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Miniature Autonomous Star Tracker Based On Cmos Aps , Dong Ying, You Zheng, Xing Fei, Chou Qin
Miniature Autonomous Star Tracker Based On Cmos Aps , Dong Ying, You Zheng, Xing Fei, Chou Qin
Small Satellite Conference
An APS (Active Pixel Sensor) based autonomous star tracker (AAST) has been proposed for small satellite and microsatellite attitude determination. A prototype of AAST has been developed. It has low mass of 1kg, low power of 3W, high rate up to 5Hz, and acquisition success rate of higher than 99.9%. The improvements in dimensions and performances are realized with the replacement of the CCD (Charge Coupled Device) by the APS. The optical design of the prototype is based on PSF (Point Spread Function) which is more adaptive for star tracker.s operation than the traditional MTF (Modulation Transfer Function) criterion and …
The Role Of Small Satellites In Aeronomy , Charles Swenson
The Role Of Small Satellites In Aeronomy , Charles Swenson
Small Satellite Conference
The scientific community and NASA are continually evaluating and setting the direction of future Aeron-omy missions, including those targeted at space weather. Missions, and the required supporting technologies, have historically been outlined within strategic plans developed for NASA by the science community. Many of the pro-posed future missions will require constellations that act as single missions, making coordinated observations as a single virtual instrument. The science return occurs from the multi-point or spatially distributed observations and not from a collocation of a complex suite of instruments, as does the current model. The only conceivable way many of these missions can …
A 1m Resolution Camera For Small Satellites, Jeremy Curtis, Nigel Morris, Bryan Shaughnessy, Nick Waltham, Ruben Edeson, Ian Tosh, John Ellis
A 1m Resolution Camera For Small Satellites, Jeremy Curtis, Nigel Morris, Bryan Shaughnessy, Nick Waltham, Ruben Edeson, Ian Tosh, John Ellis
Small Satellite Conference
The paper will describe how the performance of RALCam-1, the camera flying on TopSat, which is achieving 2.8m resolution at 686km altitude, has led to the development by the Rutherford Appleton Laboratory of an advanced, low cost, low mass, 1 meter resolution camera for small satellites. This camera, now under development, will fly at 600km on a small sat further advancing the scope for affordable constellations of high resolution imaging systems. The paper will concentrate on the innovative approach of the camera and how it will overcome the problems of stability of the optical bench through launch and in the …
Application Of Microspacecraft Design Methods To The Development Of A Miniature, Low Cost Star Tracker For Microspace Applications , Bill Seng, Rick Fleeter
Application Of Microspacecraft Design Methods To The Development Of A Miniature, Low Cost Star Tracker For Microspace Applications , Bill Seng, Rick Fleeter
Small Satellite Conference
The paper follows the entire product evolution life cycle, illustrating how small, low cost space engineering and design methods have been translated to the design of a subsystem. This description includes subsystem specifications, technologies, materials and layout, operating modes, development and test methods – including prototyping and achieving flight ready status – and even extends to the marketing approach now being instituted. AeroAstro has successfully executed this low-cost approach for subsystems ranging from optical sensors to radios and actuators with consistent results. We show in the paper how the lessons learned in 20+ years of microspacecraft experience can and should …
An Advanced High Resolution Optical Sensor For Small Satellite Mapping Missions, David Purl, Luis Gomes, Alex Da Silva Curiel, Mike Cutter, Wei Sun, Martin Sweeting
An Advanced High Resolution Optical Sensor For Small Satellite Mapping Missions, David Purl, Luis Gomes, Alex Da Silva Curiel, Mike Cutter, Wei Sun, Martin Sweeting
Small Satellite Conference
The Beijing-1 mission was launched at the end of 2005, and has commenced routine operations as a highresolution mapping mission. The space segment comprises a small 168kg satellite carrying a panchromatic imaging instrument providing 4-metre Ground Sampling Distance with 24km swath. This is in addition to a wideangle multi-spectral camera with 32-metre GSD and 600km swath as carried by the other satellites within the Disaster Monitoring Constellation[1,2,3] The spacecraft provides a large data storage capacity with solid-state storage augmented by hard drives modified for use in space, allowing the instrument to map long 3000km swaths. A software configurable image compressor …
The Brite Space Telescope: A Nanosatellite Constellation For High-Precision Photometry Of The Brightest Stars, Norman Deschamps, Cordell Grant, Dan Foisy, Robert Zee, Anthony Moffat, Werner Weiss
The Brite Space Telescope: A Nanosatellite Constellation For High-Precision Photometry Of The Brightest Stars, Norman Deschamps, Cordell Grant, Dan Foisy, Robert Zee, Anthony Moffat, Werner Weiss
Small Satellite Conference
The BRITE-Constellation is a group of Canadian/Austrian nanosatellites that will examine the apparently brightest stars in the sky for variability using precise differential photometry. The constellation consists of four low Earth-orbiting nanosatellites, divided into pairs, with each member of a pair having a different optical filter. Each BRITE satellite will observe a region of interest for up to 100 days or longer, allowing measurement of stellar variability on the order of hours to months. Each BRITE satellite utilizes a number of new, innovative technologies including reaction wheels, star tracker and optical telescope, all sized and designed around Space Flight Laboratory’s …
The First New Mexico Spaceport Launch: Up Aerospace And Aeroastro Team Together To Provide Regular And Repeatable Launches For Space Component Testing. , Simon Weiss, James Peverill, Rich Glover, Bill Seng, Jerry Larson
The First New Mexico Spaceport Launch: Up Aerospace And Aeroastro Team Together To Provide Regular And Repeatable Launches For Space Component Testing. , Simon Weiss, James Peverill, Rich Glover, Bill Seng, Jerry Larson
Small Satellite Conference
UP Aerospace (UP) and AeroAstro have teamed to produce a quick launch capability for space component testing in a sub-orbital environment. Designed for commercial endeavors, this quick launch capability has a time span of concept-to-flight measured in weeks, not months or years. As more products are developed for microspace, space component testing will become an important part of the business case for commercial sub-orbital launch vehicles. In August 2006, UP and AeroAstro will launch the inaugural flight from the New Mexico Spaceport. This first flight of the UP vehicle, SpaceLoftXL, will carry an early version of AeroAstro’s Miniature Star Tracker …
The ‘Responsive Access’ Concept (Rac) And Its Realisation In Russia, G.M. Webb, O.A. Sokolov
The ‘Responsive Access’ Concept (Rac) And Its Realisation In Russia, G.M. Webb, O.A. Sokolov
Small Satellite Conference
With the advent of the Falcon, the capability of launch on demand will be an important asset of a Western commercial launcher for small satellites for the first time. While this capability is possessed by all military missiles, only those from the former Soviet Union were developed into small launchers which retained their responsive access characteristics unimpaired. Furthermore, quite large launchers, the Cyclone and Zenit 2 were produced with this ability. In this paper the responsive access concept, its advantages and its implications for the launcher market are examined and assessed. Russian and Ukrainian launchers are examined and their suitability …
Lessons Learned Developing Separation Systems For Small Satellites, Walter Holemans
Lessons Learned Developing Separation Systems For Small Satellites, Walter Holemans
Small Satellite Conference
Several lessons learned developing separation systems for small satellites are presented. The relationship between vibration environment and quasi-static loading is shown. The relationship of separation system wiring harness schematic to the real harness is shown. The impact of dissimilar structures to load peaking is illustrated. The relationship between velocity, separation springs and tip-off is discussed. The relationship between flatness of adjoining structures and stress in the structures is discussed.
The Atlas Secondary Experience – Yesterday, Today, And Beyond , Gerald Szatkowski, George Sowers, Jim England, Chris Andrews, Emily Rodgers
The Atlas Secondary Experience – Yesterday, Today, And Beyond , Gerald Szatkowski, George Sowers, Jim England, Chris Andrews, Emily Rodgers
Small Satellite Conference
Although progress within the Space Technology Community remains constant, the dilemma of demonstrating critical technologies needed for future Space capabilities still exists. While the U.S. Government has been investing in multiple aspects of space, demonstration of these technologies in a manner that provides distinct paths to acquisition programs is cursory at best, based on the availability of funding. This paper provides an overview of the Atlas launch vehicle’s role encompassing the past, present and future, in supporting space technology demonstrations. The Atlas program has developed a wide range of capabilities in support of critical space technologies that sustain future war-fighting …
A Custom Launch System For Satellites Smaller Than 1 Kg, Dorin Patru, Jeffrey Kozak, Robert Bowman
A Custom Launch System For Satellites Smaller Than 1 Kg, Dorin Patru, Jeffrey Kozak, Robert Bowman
Small Satellite Conference
This paper presents the concept and design of a custom launch system for satellites with a mass equal or less than 1 kg. Current launch opportunities carry these satellites as secondary payloads to orbit. To date, no launch system has targeted a satellite of less than 1 kg as a primary payload. The case is made for an airborne, balloon based rocket launch. A four stage rocket using a hybrid propellant combination is proposed. With an assumed specific impulse of 235 seconds, four stages and a redundant structure to propellant mass ratio of 1/10, a burnout velocity of 9,200 m/sec …
Airlaunch’S Quickreach™ Small Launch Vehicle: Operationally Responsive Access To Space, Debra Facktor Lepore, Joseph Padavano
Airlaunch’S Quickreach™ Small Launch Vehicle: Operationally Responsive Access To Space, Debra Facktor Lepore, Joseph Padavano
Small Satellite Conference
AirLaunch LLC is developing the QuickReach™ booster under the DARPA/Air Force Falcon small launch vehicle program. Valued at $17.8 million for a one-year effort, the Falcon Phase 2B contract activity enables AirLaunch and its team of subcontractors to continue developing the QuickReach™ small satellite booster. The Falcon program goal is to develop a vehicle that can launch 1,000 pounds to Low Earth Orbit for less than $5 million with only 24 hours notice. AirLaunch’s design achieves responsiveness by carrying its QuickReach™ booster to altitude inside the cargo bay of an unmodified C-17A or other large cargo aircraft. In 2005, Team …
Icbm Derived Small Lift Vehicles: Past, Present, And Future , William Emmer, Joel Freyenhagen, Gene Hockenberry, Jeremy Geiger
Icbm Derived Small Lift Vehicles: Past, Present, And Future , William Emmer, Joel Freyenhagen, Gene Hockenberry, Jeremy Geiger
Small Satellite Conference
The United States has a rich history of space lift success, most of which is based on the Intercontinental Ballistic Missile (ICBM) heritage. For more than 40 years, the Rocket Systems Launch Program (RSLP) has been executing its charter to store and utilize deactivated ICBM assets. We have had hundreds of successful launches, in multiple launch configurations, from nearly two dozen different launch locations. From spaceports to air launches to all across the Pacific Ocean, RSLP has been the small lift vehicle of choice for the Department of Defense (DoD). RSLP currently provides affordable space launch test beds for emerging …
Responsive Flight Testing Of A Launch Hardware Tracker Experiment Using A Prototype Nanosat Launch Vehicle, John Garvey, David Garza
Responsive Flight Testing Of A Launch Hardware Tracker Experiment Using A Prototype Nanosat Launch Vehicle, John Garvey, David Garza
Small Satellite Conference
Development of a nanosat launch vehicle (NLV) that is capable of delivering 10 kg to low earth orbit has resulted in significant progress during the past year. Most visibly, an early prototype reusable launch vehicle (RLV) based on the proposed NLV first stage successfully conducted two low-altitude flights within a period of just 3.5 hours. Of particular relevance to the small sat community, this Prospector 7 (P-7) vehicle manifested several academic payloads and demonstrated the feasibility of using existing payload accommodation concepts for deploying CubeSat-class spacecraft. Subsequently, in a tangible demonstration of the potential benefits that can be achieved with …
Fuel Minimization For Constellation Phasing Maintenance Of Multi Classes Of Low-Cost Satellites, Jer Ling, Eden Hsueh
Fuel Minimization For Constellation Phasing Maintenance Of Multi Classes Of Low-Cost Satellites, Jer Ling, Eden Hsueh
Small Satellite Conference
This paper studies the constellation phasing maintenance for satellites of different designs and launched separately from different launchers. Because of the difference of designs, the satellites have different ballistic drag characteristics. Due to the different launches, the satellites will not be likely on the same orbit plane. These factors cause the orbit phasing control to be demanding. With consideration of cost reduction and hardware availability, satellites may use the low efficient gas nitrogen propulsion subsystem. The capacity of fuel is limited for the satellite mass constraint, thus, leading to the minimization of fuel consumption to be critical. This paper presents …
The Darpa / Usaf Falcon Program Small Launch Vehicles, David Weeks, Steven Walker, Tim Thompson, Robert Sackheim, John London Iii
The Darpa / Usaf Falcon Program Small Launch Vehicles, David Weeks, Steven Walker, Tim Thompson, Robert Sackheim, John London Iii
Small Satellite Conference
Earlier in this decade, the U.S. Air Force Space Command and the Defense Advanced Research Projects Agency (DARPA), in recognizing the need for low-cost responsive small launch vehicles, decided to partner in addressing this national shortcoming. Later, the National Aeronautics and Space Administration (NASA) joined in supporting this effort, dubbed the Falcon Program. The objectives of the Small Launch Vehicle (SLV) element of the DARPA / USAF Falcon Program include the development of a low-cost small launch vehicle(s) that demonstrates responsive launch and has the potential for achieving a per mission cost of less than $5M when based on 20 …
Sif – Yet Another Spacecraft Interconnection Standard, Doug Sinclair
Sif – Yet Another Spacecraft Interconnection Standard, Doug Sinclair
Small Satellite Conference
SIF is a Standard InterFace for spacecraft electronics. It combines a number of existing standards+28 V avionics power, ISO 11898-3 fault-tolerant Control Area Network (CAN), and the CANopen software protocol. Terminals are connected into a closed loop by identical cables. The resulting network is fail-operational and is easy to modify even late in satellite integration. SpaceQuest experience building a large spacecraft with SIF avionics has demonstrated the cost and schedule savings inherent in standardized interfaces. This paper contains all of the information required for the reader to build and use SIF devices. The small satellite community is invited to make …
Fine Steering Mirror For Smallsat Pointing And Stabilization, Steven Wassom, Morgan Davidson, Trent Newswander, James Cook, Zach Casper, Adam Shelley
Fine Steering Mirror For Smallsat Pointing And Stabilization, Steven Wassom, Morgan Davidson, Trent Newswander, James Cook, Zach Casper, Adam Shelley
Small Satellite Conference
SDL has used internal funds to develop a prototype low-cost 2-axis fine steering mirror (FSM) as an enabling technology for smallsats. The FSM has a lightweight high-reflectance mirror, high angular deflection capability for along-track ground motion compensation and cross-track pointing, and a high bandwidth to help cancel unwanted jitter. Key performance parameters areClear aperture, 75 mm; along-track angle, ±30 deg (mechanical); cross-track angle, ±60 deg (mechanical); slew rate, greater than 75 deg/sec; bandwidth, 70 Hz; steadystate average error, as good as 1 arcsec; average power dissipation, 0.4 Watts; and total mechanical mass, 1 kg. The FSM makes use of off-the-shelf …
Stochastic Orbital Lifetime Analysis, Kandyce Goodliff, David Cornelius, Washito Sasamoto
Stochastic Orbital Lifetime Analysis, Kandyce Goodliff, David Cornelius, Washito Sasamoto
Small Satellite Conference
Given the dynamic environment in which spacecraft exist, a better methodology for performing orbital lifetime analyses over the current practice of point analyses was desired. The approach chosen was to utilize Monte Carlo based predictions, which provides the ability to gauge the probability of meeting mission lifetime goals, as well as identifying driving factors. The Monte Carlo analysis, called Orbital Lifetime Monte Carlo (OLMC), is based on the NASA Langley Research Center long term orbit propagator Orbital Lifetime. OLMC incorporates the ability to model variations in predictions of solar flux levels and timing of associated peaks, the variation in launch …
Implications Of Internet Protocol On Leo Micro-Satellite Communication Links, Keith Nicewarner
Implications Of Internet Protocol On Leo Micro-Satellite Communication Links, Keith Nicewarner
Small Satellite Conference
Internet Protocol (IP) enables a session-based communication paradigm that is transaction-oriented rather than data stream-centric. This is a paradigm that is prevalent in ground systems (and arguably a significant factor in the success of the Internet), but is uncommon in space systems – even ones that have used IP. IP allows multiple, simultaneous, independent sessions over the same channel. This allows software that uses the space link to be written in a more modular and easily testable manner. It also allows commercial IP-based technology to be used independently of the application-specific software. For instance, a telnet session to the spacecraft …
Design, Build, And Testing Of Tacsat Thin Film Solar Arrays, J William Zuckermandel, Scott Enger, Neeraj Gupta
Design, Build, And Testing Of Tacsat Thin Film Solar Arrays, J William Zuckermandel, Scott Enger, Neeraj Gupta
Small Satellite Conference
MicroSat Systems, Inc. (MSI) has developed a low cost, lightweight, solar array system using thinfilm photovoltaic (TFPV) material to meet power generation needs for future responsive space missions. The Fold Integrated Thin Film Stiffener (FITS) is the deployment portion of the system. FITS is an integrated, passively deployed solar array structure designed specifically for TFPV, however a variety of photovoltaic (PV) options can be utilized by using the FITS deployment technology. FITS extends the boundaries of space PV systems by eliminating conventional rigid structures and mechanisms to maximize the lightweight and low stowage volume advantages of TFPV. FITS uses multifunctional, …
A Survey Of Micropropulsion For Small Satellites, William Storck, Olivia Billett, Mitul Jambusaria, Andy Sadhwani, Pierric Jammes, James Cutler
A Survey Of Micropropulsion For Small Satellites, William Storck, Olivia Billett, Mitul Jambusaria, Andy Sadhwani, Pierric Jammes, James Cutler
Small Satellite Conference
The Stanford Space Systems Development Laboratory (SSDL) is developing several CubeSat missions (including KatySat) that can benefit from onboard propulsion systems. CubeSats are generally one to two kilograms and made of one to three units of 10 cm cubes. The small size puts a premium on real estate and power. Onboard thrusters would have to be compatible with these restrictions. Ideally, a thruster system could provide thrust for attitude control and primary propulsion for docking/rendezvous, observation/inspection, and formation flying. A survey is presented of existing technology driven by the following primary requirementsIbit less than 1mNs, mass less than 1kg, and …
Hexpak – Big Area From A Small Satellite, Michael Hicks, Larry Capots
Hexpak – Big Area From A Small Satellite, Michael Hicks, Larry Capots
Small Satellite Conference
HexPak is a deployable satellite structure that offers several advantages to small satellite missions, including ease of scalability, a geometry naturally adapted for plug-and-play architectures and multiple missionspecific component layouts, and a large deployed aperture from an optimal stowed volume. It consists of hexagonal bays that stack when stowed to efficiently use payload fairing volume, but deploy to a planar structure with deck area many times the fairing cross-section. The large deployed area to fairing size ratio supports large aperture payloads, multiple payloads, heat rejection significantly beyond traditional designs, multiple manifest with minimal wasted support mass, and easy access on …
Modular Cmos Horizon Sensor For Small Satellite Attitude Determination And Control Subsystem , Mohamad Dol Bahar, Mohd Effandi, Mohd Hassan, Norhizam Hamzah, Ahmad Arshad, Xandri Farr, Lourens Visagie, Willem Steyn
Modular Cmos Horizon Sensor For Small Satellite Attitude Determination And Control Subsystem , Mohamad Dol Bahar, Mohd Effandi, Mohd Hassan, Norhizam Hamzah, Ahmad Arshad, Xandri Farr, Lourens Visagie, Willem Steyn
Small Satellite Conference
A typical horizon sensor has an average RMS accuracy of 0.2° for satellite attitude determination, with a mass of between 1 to 4kg and consumes 3 to 10W total power, while the ATSBTM CMOS horizon sensor has an RMS accuracy of better than 0.1°, a mass of 560g and consumes only 550mW when imaging. The CMOS horizon sensor which has a total Field of View (FOV) of approximately 90° can process the image data, calculate and transmit the nadir vector to the Attitude Determination and Control Subsystem (ADCS) On Board Computer (OBC) via a dual redundant CAN communication bus. Apart …
Risk Management Of Student-Run Small Satellite Programs, Elizabeth Deems
Risk Management Of Student-Run Small Satellite Programs, Elizabeth Deems
Small Satellite Conference
This paper proposes a risk management approach for university-affiliated, small satellite programs. These small programs have a unique set of risks because of a typically inexperienced workforce, limited corporate knowledge, occasional distributed tasking among universities, and a high student turnover rate. Only those risks unique to small, student-run satellite programs are presented. Additionally, several risk management strategies are explored, and the advantages and disadvantages of these risk-related tools and techniques are examined. To aid the process of risk identification in these particular programs, a Master Logic Diagram (MLD) for small satellites was created to help identify potential initiating events that …
Sseti – Past, Present And Future, Tor Viscor
Sseti – Past, Present And Future, Tor Viscor
Small Satellite Conference
The Student Space Exploration and Technology Initiative (SSETI) was started by the European Space Agency (ESA) Education Department to help students in building and launching satellites. Though originally concentrated around a single satellite project the SSETI programme now encompasses three satellite projects. These projects include over 25 universities from 14 European countries and Canada enabling currently around 400 students from 50 subsystem teams to gain experience in all aspects of satellite design, building, launching and in orbit mission control. Currently three projects are being worked on, well representing the past, the current and the future projects within the SSETI programme. …
A Model-Based Design Tool For Systems-Level Spacecraft Design , Brandon Eames, Allan Mcinnes, Jared Crace, Joe Graham
A Model-Based Design Tool For Systems-Level Spacecraft Design , Brandon Eames, Allan Mcinnes, Jared Crace, Joe Graham
Small Satellite Conference
It is standard practice to mathematically model and analyze the various subsystems that make up a spacecraft, to ensure that they will function correctly when built. However, the system-level behavior of the spacecraft is generally understood in much less rigorous terms. This leaves the spacecraft system far more vulnerable than the subsystems to unforeseen design errors which may not manifest themselves until the integration and test phase, when design changes are most expensive in terms of cost and schedule. In this paper, we present Spacecraft Design Workbench, an extensible graphical design tool built upon the Generic Modeling Environment (GME) tool …
Minnesat: Gps Attitude Determination Experiments Onboard A Nanosatellite, Vibhor Bageshwar, Demoz Gebre-Egziabher, William Garrard, Jason Mintz, Jason Andersen, Ella Field, Vincent Jusuf, Abdul Khan, Nathan Moehnke, James Pogemiller
Minnesat: Gps Attitude Determination Experiments Onboard A Nanosatellite, Vibhor Bageshwar, Demoz Gebre-Egziabher, William Garrard, Jason Mintz, Jason Andersen, Ella Field, Vincent Jusuf, Abdul Khan, Nathan Moehnke, James Pogemiller
Small Satellite Conference
This paper presents an overview of the attitude determination experiments onboard the University of Minnesota nanosatellite, Minnesat. Minnesat is designed as a test bed for conducting ultra-short baseline GPS attitude determination experiments in Earth orbit. The primary scientific mission of the Minnesat project is to design, develop, and validate an ultra-short baseline GPS attitude determination (AD) system. Minnesat is equipped with a set of sensors to support two independent AD systems that are referred to as the Primary AD System and the GPS AD System. The Primary AD System blends measurements of inertial sensors with measurements of a three-axis magnetometer …
Attitude Control Strategy For Hausat-2 With Pitch Bias Momentum System, Young-Keun Chang, Seok-Jin Kang, Byung-Hoon Lee, Jung-Won Choi, Mi-Yeon Yun, Byoung-Young Moon
Attitude Control Strategy For Hausat-2 With Pitch Bias Momentum System, Young-Keun Chang, Seok-Jin Kang, Byung-Hoon Lee, Jung-Won Choi, Mi-Yeon Yun, Byoung-Young Moon
Small Satellite Conference
The HAUSAT-2 is a 25kg class micro/nanosatellite which is being developed by graduate students at the Space System Research Laboratory(SSRL). This paper addresses a newly proposed strategy for detumbling the HAUSAT-2 and starting up a momentum wheel, and also studies performance validation and application ranges of such method through simulation. B-dot logic is generally used for controlling the initial tip-off rate. However, it has the disadvantage of taking a relatively long time to control the initial tip-off rate. To solve this problem, this paper suggests a new detumbling control method to be able to adapt to micro/nanosatellite with the pitch …
The University Nanosat Program From Concept To Flight: A Dual Student Program Perspective On What Works And What Does Not, Scott Franke, Marcin Pilinski, Millan Diaz-Aguado, Stephen Forbes, George Hunyadi
The University Nanosat Program From Concept To Flight: A Dual Student Program Perspective On What Works And What Does Not, Scott Franke, Marcin Pilinski, Millan Diaz-Aguado, Stephen Forbes, George Hunyadi
Small Satellite Conference
The University Nanosatellite Program of the Air Force Research Laboratory provides a paradigm-changing environment for the leaders of tomorrow’s space industry to envision solutions for today’s small satellites. The products of the Program are an educated, experienced workforce that will meet the demands of tomorrow, along with a spectrum of small satellite technologies onboard student-built nanosatellite flight missions. This paper reveals intangible aspects of the systems engineering and integration process that are usually lacking in new hires. Students involved in the UNP program come out with an experienced perspective well beyond what the current higher education system provides. Examples of …