Browse Topic: Telemetry

Items (121)

Acquiring and Telemetering Test Data from Hypersonic Platforms

TBMG-5212012/01/2024

VALIDATION OF FROZEN SPEEDOMETER READINGS AGAINST EDR DATA

2022-01-099903/29/2022

Around the turn of this century, the automotive industry introduced a new type of technology to drive the gauges on a vehicle’s instrument cluster. The change was unannounced to the collision reconstruction world, but soon after, investigators observed a marked increase in crashed vehicles displaying frozen gauges at what often appeared to be correct readings. The new technology was the use of stepper motors which require power to return to the zero position. Hence if electrical power is lost, the gauges remain in position. There have been a number of previous papers covering the operation of the instruments and crash testing of cars and motorcycles to establish the ability of the instruments to withstand the forces on the instrument during a collision. This paper aims to compare the frozen instrument readings from real world collisions with the available EDR data from the crashed vehicles. With the assistance of the collision reconstruction community a large dataset of 235 vehicles

Goddard, Christopher H., Anderson, Steve

Cameras Capture Asteroid Debris Retrieval

TBMG-3835401/01/2021

Space Dynamics Laboratory Utah State University Logan, UT

Military Vehicle Situational Awareness System

TBMG-3301510/01/2018

Computech International (CTI) Tikva, Israel +972-3-9211110

Integrated Ground Supported Systems Equation Processor

07/01/2015

The Integrated Science Instrument Module (ISIM) Ground Support System (IGSS) Equation Processor (IEP) allows for the general production of “derived” telemetry products in the Raytheon Eclipse ground system used to support the James Webb Space Telescope (JWST) project. The IEP works alongside the Raytheon-provided equation-processing system but provides for support of string data types that the existing equation processing does not support. The string data type production is required to support the manipulation of JWST string telemetry data types, and for the production of string data types to produce readable time conversions from a binary value to year, day, hour, minute, second format that can be directly viewed on real-time telemetry display pages. The user writes equation scripts using the Tool Command Language (TCL) and specifies as part of the definition how the equation is triggered and what the results should look like. The TCL scripting language provides for a fully featured

Spitzer Telemetry Processing System

TBMG-1722609/01/2013

The Spitzer Telemetry Processing System (SirtfTlmProc) was designed to address objectives of JPL’s Multi-mission Image Processing Lab (MIPL) in processing spacecraft telemetry and distributing the resulting data to the science community. To minimize costs and maximize operability, the software design focused on automated error recovery, performance, and information management.

Phoenix Telemetry Processor

TBMG-1722409/01/2013

Phxtelemproc is a C/C++ based telemetry processing program that processes SFDU telemetry packets from the Telemetry Data System (TDS). It generates Experiment Data Records (EDRs) for several instruments including surface stereo imager (SSI); robotic arm camera (RAC); robotic arm (RA); microscopy, electrochemistry, and conductivity analyzer (MECA); and the optical microscope (OM). It processes both uncompressed and compressed telemetry, and incorporates unique subroutines for the following compression algorithms: JPEG Arithmetic, JPEG Huffman, Rice, LUT3, RA, and SX4.

TBMG-1660806/01/2013

International Space Station Live! (ISSLive!) is a Web application that uses a proprietary commercial technology called Lightstreamer to push data across the Internet using the standard http port (port 80). ISSLive! uses the push technology to display real-time telemetry and mission timeline data from the space station in any common Web browser or Internet-enabled mobile device.

XTCE GOVSAT Tool Suite 1.0

TBMG-1591503/01/2013

The XTCE GOVSAT software suite contains three tools: validation, search, and reporting. The Extensible Markup Language (XML) Telemetric and Command Exchange (XTCE) GOVSAT Tool Suite is written in Java for manipulating XTCE XML files. XTCE is a Consultative Committee for Space Data Systems (CCSDS) and Object Management Group (OMG) specification for describing the format and information in telemetry and command packet streams. These descriptions are files that are used to configure real-time telemetry and command systems for mission operations. XTCE’s purpose is to exchange database information between different systems.

Estimating Torque Imparted on Spacecraft Using Telemetry

TBMG-1549001/01/2013

There have been a number of missions with spacecraft flying by planetary moons with atmospheres; there will be future missions with similar flybys. When a spacecraft such as Cassini flies by a moon with an atmosphere, the spacecraft will experience an atmospheric torque. This torque could be used to determine the density of the atmosphere. This is because the relation between the atmospheric torque vector and the atmosphere density could be established analytically using the mass properties of the spacecraft, known drag coefficient of objects in free-molecular flow, and the spacecraft velocity relative to the moon. The density estimated in this way could be used to check results measured by science instruments. Since the proposed methodology could estimate disturbance torque as small as 0.02 N-m, it could also be used to estimate disturbance torque imparted on the spacecraft during high-altitude flybys.

MER Telemetry Processor

TBMG-1526012/01/2012

MERTELEMPROC processes telemetered data in data product format and generates Experiment Data Records (EDRs) for many instruments (HAZCAM, NAVCAM, PANCAM, microscopic imager, Mössbauer spectrometer, APXS, RAT, and EDLCAM) on the Mars Exploration Rover (MER). If the data is compressed, then MERTELEMPROC decompresses the data with an appropriate decompression algorithm. There are two compression algorithms (ICER and LOCO) used in MER. This program fulfills a MER specific need to generate Level 1 products within a 60-second time requirement.

Monitoring of International Space Station Telemetry Using Shewhart Control Charts

TBMG-1486610/01/2012

Shewhart control charts have been established as an expedient method for analyzing dynamic, trending data in order to identify anomalous subsystem performance as soon as such performance would exceed a statistically established baseline. Additionally, this leading indicator tool integrates a selection methodology that reduces false positive indications, optimizes true leading indicator events, minimizes computer processor unit duty cycles, and addresses human factor concerns (i.e., the potential for flight-controller data overload). This innovation leverages statistical process control, and provides a relatively simple way to allow flight controllers to focus their attention on subtle system changes that could lead to dramatic off-nominal system performance. Finally, this capability improves response time to potential hardware damage and/or crew injury, thereby improving space flight safety.

Scalable Integrated Multi-Mission Support System Simulator Release 3.0

TBMG-1469009/01/2012

The Scalable Integrated Multi-mission Support System (SIMSS) is a tool that performs a variety of test activities related to spacecraft simulations and ground segment checks.

FERMI/GLAST Integrated Trending and Plotting System Release 5.0

TBMG-1468909/01/2012

An Integrated Trending and Plotting System (ITPS) is a trending, analysis, and plotting system used by space missions to determine performance and status of spacecraft and its instruments. ITPS supports several NASA mission operational control centers providing engineers, ground controllers, and scientists with access to the entire spacecraft telemetry data archive for the life of the mission, and includes a secure Web component for remote access.

Low-Cost Telemetry System for Small/Micro Satellites

TBMG-1466309/01/2012

A Software Defined Radio (SDR) concept uses a minimum amount of analog/radio frequency components to up/downconvert the RF signal to/from a digital format. Once in the digital domain, all other processing (filtering, modulation, demodulation, etc.) is done in software. The project will leverage existing designs and enhance capabilities in the commercial sector to provide a path to a radiation-hardened SDR transponder. The SDR transponder would incorporate baseline technologies dealing with improved Forward Error Correcting (FEC) codes to be deployed to all Near Earth Network (NEN) ground stations. By incorporating this FEC, at least a tenfold increase in data throughput can be achieved.

Telerobotics Workstation (TRWS) for Deep Space Habitats

TBMG-1460609/01/2012

On medium- to long- duration human spaceflight missions, latency in communications from Earth could reduce efficiency or hinder local operations, control, and monitoring of the various mission vehicles and other elements. Regardless of the degree of autonomy of any one particular element, a means of monitoring and controlling the elements in real time based on mission needs would increase efficiency and response times for their operation. Since human crews would be present locally, a local means for monitoring and controlling all the various mission elements is needed, particularly for robotic elements where response to interesting scientific features in the environment might need near- instantaneous manipulation and control.

Architecture of the Air Force Satellite Control Network

TBMG-1334404/01/2012

The Air Force Satellite Control Network (AFSCN) is a worldwide network of ground stations that supports a variety of users from NASA to the National Recon naissance Office (NRO). The network performs tracking, telemetry, and commanding (TT&C) for these users. Users, located at Satellite Operations Centers (SOCs), must compete for time on the AFSCN (see Figure 1).

Virtual Machine Language 2.1

TBMG-1325804/01/2012

VML (Virtual Machine Language) is an advanced computing environment that allows spacecraft to operate using mechanisms ranging from simple, timeoriented sequencing to advanced, multicomponent reactive systems.

Use of CCSDS Packets Over SpaceWire to Control Hardware

TBMG-1262601/01/2012

For the Lunar Reconnaissance Orbiter, the Command and Data Handling subsystem consisted of several electronic hardware assemblies that were connected with SpaceWire serial links. Electronic hardware would be commanded/controlled and telemetry data was obtained using the SpaceWire links. Prior art focused on parallel data buses and other types of serial buses, which were not compatible with the SpaceWire and the core flight executive (CFE) software bus.

Space Environments Testbed

TBMG-1222512/01/2011

The Space Environments Testbed (SET) is a flight controller data system for the Common Carrier Assembly. The SET-1 flight software provides the command, telemetry, and experiment control to ground operators for the SET-1 mission. Modes of operation (see diagram) include:

Digital Interface Board to Control Phase and Amplitude of Four Channels

TBMG-1222312/01/2011

An increasing number of parts are designed with digital control interfaces, including phase shifters and variable attenuators. When designing an antenna array in which each antenna has independent amplitude and phase control, the number of digital control lines that must be set simultaneously can grow very large. Use of a parallel interface would require separate line drivers, more parts, and thus additional failure points. A convenient form of control where single-phase shifters or attenuators could be set or the whole set could be programmed with an update rate of 100 Hz is needed to solve this problem.

Telemetry and Science Data Software System

TBMG-1186411/01/2011

The Telemetry and Science Data Software System (TSDSS) was designed to validate the operational health of a spacecraft, ease test verification, assist in debugging system anomalies, and provide trending data and advanced science analysis. In doing so, the system parses, processes, and organizes raw data from the Aquarius instrument both on the ground and while in space. In addition, it provides a user-friendly telemetry viewer, and an instant push-button test report generator. Existing ground data systems can parse and provide simple data processing, but have limitations in advanced science analysis and instant report generation.

Polished Panel Optical Receiver for Simultaneous RF/Optical Telemetry With Large DSN Antennas

TBMG-1138510/01/2011

The “polished panel” optical receiver concept described here makes use of aluminum panels on the main reflector of the Deep Space Network’s (DSN’s) 34-meter antennas at optical wavelengths by polishing and coating their surface to efficiently reflect nearinfrared wavelengths in the 1,064–1,550- nanometer range. Achievable surface smoothness is not a limiting factor for aluminum panels, and initial field experiments indicate that the surface quality of microwave aluminum panels is sufficient to concentrate the light into small, but not diffraction-limited, spots at their primary focus. Preliminary analysis of data from high-quality microwave panels has shown that the light can be concentrated into 200–400 microradian cones, resulting in spot diameters of 2–4 mm at the 10-meter primary focus F0 shown in the figure, or 2–4 cm spots at F1 after magnification by the subreflector, which results in an effective focal length of about 100 meters. Three distinct implementation options are

Polished Panel Optical Receiver for Simultaneous RF/Optical Telemetry With Large DSN Antennas

TBMG-TB-01138509/26/2011

Three options are examined. The “polished panel” optical receiver concept described here makes use of aluminum panels on the main reflector of the Deep Space Network’s (DSN’s) 34-meter antennas at optical wavelengths by polishing and coating their surface to efficiently reflect nearinfrared wavelengths in the 1,064–1,550- nanometer range. Achievable surface smoothness is not a limiting factor for aluminum panels, and initial field experiments indicate that the surface quality of microwave aluminum panels is sufficient to concentrate the light into small, but not diffraction-limited, spots at their primary focus. Preliminary analysis of data from high-quality microwave panels has shown that the light can be concentrated into 200–400 microradian cones, resulting in spot diameters of 2–4 mm at the 10-meter primary focus F0 shown in the figure, or 2–4 cm spots at F1 after magnification by the subreflector, which results in an effective focal length of about 100 meters. Three distinct

Positively Verifying Mating of Previously Unverifiable Flight Connectors

TBMG-1082509/01/2011

Current practice is to uniquely key the connectors, which, when mated, could not be verified by ground tests such as those used in explosive or non-explosive initiators and pyro valves. However, this practice does not assure 100-percent correct mating. This problem could be overcome by the following approach.

Link Analysis in the Mission Planning Lab

TBMG-1091809/01/2011

The legacy communications link analysis software currently used at Wallops Flight Facility involves processes that are different for command destruct, radar, and telemetry. There is a clear advantage to developing an easy-to-use tool that combines all the processes in one application. Link Analysis in the Mission Planning Lab (MPL) uses custom software and algorithms integrated with Analytical Graphics Inc. Satellite Toolkit (AGI STK). The MPL link analysis tool uses pre/post-mission data to conduct a dynamic link analysis between ground assets and the launch vehicle. Just as the legacy methods do, the MPL link analysis tool calculates signal strength and signal-to-noise according to the accepted processes for command destruct, radar, and telemetry assets. Graphs and other custom data are generated rapidly in formats for reports and presentations. STK is used for analysis as well as to depict plume angles and antenna gain patterns in 3D.

FPGA for Power Control of MSL Avionics

TBMG-1083909/01/2011

A PLGT FPGA (Field Programmable Gate Array) is included in the LCC (Load Control Card), GID (Guidance Interface & Drivers), TMC (Telemetry Multiplexer Card), and PFC (Pyro Firing Card) boards of the Mars Science Laboratory (MSL) spacecraft. (PLGT stands for PFC, LCC, GID, and TMC.) It provides the interface between the backside bus and the power drivers on these boards. The LCC drives power switches to switch power loads, and also relays. The GID drives the thrusters and latch valves, as well as having the star-tracker and Sun-sensor interface. The PFC drives pyros, and the TMC receives digital and analog telemetry. The FPGA is implemented both in Xilinx (Spartan 3- 400) and in Actel (RTSX72SU, ASX72S). The Xilinx Spartan 3 part is used for the breadboard, the Actel ASX part is used for the EM (Engineer Module), and the pin-compatible, radiation-hardened RTSX part is used for final EM and flight.

Positively Verifying Mating of Previously Unverifiable Flight Connectors

TBMG-TB-01082508/22/2011

New approach ensures secure connections. Current practice is to uniquely key the connectors, which, when mated, could not be verified by ground tests such as those used in explosive or non-explosive initiators and pyro valves. However, this practice does not assure 100-percent correct mating. This problem could be overcome by the following approach.

Surface Texture Control

J449_201108 (Current)08/04/2011

SAE J448, Surface Texture, has been set up for precision reference specimens using a controlled surface profile to obtain reproducible roughness values. These specimens are for instrument calibration. Appropriate symbols for roughness, waviness, and lay have also been standardized (ASA B46.1-1962 and SAE J448). For production control, especially from one geographical location to another, means are required to facilitate the inspection of surface characteristics called for by specifications which include not only roughness but profile waviness and lay. In order to integrate the requirements of the designer with the actual production of surfaces, a second grade of control standards must be adopted which will be functional in nature for the specific product being manufactured. These control standards may be Calibrated Pilot Specimens (actual parts with satisfactory texture) or Roughness Comparison Specimens (ASA B46.1-1962). This SAE Recommended Practice describes the usage of these

Surface Enhancement Committee

Monitoring Spacecraft Telemetry Via Optical or RF Link

TBMG-1076508/01/2011

A patent disclosure document discusses a photonic method for connecting a spacecraft with a launch vehicle upper-stage telemetry system as a means for monitoring a spacecraft’s health and status during and right after separation and deployment. This method also provides an efficient opto-coupled capability for prelaunch built-in-test (BIT) on the ground to enable more efficient and timely integration, preflight checkout, and a means to obviate any local EMI (electromagnetic interference) during integration and test. Additional utility can be envisioned for BIT on other platforms, such as the International Space Station (ISS).

SpaceCube Demonstration Platform

TBMG-1049907/01/2011

A document discusses how the HST SM4 SpaceCube flight spare was modified to create an experiment called the SpaceCube Demonstration Platform (SC DP) for use on the MISSE7 Space Station payload (in collaboration with NRL). It is designed to serve as an on-orbit platform for demonstrating advanced fault tolerance technologies. A simple C&DH (command and data handling) system was developed for the Virtex4 FPGAs (field programmable gate arrays). Both Virtex4s on each SpaceCube run the same program, and both receive incoming telemetry. The rad-hard service FPGA performs simple error checking to verify that the incoming telemetry is valid. The SpaceCube framework was modified to allow for new program files to be sent from the ground, to be stored on the SpaceCube, and to be executed through ground commands. Each SpaceCube Virtex4 FPGA has resources set aside for experiments that are functionally isolated from the C&DH system. The experiments communicate to the C&DH system through a set of

RAPID: Collaborative Commanding and Monitoring of Lunar Assets

TBMG-987405/01/2011

RAPID (Robot Application Programming Interface Delegate) software utilizes highly robust technology to facilitate command-ing and monitoring of lunar assets. RAPID provides the ability for intercenter communication, since these assets are developed in multiple NASA centers.

SpaceCube 2.0: An Advanced Hybrid Onboard Data Processor

TBMG-912902/02/2011

The SpaceCube 2.0 is a compact, high-performance, low-power onboard processing system that takes advantage of cutting-edge hybrid (CPU/FPGA/DSP) processing elements. The SpaceCube 2.0 design concept includes two commercial Virtex-5 field-programmable gate array (FPGA) parts protected by “radiation hardened by software” technology, and possesses exceptional size, weight, and power characteristics [5×5×7 in., 3.5 lb (≈12.7×12.7×17.8 cm, 1.6 kg) 5–25 W, depending on the application’s required clock rate]. The two Virtex-5 FPGA parts are implemented in a unique back-to-back configuration to maximize data transfer and computing performance.

Telemetry-Based Ranging

TBMG-913102/01/2011

A telemetry-based ranging scheme was developed in which the downlink ranging signal is eliminated, and the range is computed directly from the downlink telemetry signal. This is the first Deep Space Network (DSN) ranging technology that does not require the spacecraft to transmit a separate ranging signal. By contrast, the evolutionary ranging techniques used over the years by NASA missions, including sequential ranging (transmission of a sequence of sinusoids) and PN-ranging (transmission of a pseudo-noise sequence) — whether regenerative (spacecraft acquires, then regenerates and retransmits a noise-free ranging signal) or transparent (spacecraft feeds the noisy demodulated uplink ranging signal into the downlink phase modulator) — relied on spacecraft power and bandwidth to transmit an explicit ranging signal.

Browser-Based Application for Telemetry Monitoring of Robotic Assets

TBMG-869911/01/2010

AEGSE Virtuoso Charting is an application that enables animated, real-time charting of telemetry streams of data from a rover. These automatically scaled charts are completely interactive, and allow users to choose the variables that they want to monitor. The charts can process data from streams with many variables. This application allows for the simultaneous viewing of up to four individually configured charts on a small touch-screen laptop.

High-Performance CCSDS Encapsulation Service Implementation in FPGA

TBMG-847909/01/2010

The Consultative Committee for Space Data Systems (CCSDS) Encapsulation Service is a convergence layer between lower-layer space data link framing protocols, such as CCSDS Advanced Orbiting System (AOS), and higher-layer networking protocols, such as CFDP (CCSDS File Delivery Protocol) and Internet Protocol Extension (IPE). CCSDS Encapsulation Service is considered part of the data link layer. The CCSDS AOS implementation is described in the preceding article. Recent advancement in RF modem technology has allowed multi-megabit transmission over space links. With this increase in data rate, the CCSDS Encapsulation Service needs to be optimized to both reduce energy consumption and operate at a high rate.

Determining Atmospheric-Density Profile of Titan

TBMG-850309/01/2010

A method was developed for measuring the atmospheric density of Titan, the largest moon of Saturn, to create an accurate density profile as a function of altitude. This will allow mission planners to select safe flyby altitudes, and for navigation engineers to accurately predict the delta-v associated with those flybys.

High-Performance CCSDS AOS Protocol Implementation in FPGA

TBMG-847809/01/2010

The Consultative Committee for Space Data Systems (CCSDS) Advanced Orbiting Systems (AOS) space data link protocol provides a framing layer between channel coding such as LDPC (low-density parity-check) and higher-layer link multiplexing protocols such as CCSDS Encapsulation Service, which is described in the following article. Recent advancement in RF modem technology has allowed multi-megabit transmission over space links. With this increase in data rate, the CCSDS AOS protocol implementation needs to be optimized to both reduce energy consumption and operate at a high rate.

ISS Solar Array Management

TBMG-794505/01/2010

The International Space Station (ISS) Solar Array Management (SAM) software toolset provides the capabilities necessary to operate a spacecraft with complex solar array constraints. It monitors spacecraft telemetry and provides interpretations of solar array constraint data in an intuitive manner. The toolset provides extensive situational awareness to ensure mission success by analyzing power generation needs, array motion constraints, and structural loading situations.

Reception of Multiple Telemetry Signals via One Dish Antenna

TBMG-758903/01/2010

A microwave aeronautical-telemetry receiver system includes an antenna comprising a seven-element planar array of receiving feed horns centered at the focal point of a paraboloidal dish reflector that is nominally aimed at a single aircraft or at multiple aircraft flying in formation. Through digital processing of the signals received by the seven feed horns, the system implements a method of enhanced cancellation of interference, such that it becomes possible to receive telemetry signals in the same frequency channel simultaneously from either or both of two aircraft at slightly different angular positions within the field of view of the antenna, even in the presence of multipath propagation.

Forward-Link/Simulator PCI Card

TBMG-TB-00677001/11/2010

Improvements include decreases in size, cost, and power consumption and an increase in speed. The forward-link/simulator card (FLS) performs the fundamental satellite-telemetry data-transmission function for the forward (Earth-to-spacecraft) link in real time at rates up to 400 Mb/s. The FLS also simulates a Consultative Committee for Space Data Systems (CCSDS) telemetry data source that outputs data at rates up to 150 Mb/s, using industry-standard interface circuitry and standard connectors. Previously, at least two cards, each containing a central processing unit (CPU), were needed to do what the FLS now does. CPU-based cards are complex; are expensive to build, operate, and maintain; are susceptible to malfunction; and require a great deal of power and cooling.

Space-Proven Medical Monitor Provides Total Patient Care

TBMG-667301/01/2010

By mid-1963, American astronauts had visited space on six different occasions, all as part of NASA’s first human space flight program, the Mercury Program. During the final Mercury mission, launched on May 15, 1963, astronaut Leroy Gordon Cooper logged 34 hours in orbit, the longest an American had spent in space to that point. Still, very little was known about the impact that space would have on humans and spacecraft that were subjected to long-duration missions. With this in mind, NASA decided to follow the Mercury Program with a new initiative called the Gemini Program.

Ku Telemetry Modulator for Suborbital

TBMG-635812/01/2009

A modulator utilizing the Ku-band instead of the usual S-band has been developed to improve transmission rates for suborbital platforms. The unit operates in the 14.5–15.5-GHz band and supports data rates up to 200 Mbps. In order to keep the modulator costs low, the modulator is based on the LCT2 [Low Cost TDRSS (Tracking and Data Relay Satellite System)] Transceiver design, which utilizes a single-board modulator incorporating an Analog Devices quadrature modulator IC, with I&Q [inphase (I) and quadrature (Q)] bandwidths of 70 MHz. A pin-compatible version of the chips with I&Q bandwidths of up to 160 MHz is used to achieve the higher data rates. To support the higher data rate, an LVDS (low-voltage differential signaling) user interface will be incorporated into the modulator board. The LCT2 configuration uses a 1×4 in. (≈2.5×10.2 cm) high-power S-band amplifier module. The new amplifier printed circuit board (PCB) module is replaced with a compact S-band to Ku-band upconverter, with

GlastCam: A Telemetry-Driven Spacecraft Visualization Tool

TBMG-569909/01/2009

Developed for the GLAST project, which is now the Fermi Gamma-ray Space Telescope, GlastCam software ingests telemetry from the Integrated Test and Operations System (ITOS) and generates four graphical displays of geometric properties in real time, allowing visual assessment of the attitude, configuration, position, and various cross-checks. Four windows are displayed: a “cam” window shows a 3D view of the satellite; a second window shows the standard position plot of the satellite on a Mercator map of the Earth; a third window displays star tracker fields of view, showing which stars are visible from the spacecraft in order to verify star tracking; and the fourth window depicts Sun sensor measurements, enabling verification of the solar array deployment state. Each of these windows has telltales showing useful information applicable to each window, such as spacecraft axes, magnetic field vectors, the Sun-pointing direction, and the like. These can be toggled on or off as desired. By

Telemetry-Enhancing Scripts

TBMG-570009/01/2009

Scripts Providing a Cool Kit of Telemetry Enhancing Tools (SPACKLE) is a set of software tools that fill gaps in capabilities of other software used in processing downlinked data in the Mars Exploration Rovers’ (MER) flight and test-bed operations. SPACKLE tools have helped to accelerate the automatic processing and interpretation of MER mission data, enabling non-experts to understand and/or use MER query and data product command simulation software tools more effectively. SPACKLE has greatly accelerated some operations and provides new capabilities.

Aligning a Receiving Antenna Array To Reduce Interference

TBMG-550108/01/2009

A digital signal-processing algorithm has been devised as a means of aligning (as defined below) the outputs of multiple receiving radio antennas in a large array for the purpose of receiving a desired weak signal transmitted by a single distant source in the presence of an interfering signal that (1) originates at another source lying within the antenna beam and (2) occupies a frequency band significantly wider than that of the desired signal. In the original intended application of the algorithm, the desired weak signal is a spacecraft telemetry signal, the antennas are spacecraft-tracking antennas in NASA’s Deep Space Network, and the source of the wide-band interfering signal is typically a radio galaxy or a planet that lies along or near the line of sight to the spacecraft. The algorithm could also afford the ability to discriminate between desired narrow-band and nearby undesired wide-band sources in related applications that include satellite and terrestrial radio communications

More About Reconfigurable Exploratory Robotic Vehicles

TBMG-552508/01/2009

Modular exploratory robotic vehicles that will be able to reconfigure themselves in the field are undergoing development. These vehicles at the initial concept stage were described in “Reconfigurable Exploratory Robotic Vehicles” (NPO-20944), NASA Tech Briefs, Vol. 25, No. 7 (July 2001), page 56. Proposed for use in exploration of the surfaces of Mars and other remote planets, these vehicles and others of similar design could also be useful for exploring hostile terrain on Earth.

Columbus Thermal Hydraulic Operations with US Payloads

2009-01-255507/12/2009

After launch and activation activities, the Columbus module started its operational life on February 2008 providing resources to the internal and external experiments. In March 2008 two US Payloads were successfully installed into Columbus Module: Microgravity Sciences Glovebox (MSG) and a US payload of the Express rack family, Express Rack 3, carrying the European Modular Cultivation System (EMCS) experiment. They were delivered to the European laboratory from the US laboratory and followed few months later by similar racks; Human Research Facility 1 (HRF1) and HRF2. The following paper provides an overview of US Payloads, giving their main features and experiments run inside Columbus on year 2008. Flight issues, mainly on the hydraulic side are also discussed. Engineering evaluations released to the flight control team, telemetry data, and relevant mathematical models predictions are described providing a background material for the adopted work-around solutions.

De Palo, Savino, Passini, Roberto, Quaranta, Albino, Wright, Bruce D.

Biomedical Wireless Ambulatory Crew Monitor

TBMG-515705/01/2009

A compact, ambulatory biometric data acquisition system has been developed for space and commercial terrestrial use. BioWATCH (Bio medical Wireless and Ambulatory Telemetry for Crew Health) acquires signals from bio-medical sensors using acquisition modules attached to a common data and power bus. Several slots allow the user to configure the unit by inserting sensor-specific modules. The data are then sent real-time from the unit over any commercially implemented wireless network including 802.11b/g, WCDMA, 3G.

Communications and Tracking Services Support Near-Earth Missions

TBMG-354702/01/2009

Telemetry, tracking, and command services ITT Corporation White Plains, NY 914-641-2000

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