Engineering topics
Publications and source records attributed to Matteo, D. N..
The original slipring design for communications spacecraft, the handling and testing of the slipring assembly before launch, the on orbit performance indicating the need for improvement in dynamic noise, the subsequently incorporated design improvements, and the results of testing to verify noise performance improvement are described.
The technical problems encountered in the development of an advanced separation nut design are described. The nut is capable of sustaining a large preload and releasing that load with a low level of induced pyrotechnic shock, while demonstrating a tolerance for extremely high shock imposed by other pyrotechnic devices. The analysis of the separation nut was performed to acquire additional understanding of the phenomena affecting operation of the nut and to provide quantitative evaluation of design modification for aerospace applications.
The configuration and testing of a power driven hinge for deployment of the solar array and antenna boom for the LANDSAT-D spacecraft is discussed. The hinge is fully mechanically and electrically redundant and, thereby, can sustain a single point failure of any one motor (or its power supply), speed reducer, or bearing set without loss of its ability to function. This design utilizes the capability of the stepper motor drive to remove the flexibility of the drive train from the joint stiffness equation when the hinge is loaded against its stop. This feature precludes gapping of the joint under spacecraft maneuver loads even in the absence of a latching feature. Thus, retraction is easily accomplished by motor reversal without the need for a solenoid function to remove the latch.
The OSO-7 Orbiting Solar Observatory was launched on September 29, 1971. One of the two main sun pointing instruments aboard was a spectroheliograph for monitoring extreme ultraviolet and X-ray radiation from the sun. The instrument has been operating successfully in orbit for approximately two years. The design solution to each of the mechanism tasks is described. Also described are certain developmental problems and their solutions which led to the ultimate mission success.
ATS attitude stabilization boom packages, describing torque transmission, drum synchronization, electrical isolation, lubrication, etc
Mechanical properties of stabilization booms for gravity gradient studies on Applications Technology Satellites
Design, construction, and testing of preliminary 30 watts per pound roll-up solar array
Thirty watt per pound roll-up solar array feasibility
Eddy-current damper and gravity-gradient rod development