of the airlock. After 90 minutes out of the airlock, the external temperatures are expected to range between 0° and 25° C. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Power/Battery Russian space suit battery will provide power when solar panels are not illuminated. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Battery Connectors October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Battery Cable October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

825M3 Battery Specifications
Cells per unit (Ag-Zn) 18 Nominal voltage 27 V Min. capacity 14.0 Ah Initial capacity (typical) 20.5 Ah Charge method: constant current 1±0.2 A Max. charge voltage 35.8±0.15 V Min. discharge voltage 20.5±0.5 V Full charge/discharge cycles 5 Temperature range °C Min. pressure 1.33×10-6 Pa October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Design Use commercial Ag-Zn battery (Yardney) to verify spacecraft would operate on Ag-Zn type battery Make measurements on Flat-Sat model to characterize charge/discharge environment Similar battery (825M1) is already in use on ISS Battery cable includes grounding wire October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Operations Battery must be initially charged to activate satellite Battery is mission critical for first 15 minutes of flight Satellite will power down during eclipse if battery fails October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Power Supply Unit Produces efficient Regulated Power Accurately measures the power in/out of the battery. Manages and controls power to loads Supervises the IHU, and cycle power if non-responsive Drop +28V battery to subsystem voltages. +5v for Experiments, IHU, SDX and PSU CPU +8v for RF Transmitter and Receiver +12v for Cameras Switch power to each subsystem Monitor current to each subsystem Monitor performance of Solar Power Converters Report power system health to IHU via I2C. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

PSU Safety Considerations
RF Power Switcher is enabled by two sources Forced off by the Safety timers Requires IHU request RF Power PPT’s are isolated from powering the system until enabled by the Safety timers Communications can still occur October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Cameras Cameras for the SSTV system Scope Small, low cost, resolution at least as good as the SSTV format uses, low power, wide dynamic range of light levels, quick startup, color, no hazardous glass. Four small surveillance cameras from Hunt electronics Lens is small pinhole type. Verification Operate with the flat-sat and engineering units. Enable power and read data once for every data sample Status October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Design October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Camera Design Aluminum die cast housing Aperture is plugged by a small glass recessesd pinhole type lens which is captured in place with a bonded collar. Outside hole is approximately 1.3 mm in diameter. Housing has a vent hole on the front, which vents towards the spacecraft structure plate vent interior to the spacecraft Rectangular cutout on the back of the sensor for passing the four wires which will be potted with RTV. Two chrome-plated brass mirrors are mounted on the exterior of the satellite (one on top and one on bottom.) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Camera Lens - Internal View

Camera Mirror October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Camera positions Two on top and two on bottom (mirror) (mirror) Cutaway to show cameras inside Radioskaf-V/ARISSat-1 Phase II Flight Safety Review October 13-14, 2010

Camera wiring October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Antennas Transmit and receive antennas for ARISSat Scope As uniform a gain pattern as possible, linear, provide no safety hazard to the crew ¼ wave whip built along the same designs as previously flown on ISS. No sharp edges or puncture hazards for the crew. Must withstand rough handling. Inspection and test No hazard to the crew. Linear Omni directional as possible given the design constraints Tuned to the proper frequency Separate antennas for transmit and receive. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Antenna Design Based on ARISS and Columbus Module antennas. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Antenna Design New Collar design allows easy removal of the antenna for stowage during transport and test. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ARISSat Antennas October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Operations Antenna may be removed for shipment and easily installed for test and flight. Align the antenna connector over the Type N female receptacle push down and screw in until the base of the collar is tight with the face of the spacecraft and the mark on the antenna collar aligns with the corresponding mark on the satellite. Antennas not designed to radiate within ISS cabin. Anti-static connector in place for launch. Antennas installed by crew on orbit. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Telemetry The Telemetry System is used to measure and transfer the system temperature, voltage, current and status values to the ground stations. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Transmissions October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

U/V Transponder Transponder To Contain: COMM RX at 70 CM COMM TX at 2 Meters w/0.5 Watts Pout Command RX at 70 CM October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

COMM TX PERFORMANCE IF Input: MHz at ~ -6 dBm Power Output: dBm (0.25 watts maximum carrier) Total RF Power Across Transponder dBm (0.5 watts) DC Input Power: mA (1.92 watts) Overall Efficiency: 26% Frequency Accuracy : +/- 1 PPM ( 145 Hz at 145 MHz) Frequency Stability: +/- 2.5 PPM (-30 to +70C) Harmonic Rejection: -40 dBc Spurious Rejection: -50 dBc PCB Size: ” (60 cm) X 2.8” (71 cm) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Cables The Cable systems of the ARISSat-1 satellite consists of 10 cables and coaxes that electrically connect the various satellite modules. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Inventory of Cables Each ARISSat requires the following cables: Battery Cable Multi-Y Cable (Connects IHU module to Control Panel, RF Module, Upper Camera assembly, Lower Camera Assembly) MPPT Cable (2 required per ARISSat) Solar Panel Cable “A” Solar Panel Cable “B” External Thermistor Cable Experiment Cable 2M Transmit Antenna Coax 70 cm Receive Antenna Coax October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Material Selection Cables are made from the following materials: AWG 22 PTFE insulated wire per Mil-W-22759/11 AWG 22 PTFE insulated shielded twisted pair wire RG-188A/U Coax cable per Mil-C-17D RG-142B/U Coax cable AWG 24 shielded PTFE insulated wire D connectors (50, 15, 9 pins) per Mil-C-24308 Amphenol , and Right angle connectors ¼” & ½” Bentley Harris expandable sleeving Kynar shrink sleeving Lacing Tape per Mil-T 1” & ½” 3M Fiberglass electrical tape Vibra-Tite VC3 (Thread-lock compound) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety considerations are addressed through proper material and wire size selection as well as connector pin-out during cable design. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

IHU Internal House Keeping & Mission Management Scope Manage Voice messages on SD card Camera control & image capture Telemetry Gathering BPSK & Morse Generation Experiment Scheduling & data capture Measure Analog Thermistors No safety considerations October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

MPPT MPPT Extracts the most possible energy from the solar panel for use by the satellite Convert Power from a solar panel to an output capable of charging a 28V Silver-Zinc Battery Panel Input 51Volts Open Circuit, 0.5A Short Circuit Battery max Charge Voltage 35.8V Provide Telemetry Data PPT and Solar Panel Temperatures Solar Panel Voltage and Current Communicate back via RS485 Powered off Solar Panel so system can restart in case of battery failure October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

MPPT Views October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

MPPT Views (Cont’d) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

MPPT Safety Considerations
Hardware Oscillator is hardware controlled After initialization no software is needed to run the oscillator or over voltage protection SEPIC output is capacitively coupled: oscillator halts and no power is delivered to the output Hardware current limit to oscillator Failure conditions SEPIC FET stuck on Current is limited by Solar Panel Failure mode to over heating is an open Self powered: if stuck in a bad state a clean reboot happens each orbit or rotation of satellite October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Inter Connect Board Connects all PCB assemblies in the IHU stack to the outside world Provides Safety Circuitry October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Requirements Location of all safety control logic and relays Debug LEDs and switches Connect IHU to Cameras Command Decoder Experiments Connect SDX to Transmitter / Receiver Connect to Control Panel Connect PSU to MPPT Battery Safety Circuitry Transmitter Connect Command Decoder to IHU Receiver October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Stack (non-flight) October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

PCB Assembly October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ICB is critical and integral to electrical safety on the satellite Isolates Battery MPPT Isolation Relays Prevents battery overcharging Inhibits RF transmission Times events after switch changes to allow Satellite to move away from personnel Connectors that provide power are sockets, not pins October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety Interlocks October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Start Up Timeline October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Start Up Timeline (Cont’d)

Interlock 1 Crew person turns on 28V Power Switch Power is connected to: Safety Timer Circuitry PSU October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety Schematics Relays

Safety Timers Power October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Interlock 2 Crew turns on Timer 1 Switch Timer 1 begins counting Timer 1 Counting LED starts blinking ~20 seconds later, IHU powers up Takes a picture 7.5 minutes later, RF 8V switcher is enabled October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Control Panel Switch Interface – T1

Control Panel Switch Interface – T2

Timer 1 Schematic October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

IHU Reset October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

RF Power Inhibit October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Interlock 3 Crew turns on Timer 2 Switch Timer 2 begins oscillating Does not start counting time until Timer 1 is complete Timer 2 Enabled LED starts blinking RF Push to Talk is still disabled Upon expiration of Timer 2 (8 minutes) MPPTs connected to 28V Bus RF Push to talk is enabled If Crew turns off Timer 2 switch MPPTs are disconnected from 28V Bus Timer 2 stops oscillating RF Push to Talk is disabled MPPT Relay is turned on by completion of Timer 2 and off by Timer 2 switch off Prevents loss of power on satellite from being fatal October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Timer 2 Schematic October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Push To Talk Inhibit (Timer2)
ICB Control Panel Transmitter October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Command Decoder Reset Command Decoder can drive a signal high to force the Satellite to reset Upon driving this line high PSU +5V Switcher is shut down for ~20 seconds Kills power to the IHU and SDX Kills the microprocessor running on the PSU Kills the Command Decoder PSU will cycle the RF power on restart Strictly for Operational Considerations No impact on safety circuitry Inhibits must complete their remaining time, if any October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety Circuit and Control Panel
Provides the Control of the Satellite and indicate Satellite Status Compliant with all ISS safety requirements Provide an interface that a crew person in a pressure suit can control the satellite Indicate status of the Satellite Allow the system to be quickly shut down in case of a problem October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Safety Circuit Design Provide all timer functions equivalent to Suitsat-1 One Power switch with LED status Two Timer switches with LED status Same mechanical switch layout as Suitsat-1 Additional LEDs for Operational and Safety Verification Improve LED visibility Measure control panel temperature October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Control Panel Front October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Control Panel Switches
Activation Switches False activation due to switch contamination could create a safety hazard Using APEM 12000X778 Switches to ensure safety Switches are designed for high-rel applications and is QPL certified to MIL-DTL and MIL-DTL-3950 Access to switches Metal Finger guards provided so that only one switch is activated at a time October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Hazard Reports JSC 1230 Standard Hazard Report Unique Hazard Reports ARISSat-F01 Crew Exposure to RF Radiation During ARISSat-1 Deployment Activities ARISSat-F02 Battery Charging During Deployment Activities ARISSat-F03 Collision of the ARISSat with the ISS and/or Vehicles Docked with the ISS ARISSat-F04 Structural Failure ARISSat-F05 Astronaut Injury Due To Contact Hazards ARISSat-F06 Leakage in ORLAN Storage Battery Cell Housing/ Electrolyte Leakage October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

Agreements The PO agreed to provide picture of the cross-section of the Solar Panel. The PO to include the solar array glass bonding analysis and procedures in the controls, and state in the verifications that if there is any damage to the solar cells, the Lexan cover will remain attached. The PO agreed to include all certification for materials (including the Russian Orlan battery and soft cover materials) at Phase II. The PO agreed to write a new general unique battery hazard report (ARISSAT-F06) and include a wire sizing and circuit protection diagram. The PO agreed to include the Trajectory Operations Officer (TOPO) analysis. The PO agreed to include a statement that the satellite has positive structural margin and provide a fracture control assessment. October 13-14, 2010 Radioskaf-V/ARISSat-1 Phase II Flight Safety Review

ISS Ham Radioskaf V / ARISSat-1

Similar presentations

Presentation on theme: "ISS Ham Radioskaf V / ARISSat-1"— Presentation transcript:

Similar presentations

About project

Feedback

Log in

Auth with social network:

ISS Ham Radioskaf V / ARISSat-1

Similar presentations

Presentation on theme: "ISS Ham Radioskaf V / ARISSat-1"— Presentation transcript:

Similar presentations

About project

Feedback