Aaron E Rogers

US Patent:

20160311562, Oct 27, 2016

Filed:

Apr 21, 2016

Appl. No.:

15/134871

Inventors:

- Baltimore MD, US
Lake A. Kee - Silver Spring MD, US
Aaron Q. Rogers - Silver Spring MD, US

International Classification:

B64G 1/64

Abstract:

A release system may include a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space or into a ballistic (non-orbital) trajectory for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly and a biasing element assembly. The actuator release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The biasing element assembly may be configured to provide a configurable force in a first direction normal to a surface of the launch vehicle adaptor plate to separate the space vehicle separation plate from the launch vehicle adaptor plate when the actuator-release mechanism assembly is triggered to release the space vehicle separation plate from the launch vehicle adaptor plate

US Patent:

20140131521, May 15, 2014

Filed:

May 6, 2013

Appl. No.:

13/887423

Inventors:

The Johns Hopkins University - , US
Aaron Q. Rogers - Silver Spring MD, US
David F. Persons - Columbia MD, US
Robert A. Summers - Dayton MD, US

Assignee:

The Johns Hopkins University - Baltimore MD

International Classification:

B64G 1/64

US Classification:

2441733

Abstract:

An adaptor system includes a space vehicle separation plate operably coupled to a space vehicle, a launch vehicle adaptor plate operably coupled to a launch vehicle capable of carrying the space vehicle into space for release of the space vehicle from the launch vehicle, an actuator release mechanism assembly, a bend/shear restrain assembly that is non-coaxial with the actuator-release connector, and a biasing element. The actuator-release mechanism assembly may be configured to separably couple the space vehicle separation plate to the launch vehicle adaptor plate. The actuator-release actuator-release mechanism assembly may pass through the launch vehicle adaptor plate to engage the space vehicle separation plate to hold the space vehicle separation plate substantially parallel to the launch vehicle adaptor plate prior to release of the space vehicle separation plate.