Successfully developed a new class of fast burning solid propellants without the use of high energy explosives. Continuing this work to develop an end burning, long duration solid rocket motor for use in launch vehicles.Mr. Wickman was principal investigator on the development of a new solid propellant, multi-pulse satellite thruster pack. This new solid propulsion technology was launched into space in April 2018 to move an Air Force satellite to different orbital positions during a multi-year mission. Principal investigator on a US Air Force contract to develop a rapid response, Small Launch Vehicle (SLV) that uses solid rocket propellant. Principal investigator on a NASA contract that demonstrated the feasibility of a variable hot gas thruster using a highly metalized ammonium perchlorate solid propellant. This new thruster could be used to steer a Mars sample return vehicle. Principal investigator on a US Army contract to develop a new solid rocket pintle nozzle with integral thrust vector control. Designed the "S" Series of sounding rockets that were to deploy scale prototype SHARP vehicles in Space for the NASA Ames Research Center.Principal investigator on a NASA Jet Propulsion Laboratory contract to develop rocket and jet engines that burn carbon dioxide with magnesium powder. Program was concluded successfully with the delivery of the rocket and jet engines to NASA. Principal investigator on a LOX/kerosene monopropellant rocket engine contract with the NASA Glenn. Characterized LOX/kerosene monopropellant and test fired a LOX/kerosene monopropellant rocket engine. Principal investigator on a NASA Glenn contract developing liquid oxygen/metal powder propellants that can be produced from elements commonly found on the moon.Lead engineer on contract to Morton Thiokol on the Space Shuttle SRB field and nozzle joint redesigns after the Challenger accident. Presented to Thiokol engineers thermal design criteria for screening potential joint concepts.

Wrote a corporate newsletter on advanced propulsion concepts for Aerojet's top executives. In the Advanced Engineering group, performed air and ground launch missile systems design studies and trajectory analysis under subcontract to Rockwell for SICBM and stand-off applications. Ran the POST trajectory analysis computer code for both air and ground launch conditions. Ran the Aerojet AIDE preliminary missile design computer code to determine missile length and weights. Calculated solid rocket motor performance for a variety of propellants. Modified for Aerojet the AFAL MEMDOP trajectory computer code to include more accurate solid rocket design equations for missile design optimization.Before transferring over the Advanced Engineering group, Mr. Wickman was group leader of all thermal analysis in the company. This includes the MX missile, Minuteman, Polaris, and other tactical missile programs. Conducted failure analysis on Polaris and Minuteman motors that lead to remanufacturing program for both missiles.

Worked on the thermal modeling and design of the burner section of the JT9D-70 engine used on large body aircraft. He was also responsible for the scheduling, design, testing, and analysis of burner configurations in an experimental JT9D turbofan jet engine. Simulated complex flow fields inside the combustion chamber using a Water Tunnel.