TECHNOLOGY AREAS: Air Platform, Weapons

ACQUISITION PROGRAM: PMA 242 - Direct & Time Sensitive Strike

RESTRICTION ON PERFORMANCE BY FOREIGN CITIZENS (i.e., those holding non-U.S. Passports): This topic is "ITAR Restricted." The information and materials provided pursuant to or resulting from this topic are restricted under the International Traffic in Arms Regulations (ITAR), 22 CFR Parts 120 - 130, which control the export of defense-related material and services, including the export of sensitive technical data. Foreign Citizens may perform work under an award resulting from this topic only if they hold the "Permanent Resident Card", or are designated as "Protected Individuals" as defined by 8 U.S.C. 1324b(a)(3). If a proposal for this topic contains participation by a foreign citizen who is not in one of the above two categories, the proposal will be rejected.

OBJECTIVE: Develop launcher concepts and prototypes for both the 2.75 inch Rocket and Advanced Precision Kill Weapon System (APKWS) weapon systems that reduce aerodynamic drag and weight, enabling integration into new and existing aircraft platforms and unmanned aircraft.

DESCRIPTION: A reduction in aerodynamic drag and weight of aircraft stores has a direct effect on the performance and flight endurance of the transporting aircraft. Many small aircraft platforms, including various unmanned aircraft systems, could potentially be configured to support the 2.75 inch Rocket and APKWS weapon systems. In these smaller aircraft platforms, the aerodynamic drag and weight of the current LAU-68 and LAU-61 launchers is high and reduces the range of the transporting aircraft. This effort calls for the development of two (2) airborne launchers of different sizes for the 2.75 inch Rocket and APKWS weapon systems. The launchers must be mechanically interoperable with the LAU-68 and LAU-61 launchers enabling integration into existing aircraft platforms. Of the two launchers, the first must be appropriately sized to have a fully loaded weight of no more than 200 pounds, enabling integration into various unmanned platforms. The second launcher should be dimensionally similar to the LAU-61 launcher enabling integration into existing fixed and rotary wing platforms. The key focus of this development effort is to explore innovative concepts that significantly reduce aerodynamic drag, over a wide operating envelope of 0 to 300 knots and 0 to 14 degrees angle-of-attack, of the launchers, both before and after firings, reduce weight, and extend service life when compared to existing LAU-68 and LAU-61 launchers. The primary structure should employ composite materials and the launch tubes should employ high-temperature composite materials to further reduce weight and increase service life. There will be significant challenges to identifying innovative materials to achieve extended service life capability and weight savings as well as the development of manufacturing technologies. Substantial effort to develop a launcher that utilizes appropriate materials and can be manufactured properly will be required.

Aspects of increasing the service life include protection from adverse environments and from overpressure from the rocket motor exhaust plume. The designs should handle heat flux, mass flow, and dynamic pressures. The rocket launchers should be able to operate in harsh environments where blowing sand, dust or water could enter the launcher tubes and cause malfunctions in the existing launchers. Systems must also provide environmental protection and protection from damage due to firing adjacent rockets.

PHASE I: Develop a proof of concept for both launcher designs to demonstrate weight reduction and manufacturability. Provide computational data showing the reduction in aerodynamic drag.

PHASE II: Develop a prototype system for the LAU-68 launcher design for subsequent test and evaluation. Demonstrate the ability to fabricate the launcher using composite materials and the manufacturing technologies developed in Phase I. Demonstrate the reduction in aerodynamic drag of the launcher prototype through wind tunnel testing. Demonstrate the operation of the launcher prototype and the increase in service life by test firing the launcher on a test stand in an appropriate environment. 2.75 inch Rocket training rounds will be provided as government furnished equipment (GFE).

PHASE III: Develop a prototype system for the second of the two launcher designs (LAU-61) for subsequent test and evaluation. Demonstrate the reduction in aerodynamic drag of the launcher prototype through wind tunnel testing. Demonstrate the operation of the launcher prototype and the increase in service life by test firing the launcher on a test stand in an appropriate environment. 2.75 inch Rocket training rounds will be provided as GFE. Integrate onto and test both launcher prototypes on an applicable rotary wing aircraft platform, such as the H-1 Cobra. Rocket training rounds will again be provided as GFE. Transition developed technology to appropriate platforms.

PRIVATE SECTOR COMMERCIAL POTENTIAL/DUAL-USE APPLICATIONS: These launcher configurations could be applicable to numerous Homeland Security applications including platforms for firing marking rounds and illumination rounds from aircraft. The low drag launcher geometry could also be reconfigured to support other external commercial and Homeland Security payloads.

REFERENCES:
1. Hoerner, S.F. (1965). Fluid Dynamic Drag. Bakersfield, CA: Hoerner Fluid Dynamics

2. Office of the Secretary of Defense, "Unmanned Systems Roadmap (2009-2034)," 2nd Edition
http://www.jointrobotics.com/library02.php

3. Product Specification DTL WS 35493A for Launcher, 2.75-inch Rocket, LAU-61C/A, LAU-68C/A, LAU-68D/A, and LAU-68F/A, 19 May 2010, uploaded in SITIS 11/23/10.

4. Product Specification DTL WS 35238A for Intervalometer DTU-28A/A and DTR-28BB/A, 24 May 2007, uploaded in SITIS 11/23/10.

5. Drawing 1716AS302, Tube Assembly, 3 pages. (Uploaded in SITIS 11/24/10.)

6. Drawing 1716AS109 Rev A, Launcher Tube, 1 page. (Uploaded in SITIS 11/24/10.)

7. Drawing 1716AS300, LAU-68FA Assembly, 6 pages. (Uploaded in SITIS 11/24/10.)

8. Drawing 1716AS301, Tube Cluster Assembly, 4 pages. (Uploaded in SITIS 11/24/10.)

KEYWORDS: Air Launched Weapon Systems; Precision Strike Weapons; Unmanned Aircraft Systems; 2.75 inch Rocket; APKWS

** TOPIC AUTHOR (TPOC) **

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