VACCO Micro Propulsion Systems May 1 May VACCO ChEMS™ Propulsion Systems Micro Advances and Experience in CubeSat st , 2018 Propulsion System Technologies VACCO Proprietary Data VACCO – ShallNot Be Permissionof DisclosedVACCO Without Written VACCO Micro Propulsion Systems Advances Advances and Experience CubeSatin Propulsion Technologies System VACCO Industries – VACCO Industries 2 VACCO Micro Propulsion Systems Tyvak NanoACE Micro Propulsion SystemMicro NanoACE Tyvak Advances Advances and Experience CubeSatin Propulsion Technologies System Photo: Terran Orbital • • • • Provides Provides &Delta Divert Control, Attitude Cubesat of 3U 1U Center Occupies with Contract TyvakNano 2017 7 July NanoACE Launched – VACCO Industries - Satellite Inc. Satellite Systems - V 3 VACCO Micro Propulsion Systems NASA/Tyvak CPOD Micro Propulsion SystemMicro CPOD NASA/Tyvak Advances Advances and Experience CubeSatin Propulsion Technologies System Photo: Terran Orbital • • • • • Provides Provides &Delta Divert Control, Attitude Cubesat of 3U 1U Center Occupies Delivered SystemsFlight (2) Demonstration NASACPOD: Operations ProximityCubesat with Contract TyvakNano – VACCO Industries - Satellite Inc. Satellite Systems - V 4 VACCO Micro Propulsion Systems System Totalgrams 1270 “Wet”Mass: Integral Digital RS422 Interface Microcontroller withIntegralSystem Smart Propellant Green Self 510 grams Configuration Clamshell Manifold, 1U Center mN 0.10 174 N Gas Cold 10mN Thrusters Eight All - Welded - CPOD Micro Propulsion System Overview System PropulsionMicro CPOD S Sensor Suite Sensor - TotalDelta 31 m/s Impulse, S Minimum Impulse Bit Impulse Minimum S Overview Aluminum Aluminum Alloy Construction - Pressurizing Pressurizing R236fa Advances Advances and Experience CubeSatin Propulsion Technologies System - V – VACCO Industries 5 VACCO Micro Propulsion Systems Two Units will be Launched with the the with Launched be will Units Two InSight Mission May 2018 May Mission InSight JPL Mars Cube One (MarCO) Mission One (MarCO) Cube JPL Mars Advances Advances and Experience CubeSatin Propulsion Technologies System InSight’s InSight’s Entry, Descent and Landing at Provide Provide an 8kbps real – Mission Objective: VACCO Industries Mars - time time relay for 6 VACCO Micro Propulsion Systems THRUSTERS (4) (4) AXIAL JPL MarCO Micro PropulsionSystem JPL MarCO Advances Advances and Experience CubeSatin Propulsion Technologies System THRUSTERS STORAGE (4) (4) RCS TANK Microcontroller Driven: Microcontroller All watts) (<15 Continuous Power LowPower Two Interrupts Leakage Against System Self Smart, Lander,InSight withLaunch 2018 May Cubesat Interplanetary First - Welded Aluminum Alloy Construction            (3) Power Supplies, (9) ValveDrivers (3) Settable Thermal Control Zones Closed Controls Burn Type & Duration RS422 Digital Interface 3490 gram Wet Mass 755 N Contract Contract for (2) Flight Systems - in Controller Sensor & Suite (4) Axial & (4) RCS 25mN Thrusters Propellant Storage & Feed System - a - - Contained Propulsion System: Propulsion Contained - Sec Total Impulse Tank Design Including: - – Loop, Variable Thrust Control VACCO Industries 7 VACCO Micro Propulsion Systems Target JPL/MSFC Near Earth Asteroid Earth Near JPL/MSFC Advances Advances and Experience CubeSatin Propulsion Technologies System Main Propulsion: ~80m Propulsion:Main • • • • Mission Objectives: ≥30% coverage imaging at ≤10 cm/ at ≤10 imaging coverage ≥30% cm/px at ≤50 imaging coverage ≥80% orbit and mode type, spin spectral volume, properties:physical Characterize target Earth Asteroid (NEA) a Near flyby and with rendezvous Detect, Scout – VACCO Industries ² Solar Sail Mission px 8 VACCO Micro Propulsion Systems Advances Advances and Experience CubeSatin Propulsion Technologies System NEA Scout Micro PropulsionMicro System Scout NEA All while Firing watts <9 Power: Interrupts Three Leakage Against System onMarCO: based SystemPropulsion Self Smart, - Welded Aluminum Alloy Construction       2600 gram Wet Mass 500 N Contract Contract for (1) Flight System - in Controller & Sensor Suite (2) Axial& (4) RCS25mN Thrusters Propellant Storage & Feed System – - VACCO Industries a - - Contained Cold Cold GasContained - Sec Total Impulse Tank Design Including: 9 VACCO Micro Propulsion Systems 4. 3. 2. 1. CuSPMissionObjectives: SWRI Raisethe TRL of the SIS instrumentfor future missions Value’Science Strengthenthe case CubeSats for as a viablefor platform‘Highperforming Be aPathfinderfor creatinga networkWeatherof “Space Stations” StudySolarParticlesinterplanetaryspace in Cu beSat Mission to beSat Advances Advances and Experience CubeSatin Propulsion Technologies System S tudy Solartudy VACCOCuSP MiPS – P VACCO Industries articles (CuSP) articles 10 VACCO Micro Propulsion Systems (4)places Thrusters Connector 25mN Electrical Advances Advances and Experience CubeSatin Propulsion Technologies System CuSP Micro PropulsionCuSPMicro System (Thruster) Fill Fill Port Manifold All Power: <12 watts whileFiring TwoInterrupts Against Leakage System System based on MarCO: Smart, Self - Welded Aluminum AlloyConstruction     - Contract Contract (1) Flightfor System in Controller Controller Sensor & Suite (4) RCS 25mN Thrusters Propellant Storage Feed & System - a - Contained Cold Gas Propulsion - Tank Design Including: – VACCO Industries 11 VACCO Micro Propulsion Systems • • • OMOTENASHI: velocityof about30 m/s. performs asemi courseto the moon. The probe 6U CubeSatto bea putonto explorationof the lunarsurface. Will demonstratelow of Tokyo. Agency(JAXA)the and University the Japan AerospaceExploration Lunarmissiondesigned jointlyby JAXANano Impactor CubeSat (Omotenashi) Advances Advances and Experience CubeSatin Propulsion Technologies System - hard landinghardat a - cost – VACCO Industries 12 VACCO Micro Propulsion Systems 25mN ColdGas Thrusters, (4) Places Propellant TankPropellant Advances Advances and Experience CubeSatin Propulsion Technologies System Manifold Omotenashi MiPS Omotenashi Range Safety Features: Range Safety RCS Identical (2) & right): Assemblies (left (3) Interrupts Interrupts (3) Leakage Propellant Against Propellant: R236fa Green <4.0mN Bit: Impulse Minimum & Pressure Temperature Integral Sensors Interface DataBus RS422 VoltageInput Unregulated 12.6V 9V to Built Normally All Each: in Cold Gas 25mN Thrusters (4) Self - Welded Aluminum Alloy Construction - - Contained Delta Contained Max Pressure <0.69MPa (<100 psi) (<100 <0.69MPa Pressure Max Material Extinguisher Benign Fire Roll Control(2) (2) Axial, / Pitch Yaw In, Shielded Shielded Control Electronics In, - Closed Frictionless Frictionless Valves Closed – VACCO Industries - V / RCS Systems V / - Sec 13 VACCO Micro Propulsion Systems ECAPS 1N Thruster ADNon PRISMA GreenMonopropellant MicroPropulsion Systems VACCO Proprietary Data VACCO – ShallNot Be Permissionof DisclosedVACCO Without Written ECAPS 100mN ECAPS100mN Hot ADNFire Test VACCO Micro Propulsion Systems • • • • ArgoMoon CubeSatandEarth. capabilitiesthebetween Test opticalcommunication historicaldocumentation Recordimagesof the ICPS for (ICPS) PropulsionCryogenicStage operationswiththe Interim Will demonstrateproximity ItalianSpace Agency(ASI) Italiancompany for Argotecthe Lunarmissiondesignedbythe ArgoMoon Advances Advances and Experience CubeSatin Propulsion Technologies System Hybrid MicroHybrid Propulsion System – VACCO Industries 15 VACCO Micro Propulsion Systems MonopropellantThruster LMP103S 100mN ADN (LMP Fill Fill Port ArgoMoon Propellant - Tank 103S) Advances Advances and Experience CubeSatin Propulsion Technologies System Thrusters, (4)Places 25mN ColdGas Hybrid MicroHybrid Propulsion System LeadWires (2)Places (3) Interrupts Against R (3) Interrupts Against LMP R134a Pressurant / ACSPropellant Green LMP Self EM Customer is - - 1 CubeSat Contained Propulsion System: UN / US 1.4S (Commercial Aircraft) Qualified for Skybox Flight Proven on PRISMA ACSMinimum Impulse Bit: <1.25mN RS422 Data Bus Interface 9V to 12.6V Input Voltage Sensor Suite Built Normally All (4) 25mN Cold Gas ACS Thrusters: (1) Axial100mN LMP - Welded Titanium AlloyConstruction - In, In, Shielded Controller - Double Canted 15 130S Monopropellant: Argotec – - VACCO Industries Closed Frictionless Valves in Italy - 134a Leakage - 103S Leakage - 103S Delta ° in Pairs - V Thruster - Sec 16 VACCO Micro Propulsion Systems Advances Advances and Experience CubeSatin Propulsion Technologies System JPL/MSFC Lunar Flashlight Mission FlashlightLunar JPL/MSFC • • Key Technical Constraints • • Measurements: • Mission Objectives: permanently Map surficial waterlunar in ice Surface month maximum30 mission duration region potentialwith deposits. ice Multiple polar overlunar south passes quantity waterof ice ratiosto indicate presence the and d Using the illumination strategies – ifference in reflected light laser VACCO Industries - shadowedregions : 17 VACCO Micro Propulsion Systems Power Power / Data Connector VACCO Lunar Flashlight Micro PropulsionFlashlightMicro System Lunar VACCO LMP Advances Advances and Experience CubeSatin Propulsion Technologies System Manifold Tank - 103S 103S Thrusters 100mN LMP (4)Places - Range Safety Features: Self - Contained Delta Safe Safe and Arm Circuit Benign GHe Pressurant (3) Interrupts Against Leakage Green ADNMonopropellant: Minimum Impulse Bit: <5mN Full Sensor Suite RS422 Data Bus Interface 15 watts whilefiring 5V & 28V Input Voltage Built Normally All Provides Pitch, Yaw,Roll and Delta (4) 100mN ADN Thrusters - Welded Titanium AlloyConstruction - In, In, Shielded Controller UN / US 1.4S (Commercial Aircraft) Qualified for Skybox Flight Proven on PRISMA - Closed Frictionless Valves – VACCO Industries - V Propulsion System: - Sec - V 18 VACCO Micro Propulsion Systems Piezoelectric Actuator NASA MSFC ISAT Iodine PropulsionIodineISATExperiment Flight MSFC NASA Redundant Heaters Advances Advances and Experience CubeSatin Propulsion Technologies System Inconel Valve Manifold (2)ProportionalVACCO Flow Flow Control Valves    (5) flight units (4 delivered to delivered (4 units flight (5) VACCOfor contract under currently MSFC. and both GRC at tested fire hot units VACCO development (2) supplied cathode. anode and to flow vapor Valves iodine control proportionately – VACCO Industries - date). 19 VACCO Micro Propulsion Systems RF RF Thruster 2,000psi Xenon Storage Storage Tank 6U Xenon Propellant Management System (PMS) System Management XenonPropellant 6U Cathode Advances Advances and Experience CubeSatin Propulsion Technologies System 2,000 psi psi 2,000 Xenon Manifold Titanium HighPressure Transducer System Filter Transducer Flow Flow Control Proportional Pressure Valve P NC ValveNC Fill Port Isolation Fill Fill Port w/Cap Valve Proportional NC Valve Flow ResistorsFlow 17 x 8.4 x 6.4 cm envelope cm 6.4 8.4 x 17 x FlowFixed Ratio for Resistors Flow Valve.Proportional High Pressure with Cap. Fill Port Normally High Pressure High Pressure Transducer. Filter.System 10 micron psi. 2,000 @ 71 cm3 Capacity: Storage Qualified FullyComponents. All PMS. the Face of Front the to Mounts and Cathode RF 3W Thruster System.and FeedXenon Storage VACCOThe Highly a is PMS - Welded Titanium Assembly. – VACCO Industries Cathode Anode - Closed Valve. Closed - Integrated . 20 VACCO Micro Propulsion Systems Advances Advances and Experience CubeSatin Propulsion Technologies System Summary Materials of Materials Construction: Various Propellants: Smart & Versatile Self for Solutions Delta and ACS VACCO has a Variety Micro of Propulsion Tyvakon Proven Flight NanoACE - Contained SystemsContained               Inconel Aluminum Titanium LMP R236fa, R134a, Isobutane Xenon & Iodine EPFeed Systems Argotec ArgoMoon Hybrid EM JAXA Omotenashi EM SwRICuSP EM JPL/NASA NEAScout EM JPL/NASA Lunar Flashlight EM JPL MarCO MiPS NASA/TyvakCPOD MiPS TyvakNanoACE - 103S, AF – VACCO Industries - M315E, Xenon & Iodine - 1 MiPS - V: - 1 MiPS - 1 MiPS - 1 MiPS - 1 MiPS 21