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Solutions for Rapid Yaw Maneuvers for High L/D Hypersonic Vehicles

Description:

OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): Hypersonics The technology within this topic is restricted under the International Traffic in Arms Regulation (ITAR), 22 CFR Parts 120-130, which controls the export and import of defense-related material and services, including export of sensitive technical data, or the Export Administration Regulation (EAR), 15 CFR Parts 730-774, which controls dual use items. Offerors must disclose any proposed use of foreign nationals (FNs), their country(ies) of origin, the type of visa or work permit possessed, and the statement of work (SOW) tasks intended for accomplishment by the FN(s) in accordance with the Announcement. Offerors are advised foreign nationals proposed to perform on this topic may be restricted due to the technical data under US Export Control Laws. OBJECTIVE: Develop solutions for rapid yaw maneuvers for high lift to drag (L/D) hypersonic glide vehicles. DESCRIPTION: Hypersonic vehicles with non-axisymmetric lifting bodies may achieve L/D ratios around 4, which is significantly higher than finned vehicles with conical bodies, but may have slower yaw maneuver response times since bank to turn yaw maneuvers are slower than skid to turn maneuvers. This topic seeks solutions, such as innovative control surfaces and or hybrid configurations to decrease the time constant for maneuvers while maintaining the high L/D of the vehicle concepts. This topic does not seek a solution for any systems in development, but rather seeks to develop and demonstrate solutions that could be applied to future developments. Proposers should assume a glide vehicle with a non-conical geometry similar to the waveriders in reference 1 or the artistic representation of DARPA Falcon HTV-2 in reference 2. Proposers should provide their own geometry or the government may be able to provide a generic geometry after contract award. Design solutions should seek to minimize mass, volume, and drag impacts from control surfaces and/or other mechanisms. Designs should seek to enable time constant for all maneuvers comparable with time constants for finned conical vehicles. Proposers may assume a range of Mach numbers above Mach 5 and a range of altitudes up to 50km. PHASE I: Basic studies on aerodynamic controls or other mechanisms. Could include modeling and/or limited wind tunnel assessment. Estimate maneuverability and kinetic energy loss for maneuvers at a range of Mach numbers and altitudes. Down select to 1 or 2 preferred designs. PHASE II: Work with a missile defense system integrator to mature selected geometry and design. Obtain higher fidelity estimates of performance. Test in representative environment such as wind tunnel. PHASE III DUAL USE APPLICATIONS: Work with system integrator to refine requirements and integrate into full guidance navigation and control system. Demonstrate technology in a representative environment. Transition Technology into missile defense application. REFERENCES: 1. http://www.aerospaceweb.org/design/waverider/waverider.shtml; 2. https://www.darpa.mil/about-us/timeline/falcon-htv-2 (topics) Approved for Public Release 23-MDA-11365 (30 Jan 23) KEYWORDS: Aerodynamic Control; Hypersonic; Maneuvers; Lifting Body
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