DOD SBIR 24.1 BAA

Active
No
Status
Closed
Release Date
November 29th, 2023
Open Date
January 3rd, 2024
Due Date(s)
February 21st, 2024
Close Date
February 21st, 2024
Topic No.
AF241-0012

Topic

High Temperature Mach number or Static Pressure Probes for Vitiated Flows

Agency

Department of DefenseN/A

Program

Type: SBIRPhase: BOTHYear: 2024

Summary

The Department of Defense (DOD) is seeking proposals for the topic of "High Temperature Mach number or Static Pressure Probes for Vitiated Flows" as part of their SBIR 24.1 BAA program. The Air Force branch is specifically interested in this topic (AF241-0012). The objective is to develop and demonstrate a local Mach number or Static Pressure probe technology suitable for hypersonic and high enthalpy flows. The technology will be used to understand the test conditions in high-speed hypersonic test facilities and reduce the uncertainty of test results. In Phase I, the selected proposal will consult with AEDC personnel, survey the industry for potential solutions, and develop the concept and design of the probe technology. Phase II involves developing and demonstrating a prototype probe-rake device in the test facility to demonstrate robustness and accuracy. In Phase III, the technology will be further refined for use within facility rake systems and can be easily commercialized for other high-speed and high-temperature wind tunnels. The project duration is not specified, but the proposal submission deadline is February 21, 2024. This solicitation presents an opportunity for researchers and companies to contribute to the advancement of hypersonic testing capabilities and potentially commercialize the developed technology. More information can be found on the grants.gov website or the DOD SBIR/STTR Opportunities page.

Description

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics; Integrated Sensing and Cyber; Advanced Materials

 

OBJECTIVE: Develop and demonstrate a local Mach number or Static Pressure probe technology suitable for hypersonic and high enthalpy flows.

 

DESCRIPTION: The Aerodynamic and Propulsion Test Unit (APTU) at the Arnold Engineering Development Complex (AEDC) is a high-speed hypersonic (HS/H) test facility capable of producing flight representative conditions (true temperature and pressure) via a combustion air heater (CAH). Understanding of any HS/H system under test requires a thorough understanding of the as-delivered free stream test conditions. The test conditions are typically characterized during dedicated test runs using intrusive diagnostics such as flow-field rakes with multiple discrete probes. Currently, the probes are limited to the assessment of total pressure and temperature with no direct measurement of local static pressure or Mach number. As such several assumptions and iterative techniques are required to assess the flow-field characteristics. With only wall statics along the nozzle inner mold line, analysis is limited to assuming a uniform static pressure across the flow field. Any divergence in the static pressure from this assumption is superimposed on the total pressure and Mach number profiles. A direct measurement of either static pressure or Mach number will negate the need for the assumptions and reduce the overall uncertainty of test results.

 

PHASE I: Consult with AEDC personnel to understand APTU operations and gain familiarity with current intrusive rake and probe designs. Survey industry to assess potential solutions to the problem, including later commercialization opportunities.  Develop the concept and design of the probe technology for the APTU flow-field conditions. Evaluate the achievable measurement uncertainty and illustrate plans for state-of-the-art improvements.

 

PHASE II: Develop and demonstrate a prototype probe-rake devices in the APTU flow-field conditions early into the Phase II to allow design iterations design as needed to demonstrate robustness and sufficient accuracy.

 

PHASE III DUAL USE APPLICATIONS: Reduce device complexity and size for use within the facility rake systems. This technology will result in a product easily commercialized to other highspeed and high temperature wind tunnels.

 

REFERENCES:

Porro, R. A. (2001). Pressure Probe Designs for Dynamic Pressure Measurements in a Supersonic Flow Field. NASA Glenn Research Center. Cleveland, OH. Retrieved 12 2, 2022, from https://ntrs.nasa.gov/api/citations/20010093214/downloads/20010093214.pdf;
Pinckney, S. Z. (1975). A Short Static-Pressure Probe Design for Supersonic Flow. NASA Langley Research Center. Hampton, VA. Retrieved 12 2, 2022, from https://ntrs.nasa.gov/api/citations/19750019233/downloads/19750019233.pdf;
Pinckney, S. Z. (1975). US Patent 3914997;
Capone, F. J. (1961). Wind-Tunnel Tests of Seven Static-Pressure Probes at Transonic Speeds. NASA Langley Research Center. Hampton, VA. Retrieved 12 2, 2022, from https://ntrs.nasa.gov/api/citations/19980227993/downloads/19980227993.pdf;

 

KEYWORDS: High Temperature; High Pressure; Scramjet; Ground Testing; APTU