Development of a satellite structural architecture for operationally responsive space

Arritt, Brandon; Buckley, Steven; Ganley, Jeffrey M.; Welsh, Jeffry S.; Henderson, Benjamin K.; Lyall, M. Eric; Williams, Andrew D.; Preble, Jeffrey C.; DiPalma, John; Mehle, Greg; Roopnarine, R

doi:10.1117/12.776319

Cited by 6 publications

(4 citation statements)

References 4 publications

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“…In addition, RS has the potential to provide low-cost, reliable spacecraft and launch vehicles. The Operationally Responsive Space (ORS) office has been directed to strive for satellite costs under $40 million and launch costs under $20 million [17]. RS mission characteristics will fall into one of two categories.…”

Section: Responsive Spacementioning

confidence: 99%

“…0 deg c S 00 cos dt R P 0 S 00 cos dt(17) which can be rewritten as alb alb 0 deg c(18) Albedo values at a solar zenith angle of 0 deg alb 0 deg were collected from the ERBE, which includes data as a function of three distinct i bands (i.e., 0-30, 30-60, and 60-110 deg) for several averaging periods (i.e.,16, 128, and 896 s, 30 and 90 min, and 6 and 24 h). The 16-s time averaging data provide the most extreme values.…”

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confidence: 99%

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Hot- and Cold-Case Orbits for Robust Thermal Control

Hengeveld

Braun

Groll

et al. 2009

Journal of Spacecraft and Rockets

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Realizing cheaper, more flexible alternatives to traditional satellites requires robust design approaches. Robust satellite subsystems are designed to meet a broad range of mission requirements; consequently, they drastically reduce nonrecurring engineering costs and greatly diminish design, development, assembly, integration, and test schedules. Robust thermal control subsystems must be capable of handling a broad range of thermal environments, thus reducing design and development costs but can be susceptible to overdesign. Therefore, improved design methodologies are needed to maintain their advantages while minimizing excessive design. As a first step, design hotand cold-case orbits should be examined. The primary goal of the study described in this paper was to identify single hot-and cold-case design orbits that work well in the design of robust thermal control subsystems over a wide range of satellite surface properties and likely operating environments. A general approach was developed to identify worst-case orbits that employ a combination of statistical and historical data such that statistically insignificant orbits are disregarded. Using this method, individual hot-and cold-case design orbits were found at beta angle/ inclination combinations of 72 deg =52 deg and 0 deg =28 deg, respectively. The use of these design orbits works well for a wide range of different satellite surface properties. Nomenclature a = semimajor axis, km c = albedo correction term, dimensionless c = average albedo correction term, dimensionless cos = cosine solar zenith angle, dimensionless D = current day, day d = days from J2000.0, days E 00 = Earth-emitted irradiation, W=m 2 F s E = view factor from spherical satellite to spherical Earth, dimensionless f = eclipse fraction, dimensionless g = mean anomaly, deg h = low-Earth-orbit altitude, km i = inclination of orbit, deg JD = Julian Day, day K = orbital-averaged albedo flux correction factor, dimensionless L = mean longitude of the Sun, deg M = current month, month P = orbital period, min q 00 = orbital-averaged extreme external environmental heat load, W=m 2 q 00 alb = orbital-averaged albedo flux, W=m 2 q 00 OLR = orbital-averaged outgoing longwave radiation flux, W=m 2 q 00 sol = orbital-averaged direct solar flux, W=m 2 R E = Earth's radius, 6378 km r = spherical satellite radius, m S 00 = direct solar irradiation, W=m 2 t = time, day Y = current year, year = surface solar absorptivity, dimensionless = beta angle, deg = cutoff beta angle used to determine eclipse fraction, deg = reference direction in mean equinox of date system = declination of the sun, deg " = obliquity of ecliptic, deg " = surface longwave emissivity, dimensionless = solar zenith angle, deg = ecliptic longitude, deg = true anomaly, deg alb = albedo fraction, dimensionless alb = average albedo, dimensionless alb 0 deg = albedo fraction at solar zenith angle of 0 deg, dimensionless alb = solar zenith angle dependent albedo, dimensionless ' = angular orbital position measured at zero at the most-nearly su...

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Section: Responsive Spacementioning

confidence: 99%

mentioning

confidence: 99%

Hot- and Cold-Case Orbits for Robust Thermal Control

Hengeveld

Braun

Groll

et al. 2009

Journal of Spacecraft and Rockets

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“…However, over the last decade, there have been many studies focused on developing PnP components [2][3][4][5]. There has also been a concerted effort by the ORS office and AFRL to create PnP standards resulting in the first PnP satellite, named PnPSat I.…”

Section: Introductionmentioning

confidence: 99%

A constraint based approach for building Operationally Responsive Space satellites

Kahraman¹,

Swenson

Black

2009

2009 4th International Conference on Recent Advances in Space Technologies

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The Operationally Responsive Space program requires flexible and responsive satellites to meet their user's needs. Traditional satellite design methods are typically iterative processes that optimize individual components, subsystems, and ultimately the entire satellite. This study focuses on developing a new approach for creating Responsive Satellites from Plug-andPlay components. The aim is to create an approach that quickly evaluates a wide variety of possible satellite configurations and identifies the best configurations that meet the user's needs and constraints. Satellite configurations are created by matching locations on the satellite structure with Plug-and-Play components. Various constraints are derived from the user's inputs at different levels of the configuration process. As the user provides more information related to Plug-and-Play satellite, additional constraints can be applied to reduce the number of Plug-and-Play satellite configurations resulting in manageable numbers of configurations from which the user can ultimately select the final configuration.

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“…Ideally a single modular architecture will be compatible with a range of mission types, orbits and related space environments, launch vehicles, and technology upgrades. 3 Assembly, integration and test typically account for 6 months to 2 years of the spacecraft production cycle. This process could be drastically reduced by stocking component-ready modular panels for assembly.…”

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confidence: 99%

Rapid assembly of spacecraft structures for responsive space

Yachbes

Roopnarine

Sadick

et al. 2009

2009 IEEE Aerospace Conference

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In order to achieve a six-day spacecraft architecture, the assembly, integration & testing (AI&T) of the Satellite Bus could be drastically reduced by stocking component-ready modular panels for assembly. The assembly of the structure itself, however, needs to be accelerated from the typical process of securing panels with dozens of mixedsize fasteners and the associated verification, tooling, and documentation that must also take into consideration the need to pass electrical and thermal connections across panels of the bus. A method for rapidly providing a stiff mechanical attachment across panels of a spacecraft bus, while simultaneously providing electrical and thermal continuity, helps to further realize the goals of Responsive Space (RS). A fastening strategy has been developed for enabling rapid assembly of a spacecraft bus structure using Honeybee's patented Quick Insertion Nut (QIN) technology. The QINs are embedded in manifolds which reside at each edge inside the spacecraft bus (the manifold includes panel-to-panel electrical interconnects) and together form a skeletal structure for the spacecraft panels. Initial FEA analyses show that a bus construction based on this concept is capable of meeting the natural frequency requirements for a wide array of launch vehicles and that the QINs themselves are capable of withstanding very high tensile loads with positive margins of safety.

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Development of a satellite structural architecture for operationally responsive space

Cited by 6 publications

References 4 publications

Hot- and Cold-Case Orbits for Robust Thermal Control

Hot- and Cold-Case Orbits for Robust Thermal Control

A constraint based approach for building Operationally Responsive Space satellites

Rapid assembly of spacecraft structures for responsive space

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