FactSheet_v12
- 1. Mission Description Project Status Virtual Telescope Inertial Alignment CANYVAL-X is a technology demonstration CubeSat mission with a primary objective of validating technologies that allow two spacecraft to fly in formation along an inertial line-of-sight (i.e., align two spacecraft to an inertial source). Demonstration of precision dual-spacecraft alignment achieving fine angular precision enables a variety of cutting-edge heliophysics and astrophysics science. The GeorgeWashington University Micro-propulsion and Nanotechnology Lab ， Developed mCAT analog electronics and control design, based on system developed for BRICSAT mission. ， Delivered mCAT thruster heads Yonsei University ， Designed, built, and tested the 1U and 2U spacecraft and are currently integrating the mCAT. ， Spacecraft environmental testing at KARI. ， Developed ground system to conduct mission operations and alignment experiment. NASA ， Delivered Miniature Fine Sun Sensor C provides attitude measurement for 2U spacecraft. ， Completed GeorgeWashington University Micro Cathode ArcThruster (mCAT) flight electronics, performed system testing, and delivered mCAT - provides thrust for 2U cubesat. ， Conducting an assessment of CANYVAL-X¨s GN&C in regards to formation acquisition and alignment. ，Traveled toYonsei to collaborate with team. Launch on Falcon9 in mid-2016. Mission Goal: CubeSat Demonstration of Virtual Telescope Alignment Technology in Space 1U Passive Target CubeSat (JERRY) CubeSat Astronomy by NASA and Yonsei using Virtual Telescope Alignment eXperiment 9.22＜ 120＜ 10m 1.7m Alignment Camera FOV Orbit Laser Diode Beacon Deployable Solar Panel Magnetometer GPS Receiver Battery 30Wh MicroReactionWheel3-axis MicroReactionWheel&PPUMount UHFTRX OBC S-BandTX Payload Board Camera UHF Antenna S-Band Patch Antenna mCAT DNC EPS Sun sensor GPS Patch Antenna Solar Panel w/ Magnetorquer -X, + -Y, -Z UHF Antenna Antenna Deployer Sun sensor Laser Diode Access Port GPS Antenna Solar Panel Hinge NASA Delivered Hardware Fine Sun SensormCAT (GWU/NASA) (NASA) Delivered Sept 2015 Delivered June 2015 CANYVAL-XCANYVAL-X Partnership 2U Actively Controlled CubeSat (TOM) Deployable Solar Panel Magnetometer GPS Receiver Battery 30Wh MicroReactionWheel3-axis MicroReactionWheel&PPUMount UHFTRX OBC S-BandTX Payload Board Camera UHF Antenna S-Band Patch Antenna mCAT DNC EPS Sun sensor GP Antenn Sun GPS Antenna Solar Panel Hinge NASA,Yonsei University, andThe GeorgeWashington University are collaborating to develop the mission. CANYVAL-X Spacecraft
- 2. CubeSat Astronomy by NASA and Yonsei using Virtual Telescope Alignment eXperiment CANYVAL-X Teams Road Map to Cutting Edge Science CANYVAL-XCANYVAL-X Ground/Lab Demo of ComponentTechnologies In-space alignment experiment In-space science-class virtual telescope Astronomy Heliophysics CANYVAL-X matures formation alignment technology enabling the next-generation of distributed space virtual telescopes. Mission and GNC Specification Properties Value JERRY TOM Mission LifeTime 3-6 month Payload 3 Laser Diodes Visible Camera (NanoCam) Payload Performance Half Intensity Beam Angle = ＼60＜ Min- imum angle (15.5＜) intensity > 96% 2048 x 1536 pixels CMOS sensor 35mm lens/ F1.9, 9.22＜ FOV GN&C (Magnetorquer, sun sensor) mCAT, Sun Sensor, Nano- Cam, Reaction Wheels, Mag TorqRods Data Rate Up/Downlink: 4.8 kbps (UHF) Uplink: 4 Bkbps (UHF) Downlink 100 kbps (S-band) Mass 1.0 kg 2.7 kg Relative Distance > 10m (Collision Avoidance) Orbit Control GWU 20cm (1 DOF mCAT x4+3axis Reaction Wheel) Orbit Determination Each Axis ＼ 10cm (GPS) Attitude Control 5＜ (Magnetorquer) 10m x tan(5＜)=88cm 1＜ (Reaction Wheel) 10m x tan(1＜)=18cm NASA Programmatic Point of Contact: Neerav Shah, Neerav.Shah-1@nasa.gov Credit: ESA NASA Yonsei TheGeorgeWashingtonUniversity