Ranger command subsystem follow-on final engineering report no. 17-48420
Digital command detector and decoder for Ranger Block III command system
DIGITAL COMMAND SYSTEM↗
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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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Digital command - a network for manned spaceflight.
Digital Command Network for error-free radio command control of manned and unmanned spacecraft
DIGITAL COMMAND SYSTEM↗
The command system
Ground commands and internal logic functions for Relay I satellite command system
COMMAND SYSTEM↗
GEOS command assignment
Satellite operational reliability by assigning command functions to relay matrix positions of command subsystem
SATELLITE COMMUNICATION↗
Telemetry, tracking, and command consolidation in the Deep Space Network
Currently, in NASA's Deep Space Network (DSN), telemetry, tracking, and command (TT&C) functions are distributed between multiple subsystem computers. Control design of these subsystems did not consider the interaction necessary between the functions, which create opportunities for loss of data. Also, the current controller design can force the use of equipment that is not needed for the task at hand, to the detriment of others. As part of the Network Simplification Project (NSP), the TTC implementation has been re-examined, New telemetry and commanding equipment is being built, and the control of the TT&C functions is being consolidated into two controllers, Uplink and Downlink. The new equipment uses commercial components, as opposed to the custom built equipment it is replacing, which improves reliability and simplifies maintenance.
tracking↗
Project Hermes 'Use of Smartphones for Receiving Telemetry and Commanding a Satellite'
TCPIP protocols can be applied for satellite command, control, and data transfer. Project Hermes was an experiment set-up to test the use of the TCPIP protocol for communicating with a space bound payload. The idea was successfully demonstrated on high altitude balloon flights and on a sub-orbital sounding rocket launched from NASAs Wallops Flight Facility. TCPIP protocols can be applied for satellite command, control, and data transfer. Project Hermes was an experiment set-up to test the use of the TCPIP protocol for communicating with a space bound payload. The idea was successfully demonstrated on high altitude balloon flights and on a sub-orbital sounding rocket launched from NASAs Wallops Flight Facility.
Telemetry↗
Fault Protection Design for the Command and Data Subsystem on the Cassini Spacecraft
The Command and Data Subsystem (CDS) on Cassini is responsible for uplink command processing, spacecraft intercommunications and control, and downlink telemetry formatting. The 10.7 year mission life, 160 minute round-trip light time, and extended periods of operation without continuous ground communications drive the CDS design in directions of redundancy, autonomy, and fault protection to accomodate the mission objectives.
Cassini↗
Software-Only Key Management and Cryptography (KMC) for Spacecraft Command Encryption
The Jet Propulsion Laboratory (JPL) Advanced Multi-Mission Operations System (AMMOS) in partnership with NASA’s Katherine Johnson Independent Verification and Validation (NASA IV&V) Jon McBride Software Testing and Research (JSTAR) laboratory have jointly developed a command encryption capability that provides a software-only encryption solution utilizing the CCSDS Space Data Link Security Protocol. This solution, named Key Management and Cryptography (KMC), incorporates JPL’s encryption service with the JSTAR open-source CryptoLib library, providing a solution for spacecraft command encryption, which is required per NASA standard NASA-STD-1006-A. This paper will focus on its design, usage, and operation for two SmallSat missions, along with its future expanded functionality of end-to-end spacecraft encryption.
command encryption↗
Lunar Command and Control Interoperability (LuCCI) Project Overview
The Lunar Command and Control Interoperability (LuCCI) project was formed to address a gap in how Lunar Surface Systems (LSS) would interoperate across multiple programs, commercial partners, and international partners. The project objective is to define, prototype, integrate, and evaluate an interoperable lunar command, control, data, and software reference architecture to enable autonomy and informatics capability through common standards across LSS.
Communications↗
Performance Analysis of OpenSHMEM Applications with TAU Commander
The TAU Performance System® (TAU) is a powerful and highly versatile profiling and tracing tool ecosystem for performance engineering of parallel programs. Developed over the last twenty years, TAU has evolved with each new generation of HPC systems and scales efficiently to hundreds of thousands of cores. TAU’s organic growth has resulted in a loosely coupled software toolbox such that novice users first encountering TAU’s complexity and vast array of features are often intimidated and easily frustrated. To lower the barrier to entry for novice TAU users, ParaTools and the US Department of Energy have developed “TAU Commander,” a performance engineering workflow manager that facilitates a systematic approach to performance engineering, guides users through common profiling and tracing workflows, and offers constructive feedback in case of error. This work compares TAU and TAU Commander workflows for common performance engineering tasks in OpenSHMEM applications and demonstrates workflows targeting two different SHMEM implementations, Intel Xeon “Haswell” and “Knights Landing” processors, direct and indirect measurement methods, callsite, profiles, and traces.
97 MATHEMATICS AND COMPUTING↗
Multiple-mission command system
Multiple-mission command system for installation in DSN for command and control of spacecraft
Wilcher, J.↗
Development and testing of the flight command subsystem for the Mariner Mars 1971 spacecraft
The flight command subsystem for the Mariner Mars 1971 spacecraft is of the same basic design and construction as that for Mariner Mars 1969 except for its expanded capability. Its primary purpose is to provide remote control for the spacecraft. This report briefly describes the design changes, fabrication, and significant problems associated with the development of the Mariner Mars 1971 flight command subsystem.
Chitty, W. H.↗
Digital data command bus
Command bus constructed from coaxial cable has short segments of its outer jacket and shield removed and replaced with small ferrite cores carrying multiturn windings connected to decoder. Device reduces number of wire pairs required to communicate command data to systems and subsystems.
Milligan, G. C.↗
Pressure signatures for the Apollo command module and the Saturn 5 launch vehicle with a discussion of strong shock extrapolation procedures
Wind tunnel pressure signatures measured at Mach 10.1 for model of the Apollo Command Module and at Mach numbers from 3.01 to 7.91 for two models of the Saturn launch configuration are presented. The signatures for the command module were obtained at roll angles ranging from 0 deg to 180 deg. A brief discussion of the extrapolation of strong pressure signatures is included in the report.
Hicks, R. M.↗
Ground-Commanded Television Assembly (GCTA)
A ground-commanded color television assembly (GCTA) was designed for use on lunar explorations associated with NASA manned Apollo missions. The camera system as seen on Apollo 15 provided television coverage in the vicinity of the lunar module (LM) landing site, and was mounted on the lunar roving vehicle (LRV) to provide color coverage of astronaut activity and lunar topography during traverses on the surface. Remote control of the camera from earth was accomplished through the existing real-time Apollo command links. The assembly is illustrated. The configuration satisfied all anticipated requirements of the Apollo 15 mission and was fully responsive to specifications. The technical approach was based on proven designs and offered maximum mission flexibility, potential growth, and capability to withstand environmental extremes encountered on the lunar surface.
Source record↗
NASIS data base management system - IBM 360/370 OS MVT implementation. 5: Retrieval command system reference manual
The retrieval command subsystem reference manual for the NASA Aerospace Safety Information System (NASIS) is presented. The output oriented classification of retrieval commands provides the user with the ability to review a set of data items for verification or inspection as a typewriter or CRT terminal and to print a set of data on a remote printer. Predefined and user-definable data formatting are available for both output media.
Source record↗
Task four report: Telemetry, command, and data handling
An overview of the telemetry, command, and data handling features of four spacecraft developed under GSFC management is presented. Two of these spacecraft ATS and SMS, are designed for geostationary orbit; the other two OSO and ERTS, are designed for low earth orbits. The program time spans for these spacecraft are as shown. The programs are seen to be near contemporary, especially in the 1973, 1974 period. All of the spacecraft listed were developed under GSFC control and are thus subject to the standards set forth in the Aerospace Data System Standard developed by GSFC. These standards must be adhered to by all spacecraft programs under GSFC control or utilizing STDN unless waivers have been granted. The standards were developed to maximize the utilization of the large amount of standard equipment at each STDN ground facility. The standards impose bounds on both the command and telemetry formats to be compatible with the STDN ground station unless valid and acceptable reasons are raised to deviate from these restraints.
Source record↗
A velocity-command controller for a VTOL aircraft
A technique is presented for calculating feedback and feedforward gain matrices that enable a VTOL aircraft to track input commands of forward and vertical velocity while maintaining acceptable responses to pilot inputs. Leverrier's algorithm is used for determining a set of state-variable, feedback gains that force the closed-loop poles and zeros of one pilot-input transfer function to pre-selected positions in the s-plane. This set of feedback gains is then used to calculate the feedback and feedforward gains for the velocity-command controller. The method is computationally attractive since the gains are determined by solving systems of linear, simultaneous equations. The method is used in a digital simulation of the CH-47 helicopter to control longitudinal dynamics.
Reid, G. F.↗