Revision C June 5, Author: Ryan Connolly
|
|
- Gerald Collins
- 5 years ago
- Views:
Transcription
1 The P-POD Payload Planner s Guide Revision C June 5, 2000 Author: Ryan Connolly
2 P-POD Payload Planner s Guide: Revision B 5/15/00 2 of INTRODUCTION The Space Development, Manufacturing & Integration (SDMI) Team is positioning Cal Poly, San Luis Obispo to be at the center of small satellite development. Working with Stanford s Space Systems Development Laboratory (SSDL), the goal is to produce a standardized platform for small orbital experiments. Known as CubeSats, these tiny space vehicles are classified as PicoSatellites, meaning that the entire satellite weighs less then one kilogram. The 10-centimeter cubes are designed to house small experiments that otherwise would be cost-prohibitive to flight validate. Universities, alongside industrial and governmental interests, will be able to place their own CubeSats into orbit using our standardized deployment system. Cal Poly s own satellite, PolySat, will be one of the first of these new CubeSats. The SDMI is leading the way in the development of this deployment system known as the P-POD (Poly Picosatellite Orbital Deployer). The two versions of the deployer will mount to various launch vehicles, including the Delta II and the Minotaur. The maiden voyage for P-POD1 and P-POD2, along with PolySat is tentatively scheduled for Late Summer The total number of CubeSats launched is yet unknown, but the manifest could reach upwards of fifteen CubeSats on the maiden voyage. Cal Poly will oversee CubeSat development worldwide, and shall orchestrate all launching services with the launch providers. The integration design team is responsible for overseeing all incoming CubeSats, and verifying that they meet the design requirements set forth in the P-POD Payload Planner s Guide, which will be available to all interested parties. This ambitious interdisciplinary project, with students from all engineering majors and even several non-engineering majors, embodies the Cal Poly Learn by Doing credo in every respect. The purpose of the Payload Planner s Guide is to define clearly and carefully all CubeSat design requirements and all requirements for their interface with the deployer. This document is divided into the following sections: 1. Introduction 2. CubeSat Deployer Description 3. CubeSat Physical and Electrical Requirements 4. CubeSat Operational Requirements 5. Delivery Deadlines and Pricing Please refer to the SDMI website for more information regarding the project:
3 P-POD Payload Planner s Guide: Revision B 5/15/00 3 of PICOSATELLITE DEPLOYER DESCRIPTION This section of the document shall provide an overview of the CubeSat environment while onboard the deployer. The CubeSat provider shall be briefed on the following criteria required for integration into the deployer: 2.1 Deployer System Overview 2.2 CubeSat Containment and Deployer Interface 2.3 CubeSat Launch Environment 2.4 P-POD Orbital Environment Please refer to Section 3 for explicit CubeSat requirements. 2.1 Deployer System Overview The P-POD System has two distinct release platforms, each with a unique deployer that has different requirements on the CubeSats themselves Platform #1: P-POD1 With this configuration, the deployment system requires less design refinement for the CubeSats. The published specification tolerances for the CubeSat, as well as the outer mounting surface area provide for easier manufacturing of the CubeSats. The ultimate aim of this system is to provide deployment services to clients with limited manufacturing capabilities, such as universities and high schools, since the P-POD1 can accept a wider variation in CubeSat design. The mounting configuration for P-POD1 has three CubeSats per POD, with each CubeSat located by their corners via a series of mounting blocks. The three CubeSats sit next to one another on a base that slides vertically on roller slides, and two doors, which remain closed and locked until deployment, confine the entire base. Two Compression Springs provide the launching force, and the doors are opened via a cam system that ensures that the doors are fully opened when the base reaches its maximum height. Figure 2.1. P-POD1 Concept Model. (Left: Doors Open Right: Doors Closed) Note: As of the publishing date of this document, the P-POD1 is still under design review. Anticipated release of all design documentation is Winter No further mention of the P-POD1 design shall take place in this edition of the Payload Planner s Guide.
4 P-POD Payload Planner s Guide: Revision B 5/15/00 4 of Platform #2: P-POD2 This configuration of the deployment system, which is in the final design phase, represents the method of deployment for all customers. CubeSats aimed for deployment in P-POD2 must meet tighter tolerances and stricter design requirements, therefore limiting clients to those with highly accurate manufacturing capabilities. The deployment device consists of a series of machined aluminum tubes, with each tube composing one unit, or pod. Each pod is modular and can be assembled in a variety of configurations with other pods to accommodate many launch vehicle requirements. A single spring handles the deployment force, and a hinged spring-loaded door at one end of the tube restrains the CubeSats. A non-explosive actuator releases the door. Three CubeSats shall be positioned in each P-POD2 unit, with a 6.5 mm clearance distance from all six sides of the CubeSats. This clearance distance allows for mounting of any external features (solar panels, antennas, etc.) that extend above the CubeSat surface. Four 7mm standoffs shall be included (on two opposing sides) in the structure of each CubeSat in order to achieve proper spacing between each satellite within the launch tube. Detailed drawings of the deployer and CubeSat form factors can be found in Appendix A. Figure 2.2. Artist s conception of P-POD2 Deployment Device
5 P-POD Payload Planner s Guide: Revision B 5/15/00 5 of CubeSat Containment and Deployer Interface The CubeSats, when loading within the deployer, shall be constrained by the rail system of the tube, as well as secondary loading washers pressing them against the secured door. The rail design prevents jamming of the CubeSats during deployment, but requires tight tolerances on the outside dimensions of the CubeSats. The designated rail contact surfaces on each CubeSat must have a smooth surface finish, as detailed in the CubeSat requirements drawings in Appendix A. When loaded into the deployer, all CubeSat power must be completely off, and the CubeSats may only be powered on once clear of the tube. To accomplish this, killswitches (microswitches) must be mounted to the exterior of each CubeSat (in designated areas stipulated on the requirements drawings) to turn off all power when compressed. Also, the microswitches must be flush with the CubeSat surface when compressed. In addition to the kill-switches, a remove before flight pin must be furnished in the location stipulated on the CubeSat requirements drawings. This provides a universal method to ensure all CubeSats remain dormant during loading into the deployer. Additionally, an optional USB data port may be provided on the CubeSats in the location shown on the specification drawings. Access to the port will be provided on the deployer tube, such that final access to the CubeSat is available after integration to the deployer CubeSat Launch Environment The CubeSats shall be launched with an exit velocity between 0.5 and 1 foot per second. The CubeSats shall have a small relative velocity and will remain close to one another for a relatively long time. No intentional spin is imparted to the CubeSat during launch P-POD Orbital Environment The P-POD2 system may be launched aboard the OSP Space Launch Vehicle, and hardmounted to the JAWSAT satellite as its primary payload. The details of the orbit and launch altitude are not yet known. Additional launch possibilities may arise, and any changes shall be published immediately. The launch vector of the CubeSats with respect to Earth and launch vehicle will be unknown at the time of deployment, and all clients must accept this factor at time of CubeSat installation into the Deployer. P-POD2 shall experience the space vacuum and radiation dosage of a typical low-earth orbit environment. Predicted temperatures range from -40 C to 80 C, and large temperature fluctuations are possible. There will be no thermal control within P-POD2, so all CubeSats must be able to withstand these environmental fluctuations.
6 P-POD Payload Planner s Guide: Revision B 5/15/00 6 of CUBESAT PHYSICAL AND ELECTRICAL REQUIREMENTS This section of the document shall provide the physical (overall shape, size, weight) and electrical requirements for the CubeSats traveling aboard the P-POD2 system. The supplier testing criteria for the CubeSats is also outlined in this section, and should be used by CubeSat designers to design, construct, and test the satellites before delivery to Cal Poly. Any CubeSat that meets all of the requirements and passes all of the required tests shall be considered flight worthy by the P-POD team. Note: Once the design of P-POD1 is complete, requirements shall also be set forth for flight aboard that system as well Dimensions The CubeSat shall conform to the shape and size specified in the CubeSat specification drawings in Appendix A Mass Properties The CubeSat shall have a maximum mass of one kilogram. A requirement for the location of the center of mass for each CubeSat has not been established, but design teams should consult with Cal Poly before finalizing any design Materials All CubeSats must be constructed of, and contain, only NASA space qualified materials. Please refer to the Cal Poly Integration Team for questions concerning materials. No explosive devices or materials shall be used unless explicitly approved by the P-POD team. All surfaces that are designated on the CubeSat requirements specifications as rail interfacing shall be constructed to minimize friction at the rail/cubesat interface. All CubeSat shells shall be constructed of 7075 Aluminum to avoid any thermal mismatch between the deployer and CubeSat Electrical Requirements The CubeSats shall have no external electrical wire connections to the P-POD system Testing Requirements A modified, single CubeSat version of the deployer will be provided to each CubeSat design team to allow full environmental testing of the CubeSats. This Test-Tube will have mounting brackets for a 3-axis shake table test, and also will serve as the shipping container for the CubeSat.
7 P-POD Payload Planner s Guide: Revision B 5/15/00 7 of Vibration Tests The CubeSats shall successfully complete an independent vibration test simulating the expected launch load conditions Thermal Vacuum Tests The CubeSats shall successfully complete an independent thermal vacuum test simulating in-orbit conditions Electromagnetic Interference Testing The CubeSats shall successfully complete an independent electromagnetic interference test Integration Tests The CubeSats shall successfully complete a vibration test after integration with the P- POD2 system. The CubeSats shall successfully complete a thermal vacuum test after integration with the P-POD2 system. The CubeSats shall successfully complete a electromagnetic interference test after integration with the P-POD2 system. NOTE: The P-POD team must approve all independent testing and proof of results must be provided at time of delivery Adverse Affects of P-POD Thermal Affects The CubeSat operations shall not thermally affect P-POD2 in any adverse manner Electrical Affects The CubeSat operations shall not interfere with operations of the P-POD2 electrical system in any way Radio Frequency (RF) Effects The CubeSat operations may not interfere with the P-POD2 communication system in any way.
8 P-POD Payload Planner s Guide: Revision B 5/15/00 8 of Physical Effects The CubeSat operations cannot interfere with the normal operations of the P-POD2 structure or components. 4. CUBESAT OPERATIONAL REQUIREMENTS This section of the document outlines the operational requirements for each CubeSat. These requirements are necessary in order to ensure that no one CubeSat is a threat to any other within the same launch tube, or a threat to the mission as a whole. Because CubeSat deployment is the sole mission of P-POD, the highest level of importance is given to the CubeSat missions themselves. In this section, operational requirements are divided into three areas: 4.1. Pre-deployment operations: This sections covers preflight planning and testing to ensure that all CubeSats are flight-worthy and ready for integration into the deployer Deployment operations: The focus in this section is on the state in which the CubeSats must operate when contained within the deployer, and the methods allowed to activate the CubeSats upon deployment from P-POD Post-deployment operations: this section covers methods of communication between the CubeSat and ground station Pre-Deployment Requirements Testing Plans Each CubeSat design team must submit a plan and detailed procedure for the following validation tests: Vibration, Thermal-Vacuum, Electromagnetic Interference, and Integration. All test plans must be in accordance with the requirements set forth in Section 3 of this document. All results must be submitted to the P-POD team for review, and should be contained in a formal report. The CubeSat design teams shall perform all tests independently, and a member of the P- POD team will be available to aid of consult during each procedure. For the integration test, a joint team shall ensure proper interface between CubeSat and the deployer. In addition to pre-flight testing, each CubeSat team must provide a detailed list for preand post-launch checkout. This plan must indicate that the CubeSat is ready for the mission, and all internal systems are operating nominally. Once the CubeSat is deployed, the post-launch procedures shall be carried out to confirm that the CubeSat is able to begin its mission.
9 P-POD Payload Planner s Guide: Revision B 5/15/00 9 of Operations Guide The CubeSat design team must submit a formal operations guide to the P-POD team in order to outline the primary mission and identify the functions of the CubeSat s payload. This guide should also document the CubeSat s compliance with all of the requirements set forth in this document. Expected behavior of the CubeSat during the entire mission (Pre-deployment, deployment, post-deployment) shall also be documented within this guide. Uplink and downlink frequencies shall also be clearly documented to avoid communications error with the other CubeSats on the mission. All communications with the CubeSats are left to the CubeSat design teams. P-POD shall not provide any communication with any of the CubeSats prior, during, or after they are deployed. However, the deployer will relay launch information back to the ground station, which will verify if the CubeSats were properly deployed from the system Physical Constraints This section of the document outlines the method in which all CubeSats are loaded into the deployer to achieve proper dormancy in each satellite. A detailed procedure must be submitted to the P-POD design team, prior to launch, that will explain the proper loading procedure for each CubeSat in order to ensure that all power is turned off when loaded into the deployer. As stated in Section 3, all CubeSat operations (electromagnetic, electrical, etc.) must be suspended until the CubeSat is clear of the launch tube during deployment Deployment Requirements Because no single CubeSat s mission is seen as more important than any other during the mission, no CubeSat design team shall be given the choice of deployment times or vectors. All CubeSat design teams must agree that their mission may begin at any time, and should be ready to begin their mission within the defined launch window. Because each P-POD tube will contain up to three CubeSats, the CubeSat design teams must coordinate with one another concerning which tubes they will mount into. The P-POD design team will assign tubes and have the ultimate decision if any conflicts arise. CubeSats may only begin their missions upon exiting the deployment tube. No CubeSat may self-actuate until clear of the deployer. Also, no exterior components of the CubeSats, such as antennas or other devices, are allowed to contact the deployment tube. See CubeSat Specifications, Appendix A for details Post Deployment Requirements Once free of the deployer, the CubeSat should activate and begin communication with its ground station. At this time no ground station has been established for CubeSat communication, and we will supply all interested parties this information as soon as it becomes available.
10 P-POD Payload Planner s Guide: Revision B 5/15/00 10 of 19 Once the CubeSat s mission ends, it must not pose a threat to any other orbiting spacecraft. There must be proof that the CubeSat will de-orbit within a reasonable span of time after completing its mission. This proof should be given and documented in the CubeSat operations guide. 5. DELIVERY DEADLINES AND PRICING The current anticipated launch date for the P-POD2 maiden mission is Late Summer 2001, with a delivery date in Late Spring This requires constant and committed communication between the P-POD team and all CubeSat design teams. This final section of the document details the business-related aspects of the deployment system. Issues related to the following topics shall be covered: 5.1 P-POD Design Schedule 5.2 Design Reviews 5.3 Payload Planner s Guide Negotiations 5.4 Pricing 5.5 Contact Information 5.1. P-POD Design Schedule As stated above, the anticipated launch for P-POD and the CubeSats is August This launch opportunity is in the process of acquisition aboard the JAWSAT deployment vehicle on board the OSP Space Launch Vehicle. Table 5.1 outlines the major milestones and completion dates for the P-POD system. Milestone Completion Date Engineering Model Fabrication March 20, 2000 Flight Model Fabrication July 21, 2000 Environmental Testing of Flight Spacecraft September 1, 2000 Deployer Operational Verification October 1, 2000 Deployer Design Completion (Ready for Flight) December 1, 2000 Table 5.1. P-POD Completion Timeline
11 P-POD Payload Planner s Guide: Revision B 5/15/00 11 of 19 All CubeSats should follow the Timeline in Table 5.2: Milestone Completion Date Engineering Model Fabrication Summer, 2000 Flight Model Fabrication Mid-Fall, 2000 Environmental Testing of Flight Spacecraft Winter, 2001 Spacecraft Operational Verification Spring, 2001 CubeSat Delivery to Cal Poly Late Spring/Early Summer, 2001 Table 5.2. CubeSat Completion Timeline 5.2. Design Reviews The P-POD design team is currently scheduling weekly design reviews between the P- POD team and all CubeSat design teams. Once the CubeSat teams are identified, the P- POD team shall finalize the times for these reviews Payload Planner s Guide Negotiations The Payload Planner s Guide is a living document, and changes shall be made to this document as the P-POD design team sees fit. All CubeSat teams shall be given notice of the updates, and copies of the updated Guide provided immediately. If any CubeSat team feels that changes are required to this document, the P-POD design team shall put forth the highest degree of effort to see that those changes are made in a timely manner. If any problems should arise between the P-POD team and the CubeSat teams, Prof. Jordi Puig- Suari shall serve an arbitrator Pricing The P-POD Design team is providing launching and deployment services to all CubeSat teams. The price per CubeSat aboard the P-Pod system has not been determined. Please refer to the contact information at the end of this section for further details Contact Information The SDMI Student Project Leader is: Jeremy Schoos Voice: (805) jschoos@calpoly.edu
12 P-POD Payload Planner s Guide: Revision B 5/15/00 12 of 19 The Academic Advisor to the SDMI team is: Professor Jordi Puig-Suari Voice: (805) Fax: (805) jpuigsua@calpoly.edu Any questions related to this document or any other CubeSat questions should be directed towards the student project leader and carbon copied to Prof. Jordi Puig-Suari. Additional information concerning the P-POD system can be found at the following website:
13 P-POD Payload Planner s Guide: Revision B 5/15/00 13 of 19 Appendix A: CubeSat Design Requirements
14 P-POD Payload Planner s Guide: Revision B 5/15/00 14 of 19
15 P-POD Payload Planner s Guide: Revision B 5/15/00 15 of 19 Appendix B: Deployer Overview
16 P-POD Payload Planner s Guide: Revision B 5/15/00 16 of 19 The Poly Picosatellite Orbital Deployer has been designed to provide a reliable and inexpensive solution to picosatellite deployment in space. It is the intent that universities and industry will be able to use the PPOD as a means of deploying standardized multifunctional satellites in space. The Cal Poly WESTEC team has developed picosatellite specifications for universities and industry wishing to use the PPOD to deploy space bound experiments. These specifications can been seen in DWG in Appendix B. An exploded view of the PPOD mechanical assembly is shown in DWG It uses a pin-puller actuator to release the spring-loaded door. A compression spring provides the initial force to deploy three CubeSats loaded in the PPOD. The picosatellites will be loaded into the device using the configuration shown in DWG Design Criteria The following criteria was used in the development of the PPOD: Temperature Extremes: -40 C to 65 C Maximum Force during Launch: 15g s Mass of the deployer must be equal to or less than 1.50 kg [3.3 lb] The satellites will weigh no more than 1kg The satellites will be 10cm X 10cm X 10cm Must ensure that the picosatellites will not tumble upon launch Must deploy the satellites at an exit velocity of no greater than 0.3 m/s [1 ft/s] (the slower the better but they must get out) Must provide a faraday cage to shield against any premature transmission from the picosatellites Must not be a threat to any other mission aboard the rocket Must be able to accommodate satellites with solar panels mounted on the external walls PPOD Design Results Material: 7075-T7351 AL Mass (empty): 1.67kg [3.7 lb] Fasteners: 6-32 machine screws and lock washers Spring Specs: Constant =.85 lb/in Free Length = 15 in. Solid Ht. = 1.5in
17 P-POD Payload Planner s Guide: Revision B 5/15/00 17 of 19 Part-by-Part Notes DOOR: DWG The door of the PPOD was designed to be as light as possible without sacrificing strength. The thickness of the door is in with portions trussed out to for weight reduction purposes. The pin-puller locates its pin through a 0.081in hole in one of the two flanges on the bottom of the door. When the pin on the actuator is triggered, the door will open as a result of the force applied by the torsion spring. It is intended that the force opening the door of the deployer will be strong enough to accelerate the door such that there will be no contact with the top picosatellite as it accelerates out of the deployer. This would prevent the satellite from tumbling upon deployment. The torsion spring and compression spring may need to be adjusted if future testing proves them ineffective in this respect. HINGE ROD: DWG The hinge rod is a 0.25in diameter steel rod. The door pivots about this rod. SIDE A: DWG There are two Side A parts to each PPOD deployer. The function of the Side A part is to act as a structural member of the assembly as well as a faraday cage. Side A has three in thick bars across the bottom, middle, and top of the part. These bars will eventually serve as mounting surfaces when the attachment configuration has been determined. The thicker material is needed in order to use countersunk fasteners for the final mounting configuration. The remaining material is in with portions trussed out to.030 in for weight reduction purposes. The rails are to provide a sliding surface for the picosatellites as they are being deployed. The rails will be treated with a Dicronite coating to reduce the coefficient of friction and to serve as a protective coating. By doing thermal expansion calculations for the given geometries, it was determined a in spacing could be left between the picosatellite side and each rail (see calculations in Appendix B). This would ensure that any expansion would not wedge the satellite inside the deployer. A +/-.005 in tolerance is also required for each picosatellite deployed using the PPOD. There are 12 holes in Side A for the 6-32 machine screws to pass through. These holes are not tapped. SIDE B: DWG There are 2 Side B parts to each PPOD deployer. The Side B parts are identical to the Side A parts except for their width and the location of the holes. The holes in Side B are drilled and tapped blind holes for the 6-32 machine screws. SLIDE: DWG
18 P-POD Payload Planner s Guide: Revision B 5/15/00 18 of 19 The slide is mounted on the compression spring and moves up and down throughout the assembly. The long legs serve to prevent any jamming against the rails within the launch tube. SPRING: DWG The spring has a free length of 15in and a solid height of 1.5in with a constant of 0.85 lb/in. It was designed based on providing a 3 kg mass an exit velocity of 1ft/s BASE: DWG The base is 0.25 inches thick and completes the enclosure of the PPOD. It has a circular pocket to locate the spring and to serve as weight reduction. The spring is attached to the base using a flat sheet metal part and small machine screws. There are four drilled and tapped blind holes that are used to fasten sides to the base. HINGE A & B: DWG & DWG The hinges A & B are mirror images of one another. They are used to locate the 0.25in rod, torsion spring, and the door to Side B.
19 P-POD Payload Planner s Guide: Revision B 5/15/00 19 of 19
Poly Picosatellite Orbital Deployer Mk. III Rev. E User Guide
The CubeSat Program California Polytechnic State University San Luis Obispo, CA 93407 X Document Classification Public Domain ITAR Controlled Internal Only Poly Picosatellite Orbital Deployer Mk. III Rev.
More informationCubeSat Design Specification
Document Classification X Public Domain ITAR Controlled Internal Only CubeSat Design Specification (CDS) Revision Date Author Change Log 8 N/A Simon Lee N/A 8.1 5/26/05 Amy Hutputanasin Formatting updated.
More informationNanoRacks CubeSat Deployer (NRCSD) Interface Control Document
NanoRacks CubeSat Deployer (NRCSD) Interface Control Document NanoRacks, LLC 18100 Upper Bay Road, Suite 150 Houston, TX 77058 (815) 425-8553 www.nanoracks.com Version Date Author Approved Details.1 5/7/13
More informationCubeSat Test Pod User s Guide Revision IV June, 2005
Contacts: CubeSat Test Pod User s Guide Revision IV June, 2005 Cal Poly, San Luis Obispo Stanford University Prof. Jordi Puig-Suari Prof. Bob Twiggs, Director Aerospace Engineering Dept. Space Systems
More informationCUBESAT P-Pod Deployer Requirements
CUBESAT P-Pod Deployer Requirements May 2002 Authors: Isaac Nason Michelle Creedon Nick Johansen Introduction The CubeSat program is a joint effort between Cal Poly and Stanford Universities to develop
More informationCoach Class to Orbit: the NPS CubeSat Launcher
Calhoun: The NPS Institutional Archive Faculty and Researcher Publications Faculty and Researcher Publications Collection 2009-08 Coach Class to Orbit: the NPS CubeSat Launcher Hicks, Christina http://hdl.handle.net/10945/37306
More information6U SUPERNOVA TM Structure Kit Owner s Manual
750 Naples Street San Francisco, CA 94112 (415) 584-6360 http://www.pumpkininc.com 6U SUPERNOVA TM Structure Kit Owner s Manual REV A0 10/2/2014 SJH Pumpkin, Inc. 2003-2014 src:supernova-rev00_20140925.doc
More informationABSTRACT INTRODUCTION
COMPASS-1 PICOSATELLITE: STRUCTURES & MECHANISMS Marco Hammer, Robert Klotz, Ali Aydinlioglu Astronautical Department University of Applied Sciences Aachen Hohenstaufenallee 6, 52064 Aachen, Germany Phone:
More informationCubeSats: From Launch to Deployment Necessity for a standard.
1 Necessity for a standard. Creation of a standard to facilitate the design process of small satellites. Deployment system to support the standard. Safe and reliable. Efficient and cost effective. Versatile.
More information6U CubeSat Design Specification Revision 1.0
X Document Classification Public Domain 6U CubeSat Design Specification Revision 1.0 (CP-6UCDS-1.0) Page 1 CHANGE HISTORY LOG Effective Date Revision Description of Changes 04/20/16 X1 Provisional release
More informationThe Future for CubeSats Present and Coming Launch Opportunities 18th Annual AIAA / USU Conference on Small Satellites CubeSat Workshop
The Future for CubeSats Present and Coming Launch Opportunities 18th Annual AIAA / USU Conference on Small Satellites CubeSat Workshop Presented By: Armen Toorian California Polytechnic State University
More informationTest Pod User s Guide
Document Classification X Public Domain ITAR Controlled Internal Only Test Pod User s Guide Revision Date Author Change Log 6 11/6/2006 Jonathan Brown Moved to standard document format 1 of 6 1 Introduction
More informationSelf-Steering Antennas for CubeSat Networks
Self-Steering Antennas for CubeSat Networks Blaine Murakami and Wayne Shiroma University of Hawaii CubeSat Developers Workshop CalPoly - San Luis Obispo March 9, 2004 Outline Overview of the UH Small-Satellite
More information2013 RockSat-C Preliminary Design Review
2013 RockSat-C Preliminary Design Review TEC (The Electronics Club) Eastern Shore Community College Melfa, VA Larry Brantley, Andrew Carlton, Chase Riley, Nygel Meece, Robert Williams Date 10/26/2012 Mission
More informationStrategies for Successful CubeSat Development. Jordi Puig-Suari Aerospace Engineering Department Cal Poly, San Luis Obispo CEDAR Workshop July, 2009
Strategies for Successful CubeSat Development Jordi Puig-Suari Aerospace Engineering Department Cal Poly, San Luis Obispo CEDAR Workshop July, 2009 1 Some CubeSat Facts Over 100 Developers Worldwide Including
More informationIn the summer of 2002, Sub-Orbital Technologies developed a low-altitude
1.0 Introduction In the summer of 2002, Sub-Orbital Technologies developed a low-altitude CanSat satellite at The University of Texas at Austin. At the end of the project, team members came to the conclusion
More informationRAX: Lessons Learned in Our Spaceflight Endeavor
RAX: Lessons Learned in Our Spaceflight Endeavor Matt Bennett University of Michigan CubeSat Workshop Cal Poly, San Luis Obispo April 21 st, 2010 Background Sponsored by National Science Foundation University
More informationInterplanetary CubeSat Launch Opportunities and Payload Accommodations
Interplanetary CubeSat Launch Opportunities and Payload Accommodations Roland Coelho, VP Launch Services Tyvak Nano-Satellite Systems Inc. +1(805) 704-9756 roland@tyvak.com Partnered with California Polytechnic
More informationRome, Changing of the Requirements and Astrofein s Business Models for Cubesat Deployer
Rome, 07.12.2017 4 th IAA Conference on University Satellite Missions and Cubesat Workshop Changing of the Requirements and Astrofein s Business Models for Cubesat Deployer Stephan Roemer Head of Space
More informationCubeSat Proximity Operations Demonstration (CPOD) Mission Update Cal Poly CubeSat Workshop San Luis Obispo, CA
CubeSat Proximity Operations Demonstration (CPOD) Mission Update Cal Poly CubeSat Workshop San Luis Obispo, CA 04-22-2015 Austin Williams VP, Space Vehicles ConOps Overview - Designed to Maximize Mission
More informationSatellite Testing. Prepared by. A.Kaviyarasu Assistant Professor Department of Aerospace Engineering Madras Institute Of Technology Chromepet, Chennai
Satellite Testing Prepared by A.Kaviyarasu Assistant Professor Department of Aerospace Engineering Madras Institute Of Technology Chromepet, Chennai @copyright Solar Panel Deployment Test Spacecraft operating
More informationAchievements in Developing an Advanced Standard for CubeSats
Achievements in Developing an Advanced Standard for CubeSats 10 th Annual CubeSat Workshop Ryan Williams, Engineer (presenting) Ryan Hevner, PSC 6U Canisterized Satellite Dispenser (CSD) Planetary Systems
More informationTropnet: The First Large Small-Satellite Mission
Tropnet: The First Large Small-Satellite Mission SSC01-II4 J. Smith One Stop Satellite Solutions 1805 University Circle Ogden Utah, 84408-1805 (801) 626-7272 jay.smith@osss.com Abstract. Every small-satellite
More informationAmateur Radio and the CubeSat Community
Amateur Radio and the CubeSat Community Bryan Klofas KF6ZEO bklofas@calpoly.edu Electrical Engineering Department California Polytechnic State University, San Luis Obispo, CA Abstract This paper will explore
More informationMaking it Small. April 22-24, 24, Cal Poly Developers Workshop California State Polytechnic University San Luis Obispo, CA
Making it Small April 22-24, 24, 2009 2009 Cal Poly Developers Workshop California State Polytechnic University San Luis Obispo, CA Prof. Bob Twiggs Bob.Twiggs@Stanford.Edu What started the miniaturization
More informationNanosat Deorbit and Recovery System to Enable New Missions
SSC11-X-3 Nanosat Deorbit and Recovery System to Enable New Missions Jason Andrews, Krissa Watry, Kevin Brown Andrews Space, Inc. 3415 S. 116th Street, Ste 123, Tukwila, WA 98168, (206) 342-9934 jandrews@andrews-space.com,
More informationDevelopment of Random Vibration Profiles for Test Deployers to Simulate the Dynamic Environment in the Poly-Picosatellite Orbital Deployer
Development of Random Vibration Profiles for Test Deployers to Simulate the Dynamic Environment in the Poly-Picosatellite Orbital Deployer Steve Furger California Polytechnic State University, San Luis
More informationInnovative Uses of the Canisterized Satellite Dispenser (CSD)
Innovative Uses of the Canisterized Satellite Dispenser (CSD) By Walter Holemans (PSC), Ryan Williams (PSC), Andrew Kalman (Pumpkin), Robert Twiggs (Moorehead State University), Rex Ridenoure (Ecliptic
More informationGEM Student Tutorial: Cubesats. Alex Crew
GEM Student Tutorial: Cubesats Alex Crew Outline What is a Cubesat? Advantages and disadvantages Examples of Cubesat missions What is a cubesat? Originally developed by California Polytechnic State University
More informationAttitude Determination and Control Specifications
Attitude Determination and Control Specifications 1. SCOPE The attitude determination and control sub system will passively control the orientation of the two twin CubeSats. 1.1 General. This specification
More informationA Failure Analysis of the ExoCube CubSat. 13 th Annual Cubesat Workshop San Luis Obispo, CA Wednesday, April 20 th, 2016
A Failure Analysis of the ExoCube CubSat 13 th Annual Cubesat Workshop San Luis Obispo, CA Wednesday, April 20 th, 2016 1 Background To characterize Hydrogen, Helium, Nitrogen and Oxygen, ions and neutrals
More informationCONTENTS TOOL LIST U P S I D E I N N O V A T I O N S, L L C RAMP AND STEP SYSTEM ASSEMBLY INSTRUCTIONS. Revised: June 2013
U P S I D E I N N O V A T I O N S, L L C RAMP AND STEP SYSTEM ASSEMBLY INSTRUCTIONS TOOL LIST Required Tools: - Reciprocating Saw with Metal Cutting Blade - Drill - 7/16 Drill Bit for Metal Drilling -
More informationAn Information Session on Canadian Cubesat Project
An Information Session on Canadian Cubesat Project Presenter: Dr. Johanne Heald Webinar Goal To provide professors in post-secondary institutions across Canada with information on the upcoming Canadian
More informationAssembly Instructions 10 X 10 Aluminum Roof Support
Assembly Instructions 10 X 10 Aluminum Roof Support Aluminum Roof Support Bolt Package 16-5/16 X 2 ¼ SS Bolt 24-5/16 X 1 SS Bolt 40-5/16 SS Nylon Lock Nuts 16-5/16 SS Flat Washers 28-4 ½ Wood Screws 36-1
More informationAdvanced Electrical Bus (ALBus) CubeSat Technology Demonstration Mission
Advanced Electrical Bus (ALBus) CubeSat Technology Demonstration Mission April 2015 David Avanesian, EPS Lead Tyler Burba, Software Lead 1 Outline Introduction Systems Engineering Electrical Power System
More informationEquilibrium. Conference Table. Installation Instruction. Revision B 11/07/16
Equilibrium Conference Table Installation Instruction Revision B 11/07/16 Equilibrium End User Agreement Enwork Equilibrium table bases must be installed directly onto a four inch minimum thickness concrete
More informationDavid M. Klumpar Keith W. Mashburn Space Science and Engineering Laboratory Montana State University
Developing the Explorer-1 [PRIME] Satellite for NASA s ELaNa CubeSat Launch Program David M. Klumpar Keith W. Mashburn Space Science and Engineering Laboratory Montana State University Outline E1P Mission
More informationUCISAT-1. Current Completed Model. Former Manufactured Prototype
UCISAT-1 2 Current Completed Model Former Manufactured Prototype Main Mission Objectives 3 Primary Mission Objective Capture an image of Earth from LEO and transmit it to the K6UCI Ground Station on the
More informationAug 6 th, Presented by: Danielle George- Project Manager Erin McCaskey Systems Engineer. LSP-F , Rev. B
Aug 6 th, 2011 Presented by: Danielle George- Project Manager Erin McCaskey Systems Engineer Agenda Purpose Background Firsts Activities Mission Objectives Con Ops Mission Timeline Risks Challenges Power
More informationProximity Operations Nano-Satellite Flight Demonstration (PONSFD) Overview
Proximity Operations Nano-Satellite Flight Demonstration (PONSFD) Overview April 25 th, 2013 Scott MacGillivray, President Tyvak Nano-Satellite Systems LLC 15265 Alton Parkway, Suite 200 Irvine, CA 92618-2606
More informationSummary. ESPA 6U Mount (SUM) overview SUM qualification status Future SUM enhancements Moog CSA adapters and ESPA family
Summary ESPA 6U Mount (SUM) overview SUM qualification status Future SUM enhancements Moog CSA adapters and ESPA family 1 CubeSat Summer Workshop 11 August 2012 ESPA Six-U Mount SUM Adapter with ESPA standard
More informationSeparation Connector. Prototyping Progress Update March 1, 2013
Separation Connector By Koll Christianson, Luis Herrera, and Zheng Lian Team 19 Prototyping Progress Update March 1, 2013 Submitted towards partial fulfillment of the requirements for Mechanical Engineering
More informationCIRRUS AIRPLANE MAINTENANCE MANUAL
FASTENER AND HARDWARE GENERAL REQUIREMENTS 1. DESCRIPTION This section contains general requirements for common hardware installation. Covered are selection and installation of cotter pins, installation
More information14000 I/O Series Flush Glaze. Fabrication and Installation Instructions
14000 I/O Series Flush Glaze Fabrication and Installation Instructions Last saved on 12/18/2009 Table of Contents GENERAL CONSTRUCTION NOTES...3 EXTRUDED ALUMINUM PARTS...4 ACCESSORIES...5 OVERVIEW...6
More informationTesting. Material testing will be according to applicable AASHTO, ASTM or Department methods as specified.
907.01 Section 907. FENCING MATERIALS 907.01 General Requirements. Materials for use in fencing property, right-of-way and other installations must comply with this section. 907.02 Testing. Material testing
More informationMiniature Deployable High Gain Antenna for CubeSats
Phantom Works Miniature Deployable High Gain Antenna for CubeSats Charles S. Scott MacGillivray Office: (714) 372-1617 e-mail: charles.s.macgillivray@boeing.com Mobile: (714) 392-9095 e-mail: zserfv23@gmail.com
More informationMANUFACTURING INC. Specifications
Page 1 of 4 GENERAL 11 Aluminum security screen doors must be tested by a recognized testing laboratory to conform to SMA 6001-2002 Proposed American National Standard Specifications for Metal Protection
More informationClearSpan End Frame Kit 26' Wide x 12' High
ClearSpan End Frame Kit 26' Wide x 12' High Diagram shows the end frame kit for an end wall without a door. (Door and end panel are purchased separately.) Rafter and struts shown in the above diagram are
More informationCubeSat Integration into the Space Situational Awareness Architecture
CubeSat Integration into the Space Situational Awareness Architecture Keith Morris, Chris Rice, Mark Wolfson Lockheed Martin Space Systems Company 12257 S. Wadsworth Blvd. Mailstop S6040 Littleton, CO
More informationCubeSat De-Orbit Project
CubeSat De-Orbit Project Brockton Baskette Sahil Dhali Michael Foch Nicholas Montana Kyle Wade MAE 434W April 30, 2013 Outline Background Project Goals Develop commercial cubesat de-orbit device Demonstrate
More informationSmall Satellites: The Execution and Launch of a GPS Radio Occultation Instrument in a 6U Nanosatellite
Small Satellites: The Execution and Launch of a GPS Radio Occultation Instrument in a 6U Nanosatellite Dave Williamson Director, Strategic Programs Tyvak Tyvak: Satellite Solutions for Multiple Organizations
More informationINSTALLATION MANUAL IOWA MOLD TOOLING CO., INC. BOX 189, GARNER, IA MANUAL PART NUMBER:
PARTS-1 Model 24562/28562 Crane INSTALLATION MANUAL IOWA MOLD TOOLING CO., INC. BOX 189, GARNER, IA 50438-0189 641-923-3711 MANUAL PART NUMBER: 99903701 Iowa Mold Tooling Co., Inc. is an Oshkosh Truck
More informationASSEMBLY INSTRUCTIONS FOR SERVICE BODY A MOUNT RACKS
ASSEMBLY INSTRUCTIONS FOR SERVICE BODY A MOUNT RACKS T12 Service Body A shown with optional middle crossbar Package Contents: HARDWARE KIT PARTS (8) 3/8-16 x 3 CARRAIGE BOLTS (1) RAIL DRIVER S SIDE ASSEMBLIES
More informationOxford Stalls Installation Instructions
Oxford Stalls Installation Instructions RAMM Horse Fencing and Stalls 13150 Airport Hwy. Swanton, OH 43558-9615 1-800-434-8456 Rev. 8/15/17 Before You Start Typical stall sizes are 10 x 10, 12 x 12 or
More informationCubeSat: Developing a Standard Bus for Picosatellites
CubeSat: Developing a Standard Bus for Picosatellites I.Galysh, K. Doherty, J. McGuire, H.Heidt, D. Niemi, G. Dutchover The StenSat Group 9512 Rockport Rd, Vienna, VA 22180 http://www.stensat.org Abstract
More informationCubeSat Standard Updates
CubeSat Standard Updates Justin Carnahan California Polytechnic State University April 25, 2013 CubeSat Developers Workshop Agenda The CubeSat Standard CDS Rev. 12 to Rev. 13 Changes The 6U CubeSat Design
More informationHermes CubeSat: Testing the Viability of High Speed Communications on a Picosatellite
Hermes CubeSat: Testing the Viability of High Speed Communications on a Picosatellite Dustin Martin, Riley Pack, Greg Stahl, Jared Russell Colorado Space Grant Consortium dustin.martin@colorado.edu March
More informationSCI-FAB Product Specifications. Casework Section 1. Part 1 General
SCI-FAB Product Specifications Casework Section 1 Part 1 General 1.1 SCOPE OF WORK Includes all factory fabricated stainless steel casework as required by the project drawings. 1.2 TYPICAL INCLUSIONS A.
More informationELaNa Educational Launch of Nanosatellite Enhance Education through Space Flight
ELaNa Educational Launch of Nanosatellite Enhance Education through Space Flight Garrett Lee Skrobot Launch Services Program, NASA Kennedy Space Center, Florida; 321.867.5365 garrett.l.skrobot@nasa.gov
More informationAPPENDIX FENCE GENERAL NOTES
APPENDIX FENCE GENERAL NOTES 1. Fabric: 9 gage, 2" mesh, knuckle top and bottom, placed on the outside of posts, single fabric width for the entire height. 2. All fencing to be standard galvanized finish.
More informationASSEMBLY INSTRUCTIONS FOR HAULER II SERVICE BODY A RACK
ASSEMBLY INSTRUCTIONS FOR HAULER II SERVICE BODY A RACK T12USBA-1 shown above Package Contents: HARDWARE KIT PARTS (4) 3/8-16 x 3 CARRAIGE BOLTS (1) RAIL DRIVER S SIDE ASSEMBLY (20) 3/8-16 x 2 CARRAIGE
More information14000 Series. Fabrication and Installation Instructions
14000 Series Fabrication and Installation Instructions 14000 Series Revision December 01, 2009 Table of Contents GENERAL CONSTRUCTION NOTES... 3 EXTRUDED ALUMINUM PARTS... 4 ACCESSORIES... 7 OVERVIEW...
More informationLarge, Deployable S-Band Antenna for a 6U Cubesat
Physical Sciences Inc. VG15-073 Large, Deployable S-Band Antenna for a 6U Cubesat Peter A. Warren, John W. Steinbeck, Robert J. Minelli Physical Sciences, Inc. Carl Mueller Vencore, Inc. 20 New England
More informationHardened Structures Hardened Shelters, LLC. Explosion Resistant Pre-hung Sealed Blast Door
Hardened Structures Hardened Shelters, LLC Explosion Resistant Pre-hung Sealed Blast Door Drawing number: ASR-50-BD Revision: E Date: December 8, 2008 Table of Contents Contact Information... 3 Description...
More informationRetractable Pool Cover
Retractable Pool Cover By: Abdulhadi Alkhaldi, Zachary Keller, Cody Maurice, Bradley Miller, and Patrick Weber Team 12 Midpoint Review Document Submitted towards partial fulfillment of the requirements
More informationMK52 Series ULTRA-LOW FREQUENCY VIBRATION ISOLATION WORKSTATION ASSEMBLY AND OPERATION INSTRUCTIONS
MK52 Series ULTRA-LOW FREQUENCY VIBRATION ISOLATION WORKSTATION ASSEMBLY AND OPERATION INSTRUCTIONS i Information contained in this document is subject to change without notice and does not represent a
More informationModular XP Ramp Assembly Manual
Modular XP Manual 1 Contents Overview... 2-5 1.1 Tools required...6 1.2 Hardware list...6 Ramp & Platform Standard Parts 2.1 Ramp Parts...7 2.2 Platform Parts...8 2.3 Standard Platform Configurations...
More informationA Systems Approach to Select a Deployment Scheme to Minimize Re-contact When Deploying Many Satellites During One Launch Mission
A Systems Approach to Select a Deployment Scheme to Minimize Re-contact When Deploying Many Satellites During One Launch Mission Steven J. Buckley, Volunteer Emeritus, Air Force Research Laboratory Bucklesjs@aol.com,
More informationCubeSat Model-Based System Engineering (MBSE) Reference Model Development and Distribution Interim Status
CubeSat Model-Based System Engineering (MBSE) Reference Model Development and Distribution Interim Status David Kaslow 1 Consultant, Berwyn, PA 19312 USA Bradley J. Ayres 2 The Aerospace Corporation, Wright
More informationPage 1. SureMotion Quick-Start Guide: LACPACC_QS 1st Edition - Revision A 03/15/16
R K C T I Repair Kit Product Compatibility Repair Kit # Linear Actuator Assembly # LACPACC-002 LACPACC-003 LACP-16TxxLP5 (0.5-in lead screw pitch) LACP-16TxxL1 (1-in lead screw pitch) C P I R K 4 ea Flanged
More informationSystem 3000 specifications
System 3000 specifications Scope: Materials: Type of Bookstack: This specification covers delivery and installation of steel library shelving of the bracket type. Height, depth and accessories shall be
More informationTable of Contents. B. Base Tool Changer...2 MC-6 Manual Tool Changer...2
Table of Contents B. Base Tool Changer...2 MC-6 Manual Tool Changer...2 1. Product Overview... 2 1.1 Master Plate Assembly... 2 1.2 Tool Plate Assembly... 3 1.3 Optional Modules... 3 2. Installation...
More informationA Standardized Geometry For Space Access Ports
A Standardized Geometry For Space Access Ports A New Standard for 6 and 12U CubeSat Components 21 APRIL 2016 DOV JELEN, PUMPKIN, INC 1 History : Early Standards CubeSat Design Specification (CDS) from
More information10 August 2005 Utah State University Logan, UT
19th Annual AIAA SmallSat Conference The *.Sat CubeSat Bus When Three Cubes Meet Eric P. Lee, *.Sat Project Manager (eric.p.lee@lmco.com, leeep@stanford.edu) and Matthew D Ortenzio, Stevan M. Spremo, Belgacem
More informationELaNa Educational Launch of Nanosatellite Providing Routine RideShare Opportunities
ELaNa Educational Launch of Nanosatellite Providing Routine RideShare Opportunities Garrett Lee Skrobot Launch Services Program, NASA Kennedy Space Center, Florida; 321.867.5365 garrett.l.skrobot@nasa.gov
More informationNational Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology
QuikSCAT Mission Status QuikSCAT Follow-on Mission 2 QuikSCAT instrument and spacecraft are healthy, but aging June 19, 2009 will be the 10 year launch anniversary We ve had two significant anomalies during
More information1.8 METER SERIES 1184 ANTENNA SYSTEM
REVISION F January 10, 2002 ASSEMBLY MANUAL 1.8 METER SERIES 1184 ANTENNA SYSTEM PRODELIN CORPORATION 1500 Prodelin Drive Newton NC 28658 1.8 METER SERIES 1184 ANTENNA SYSTEM F Revised Address 1/10/02
More informationCubeSat Launch and Deployment Accommodations
CubeSat Launch and Deployment Accommodations April 23, 2015 Marissa Stender, Chris Loghry, Chris Pearson, Joe Maly Moog Space Access and Integrated Systems jmaly@moog.com Getting Small Satellites into
More informationRITE-HITE RAINGUARD TM
RITE-HITE RAINGUARD TM RG-3000 Trailer Top Seal Installation Instructions & Owner s Manual Date of Installation: This Manual Covers All Units Shipped 8/04 to Date PRINTED IN U.S.A. PUBLICATION NO. RG30-0010
More informationARMADILLO: Subsystem Booklet
ARMADILLO: Subsystem Booklet Mission Overview The ARMADILLO mission is the Air Force Research Laboratory s University Nanosatellite Program s 7 th winner. ARMADILLO is a 3U cube satellite (cubesat) constructed
More informationModular XP Ramp Assembly Manual
Modular XP Manual 1 Contents Overview... 2-5 Section 1: 1.1 Tools required...6 1.2 Hardware list...6 Ramp & Platform Standard Parts 2.1 Ramp Parts...7 2.2 Platform Parts...8 2.3 Standard Platform Configurations...
More informationRAX: The Radio Aurora explorer
RAX: Matt Bennett University of Michigan CubeSat Workshop Cal Poly, San Luis Obispo April 22 nd, 2009 Background Sponsored by National Science Foundation University of Michigan and SRI International Collaboration
More informationMODEL# SLA001-3 "SLIDE & LOCK" A-FRAME POOL LADDER
MODEL# SLA001-3 "SLIDE & LOCK" A-FRAME POOL LADDER IMPORTANT INSTRUCTIONS: : Read all instructions carefully & completely to become familiar with parts, assembly, safety and proper use of this product.
More informationASSEMBLY INSTRUCTIONS FOR HAULER II UNIVERSAL CAMPER SERIES RACKS
ASSEMBLY INSTRUCTIONS FOR HAULER II UNIVERSAL CAMPER SERIES RACKS C11U2873-1 shown above Package Contents: HARDWARE KIT PARTS (4) 3/8-16 x 3 CARRAIGE BOLTS (1) RAIL DRIVER S SIDE ASSEMBLY (20) 3/8-16 x
More informationCHEVY/GMC SuperRail Mounting Kit #3117
CHEVY/GMC SuperRail Mounting Kit #3117 #3100 SuperGlide (12K) Gross Trailer Weight (Maximum) Vertical Load Weight (Max. Pin Weight) 12,000 lbs. 3,000 lbs. Installation Instructions SPECIFICATIONS Fits
More informationSpace Access Technologies, LLC (Space Access)
, LLC (Space Access) Rachel Leach, Ph.D. CubeSat Manager/Coordinator www.access2space.com April 2006 >>Cost Effective access to Space for Research & Education Payloads
More informationFor installation assistance, contact SARGENT at DOORS SHOWN HERE SWING IN FOR ILLUSTRATION PURPOSES ONLY.
SARGENT Installation Instructions for LP8600 x LR8600 & 12-LP8600 x 12-LR8600 Series Low Profile Panic and Fire Exit Devices on Double Egress & Double Doors or LS8600 & 12-LS8600 Low Profile Exit Device
More informationINSTALLING INVISIRAIL GLASS PANELS POST INFORMATION... 2 PRE-INSTALLATION... 2
Contents POST INFORMATION... 2 PRE-INSTALLATION... 2 STEP A1: MEASURING FOR INVISIRAIL CUSTOM GLASS PANELS (skip if using Standard Sized Panels)... 2 STEP A2: GATHER ADDITIONAL TOOLS/SUPPLIES... 2 STEP
More informationHASP Payload Specification and Integration Plan
Payload Title: High Altitude Tracking Solar Survey (HATS 2.0) Payload Class: Small Large (circle one) Payload ID: 09 Institution: Contact Name: Arizona State University Elizabeth Dyer Contact Phone: 6025702298
More informationAssembly Manual for the 1.2m Quick-Deploy Antenna System
704 North Clark Street Albion, MI 49224 USA Phone +1 517 680 0125 Fax +1 517 680 0133 www.challengercommunications.com Challenger Communications Assembly Manual for the 1.2m Quick-Deploy Antenna System
More informationRodney Hunt. A GA Industries Company Glydaseal Gates
Rodney Hunt A GA Industries Company Glydaseal Gates GUIDE BRONZE GUIDE BAR FRAME NUT POCKET SEAT FACING RESILIENT INVERT SEAT DISC GUIDE BAR ADJUSTMENT BOLT WITH LOCK NUT GUIDE BAR ATTACHING BOLT The Glydaseal
More informationCUBESAT-TO-GROUND COMMUNICATION AND MOBILE MODULAR GROUND- STATION DEVELOPMENT
CUBESAT-TO-GROUND COMMUNICATION AND MOBILE MODULAR GROUND- STATION DEVELOPMENT Dylan Ichikawa Department of Electrical Engineering University of Hawaii at Manoa Honolulu, HI 96822 ABSTRACT A mobile modular
More informationResearch Activities on Small Satellite in HIT
7th UK-China Workshop on Space Science and Technology Research Activities on Small Satellite in HIT Prof. ZHANG Shijie (RCST) Contents 7th UK-China Workshop on Space Science and Technology 1. RCST Overview
More informationNanoCom ANT430. Datasheet 70 cm band Omnidirectional UHF CubeSat antenna
NanoCom ANT430 Datasheet 70 cm band Omnidirectional UHF CubeSat antenna 1 Table of Contents 1 TABLE OF CONTENTS... 2 2 OVERVIEW... 3 2.1 HIGHLIGHTED FEATURES... 3 2.2 FUNCTIONAL DESCRIPTION... 3 2.2.1
More informationCopyright Black Box Corporation. All rights reserved Park Drive Lawrence, PA Fax
Copyright 2003. Black Box Corporation. All rights reserved. 1000 Park Drive Lawrence, PA 15055-1018 724-746-5500 Fax 724-746-0746 JULY 2003 RM3010A RM315-R2 RM323-R2 RM329 RM451 RM457 RM3020A RM316 RM324-R2
More informationAPTUS : Applications for Tether United Satellites
SSC01-VII-5 APTUS : Applications for Tether United Satellites m_fitzpatrick@mail.utexas.edu The University of Texas at Austin Department of Aerospace Engineering WRW 412A C0600 The University of Texas
More informationIncorporating a Test Flight into the Standard Development Cycle
into the Standard Development Cycle Authors: Steve Wichman, Mike Pratt, Spencer Winters steve.wichman@redefine.com mike.pratt@redefine.com spencer.winters@redefine.com 303-991-0507 1 The Problem A component
More informationESPA Satellite Dispenser
27th Annual Conference on Small Satellites ESPA Satellite Dispenser for ORBCOMM Generation 2 Joe Maly, Jim Goodding Moog CSA Engineering Gene Fujii, Craig Swaner ORBCOMM 13 August 2013 ESPA Satellite Dispenser
More informationSliding Door Kit
YOU MUST READ THIS DOCUMENT BEFORE YOU BEGIN TO ASSEMBLE THE DOOR KIT. Thank you for purchasing this GrowSpan door kit. When properly assembled and maintained, this product will provide years of reliable
More informationUnderstand that technology has different levels of maturity and that lower maturity levels come with higher risks.
Technology 1 Agenda Understand that technology has different levels of maturity and that lower maturity levels come with higher risks. Introduce the Technology Readiness Level (TRL) scale used to assess
More information