Navy RFI Hypersonic Weapons Technolgy

bobbymike

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Request for Information - Hypersonic Weapons Technologies

Description:

1. This is a special notice open to U.S. industry and academia requesting information on technologies pertaining to hypersonic flight vehicles. The High Speed Weapons Office of the Naval Air Warfare Center Weapons Division (NAWCWD) is interested in reviewing technologies, in both the concept and development phases, which will enable/enhance the operation and survival of two classes of hypersonic vehicles. The first concept is a rocket boosted hypersonic glider (Mach 8-10) and the second concept is an airbreathing cruise vehicle (Mach 5-6). The durability requirement is several minutes at elevated temperature with high gradient heat fluxes.

This request for information (RFI) includes power, materials, and structure technologies.

2. Objective: Identify technologies that will enable/enhance the operation and survival of hypersonic vehicles in two speed regimes Mach (5-6) and Mach (8-10). A vehicle operating in the Mach 10 environment is expected to experience temperatures up to 2200°C therefore thermal and environmental barrier coating (TBC and EBC) technologies and ceramic composite structure technologies that can survive this environment are of extreme interest. Other technologies of particular interest include, but are not limited to:

2.1. Folding and morphing structures that allow the vehicle to be stored in a launch tube and allow for dimensional changes in the vehicle to optimize for reduced drag, controllability, and aerodynamic heating throughout the vehicle's flight profile.

2.2. Long duration power systems with extended shelf life, including but not limited to ram-air turbines.

2.3. High temperature electronic components and antennas which can operate at elevated temperatures, thereby reducing cooling requirements.

2.4. Technologies that address not only performance but affordability for cooled structures and electrical components.

3. Background: Studies have indicated that a long range rapid strike capability is operationally desirable.

Both hypersonic boost-glide and airbreathing vehicles can address this capability need but affordability is a major concern. The boost-glide concept requires high temperature materials and aerodynamic shapes that can achieve improved lift-to-drag ratios. The airbreathing concepts lose volume to internal propulsion flowpath and fuel delivery systems. Both concepts have to be implemented within volume constraints of Navy ship and submarine launchers.

4. Information Desired:

4.1. Thermal Barrier Coating (TBC) and Environmental Barrier Coating (EBC) Materials: Materials are of particular interest due to the extreme temperatures a hypersonic glider will experience. Temperatures have been estimated up to 1200°C for a vehicle operating at Mach 6 and 2200°C for operation at Mach 10.

Information is desired for TBC and EBC technologies that may protect the hypersonic vehicle structure from this harsh operating environment. Non-ablative solutions are preferred. Current known issues with barrier coating technologies include inability to operate at temperatures up to 2200°C without ablating, poor thermal shock resistance, inability to retain sharp features in the structure during processing, and introduction of defect(s) in the barrier coating around geometries with high curvature or sharp features during fabrication. Information is desired for both the material itself and manufacturing techniques. Information on current known issues with barrier coatings and possible solutions are also desired.

4.2. Carbon-Silicon Carbide (C-SiC) and Silicon Carbide-Silicon Carbide (SiC-SiC) Composites: Information is desired on C-SiC and SiC-SiC composites and manufacturing techniques.

C-SiC and SiC structures are a valid option for the lower end of the Mach 5-10 environment but do not have the thermal properties required to operate at the high end of the environment without complex thermal barrier systems. Information regarding mechanical properties of these composites as a function of temperature is highly desired. Information pertaining to achievable geometries and attachment methods to other structures (i.e. joints, support structures, and actuators) is also desired.

4.3. Space Constraints: Information is desired on folding and morphing structures technologies that will allow the vehicle to be launched from a ship or submarine launch tube, to be controlled, and to survive the high temperature environment.

Space constraints are currently set by the Mk41 Vertical Launch System (VLS). Without a folding or morphing structure capability for the hypersonic vehicle, the vehicle will not be able to achieve the high Lift-to-Drag ratios (L/D) required for the desired fly-out ranges.

4.4. Optimization of flight conditions: Information is desired for morphing structures technologies that enable the optimization of leading edge and other wing dimensions throughout a flight profile (up to Mach 10). Optimization of these dimensions would help with drag and aerodynamic heating across the majority of the Mach range of the vehicle rather than a narrow Mach range due to fixed wing dimensions. There is also a specific interest in this technology for waverider vehicles.

Waveriders maximize L/D by minimizing underside pressure loss through shock flow containment. The configurations are generated by constraining shapes within wedge or cone flow streamlines. While high L/D is achieved, the shapes often provide little volume for required missile subsystems. Also, the design approach leads to designs that are optimized about a narrow Mach range. Adding a morphing structure capability would allow for optimization across a large Mach range.

4.5. Flight Control: Information is desired for morphing structures technologies that enables control of flight through the change in wing/body shape. This technology would be used in lieu of actuated control surfaces. This may be directly related to the paragraph 4.4.

4.6. Actuator and mission computer power: Information is desired for storable long flight duration power systems and high temperature hydraulic or electrical actuators for flight vehicle response.

Temperatures may reach a point where magnetic actuators are no longer a viable option.

4.7. High temperature electronic components, seekers, and antennas: Information is desired on electronic components and antennas which can operate at elevated temperatures, thereby reducing cooling requirements. Information is also desired on seeker and antenna technology that may be able to operate through a window/structure and the boundary conditions surrounding the vehicle in hypersonic flight.

4.8. Manufacturing Technologies: Information on technologies that address not only performance but manufacturing affordability for cooled structures and electrical components.

4.9. Vehicle Packaging and components volumes: Volumetric efficiency has been shown to be a significant air vehicle performance driver.

Technologies including but not limited to those that maximize fuel volume and minimize volume while maximizing lethality are of interest.

4.10. Thermal management: Information is desired on vehicle thermal management including active cooling, phase change materials, and passive heat management.

4.11. Analytical techniques: Information on analytical techniques that can address complex thermal-structure interaction problems (like the effects of thermal shock on a primary structure and interfacing material) or fluid-thermal-structures interactions (like the erosion of leading edges subjected to hypersonic flow) that can be used in lieu of expensive custom tests are also desired.

4.12. Other: Information on other methods or technologies that may aid in the management of the expected high temperature environment or optimization of the aerodynamic conditions around the vehicle is also welcome to be submitted.
 
bobbymike said:
2.1. Folding and morphing structures that allow the vehicle to be stored in a launch tube and allow for dimensional changes in the vehicle to optimize for reduced drag, controllability, and aerodynamic heating throughout the vehicle's flight profile.

4.4. Optimization of flight conditions: Information is desired for morphing structures technologies that enable the optimization of leading edge and other wing dimensions throughout a flight profile (up to Mach 10). Optimization of these dimensions would help with drag and aerodynamic heating across the majority of the Mach range of the vehicle rather than a narrow Mach range due to fixed wing dimensions. There is also a specific interest in this technology for waverider vehicles.

Waveriders maximize L/D by minimizing underside pressure loss through shock flow containment. The configurations are generated by constraining shapes within wedge or cone flow streamlines. While high L/D is achieved, the shapes often provide little volume for required missile subsystems. Also, the design approach leads to designs that are optimized about a narrow Mach range. Adding a morphing structure capability would allow for optimization across a large Mach range.

Thanks for posting this.

Morphing structures? Can someone explain this one to me? Is this something more than "folding wingtips" like on the XB-70?

They looking to work around the narrow diameter of the MK 41 with technology to morph the structure in flight? Did I read that correctly?
 
jjnodice said:
bobbymike said:
2.1. Folding and morphing structures that allow the vehicle to be stored in a launch tube and allow for dimensional changes in the vehicle to optimize for reduced drag, controllability, and aerodynamic heating throughout the vehicle's flight profile.

4.4. Optimization of flight conditions: Information is desired for morphing structures technologies that enable the optimization of leading edge and other wing dimensions throughout a flight profile (up to Mach 10). Optimization of these dimensions would help with drag and aerodynamic heating across the majority of the Mach range of the vehicle rather than a narrow Mach range due to fixed wing dimensions. There is also a specific interest in this technology for waverider vehicles.

Waveriders maximize L/D by minimizing underside pressure loss through shock flow containment. The configurations are generated by constraining shapes within wedge or cone flow streamlines. While high L/D is achieved, the shapes often provide little volume for required missile subsystems. Also, the design approach leads to designs that are optimized about a narrow Mach range. Adding a morphing structure capability would allow for optimization across a large Mach range.

Thanks for posting this.

Morphing structures? Can someone explain this one to me? Is this something more than "folding wingtips" like on the XB-70?

They looking to work around the narrow diameter of the MK 41 with technology to morph the structure in flight? Did I read that correctly?

to optimize for reduced drag, controllability, and aerodynamic heating throughout the vehicle's flight profile.

Optimization of flight conditions: Information is desired for morphing structures technologies that enable the optimization of leading edge and other wing dimensions throughout a flight profile (up to Mach 10). Optimization of these dimensions would help with drag and aerodynamic heating across the majority of the Mach range of the vehicle rather than a narrow Mach range due to fixed wing dimensions

The way I read it, this RFI seeks to solve all the problems encountered during all phases of hypersonic flight, ameliorating/improving all the envelope through "shapeshifting" or morphing techniques from launch to endgame.

Dale Brown, go back to your novel-drafts!
 
SHape morphing is under study. Example :


http://www.dtic.mil/dtic/tr/fulltext/u2/a552599.pdf


A Navy SBIR contract was award a couple of years ago to Mide Corp.
 
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