DR-2652-5042026 Two-Axis Gimbal for Kilowatt-Class Hall Thrusters RFI.docx

Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Drive Pasadena, CA 91109-8099

June 3, 2026

SUBJECT: REQUEST FOR INFORMATION (RFI) DR-2652-5042026: Two-Axis Gimbal for Kilowatt-Class Hall Thrusters

The Jet Propulsion Laboratory (JPL) is seeking information from qualified vendors regarding their capability to provide two-axis Thruster Gimbal Assembly (TGA) mechanisms now or in the near-term that could meet the requirements outlined below.

This RFI is for planning purposes only and does not constitute a solicitation or commitment to procure any services. Neither JPL nor the U.S. Government will be responsible for any costs incurred by you in furnishing any information. Responses received will be carefully reviewed by JPL and may be considered as part of a future solicitation. Prospective subcontractors are advised that any information provided shall be deemed to be furnished with unlimited rights to JPL, with JPL assuming no liability for the disclosure, use, or reproduction of such data. The requested information is intended to be shared by JPL with internal JPL requesters.

This RFI is to also gather information of potential qualified sources and to obtain your business size relative to the following NAICS code: 336414 – Guided Missile and Space Vehicle Manufacturing with a size standard of 1,300 employees. Responses to this RFI may be used by JPL to make appropriate decisions regarding a Small Business Set-Aside procurement.

All responses shall be submitted by 3:00 PM Pacific Time on July 17, 2026 electronically to the undersigned.

Below are some critical dates as it pertains to this Request for Information (RFI):

· Written RFI Questions are due by June 24, 2026, via submission to the undersigned by email. No written questions will be accepted after June 24, 2026.

· JPL will respond to written questions by July 8, 2026.

· As stated above, all responses shall be submitted by 3:00 PM Pacific Time on July 17, 2026.

Information about JPL can be found at: https://www.jpl.nasa.gov/who-we-are/.

Thank you, Dominique Reyes JPL Subcontracts Manager

(626) 659-3497 Dominique.reyes@jpl.nasa.gov

1.0 BACKGROUND

The Jet Propulsion Laboratory (JPL), a Federally Funded Research and Development Center (FFRDC) managed by Caltech, is NASA's center for robotic exploration of the solar system, driving critical, nationally significant missions that range from Mars rovers to deep space telescopes.

NASA is maturing two high-performance, long-life kW-class Hall thruster models for deep-space small satellite missions: the Magnetically Shielded Miniature (MaSMi) Hall thruster was developed at the Jet Propulsion Laboratory (JPL), and the NASA-H71M Hall thruster was developed at the NASA Glenn Research Center (GRC).

Figure 1: The MaSMi (left) and NASA-H71M (right) Hall thrusters, mounted for testing in the laboratory.

For most spacecraft applications of these thrusters, a two-axis Thruster Gimbal Assembly (TGA) mechanism is required to provide thrust vector control during primary firings and for spacecraft attitude management and momentum unloading. NASA and JPL are assessing potential commercially available TGA solutions that may be compatible with these thrusters and suitable for integration into future small-satellite propulsion systems.

The objective of this Request for Information (RFI) is to gather technical and programmatic information regarding TGAs available now or in the near-term that could meet the requirements outlined below.

Respondents are encouraged to provide information regarding existing products, designs currently in development, or concepts that could be adapted to meet the requirements described in this document.

Vendors may choose to respond to all of the questions listed below, or a subset of them (partial responses will be accepted for this RFI).

Spacecraft body 2-axis Gimbal Hall Thruster

Figure 2: Typical configuration.

2.0 SCOPE TASKS

Technical Details and Requirements

2.1 A two-axis (orthogonal) TGA is required. The following parameters represent initial target specifications for compatibility with the MaSMi and NASA-H71M Hall thrusters. Provide confirmation of whether your existing two‑axis (orthogonal) TGA hardware meets the following target specifications. If not, describe what modifications would be required.

· Angular range per axis: +/- 15 degrees minimum

· Angular pointing accuracy: +/- 0.1 degrees or better

· Mass: ≤ 5 kg

· Mounting footprint: < 24 cm x 24 cm

· Height: ≤ 15 cm

· Power consumption: maximum < 20 W, idle < 5 W

· Input voltage: 28 V nominal

· Minimum operating temperature: -40 C

· Capable of handling heat flux to gimbal from MaSMi and NASA-H71M (refer to thruster specs below) while staying below maximum operating temperature

· Position locking capability required for launch

2.2 Provide the following additional technical information:

· Actuator type (stepper, brushless DC, etc.)

· Control electronics architecture

· Position sensing approach (resolver, encoder, etc.)

· Achievable slew rates and response times

2.3 Confirm compatibility with the following thruster specifications. If any interface constraints or modifications are required, please identify them.

a. MaSMi:

· Thruster mass: 3.4 kg

· Mounting interface: 8.25 cm diameter hole pattern, 6x 1/4‑28 bolts torqued to 105 in‑lbs

· Two propellant lines (1/8 in OD tube) connected to upstream (gimbal‑facing) side

· One electrical harness connected to upstream (gimbal‑facing) side

· Heat flux to gimbal during operation: ≤15 W

b. NASA‑H71M:

· Thruster mass: 3.2 kg

· Mounting interface: ~12.2 cm diameter hole pattern, 6x 8‑32 screws torqued to 27 in‑lbs

· Two 1/8 in OD stainless steel propellant lines connected to the side face

· Main electrical harness connected to the side face

· Secondary harness carrying survival heater power and temperature measurement from gimbal‑thruster interface

· Heat flux to gimbal during operation: ≤15 W Environmental and Qualification Information

2.4 Describe the capability of your TGA design to survive the following relevant launch and on-orbit environments:

· Launch vibration and shock

· Thermal vacuum (operational and non‑operational)

· Radiation tolerance in krad

· Operational lifetime in cycles

2.5 Describe your proposed interface between the thruster and gimbal to manage thermal load and mechanical interface requirements.

2.6 Provide information (if available) regarding:

· Development and qualification testing history

· Maturity and validation of dynamic and thermal models

· Technology readiness level (TRL)

· Flight heritage

Cost Estimate and Schedule Information Affordability and lead time are important considerations for electric propulsion systems proposed for small satellite missions.

2.7 Provide non‑binding rough order of magnitude (ROM) cost and schedule information for the proposed TGA for both flight units and engineering/qualification units. Include any configurable options that significantly affect cost.

· Estimated cost and schedule for flight units

· Estimated cost and schedule for engineering or qualification units

2.8 Short‑answer questions regarding cost sensitivity:

· How would cost change if the required angular range per axis is narrowed or expanded?

· How would cost change if angular pointing accuracy is relaxed or tightened?

· How would cost change if the operating temperature range is narrowed or expanded?

· How would cost change if mass and volume requirements are narrowed or relaxed?

3.0 VENDOR RESPONSE TEMPLATE

Company Information

Company Name

Address

Point of Contact

Title

Email

Phone Number

CAGE/UEI

☐ SDB

☐ SBA Certified WOSB ☐ SBA Certified VOSB ☐ SBA Certified SDVOSB ☐ SBA Certified HUBZone

☐ HBCU/MSI

☐ Large Business

☐ No

☐ No

☐ No

If applicable, please list your teaming partners.

The scope tasks below correspond to those listed in Section 2. In the chart below, please mark an “X” under “Yes” for each area that aligns with your company’s capabilities and experience.

2.1 Technical Requirements

Two‑axis (orthogonal) TGA provided

Angular range per axis of +/- 15 degrees minimum

Angular pointing accuracy of +/- 0.1 degrees or better

Total mass ≤ 5 kg

Mounting footprint < 24 cm x 24 cm

Height ≤ 15 cm

Power consumption < 20 W maximum

Idle power < 5 W

Input voltage of 28 V nominal supported

Minimum operating temperature of -40 C

Capability to handle thruster heat flux (≤15 W) while staying below maximum operating temperature

Position locking capability for launch

2.3 Thruster Capability

a. MaSMi

Compatible with 3.4 kg thruster mass

Compatible with 8.25 cm diameter, 6x 1/4‑28 mounting interface

Accommodates two 1/8 in OD propellant lines on upstream side

Accommodates upstream electrical harness routing

b. NASA-H71M

Compatible with 3.2 kg thruster mass

Compatible with ~12.2 cm diameter, 6x 8‑32 mounting interface

Accommodates two 1/8 in OD stainless steel propellant lines on side face

Accommodates side‑face main electrical harness

Accommodates secondary survival‑heater/temperature harness

Short Answer Questions Note that we will accept partial vendor responses to these questions.

2.1 Describe any hardware modifications to meet the target TGA specifications.

2.2 Provide the following additional technical information:

· Actuator type (stepper, brushless DC, etc.)

· Control electronics architecture

· Position sensing approach (resolver, encoder, etc.)

· Achievable slew rates and response times

2.3 Identify any interface constraints or modifications required to accommodate the MaSMi and/or the NASA-H71M thruster

2.4 Describe environmental survivability, including launch vibration and shock, thermal vacuum, radiation tolerance (krad), and operational lifetime in cycles.

2.5 Describe your proposed interface between the thruster and gimbal to manage thermal load and mechanical interface requirements.

2.6 Provide development and qualification testing history, maturity and validation history of dynamic and thermal models, TRL, and flight heritage (if available).

2.7 Provide non‑binding rough order of magnitude (ROM) cost and schedule information for the proposed TGA for both flight units and engineering/qualification units. Include any configurable options that significantly affect cost.

· Estimated cost and schedule for flight units

· Estimated cost and schedule for engineering or qualification units

2.5 Describe your proposed interface between the thruster and gimbal to manage thermal load and mechanical interface requirements.

2.8 Cost Sensitivity Questions

· How would cost change if the required angular range per axis is narrowed or expanded?

· How would cost change if angular pointing accuracy is relaxed or tightened?

· How would cost change if the operating temperature range is narrowed or expanded?

· How would cost change if mass and volume requirements are narrowed or relaxed?

[Optional – Attach or enter Capabilities Statement for areas outside those identified above]

Please give us 3 or more examples of your relevant past performance in the format below.

Past Performance #1

Contract Name:

Tier 1 (Prime) /Tier 2/ Tier 3?:

Summarized Scope of Work – Provide Technical Details Here

Past Performance #2

Contract Name:

Tier 1 (Prime) /Tier 2/ Tier 3?:

Summarized Scope of Work – Provide Technical Details Here

Past Performance #3

Contract Name:

Tier 1 (Prime) /Tier 2/ Tier 3?:

Summarized Scope of Work – Provide Technical Details Here

Please include “Two-Axis Gimbal for Kilowatt-Class Hall Thrusters RFI Response” in the subject line of your email to the Dominique Reyes, Subcontracts Manager, at Dominique.reyes@jpl.nasa.gov. JPL may contact you to ask questions or request further information.

DISCLAIMER: There is no commitment or guarantee on the part of JPL to move forward with a Request for Proposal (RFP) at this time.

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