Overview of Proximity Operations Missions Relevant to NanoSats

Transcription

1 Overview of Proximity Operations Missions Relevant to NanoSats Scott MacGillivray, President Tyvak Nano-Satellite Systems LLC (714) April 2012 This document does not contain technical data within the definition contained in the International Traffic in Arms Regulations (ITAR) and the Export Administration Regulations (EAR), as such, it is releasable by any means to any person whether in the U. S. or abroad. Copyright Unpublished All rights reserved under the copyright laws by Tyvak Nano-Satellite Systems LLC.

2 DARPA Orbital Express Program Orbital Express (OE) Demonstrated the Technical Feasibility, Operational Utility, and Cost Effectiveness of Autonomous Techniques for On-Orbit Satellite Servicing The Specific Objectives Were to Develop and Demonstrate: A nonproprietary satellite servicing interface specification Orbit propellant transfer between a depot/serviceable satellite and a servicing satellite Component transfer and verified operation of the component Autonomous rendezvous, proximity operations, and capture Spacecraft Year Flown March 2007 Vehicle Mass Main Prox Ops Sensor Propulsion Orbital Express Boeing Phantom Works ~1100 kg (ASTRO) Advanced Video Guidance Sensor Vis-Star / ARCSS Hydrazine; 6 DOF (Used for fluid transfer as well) 2

3 Orbital Express On-Orbit Mission Goals 3

4 OE Autonomous Rendezvous and Capture Sensor System - ARCSS 4

5 Vis-STAR Software The Vis-STAR software provides the capability for passive relative range and attitude determination of a target, based on imaging sensor data only A real-time image correlation algorithm takes advantage of a priori knowledge, enabling relative navigation with respect to a completely passive client Virtually identical software operates with all ARCSS imaging sensors so that no additional hardware is required 5

6 Air Force XSS-10 Micro Satellite Program On-Orbit Demonstration of Autonomous Micro-Satellite Tracking and Inspection of a Resident Space Object (RSO) Demonstrated: Autonomous and manual control of Micro-Satellite on-orbit Autonomous navigation and inspection of object of interest (Delta 2nd Stage) by Micro-Sat Proof of Micro-Satellite architecture for Air Force mission areas Spacecraft XSS-10 Boeing Phantom Works Year Flown October 2001 Vehicle Mass Main Prox Ops Sensor Propulsion 56 kg Visible Camera System Hydrazine 6

7 XSS-10 Sensor Suite Configuration Visible Camera System (VCS) Star Tracker camera/fixed focus imager Developed and field tested on XSS-10 Dual FPAs: 768 (H) x 494 (V) 6.8 deg (H) x 5.1 deg (V) (Imager) 20.4 deg(h) x 15.3 deg (V) (Star Track) Sensitivity: Mv 7.2 Star Resolution m Weight: 3.6 lb Power: 14 watt 7

8 NASA/JPL Micro-Inspector Demonstrate a Micro-Spacecraft Platform Capable of External Visual Inspection of a Host Spacecraft in Space Conditions Provide Inspection That Does not Interfere with the Host Primary Mission Spacecraft Micro-Inspector NASA Jet Propulsion Lab Year Flown N/A [1 st Qtr Review, June 2005] Vehicle Mass Vehicle Power Main Prox Ops Sensor Propulsion 5.5 kg 11.7 W (Nominal) Structured Light Hazard Avoidance System Laser Illuminated, Vision Based (<10m) 8 Cold Gas (Iso-Butane) thrusters Structured Light Hazard Avoidance Subsystem Showing Laser Projection 8

9 Micro-Inspector Baseline Design Sandwich Structure Multifunctional Tank (MFT) Multilayer Circuit Board (MCB) Solar Panel Assembly (SPA) Solar Panel is Thermally Isolated Thin fiberglass standoffs provide structural support Long, small gauge wires connect antenna, solar cells, and temperature sensor from SPA to circuit board Electrochromic Surface Mounted to Bottom Side of Tank Payload Components Mounted on Standoffs over Circuit Board Underneath Solar Panel and Mounted Through tank Battery assemblies (x2) Gyro Cameras (x3) Micro Sun Sensor Laser Laser Grating Multilayer Circuit Board Pressure Sensor Gyro +X Camera Micro Sun Sensor Standoff Solar Panel Assembly Collision Multifunctional Tank Avoidance Camera -Z Camera Battery Housing (1 of 2) Liquid Valve Thruster (1 of 8) 9

10 NASA JSC Mini AERCam Program Nanosatellite Free-Flyer Intended for Future External Inspection and Remote Viewing of Human Spaceflight Activities Mini AERCam is Follow-On Program to AERCam Sprint flown on STS-87 in 1987 Spacecraft Year Flown Vehicle Mass Vehicle Power Main Sensor Propulsion NASA JSC Micro-Inspector N/A (fully functional prototype) 5 kg 15 W (Rechargeable Batteries) NTSC-Quality color cameras. High resolution still imagery. Primary human in the loop operation, some autonomous hold capability. Relative GPS Navigation Cold Gas, Xenon. 12 Thrusters 10

11 Full Vehicle Exploded View 11

12 University NanoSat Program (UNP) Bandit Vehicle Demonstrate On-Orbit Navigation and Control Repeatedly deployable, studentdesigned & built service vehicle Adaptable for future on-orbit servicing missions Navigation: Actuators: 6 DOF cold-gas propulsion system Sensors: Thrusters, Rate Gyros and Image-based sensing Structure and Mechanisms: Extended CubeSat-type Structure in a heavily modified MEPSI/ PPOD style launcher. Spacecraft Year Flown Vehicle Mass Main Sensor Propulsion Micro-Inspector Washington University, St Louis N/A. Circa 2006 (Design Work) 4 kg Visible Camera Cold Gas, 6 DOF Command and Data Handling: Atmega128-based processor; latch-up protection Communications: Linx Radio 418-LC-S transmitter and receiver chips(4 dbm out, 4800 baud) near 418 MHz Short-range video relay Imaging: C3188A CMOS Camera Xilinx FPGA for image processing (on host) 12

13 Bandit Dock Design Launch Containment in Bay Similar to P-POD with Sliding Door and Locking Drive On-orbit Dock is co-located Soft dock Consisting of Hook-and Loop Fasteners on a Mobile Pullrod Pullrod Charging Plate Hook and Loop Electrically Conducting Self-Gripping Fasteners 13

14 JAXA Minerva Vehicle - Released from Japanese Hayabusa Spacecraft 16-Sided Prism Measuring 12 cm in Diameter and 10 Centimeters in Height Released from Hayabusa During its Descent to Itokawa Asteroid Designed to Move Around on the Asteroid Autonomously by Hopping Perform Observations with a Camera and Thermometer Spacecraft Year Flown Vehicle Mass Main Sensor Propulsion Minerva Japan Aerospace Exploration Agency (JAXA) November, 2005 (released) kg Imaging Camera None. Mechanical Hopping Image of Hayabusa's solar panel taken by MINERVA 14

15 Thank You!