MBARS Antenna

NASA Request For Proposals Dual Frequency, Lens Antenna for the Microwave Barometric Attenuation Radar and Sounder (MBARS) Instrument
1. Objective
The National Aeronautics and Space Administration is seeking to procure a compact, light-weight, high-gain, dual-frequency antenna that will be incorporated into a high-altitude, remote sensing system. While there are multiple designs that could meet the basic requirements, the antenna must be compatible with TWO radar systems and a beam scanner subsystem; therefore, the referenced design is shown here that is STRONGLY preferred to maximize compatibility with the other subsystems. Other designs can be offered and will be evaluated on their performance and compatibility with the overall system design and performance objectives.
The following specifications will be used to evaluate candidate Proposals for this procurement, assuming sufficient funding is available; each category/criteria should be individually addressed in the offeror’s proposal.
2. Mechanical/Electrical Characteristics
The antenna should produce TWO concentric RF beams: one supporting V-band (65-70GHz) and a second supporting W-band (94GHz). The individual specifications are listed below (note, the term nominal expresses a general interest in meeting the provided specification, the term maximum or
minimum expresses a limit on a specification, and the term required expresses a firm specification that must be met).
General Specification
Value/Range
Maximum outside diameter of the antenna (including the side feed)
14 in
Nominal diameter of lens
12 in
Maximum length of antenna (fore-to-aft)
20 in
Nominal weight
10 lb
Air Pressure (unsealed design)
0 – 70,000 Mean Sea Level
V-Band Specification
Value/Range
Required Operating Frequency
65 – 70GHz
Nominal Feed Location
Side Mounted
Minimum Overall Gain
44dBi
Nominal Half-Power Beam-Width
1.1 deg
Maximum Return Loss
-15db
Required Polarization
Parallel (to wires in reflector)
Minimum Cross-Pol Isolation
30dB
Maximum Sidelobe
-23dB
Required Waveguide Mount
WR-15
W-Band Specification
Value/Range
Required Operating Frequency
94 – 94.1GHz
Nominal Feed Location
Vertex of lens
Minimum Overall Gain
46dBi
Nominal Half-Power Beam-Width
0.8 deg
Maximum Return Loss
-15dB
Required Polarization
Perpendicular (to wires in reflector)
Minimum Cross-Pol Isolation
30dB
Maximum Sidelobe
-18dB
Required Waveguide Mount
WR-10
Operational Requirements
The antenna subsystem will be located in an unpressurized section of a high altitude aircraft; however, it will NOT be directly impacted by the wind stream.
The antenna subsystem shall operate nominally for upto 9hrs in high-altitude atmospheric conditions (eg, 10mb, -70°F, 0%RH) as well as show no performance degradation due to altitude cycling.
The use of heating or cooling components during flight operation is acceptable but shall be disclosed in the proposal to enable evaluation of the design and complexity of the anticipated installation.
General Requirements
The materials, wiring, connectors, and overall design for this subsystem must conform to aviation-grade materials, wiring, and connectors.
3. Deliverables
The following list represents the complete list of physical deliverables for this procurement:
3.1 The antenna design (CAD files, compatible with SolidWorks®).
3.2 The antenna hardware (in flight worthy condition) along with material, connector certifications that meeting the technical and operational requirements as stated herein.
3.3 RF performance data from the Contractor’s testing that demonstrates the Antenna meets the performance requirements as stated herein.
3.4 Installation/alignment documentation and acceptance test procedure.
4.1 Approximate Schedule of Events (relevant to ARO)
(15d) The Contractor shall conduct a Kickoff meeting to discuss design requirements. Purpose is to assure the Contractor fully understands the requirements and ensure the future design will meet NASA/project needs. This meeting can be remote (MS TEAMS) and should only require about 30-60 minutes.
(30d) The Contractor shall provide a preliminary design (CAD) and conduct a Preliminary Design Review to ensure the proposed design will: interface with the TWO radar systems, meet their technical needs, fit within / allow mounting to aircraft, and is compatible with the expected environmental/operational conditions. This meeting can be remote (MS TEAMS) and should only require about 60 minutes.
An updated status Email/telecom shall be provided every 10 business days after the PDR.
(180d) The Contractor shall work with NASA researchers (in person OR remotely) to demonstrate the antenna meets the technical requirements and successfully completes the acceptance procedure.