Tab_19-_Specifications_post.pdf

ATTACHMENT 1: 80GRC019Q0002

Electronically Steered Ka‐Band Antenna Specifications This procurement is for a low‐cost, small‐satellite‐class, Ka‐band phased array antenna for direct‐to‐earth communications links in support of the NASA SmallSat Ka‐band Operations User Terminal (SKOUT) project.

The objectives of SKOUT are to:

1. Demonstrate Ka‐band phased array technology for direct‐to‐earth links to meet the needs of near‐term NASA missions;

2. Develop a Ka‐band antenna that meets or exceeds current communications payload performance (e.g., size, weight, power, cost, data rate) used today at S/X/Ka‐bands;

3. Utilize commercial best practices, leveraging components from the growing commercial 5G Ka‐band market, with appropriate screening/analysis for space applications.

The antenna shall meet the following ‘Minimum Requirements’. The ‘Target Performance Values, which are provided as desired performance metrics, may be met individually in the base bid or as options.

Requirements for Electronically Steered Ka‐Band Antenna

Parameter Minimum Requirements Target Performance Values

Transmit (Tx) Frequency Range 25.5 – 27.0 GHz 25.25 – 30.0 GHz

Receive Frequency Range Not required 25.25 – 27.5 GHz

Field of View (FOV) +/‐ 60 degrees 2D +/‐ 65 degrees 2D

Polarization RHCP or LHCP Selectable RHCP and LHCP

Instantaneous Bandwidth (BW) >250 MHz 1 GHz

Axial Ratio < 8dB over FOV for full frequency range

< 3dB over FOV for full frequency range

Effective Isotropic Radiated Power (EIRP) at Boresight at the 1dB Compression Point

+20 dBW low power mode, and +30 dBW high power mode

Sidelobe Level Across Operating Temperature Range

‐10 dB or less from main beam over FOV

‐20 dB or less from main beam over FOV

Number of Tx Beams 1 **

Return Loss Over Operating Frequency and Temperature

< ‐10 dB < ‐15 dB

Radio Frequency Interface Coax, < 10 dBm input **

Beamformer Controller Control at the individual element level, plus Az/El

Beam Update Rate <= 15 microseconds **

Expected Lifetime at 400‐700km Orbit

6 months 2 years

Antenna Weight* <= 3 kilograms <= 1 kilogram

Operating Temperature ‐40C to +85C **

DC Power Consumption <30 Watts low power mode <70 Watts high power mode

Bus Voltage < 30 Volts **

* ‐ Weight of antenna, not including a thermal solution.

** ‐ No target performance value is established for this parameter.

The vendor shall propose an appropriate antenna control interface (e.g., LVDS, CAN, RS422, Ethernet). Antenna size shall be suitable for mounting on/in a standard 6U or 12U CubeSat form factor, where 1U is 10 x 10 x 10 cm.

The antenna requirements reference low and high power modes to provide mission flexibility based on the ability of the spacecraft bus to provide power and dissipate thermal load. The high power mode uses all elements of the phased array antenna at once; the low power mode uses only a subset of the elements. For example, high power mode may use 256 elements, while low power mode may use 64 elements with the remaining 192 elements in low‐power standby. The beamformer controller shall provide the ability for individual elements or groups of elements to be powered off or placed in standby mode to enable high and low power operation.

The vendor shall provide analysis showing that the antenna and beamformer controller will survive operation in a 400 – 700km orbit radiation environment for a minimum life of 6 months. The analysis should address typical space electronics concerns such as Single Event Effects, latch‐up, total dose, etc. The antenna should leverage commercial components with up‐screen for potential future space applications, and therefore formal space qualification is NOT required.

The antenna and beamformer controller shall operate in a space environment. Their designs shall include considerations for vacuum, outgassing, and thermal cooling via conduction mechanisms.

Evaluation of Quotations

The vendor shall provide a proposal that contains the phased array antenna design, manufacturability, expected performance, consideration of space environment effects, schedule to delivery, evidence of management capability and prior performance in developing spaceflight hardware, and cost. If desired, proposals may contain option(s) to meet Target Performance Value(s).

The government will select a proposal for award based on Best Value criteria. Best value takes into account these factors, applied to the base bid, in ranked order of importance:

[Significantly Important] Technical capability and quality

[Important] Cost

[Important] Vendor prior performance in developing spaceflight hardware

[Less Important] Schedule to delivery

The evaluation process will not consider options presented in a proposal. Vendors should balance the technical capability of the base bid against cost and schedule, reserving options for cases where enhanced technical capability adds significant cost or schedule.

Deliverables

At conclusion of the contract, the vendor shall provide the following deliverables:

Electronically steered Ka‐band antenna and beamformer controller

Software for antenna operation, if applicable

Performance test results and/or analysis for each requirement

Documentation of antenna interfaces, control parameters, set‐up, and related.

Final antenna data sheet showing measured performance

Supplemental Acronym List

Az Azimuth

CAN Controller Area Network

DC Direct Current

El Elevation

LHCP Left Hand Circular Polarization

LVDS Low Voltage Differential Signaling

RHCP Right Hand Circular Polarization