No abstract

No abstract

No abstract

The oscillating heat pipe is a novel, simply formed, wickless heat pipe that relies on the phase-change-induced motion of a contained working fluid to transport heat between the evaporator (hot end) and condenser (cold end). The improved heat transfer capability, simplicity, and reduced mass of oscillating heat pipes have led to great interest in the oscillating heat pipe. This paper details the terrestrial and microgravity validation of an ultrasonic consolidation manufactured structurally embedded oscillating heat pipe. It is shown that 1) for conditions in which an oscillating heat pipe is terrestrially orientation-independent, it is also likely to be gravity-independent, and 2) for conditions in which an oscillating heat pipe is not terrestrially orientation-independent, it is likely to perform better in microgravity than in a terrestrial environment. Additionally, this test campaign provides evidence that the "knee" found in most oscillating heat pipe performance versus input heat curves roughly corresponds to the point at which 1) oscillating heat pipe performance variation drops off, 2) oscillating heat pipe performance becomes orientation-independent, and 3) the oscillating heat pipe performance becomes gravity-independent. These results can be used to better predict oscillating heat pipe performance using terrestrial test data.

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...

Graphite Storable Tubular Extendable Masts (GSTEMs) are being investigated and developed for use as an extendable spacecraft boom that can be deployed and retracted on orbit. The advantages of GSTEMs over traditional metallic deployable booms include reduced thermal deformations due to reduced coefficient of thermal expansion and stronger/stiffer booms due to higher strain limit allowing thicker materials to be used. Despite the advantages of GSTEMs, much work is needed to understand and characterize their performance. The work presented here investigates thermal characteristics of GSTEMs. Challenges include accurately capturing anisotropic thermal properties and inherent overlapping construction. Consequently, experimental work was necessary to correlate thermal modeling efforts. Work presented here has illustrated the effectiveness of thermal models for predicting overlapped GSTEM temperatures in a simulated space thermal environment. These models were verified against thermal vacuum testing and can be used to extrapolate models to predict on-orbit GSTEM temperature distributions. These correlated models will provide a useful tool for predicting on-orbit thermal performance which can then be used to predict other performance aspects including thermal deformations.

No abstract

No abstract