VACCO ChEMS Micro Propulsion Systems Advances and Experience in CubeSat Propulsion System Technologies
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1 VACCO ChEMS Micro Propulsion Systems Advances and Experience in CubeSat Propulsion System Technologies May 1 st, 2018 VACCO Proprietary Data Shall Not Be Disclosed Without Written Permission of VACCO
2 VACCO Industries 2
3 Tyvak NanoACE Micro Propulsion System NanoACE Launched 7 July 2017 Contract with Tyvak Nano-Satellite Systems Inc. Occupies Center 1U of 3U Cubesat Provides Attitude Control, Divert & Delta-V Photo: Terran Orbital 3
4 NASA/Tyvak CPOD Micro Propulsion System Contract with Tyvak Nano-Satellite Systems Inc. CPOD: NASA Cubesat Proximity Operations Demonstration (2) Flight Systems Delivered Occupies Center 1U of 3U Cubesat Provides Attitude Control, Divert & Delta-V Photo: Terran Orbital 4
5 CPOD Micro Propulsion System Overview System Overview All-Welded Aluminum Alloy Construction Eight 10mN Cold Gas Thrusters 174 N-S Total Impulse, 31 m/s Delta-V 0.10 mn-s Minimum Impulse Bit 1U Center Manifold, Clamshell Configuration 510 grams Self-Pressurizing R236fa Green Propellant Smart System with Integral Microcontroller RS422 Digital Interface Integral Sensor Suite Total Wet Mass: 1270 grams 5
6 JPL Mars Cube One (MarCO) Mission Mission Objective: Provide an 8kbps real-time relay for InSight s Entry, Descent and Landing at Mars Two Units will be Launched with the InSight Mission May
7 JPL MarCO Micro Propulsion System (4) AXIAL THRUSTERS STORAGE TANK (4) RCS THRUSTERS First Interplanetary Cubesat Launch with InSight Lander, May 2018 Smart, Self-Contained Propulsion System: Contract for (2) Flight Systems 755 N-Sec Total Impulse 3490 gram Wet Mass System-in-a-Tank Design Including: Propellant Storage & Feed System (4) Axial & (4) RCS 25mN Thrusters Controller & Sensor Suite Two Interrupts Against Leakage Low Power Continuous Power (<15 watts) All-Welded Aluminum Alloy Construction Microcontroller Driven: RS422 Digital Interface Controls Burn Type & Duration Closed-Loop, Variable Thrust Control (3) Settable Thermal Control Zones (3) Power Supplies, (9) Valve Drivers 7
8 JPL/MSFC Near Earth Asteroid Scout Mission Target Mission Objectives: Detect, rendezvous with and flyby a Near Earth Asteroid (NEA) target Characterize physical properties: volume, spectral type, spin mode and orbit 80% coverage imaging at 50 cm/px 30% coverage imaging at 10 cm/px Main Propulsion: ~80m² Solar Sail 8
9 NEA Scout Micro Propulsion System Smart, Self-Contained Cold Gas Propulsion System based on MarCO: Contract for (1) Flight System 500 N-Sec Total Impulse 2600 gram Wet Mass System-in-a-Tank Design Including: Propellant Storage & Feed System (2) Axial & (4) RCS 25mN Thrusters Controller & Sensor Suite Three Interrupts Against Leakage Power: <9 watts while Firing All-Welded Aluminum Alloy Construction 9
10 SWRI CubeSat Mission to Study Solar Particles (CuSP) VACCO CuSP MiPS CuSP Mission Objectives: 1. Study Solar Particles in interplanetary space 2. Be a Pathfinder for creating a network of Space Weather Stations 3. Strengthen the case for CubeSats as a viable platform for performing High Value Science 4. Raise the TRL of the SIS instrument for future missions 10
11 CuSP Micro Propulsion System 25 mn Thrusters (4) places Fill Port (Thruster) Smart, Self-Contained Cold Gas Propulsion System based on MarCO: Contract for (1) Flight System System-in-a-Tank Design Including: Propellant Storage & Feed System (4) RCS 25mN Thrusters Controller & Sensor Suite Two Interrupts Against Leakage Power: <12 watts while Firing All-Welded Aluminum Alloy Construction Electrical Connector Manifold 11
12 JAXA Nano Impactor (Omotenashi) CubeSat OMOTENASHI: Lunar mission designed jointly by the Japan Aerospace Exploration Agency (JAXA) and the University of Tokyo. Will demonstrate low-cost exploration of the lunar surface. 6U CubeSat to be put onto a course to the moon. The probe performs a semi-hard landing at a velocity of about 30 m/s. 12
13 Omotenashi MiPS 25mN Cold Gas Thrusters, (4) Places Propellant Tank Manifold (2) Identical RCS Assemblies (left & right): Self-Contained Delta-V / RCS Systems (4) 25mN Cold Gas Thrusters in Each: (2) Axial, Pitch / Yaw (2) Roll Control All-Welded Aluminum Alloy Construction Normally-Closed Frictionless Valves Built-In, Shielded Control Electronics 9V to 12.6V Unregulated Input Voltage RS422 Data Bus Interface Integral Pressure & Temperature Sensors Minimum Impulse Bit: <4.0mN-Sec Range Safety Features: Green R236fa Propellant: Benign Fire Extinguisher Material Max Pressure <0.69MPa (<100 psi) (3) Interrupts Against Propellant Leakage 13
14 Green Monopropellant Micro Propulsion Systems ECAPS 1N ADN Thruster on PRISMA ECAPS 100mN ADN Hot Fire Test VACCO Proprietary Data Shall Not Be Disclosed Without Written Permission of VACCO
15 ArgoMoon Hybrid Micro Propulsion System ArgoMoon Lunar mission designed by the Italian company Argotec for the Italian Space Agency (ASI) Will demonstrate proximity operations with the Interim Cryogenic Propulsion Stage (ICPS) Record images of the ICPS for historical documentation Test optical communication capabilities between the CubeSat and Earth. 15
16 ArgoMoon Hybrid Micro Propulsion System LMP103S Fill Port Propellant Tank 25mN Cold Gas Thrusters, (4) Places Customer is Argotec in Italy EM-1 CubeSat Self-Contained Propulsion System: (1) Axial 100mN LMP-103S Delta-V Thruster (4) 25mN Cold Gas ACS Thrusters: Double Canted 15 in Pairs All-Welded Titanium Alloy Construction Normally-Closed Frictionless Valves Built-In, Shielded Controller Sensor Suite 9V to 12.6V Input Voltage RS422 Data Bus Interface ACS Minimum Impulse Bit: <1.25mN-Sec Green LMP-130S Monopropellant: 100mN ADN (LMP-103S) Monopropellant Thruster Lead Wires (2) Places Flight Proven on PRISMA Qualified for Skybox UN / US 1.4S (Commercial Aircraft) R134a Pressurant / ACS Propellant (3) Interrupts Against LMP-103S Leakage (3) Interrupts Against R-134a Leakage 16
17 JPL/MSFC Lunar Flashlight Mission Mission Objectives: Map surficial lunar water ice in permanently-shadowed regions Measurements: Using the difference in reflected laser light ratios to indicate the presence and quantity of water ice Multiple passes over lunar south polar region with potential ice deposits. Key Technical Constraints: 30 month maximum mission duration Surface illumination strategies 17
18 VACCO Lunar Flashlight Micro Propulsion System Self-Contained Delta-V Propulsion System: LMP-103S Tank (4) 100mN ADN Thrusters Provides Pitch, Yaw, Roll and Delta-V All-Welded Titanium Alloy Construction Normally-Closed Frictionless Valves Built-In, Shielded Controller 5V & 28V Input Voltage 15 watts while firing RS422 Data Bus Interface Full Sensor Suite Minimum Impulse Bit: <5mN-Sec Range Safety Features: Green ADN Monopropellant: Flight Proven on PRISMA Power / Data Connector Manifold 100mN LMP- 103S Thrusters (4) Places Qualified for Skybox UN / US 1.4S (Commercial Aircraft) (3) Interrupts Against Leakage Benign GHe Pressurant Safe and Arm Circuit 18
19 NASA MSFC ISAT Iodine Propulsion Flight Experiment Inconel Valve Manifold Valves proportionately control iodine vapor flow to anode and cathode. VACCO supplied (2) development units hot fire tested at both GRC and MSFC. VACCO currently under contract for (5) flight units (4 delivered to-date). (2) VACCO Proportional Flow Control Valves Piezoelectric Actuator Redundant Heaters 19
20 6U Xenon Propellant Management System (PMS) 2,000 psi Xenon Storage Tank RF Thruster Cathode Titanium Manifold 2,000 psi Xenon Proportional Flow Control Valve Fill Port w/cap NC Isolation Valve High Pressure Transducer System Filter Pressure Transducer P NC Valve Proportional Valve The VACCO PMS is a Highly-Integrated Xenon Storage and Feed System. 3W RF Thruster and Cathode Mounts to the Front Face of the PMS. All-Welded Titanium Assembly. Fully Qualified Components. Storage Capacity: 71 2,000 psi. 10 micron System Filter. High Pressure Transducer. High Pressure Normally-Closed Valve. Fill Port with Cap. High Pressure Proportional Valve. Flow Resistors for Fixed Flow Ratio. 17 x 8.4 x 6.4 cm envelope Flow Resistors Anode Cathode Fill Port 20
21 Summary Flight Proven on Tyvak NanoACE VACCO has a Variety of Micro Propulsion Solutions for ACS and Delta-V: Tyvak NanoACE NASA/Tyvak CPOD MiPS JPL MarCO MiPS JPL/NASA Lunar Flashlight EM-1 MiPS JPL/NASA NEAScout EM-1 MiPS SwRI CuSP EM-1 MiPS JAXA Omotenashi EM-1 MiPS Argotec ArgoMoon Hybrid EM-1 MiPS Xenon & Iodine EP Feed Systems Self-Contained Systems Smart & Versatile Various Propellants: R236fa, R134a, Isobutane LMP-103S, AF-M315E, Xenon & Iodine Materials of Construction: Titanium Aluminum Inconel 21
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