TARGETED DRUG RELEASE IN VIRUS-INFECTED MACROPHAGES

Award Information
Agency:
Department of Health and Human Services
Branch
n/a
Amount:
$99,999.00
Award Year:
1999
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Agency Tracking Number:
1R43AI044546-01
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
CHEMICA TECHNOLOGIES, INC.
325 SW CYBER DR, BEND, OR, 97702
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
TAKUJI TSUKAMOTO
() -
Business Contact:
(541) 385-0355
DBROSE@CHEMICA.COM
Research Institution:
n/a
Abstract
Not Available Hybrid rocket motors based on gaseous and liquid oxidizers have been successfully demonstrated in the past. The offeror's proposed design consists of the consolidation of high performance solid or semi-solid oxidizers into individual high density sealed packages. These packets would be stored in the oxidizer section of the rocket and could be delivered at a controlled rate to the hybrid combustion chamber. Throttling and start/stop capabilities which are inherent characteristics of hybrid propulsion systems would be realized in this design. Delivery of these packets could be accomplished by a number of means such as pyrotechnics and gas charge or either method in combination with acceleration forces. Geometry of the packages can be tailored to optimize packaging, structural efficiency, delivery systems and storage (pressurization). Storage, stability, safety and munition sensitivity could be improved while realizing the benefits of these high performance oxidizers. Hybrid propulsion systems offer a number of advantages over conventional solid motors when used in conjunction with high performance oxidizers. Because the oxidizer is stored separately from the fuel component until use, the need to compound the oxidizer with the appropriate fuel/binder system is eliminated. This is a definite advantage because high performance oxidizers such as HNF have been shown to react with a number of common curative agents used in solid propellant binder systems. Hermetically sealed o

* information listed above is at the time of submission.

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