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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS1982

Centerline latch tool for contingency orbiter door closure

The centerline latch tool was designed and developed as an EVA manual backup device for latching the Space Shuttle Orbiter's payload bay doors for reentry in case of a failure of the existing centerline latches to operate properly. The tool was designed to satisfy a wide variety of structural, mechanical, and EVA requirements. It provides a load path for forces on the payload bay doors during reentry. Since the tool would be used by an EVA crewmember, control, handgrips, operating forces, and procedures must be within the capabilities of a partially restrained, suited crewmember in a zero-gravity environment. The centerline latch tool described was designed, developed, and tested to meet these requirements.

Trevino, R. C.↗
NASA NTRS1983

Retractable Rotating Door Latch

New mechanism turns door latch, latching or unlatching door, then retracts until latch is flush with surface of door frame. Concentric cylinders have cam grooves machined in surfaces. When rotated relative to each other cylinders impart rotation and translation to shaft of door latch. Motions may proceed separately or simultaneously.

Carsley, R. B.↗
NASA NTRS1986

Direction-Sensitive Latch

Mechanism eliminates clearance and applies positive load latched to member. Simpler and lighter than previous direction-sensitive latches (also called "vector-sensitive latches"). New mechanism well suited to operation by automatic control or by remote controlled manipulator. Stages of latching process begin with application of downward force to secondary member, causing it to displace roller. After secondary member has passed roller and joined primary member, actuator removes clearance between roller and secondary member.

Acres, W. R.↗
NASA NTRS1986

Latching mechanism for deployable/re-stowable columns useful in satellite construction

A column longeron latch assembly provides the securing mechanism for the deployable, telescoping column of a hoop/column antenna. The column is an open lattice structure with three longerons disposed 120 deg apart as the principle load bearing member. The column is deployed from a pair of eleven nested bays disposed on opposite sides of a center section under the influence of a motor-cable-pulley system. The longeron latch is a four bar linkage mechanism using the over-center principle for automatically locking the longeron sections into position during deployment. The latch is unlocked when the antenna is to be restowed. A spring pack disposed in the end of each longeron serves to absorb stress forces on the deployed column through the cam head piston and abutting latch from an adjacent longeron.

Ahl, E. L., Jr.↗
NASA NTRS2018

Capture Latch Assembly for the NASA Docking System

Final Paper and not the abstract is attached. a summary of the Design, Development, and Qualification of the Capture Latch Assembly (CLA) for the NASA Docking System Block 1 (NDSB1). The CLA is an integral part of the Soft Capture System (SCS) of the NDSB1, serving the purpose of connecting the mating SCS Rings of two docking vehicles. The paper will present an overview of the function of the CLA and its basic concept of operations, including a summary of the major components of the CLA. The development, qualification, and production of the CLA will then be described. Particular focus will be provided on two major issues that occurred during production and qualification of the CLA. The first issue was failures of the CLA Motor (CLM) during acceptance testing (AT). The failures of the CLM were ultimately determined to be due to design defects and manufacturing errors in the motor commutation sensor assembly. The second issue was failure of the secondary release mechanism, or Contingency Capture Latch Release (CCLR) mechanism during development and qualification testing. The CCLR failures were found to be a result of excess free play in the release mechanism, resulting in wear leading to galling inside the release mechanism. An overview of each failure will be provided, along with a summary of the failure investigation and recovery process. Finally, Lessons Learned from each of the major issues and the overall development of the Capture Latch will be presented.

Capture Latch↗
NASA NTRS1970

High-powered automatic latching device

Latches automatically lock together two remotely controlled bodies when their triggers are engaged by the docking ring of the lesser body. Latches are disengaged by manual actuation of the handle of each latch through two complete cycles. Emergency locking by manual actuation is also provided.

Cobin, J. C.↗
NASA NTRS1975

Latching device

A latching device is suited for use in establishing a substantially motionless connection between a stationary receiver and a movable latching mechanism. The latching mechanism includes a pivotally supported restraining hook continuously urged into a capturing relationship with the receiver, characterized by a spring-biased pawl having a plurality of aligned teeth. The teeth are seated in the surface of the throat of the hook and positionable into restraining engagement with a rigid restraining shoulder projected from the receiver.

Ulrich, G. W.↗
NASA NTRS1981

Payload retention latches for the shuttle orbiter

Two latches were designed to mount payloads in the shuttle orbiter bay. Multiple retention latches attach a payload to the sill longerons and another latch device attaches it to the keel. Requirements for each actuator are defined and drive mechanisms are described. Other design aspects discussed include: switch mechanisms, motors, gearboxes, redundancy provisions, structural materials, and lubricants. A preliminary dry lubricant test program is also reviewed and results presented.

Renken, R. D.↗
NASA NTRS1981

Latch mechanism for the space telescope

Latch mechanisms to secure, release, and relatch deployables on the Space Telescope are described. The latch mechanisms are mechanical pre-loading devices composed of a four-bar linkage driven by an electro-mechanical rotary actuator. The latch mechanism requirements, unique design features, analytical highlights, and the development testing are discussed.

Schmidt, H. F.↗
NASA NTRS1982

A ball trunnion capture latch

The Ball Trunnion Capture Latch described was developed and designed to restrain a spacecraft deployable appendage in three translational directions. The latch is capable of supporting an appendage during STS ascent and landing events and is capable of releasing and restowing an appendage distorted in three translational directions by thermal growth. The requirements, design, analyses, and tests conducted on a development unit of the latch are discussed.

Adams, D. V.↗
NASA NTRS1983

Hinge latch mechanism

The device described in this paper is a modular hinge latch mechanism. It is used to latch and preload four motorized hinges after their deployment. The paper describes design requirements, hardware development and initial testing of this hinge latch module. A special effort has been made to cover the design philosophy incorporated into this hardware.

Walker, J. C.↗
NASA NTRS1984

Radial SI latches vibration test data review

Dynamic testing of the Space Telescope Scientific Instrument Radial Latches was performed as specified by the designated test criteria. No structural failures were observed during the test. The alignment stability of the instrument simulator was within required tolerances after testing. Particulates were discovered around the latch bases, after testing, due to wearing at the B and C latch interface surfaces. This report covers criteria derivation, testing, and test results.

Harrison, P. M.↗
NASA NTRS1986

Latch for Telescoping Structures

Latch for three-member telescoping column developed for deployment of antenna 122 meters in diameter. Deployable column along axis of antenna open lattice structure with three longerons as principal loadbearing members. Column divided into telescoping sections that deploy, one section at time. Latch automatically locks sections into position during deployment and unlocks them when antenna restowed. Latch is four-bar linkage using over-center principle for locking, with Belleville spring washers to absorb deflections.

Ahl, Elvin L., Jr.↗
NASA NTRS1985

Hemispherical latching apparatus

An apparatus for securing payloads in a space vehicle such as the space shuttle is described. The apparatus includes many latching assemblies carried by a platform on the vehicle and a like number of latching elements carried by the payload and adapted to mate with the latching assemblies. The novelty of the invention is believed to reside in the use of complementary hemispherical elements which automatically align and engage with one another. This enables a simple but effective mode of operation and avoids the need for hinged linkages and similar moving parts.

Clark, K. H.↗
NASA NTRS1988

Structural latches for modular assembly of spacecraft and space mechanisms

Latching techniques are changing from early approaches due to the advent of berthing technology. Latch selection for a given interface may be conducted by evaluating candidate capabilities which meet functional interface requirements. A judgment criteria system is presented along with an example of its use in choosing the Rollerscrew Structural Latch (RSL) for the NASA Flat Plate Interface Prototype (FPIP). Details are given on Rollerscrew operation, design, and development difficulties. A test plan is also outlined for the RSL and FPIP.

Mccown, William↗
NASA NTRS1991

Resettable binary latch mechanism for use with paraffin linear motors

A new resettable Binary Latch Mechanism was developed utilizing a paraffin actuator as the motor. This linear actuator alternately latches between extended and retracted positions, maintaining either position with zero power consumption. The design evolution and kinematics of the latch mechanism are presented, as well as the development problems and lessons that were learned.

Maus, Daryl↗
NASA NTRS1992

Manual Override For Electromechanical Latch

Override mechanism enables user to operate electromechanical latching mechanism manually if primary mechanism fails. Release/Engage Mechanism (REM) moves pin receivers to confine pins on object to be held. Clutch disengages electrically driven latch normally used. Used to latch and unlatch large, heavy objects from fixed support structure.

Scott, Richard↗
NASA NTRS1991

Bench-level characterization of a CMOS standard-cell D-latch using alpha-particle sensitive test circuits

A methodology is described for predicting the SEU susceptibility of a standard-cell D-latch using an alpha-particle sensitive SRAM, SPICE critical charge simulation results, and alpha-particle interaction physics. Measurements were made on a 1.6-micron n-well CMOS 4-kb test SRAM irradiated with an Am-241 alpha-particle source. A collection depth of 6.09 micron was determined using these results and TRIM computer code. Using this collection depth and SPICE derived critical charge results on the latch design, an LET threshold of 34 MeV sq cm/mg was predicted. Heavy ion tests were then performed on the latch and an LET threshold of 41 MeV sq cm/mg was determined.

Blaes, B. R.↗