SBIR/STTR Research Award

Extendable Loitering Wing (ELW) based on Spacecraft Boom Technology Adaptation

Award identifier b296b7ab6a8ae7758178a74870d08dfbe10817bfd52f4024e08ab578db1c6b4eAwarding agency Department of Defense · Air Force

Award amount

$100,000

Program and phase

SBIR · Phase I

Award year

2003

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Award details

Awarding agency
Department of Defense
Branch
Air Force
Recipient company
KaZaK Composites Incorporated
Proposal award date
Not reported
Contract end date
Not reported
UEI
NE6AZWKUS6Z7
Solicitation number
Not reported
Topic code
Not reported

Research abstract

An Extendable Loitering Wing (ELW) weapon is proposed in which a large flying wing lifting surface is deployed from a vehicle with a stored volume not much larger than LOCAAS. After weapon release, a tail-mounted parachute slows vertical descent such thatwing deployment occurs at low airspeed and high altitude (i.e. low dynamic pressure). After the parachute cord is cut the ELW pitches up to achieve best L/D and glides to the target area, providing significant standoff range (87 miles) and conserves fuelfor loitering. Upon reaching loitering altitude for the LADAR seeker (300 to 750 ft AGL), the reciprocating engine is started and the search pattern is established. The weapon has 12 hour endurance at 67 mph and a 750 meter wide scanning footprint,covering a 382 square mile area, more than ten times greater than LOCAAS (which has only 30 minute endurance).Key to this performance is an extremely lightweight and aerodynamically efficient deployable structure using low cost pultruded composites for deployable wing spars. The fundamental technology for the deployable spar has been used on numerous deployablespacecraft booms, and can be readily adapted to Loitering Weapon requirements using novel methods such as Shape Memory Alloy locking elements. Upon completion of Phase I, a detailed weapon aerodynamic and structural design and analysis will be generated. A full-scale wing deployable spar shall be fabricated. This structure will be used to demonstrate multiple deployment and retraction cycles toverify the robustness and reliability of the deployable structure. It shall then be proof loaded to assure that the structure has adequate safety margins for all flight conditions. Many military systems use deployable wing structures based on inflatablefabrics and rigid hinged structures. The proposed concept, once proven, would provide designers with another viable approach to developing a large wing from a small package. Markets could include easily transportable UAVs and long-range weapons. Sizescould be scaled down for man-portable

Technology keywords

Not reported

Other awards by this recipient

Verified by the same UEI. These are other public SBIR/STTR award pages, not a merged company record.

Research funding history

156 SBIR/STTR records share this UEI (1995–2011). Reported award amounts total $40,421,900. Reported amounts are not federal obligations.

Phases: Phase I, Phase II

Agencies: Department of Defense, National Aeronautics and Space Administration, Department of Transportation, National Science Foundation

Agency intelligence

Department of Defense

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