Solid Underconstrained Multi-Frequency Deployable Antenna

A solution for a high frequency (up to 240 GHz), wide bandwidth, deployable reflector is needed to enable a low-cost and platform-versatile approach for the integration of three key instruments in upcoming Earth Science space missions. Cloud and precipitation radar payloads require a ~2-meter antenna aperture to capture the evolution of atmospheric processes at high spatial resolution. Microwave radiometers require an antenna operating from 6 to 200 GHz with a ≥ 2-meter diameter conically scanning (spinning) antenna for adequate footprint. The Differential Absorption Radar (DAR) instrument, pioneered by JPL, requires a large ~2-meter diameter antenna to focus and detect radar signals from hydrometeors at frequencies spanning from 155 to 175 GHz. Currently, all approaches for deployable reflectors operating above 90 GHz are in the TRL2-TRL3 range, and none appear to be conducive to spinning applications. Therefore, current mission baselines require a solid reflector, increasing cost and spacecraft size. A deployable reflector that supports frequencies from 6-240 GHz would decrease the cost of future missions, enabling missions that are performance-constrained by the size of antennas to fit on a smaller spacecraft, thereby enabling constellations. To provide a solution to this antenna need, we are proposing the Solid Underconstrained Multi-Frequency (SUM) deployable antenna, a multi-segment, offset-fed parabolic solid deployable antenna system, which would enable large, high-frequency apertures to deploy from a compact volume of stacked segments. The proposed antenna is 2 meters in diameter, operating at frequencies between 2 GHz and 240 GHz, and can stow in a volume of 0.5 x 0.56 x 0.7 m^3. The core elements of the SUM deployable antenna consist of the aperture segments (semi-hexagons), rough deployment guides (high strain composite (HSC) rods), and systems for retrieval, preloading (cable), and kinematic location. When stowed, the segments stack neatly on top of each other into a compact volume. After launch, launch locks are activated, releasing the segments, and the HSC rods deploy the system into an initial configuration. Two HSC rods arrange each element in its proper orientation, so the system can be pulled together. After the deployable antenna opens, the cables are then retracted, slowly reeling in each of the segments into the final deployed shape. Kinematic joints precisely locate each segment relative to each other within 20 microns, preloaded in place by the cable, for an overall surface root mean squared (RMS) error of ~60 microns. The final system has only rigid segments in the design, meaning it is not subject to errors from creep. Because of its under-constrained deployment configuration, unlike hinged antennas, the segments can be stored anywhere on the spacecraft where there is spare volume, maximizing stowed efficiency. Under this ACT, we will first build a prototype of the kinematic joint, and a small-scale prototype of the system. Then, a full-scale set of 3 segments will be constructed, deployment tested multiple times, and then the RF performance will be measured, demonstrating component validation in a laboratory. This work will occur over three years, and raise the TRL of the concept from an entry TRL of 2, to an exit TRL of 4.

Accelerate mission development and reduce risk by developing critical components and subsystems for advanced instruments and observing systems

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