研究目的
To develop a low-profile, ultra-wideband, active electronically scanned array (AESA) inside a size-constrained spacecraft, a 3U CubeSat, for space-borne applications.
研究成果
The AM-FUSE AESA represents a cost-effective deployment of multi-function CubeSat, suitable for space-borne missions with its wideband characteristic, electronic steering, and low SWaP-C. The AESA is scalable to other frequencies and array sizes.
研究不足
The pointing accuracy is limited by the small size of the 8x4 array. The design requires protection for semiconductor subcomponents in the beamforming electronics to extend the lifetime in space environments.
1：Experimental Design and Method Selection:
The AESA was designed as a broadband multifunction array providing continuous operation over L, S, and C bands, scanned +/- 45 degrees with no beam squinting. It includes an 8x4 array based on Frequency-scaled Ultra-wide Spectrum Element (FUSE) radiating elements realized by all-metal additive manufacturing (AM), a printed circuit board (PCB) of combiners, and a beamforming circuit board utilizing true-time-delay unit (TDU) and a transmit and receive (T/R) switch.
2：Sample Selection and Data Sources:
The array is required to operate from
3：5 GHz to 6 GHz. An 8x4 elements array sized for half-wavelength lattice at maximum frequency of 6 GHz was chosen. List of Experimental Equipment and Materials:
The AESA includes an 8x4 linearly polarized aperture, low-profile feed circuitry with eight true-time delay units (TDU), and beamforming boards.
4：Experimental Procedures and Operational Workflow:
The AESA was characterized before being installed on the CubeSat, including radiation shielding analysis, radiation patterns measurement at wide scan angles, and environmental testing under thermal cycling and random vibration exposure.
5：Data Analysis Methods:
The performance of the AESA was evaluated through simulations and measurements, including active input impedance, radiation patterns, and s21 transmission coefficient.
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