MARINER VENUS '62 FLIGHT TELECOMMUNICATION SYSTEM
Mariner /venus 62/ flight telecommunication system for data transmission and trajectory determination
DATA TRANSMISSION↗
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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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Super Loki Dart meteorological rocket system Final report
Design and flight test data on Super Loki Dart sounding rocket system for obtaining high altitude wind profiles with low cost rocket vehicle and radar-reflective chaff payload
Bollermann, B.↗
Research directed toward determination of advanced avionics technology for a V/STOL aircraft program Final report
Flight control system design data and helicopter simulation data for V/STOL aircraft advanced avionic technology
Source record↗
Central nervous, cardiovascular and metabolic data of a Macaca nemestrina during a 30-day experiment.
Central nervous, cardiovascular and metabolic data of Macaca nemestrina during simulated Biosatellite flight, testing data acquisitions systems
Adey, W. R.↗
Telemetry and communications to Apollo flight controllers
Telemetry and communications roles in Apollo flight operations, describing data system management
Glines, A.↗
A method for determining the response of space shuttle to atmospheric turbulence. Volume 2: Computer program description and usage instructions
A description is given of a computer program which calculates the response of an elastic aerospace vehicle to random and discrete turbulence. The program uses vibration modes as generalized coordinates. Inputs to the program include modal information, generalized aerodynamic forces, flight data, stability augmentation system description, and description of the disturbing function. Program outputs include tabulations of the ratio of root-mean-square response to root-mean-square turbulence and response upward zero crossings per second, and SC4020 plots of transfer functions, response power spectral densities, and Nyquist stability traces.
Huntington, R.↗
Flight study of a vehicle operational status and monitoring system
An analog onboard monitoring system was installed on a YF-12 airplane as the first phase of a program to monitor the engine inlet and portions of the airplane's electrical and fuel management subsystems in flight. The system provided data which were considered to form a suitable base for diagnostic test logic and decision criteria for the rest of the program. The data were also adequate for the purpose of maintaining the engine inlet and identifying malfunctions within it. The investigation showed that the requirements of an onboard monitoring system should be considered during the original design of the system to be monitored.
Love, J. E.↗
Equations for determining aircraft motions for accident data
Procedures for determining a comprehensive accident scenario from a limited data set are reported. The analysis techniques accept and process data from either an Air Traffic Control radar tracking system or a foil flight data recorder. Local meteorological information at the time of the accident and aircraft performance data are also utilized. Equations for the desired aircraft motions and forces are given in terms of elements of the measurement set and certain of their time derivatives. The principal assumption made is that aircraft side force and side-slip angle are negligible. An estimation procedure is outlined for use with each data source. For the foil case, a discussion of exploiting measurement redundancy is given. Since either formulation requires estimates of measurement time derivatives, an algorithm for least squares smoothing is provided.
Bach, R. E., Jr.↗
Stability and control flight test results of the space transportation system's orbiter
Flight testing of the Space Shuttle Orbiter is in progress and current results of the post-flight aerodynamic analyses are discussed. The purpose of these analyses is to reduce the pre-flight aerodynamic uncertainties, thereby leading to operational certification of the Orbiter flight envelope relative to the integrated airframe and flight control system. Primary data reduction is accomplished with a well documented maximum likelihood system identification techniques.
Culp, M. A.↗
Interface control document between the NASA Goddard Space Flight Center (GSFC) and Department of Interior EROS Data Center (EDC) for LANDSAT-D. Thematic mapper high resolution 241 mm film
The 241 mm photographic product produced by the Goddard Space Flight Center Data Management System for LANDSAT-D is described. Film type and format, image dimensions, frame ID, gray scale, resolution patterns, registration marks, etc. are addressed.
Source record↗
ACCESS (Assembly Concept for Construction of Erectable Space Structure) - A Shuttle flight experiment
ACCESS is a planned Shuttle flight experiment to assess the potential of an on-orbit construction concept designed for efficient manual assembly of a space truss. The experiment, which is scheduled for launch November 27, 1985, on the Space Transportation System (STS) flight 61-B, uses two astronauts secured in fixed foot restraints located in the Shuttle cargo bay to assemble a 45-foot long aluminum truss beam from 93 tubular struts and 33 nodal joints. Neutral buoyancy simulations of the flight experiment indicate the truss can be assembled in less than thirty minutes. Structural assembly, structural repair, flexible cable attachment and manual manipulation of the truss is also planned for the experiment using an astronaut secured in the Manipulator Foot Restraint attached to the Remote Manipulator System arm. Flight assembly data will be generated for correlation of the neutral buoyancy ground test data. This paper describes the ACCESS flight experiment and presents results of the neutral buoyancy development and training tests.
Heard, W. L., Jr.↗
Implementation and flight-test of a multi-mode rotorcraft flight-control system for single-pilot use in poor visibility
A flight investigation was conducted to evaluate a multi-mode flight control system designed according to the most recent recommendations for handling qualities criteria for new military helicopters. The modes and capabilities that were included in the system are those considered necessary to permit divided-attention (single-pilot) lowspeed and hover operations near the ground in poor visibility conditions. Design features included mode-selection and mode-blending logic, the use of an automatic position-hold mode that employed precision measurements of aircraft position, and a hover display which permitted manually-controlled hover flight tasks in simulated instrument conditions. Pilot evaluations of the system were conducted using a multi-segment evaluation task. Pilot comments concerning the use of the system are provided, and flight-test data are presented to show system performance.
Hindson, William S.↗
Development and flight test of a precision autohover capability for tactical rotorcraft
This paper describes the implementation of an automatic position-hold system in the NASA/Army CH47B variable-stability research helicopter. The test helicopter is briefly described, and a detailed documentation is given of the position-measurement system. The control system design model and the design procedure are described, and flight-test data describing overall system performance in strong winds are presented.
Hindson, W. S.↗
Airborne observations of electric fields around growing and decaying cumulus clouds
Airborne electric field data were gathered in an atmospheric electrification study near Cape Canaveral, FL. A Learjet 36A was instrumented with eight electric field meters (mills) and five different particle probes. The local electric field enhancements at each field mill site were determined under lab conditions and verified using in-flight data. The overdetermined system of eight equations (one for each field mill) was solved using a weighted least squares algorithm to compute the magnitude and direction of the ambient electric field. The signal processing system allowed the measured data to be expressed in terms of earth coordinates, regardless of the attitude of the aircraft. Thus, it was possible to take maximum advantage of the Learjet's speed and maneuverability in studying the electric field structure in the vicinity of the clouds. Data gathered while circling just outside the boundary of a growing cumulus cloud show a nonsymmetric pattern of electric field strength. Field intensity grew rapidly over a period of less than 10 minutes. The observed direction of the ambient electric field vector can be explained by an ascending motion of the charge centers of a classic tripole model of a thunderstorm.
Giori, K. L.↗
Flight performance of a Shuttle-based image motion compensation system for the Ultraviolet Imaging Telescope
The design of the Ultraviolet Imaging Telescope (UIT) Image Motion Compensation System developed for the Columbia's Astro-1 mission is described, and the performance improvements derived through the use of this system are discussed. Flight data are presented, demonstrating the superb image stability achieved by UIT resulting in outstanding scientific data returns.
Deily, John J.↗
A graphical weather system design for the NASA transport systems research vehicle B-737
A graphical weather system was designed for testing in the NASA Transport Systems Research Vehicle B-737 airplane and simulator. The purpose of these tests was to measure the impact of graphical weather products on aircrew decision processes, weather situation awareness, reroute clearances, workload, and weather monitoring. The flight crew graphical weather interface is described along with integration of the weather system with the flight navigation system, and data link transmission methods for sending weather data to the airplane.
Scanlon, Charles H.↗
Dynamics modeling for ERBS attitude propagation
The development and evaluation of a model of the Earth Radiation Budget Satellite (ERBS) attitude dynamics for use in attitude determination is described. Attitude rates for the three axis stabilized spacecraft are derived analytically from Euler's equation using modeled disturbance torques and telemetered flight data from control system actuators for computation of the control torques. The modeled rates are used for attitude propagation in a batch least squares attitude estimation algorithm originally designed to use onboard gyro measurements of attitude motion. The capabilities for near fine attitude determination without gyros is important for operational attitude ground support of the aging ERBS spacecraft as two out of three gyro axes have failed. The accuracy of this method of dynamic propagation is strongly dependent on the quality and availability of control system telemetry data. Detailed disturbance torque models are also necessary to accurately model attitude rates. Even with the relatively coarse ERBS control system telemetry, accuracy to within 0.2 deg of gyro propagated reference attitudes is achieved.
Harvie, E.↗
Extracting a representative loading spectrum from recorded flight data
One of the more important ingredients when computing the life of a structure is the loading environment. This paper describes the development of an aircraft loading spectrum that closely matches the service experience, thus allowing a more accurate assessment of the structural life. The paper outlines the flight loads data collection system, the procedures developed to compile and interpret the service records and the techniques used to define a spectrum suitable for structural life analysis. The areas where the procedures were tailored to suit the special situation of the USAF B-1B bomber are also discussed. the results of the methodology verification, achieved by comparing the generated spectra with the results of strain gage monitoring during service operations, are also presented.
Denyer, Anthony G.↗