JPL Technical Report Server

Retro rocket motor self-penetrating scheme for heat shield exhaust ports

Show simple item record

dc.contributor.author Marrese-Reading, Colleen
dc.contributor.author St.Vaughn, Josh
dc.contributor.author Zell, Peter
dc.contributor.author Hamm, Ken
dc.contributor.author Corliss, Jim
dc.contributor.author Gayle, Steve
dc.contributor.author Pain, Rob
dc.contributor.author Rooney, Dan
dc.contributor.author Ramos, Amadi
dc.contributor.author Lewis, Doug
dc.contributor.author Shepherd, Joe
dc.contributor.author Inaba, Kazuaki
dc.date.accessioned 2015-07-01T17:14:53Z
dc.date.available 2015-07-01T17:14:53Z
dc.date.issued 2009-03-07
dc.identifier.citation 2009 IEEE Aerospace Conference, Big Sky, Montana, March 7-14, 2009 en_US
dc.identifier.clearanceno 09-0077
dc.identifier.uri http://hdl.handle.net/2014/45320
dc.description.abstract A preliminary scheme was developed for base-mounted solid-propellant retro rocket motors to self-penetrate the Orion Crew Module heat shield for configurations with the heat shield retained during landings on Earth. In this system the motors propel impactors into structural push plates, which in turn push through the heat shield ablator material. The push plates are sized such that the remaining port in the ablator material is large enough to provide adequate flow area for the motor exhaust plume. The push plate thickness is sized to assure structural integrity behind the ablative thermal protection material. The concept feasibility was demonstrated and the performance was characterized using a gas gun to launch representative impactors into heat shield targets with push plates. The tests were conducted using targets equipped with Fiberform® and PICA as the heat shield ablator material layer. The PICA penetration event times were estimated to be under 30 ms from the start of motor ignition. The mass of the system (not including motors) was estimated to be less than 2.3 kg (5 lbs) per motor. The configuration and demonstrations are discussed. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2009 en_US
dc.subject landing system en_US
dc.title Retro rocket motor self-penetrating scheme for heat shield exhaust ports en_US
dc.type Preprint en_US


Files in this item

This item appears in the following Collection(s)

Show simple item record

Search


Browse

My Account