Garvey Spacecraft Corporation

Latest events

• Jun 2017Federal contractNASA · Igf::ot::igf The Referenced STTR Phase II Technical Objectives Focus On The Integration Of Several Advanced Technologies Into A Prototype Nlv Upper Stage, Initial Functional Verification Through Static Fire Testing And Then Continuation Of Pathfinding Of Launch Operations At Kodiak That Could Ultimately Result In A Suborbital Flight Attempt Of A "p-ak" Test Vehicle. STTR Phase II Task 1 (reference Proposal Page 9) Includes `NASA Aco SAA-3D Am Injectors' As A Parallel Project That Could Generat$200K
• Oct 2016Federal grantNASA · Phase II · NLV Upper Stage Development and Flight Testing$749K
• Sep 2016Federal contractDefense · Igf::ot::igf Darpa SBIR Phase II Base Award$1.5M
• Jun 2016Federal contractNASA · Igf::ot::igf The Technical Innovation Proposed Here Is The Introduction Of Torch-augmented Spark Ignition For High Performance Liquid Oxygen (lox) / Propylene Rocket Engines Now In Development For A Future Two-stage Nanosat Launch Vehicle. Spark Ignition Is Critical For Reliably Achieving Multiple In-flight Restarts Of Nlv Upper Stage Engines. In Addition, This New Capability Will Generate Immediate R&d Benefits Through The Streamlining Of Ongoing Lox/propylene Engine Testing. By Replacing Pyro$125K
• Sep 2015Federal grantDefense · Phase I · Modification of a Commercial NLV Booster Concept for Use as a Low-Cost Upper Stage for the XS-1$149K
• Jun 2015Federal contractNASA · Igf::ot::igf The Technical Innovation Proposed Here Is The Design During Phase I Of A High Performance Upper Stage For A Two-stage "20 / 450" Nanosat Launch Vehicle (nlv) That Is Configured To Deliver Up To 20 Kg To A 450 Km Low Earth Orbit (figure 1). Parallel Tasks Prepare For The Phase II Development And Sub-orbital Flight Testing Of A Prototype Vehicle That Is Directly Traceable To The Orbital-capable Nlv. Furthermore, By Teaming With The University Of Alaska Fairbanks And Alaska Space Corpo$125K
• Jun 2014Federal contractNASA · Igf::ot::igf The Technical Innovation Proposed Here Expands Upon Early Research Into The Viability Of Additive Machining (am) For Liquid Rocket Engine Components And Other Emerging Capabilities To Initiate Trl 6 Flight Test Evaluations Of Candidate Applications That Could Enhance The Affordability Of A Small Launch Vehicle (slv) Booster Stage. University Of California, San Diego (uscd) Has Achieved Success In Applying 3D Am To Fabricate A 200 Lbf-thrust Lox/kerosene Engine. Concurrently, The Gar$125K

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