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K. Mark Caviezel         

2432 Gray Street                 kmcaviezel@yahoo.com

Edgewater, CO 80214

(720)333-2248

 

OBJECTIVE:

Expert consultation in rocket propulsion, space launch, or related field.  Prefer innovative and pioneering projects.

 

 

PROFESSIONAL EXPERIENCE:

2003-present independent contract Aerospace Engineer, working on projects such as MDA-funded High Altitude Airship (HAA) in a PI capacity, LOX/Cryogenic Propylene propulsion for Lunar Descent Vehicle, and stratospheric heavy lift systems for an innovative manned sub-orbital vehicle.  Recently completed a two phase program for the Canadian daVinci project, designing, building and test flying a highly stressed, scaled stress prototype, leading into the design and fabrication of a heavy lift 3.7 million cubic foot balloon.   That balloon is designed to hoist 10,000 lbs to 70,000 feet.  

 

2000-2004 Engineer at Pioneer Astronautics, a small space exploration technology R&D firm.   Most projects had emphasis on Mars exploration.  I was the Principle Investigator of NASA-funded LOX/Olefin (LOXO) Engine for deep space propulsion.   The LOXO concept allows common bulkhead tanks for isothermal storage of LOX and Propylene, and propellant combination that is more energetic than LOX and kerosene.   For space launch or long duration deep space missions, this propellant combination has numerous advantages.  The LOXO program completed it's first round of hot fire testing, with complete success.  The initial test engine is a 120lbf nominal thrust workhorse engine.

Previously at Pioneer, I was lead development engineer on NOMR (Nitrous Oxide Monopropellant Rocket) a program that demonstrated pure N₂O decomposition thruster at 1.2 lb thrust level.    Later work funded by Lockheed Martin pushed the thrust level to 12 lbs, establishing the possibility of non-toxic nitrous oxide thrusters for use on the Centaur upperstage ACS system. 

Earlier work at Pioneer was in the area of premixed nitrous oxide and fuel blends, with promise for I_sp higher than 320 seconds.   Successful test runs were made, but the system was plagued by violent detonations.   I was lead engineer on this program, implementing thruster design, test stand design, fully remote controlled operation and data acquisition.

 

 Additionally, I was lead engineer on the NASA-funded all-CO₂ propelled 'Mars Gashopper' proof of concept vehicle which went from concept to test stand boilerplate rocket engines to a small proof of concept flight vehicle in mere weeks.  Also, I acted as contributing engineer for design and implementation of the reverse water gas shift (RWGS) Mars Oxygen Machine, a machine that can manufacture propellant-grade LOX from the Mars atmosphere, and I assisted with the planning and flight operations of the Mars Methanol Balloon, which has undergone successful flight testing over 120,000 feet altitude in the Earth's atmosphere.  Skills used in this job included structural design, rocket engine design, instrumentation and data acquisition and Labview control, and all nature of hardware fabrication and test.  Furthermore, I served as lead development engineer for numerous experimental rocket propulsion systems, including a nitrous hybrid rocket, CO₂/Magnesium hybrid rocket, and a CO₂/liquid Lithium rocket.  Also while at Pioneer, I was the lead development engineer for the Mars Solar Balloon Lander phase one, funded out of NASA/JPL.  During the phase one we developed a sophisticated solar heated Montgolfiere balloon and flight tested it to confirm its operational characteristics.  The MSBL was controllable in low level flight, was commanded to perform a touch and go, then was sent off on a maximum performance mission.   It achieved a 400 mile flight to eastern Nebraska at a cruising altitude of 46,000 feet.

 

1999-2000 Engineer at Truax Engineering, Inc., a small rocket technology R&D firm. I was lead engineer on some investigational studies and hardware fabrication of innovative space launch technology, and a contributing member of the development team in other areas, including the DoD-funded TEI 75,000 lb thrust LOX/kerosene rocket engine.  Adjacent picture shows prototype of an integrated launch vehicle propellant valve that I took from concept to operable hardware while at TEI.

 

1996-99 Engineer on Boeing Commercial Space Company's Sea Launch program.  I was heavily involved in mechanical test of Sea Launch flight hardware and ground support equipment, both mechanical and electrical.  I developed the procedures for preparing the spacecraft processing facility for reception of flight hardware, and transfer of the hypergol fueled spacecraft to the Sea Launch ship onboard a 257,000 lb, 56 wheel heavy duty transporter.  The picture shows me and a co-worker in front of the 16,000 lb payload unit before integration on the Zenit 3 SL upper stage.

 

While at Boeing, I participated in spacecraft to spacecraft-adapter mating tests at the Hughes Communications factory in El Segundo, CA. I personally directed the performance of procedures for the payload fairing and other flight hardware receive/inspection operations at the Sea Launch Home Port in Long Beach, CA.  Prior to my departure from the project, the Sea Launch program finished it's "Pathfinder" phase and launched a 10,000 lb satellite simulator payload into lofted perigee geosynchronous transfer orbit (GTO). The launch platform "Odyssey" was moved to the waters of the equatorial Pacific for the launch. I was one of only two mechanical test conductors for the first ever horizontal integration of a space payload to the booster in the USA.

 

1989-90 Electrical Technician for Dept. of Astronautics Space Shuttle experiment. Served as primary electrical technician during zero-gravity (micro-gravity) flights aboard NASA's KC-135 research plane.  During two days of flight testing, I personally experienced over 32 minutes of zero-gravity during the micro-gravity demonstration of the University of Washington's liquid droplet radiator hardware.

 

1988-89 Advertising Sales Manager for independent student newspaper on the University of Washington

 

AWARDS AND DISTINCTIONS:

·         Rockwell International Aerospace Design Award for work done in NASA sponsored USRA advanced space systems design class on "A Direct Manned Mars Mission Using Indigenously Produced Propellants."  I was selected as delegate to national convention to present our work.    

·         Speaker at Commencement ceremonies, selected by UW Aeronautical and Astronautical Engineering class.

·         Amateur radio/high altitude balloon records:   longest telemetry reception (388 miles) and longest voice QSO (395 miles) .  This record is for low power UHF and VHF communications through balloon-borne payloads.

 

EDUCATION:

University of Washington, Seattle WA

Bachelors Degree

BSAAE (Bachelor's of Science in Aeronautical and Astronautical Engineering) Completed coursework includes:

·         Aerodynamics

·         Technical Writing

·         Space Systems Design

·         Elementary Elec. Engr.

·         Computer Aided Drawing

·         Heat Transfer

·         Composite Structures

·         Rocket Propulsion

·         Finite Element Methods

·         Computer Programming

 

 

TRAINING:

·         Pro-E (PROENGINEER) CAD familiarization

·         Labview Data Acquisition

·         Hypergol Safety

·         Oxygen Safety

·         High Pressure Gas Safety

·         Cryogenic Liquid Safety

·         Overhead Crane Safety

·         Electro-static Discharge Awareness

·         Cleanroom Certification

·         Explosive Ordnance Awareness

·         Test Program Design

·         Russian Cross-cultural training

 

ADDITIONAL PROJECTS:

            Designed, manufactured and tested a 1500 lb thrust regeneratively-cooled LOX/ethanol rocket engine.   Successful static test with nominal performance conducted on first trip out to Mojave Test Area, in January, 2000.

            I have designed and successfully test flown stratospheric balloons:  The largest balloon to date was 126,000 cubic feet.  Highest flight to date was to over 107,400 feet MSL.   The heaviest payload has been in excess of 150 lbs.  The balloons are made from thermally welded sub mil thick polyethylene plastic and fly with GPS-equipped telemetry packages.  In conjunction with these balloon flights, I conduct high altitude remote-commanded photography and use Longly-Rice RF path predictive tools to calculate the 'view shed' of low power radio coverage.

 

OTHER:

            FAA certificated private pilot, lighter than air, owns and flies a 90,000 cubic foot hot air balloon.

FCC licensed radio amateur operator, Extra (highest) class.

            Implemented low cost, solar powered hill top repeater for scientific field operations in Utah and on Devon Island in the Canadian Arctic.  The Utah repeater has a demonstrated range of over 19 miles with only 0.5 watts RF power and has functioned without fault for over 4 years running.

 

Affiliations:

            Member, RRS (Reaction Research Society)

            Member, AIAA (American Institute for Aeronautics and Astronautics)

            Member, ARRL (American Radio Relay League)

Inflation of "Milk Bottle Balloon" with ten cylinders of Helium

 

Launch