A feasibility study for an advanced avionics flight test aircraft Final report
Advanced aircraft for flight testing of integrated electronics system for reusable space shuttle
Kidder, R. C.↗
SEARCH · Engineering Papers
Results for “Avionics”
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Overview of the AF Avionics Laboratory reentry electromagnetics program
Radio wave propagation through plasmas studied for communication with hypersonic vehicles during reentry
Robert Rawhouser↗
Space Shuttle Avionics: a Redundant IMU On-Board Checkout and Redundancy Management System
A failure detection and isolation philosophy applicable to multiple off-the-shelf gimbaled IMUs are discussed. The equations developed are implemented and evaluated with actual shuttle trajectory simulations. The results of these simulations are presented for both powered and unpowered flight phases and at operational levels of four, three, and two IMUs. A multiple system checkout philosophy is developed and simulation results presented. The final task develops a laboratory test plan and defines the hardware and software requirements to implement an actual multiple system and evaluate the interim study results for space shuttle application.
Mckern, R. A.↗
STOL terminal area operating systems (aircraft and onboard avionics, ATC, navigation aids)
Operational procedures and systems onboard the STOL aircraft which are required to enable the aircraft to perform acceptably in restricted airspace in all types of atmospheric conditions and weather are discussed. Results of simulation and flight investigations to establish operational criteria are presented.
Burrous, C.↗
Implications of equipping a DC-8-61 fleet with RNAV/two-segment approach avionics
Due to the costs of implementing two-segment approaches with special purpose computers, and the fact that such systems rely on special ground equipment not generally in use today, it is useful to consider the possibility of adding a two-segment approach capability to area navigation (RNAV) systems. The addition of the capability to provide two-segment approach navigation in an RNAV system which already interfaces with the standard instrument landing system is estimated to cost $1430 per aircraft. This includes the cost to add an approach progress display, to make necessary modifications to RNAV software, and to develop special approach plates.
Anderson, E. B.↗
Analysis of technology requirements and potential demand for general aviation avionics systems in the 1980's
The trend for the increasing need for aircraft-in-general as a major source of transportation in the United States is presented (military and commercial aircraft are excluded). Social, political, and economic factors that affect the aircraft industry are considered, and cost estimates are given. Aircraft equipment and navigation systems are discussed.
Cohn, D. M.↗
Space shuttle main engine definition (phase B). Volume 2: Avionics
The advent of the space shuttle engine with its requirements for high specific impulse, long life, and low cost have dictated a combustion cycle and a closed loop control system to allow the engine components to run close to operating limits. These performance requirements, combined with the necessity for low operational costs, have placed new demands on rocket engine control, system checkout, and diagnosis technology. Based on considerations of precision environment, and compatibility with vehicle interface commands, an electronic control, makes available many functions that logically provide the information required for engine system checkout and diagnosis.
Source record↗
Space Tug avionics definition study. Volume 4: Supporting trade studies and analyses
Analyses and trade studies were performed for the evaluation of the most desirable solutions to space tug subsystem requirements. These were accomplished at system, subsystem, and at component levels. The criteria, the candidate options evaluated, the selection process, and the recommended solutions that have been integrated together in the configuration descriptions are reported.
Source record↗
Avionics systems in the management of air transportation
Aspects of aircraft operating systems technology are discussed along with the requirements of the National Airspace System and the system requirements for transport and light aircraft. Attention is given to problems regarding man's role as systems become increasingly complex. It is pointed out that science does not know enough concerning the operation of the human body to provide information for an optimal exploitation of man's unique capabilities as manager of his aircraft.
Berkstresser, B. K.↗
Space shuttle alternate concepts study avionics status review
Explore the source record for details and available documents.
Source record↗
Airways and avionics
Terminal and enroute traffic control are summarized along with visual and radio navigation aids.
Source record↗
Space shuttle orbiter avionics software. Ramp function generator I/O jitter study
The ability of the Ramp Generator to output linear ramp function stimuli to the space shuttle aerosurfaces is determined. Recommendations are included.
Source record↗
Analysis of the survivability of the shuttle (ALT) fault-tolerant avionics system
An extension of the Complementary-Analytic-Simulative Technique (CAST) is presented which is applicable to the Shuttle Data Processing Subsystem (DPS). A two step process was used. The first step provides models, both analytic and simulative, for analysis of the Approach-Landing Test (ALT) configuration. The ALT modeling and analysis are presented. Since CAST had already been shown to be multicomputer systems, the emphasis was placed on extending the CAST concept so it is applicable to computer systems including the multiplicity of input and output devices found in a real-time control system application. The DPS mission-critical survivability for a six-hour mission was determined to be 0.999863 for the Shuttle ALT baseline configuration. Thus it can be said that for ALT, the survivability is adequate. However, the fact that orbiting missions of up to 30 days are planned illustrates the necessity of extending the ALT work to be applicable to OFT and actual mission scenarios. The above analysis led to the evaluation of three selected options which identified two areas of possible improvement. These improvements would result from use of a recovery technique which combines roll ahead with memory copy, and increased TACAN fault detectability.
Source record↗
Analysis of the survivability of the shuttle (ALT fault-tolerant avionics system, appendices
The analytic model program which calculated the baseline parameter data is described along with the input deck setup which includes four groups of input parameters.
Source record↗
Avionics design for reliability bibliography
A bibliography with abstracts was presented in support of AGARD lecture series No. 81. The following areas were covered: (1) program management, (2) design for high reliability, (3) selection of components and parts, (4) environment consideration, (5) reliable packaging, (6) life cycle cost, and (7) case histories.
Source record↗
Space shuttle engineering and operations support. Orbiter to spacelab electrical power interface. Avionics system engineering
The results are presented of an investigation of the factors which affect the determination of Spacelab (S/L) minimum interface main dc voltage and available power from the orbiter. The dedicated fuel cell mode of powering the S/L is examined along with the minimum S/L interface voltage and available power using the predicted fuel cell power plant performance curves. The values obtained are slightly lower than current estimates and represent a more marginal operating condition than previously estimated.
Emmons, T. E.↗
Lockheed L-1101 avionic flight control redundant systems
The Lockheed L-1011 automatic flight control systems - yaw stability augmentation and automatic landing - are described in terms of their redundancies. The reliability objectives for these systems are discussed and related to in-service experience. In general, the availability of the stability augmentation system is higher than the original design requirement, but is commensurate with early estimates. The in-service experience with automatic landing is not sufficient to provide verification of Category 3 automatic landing system estimated availability.
Throndsen, E. O.↗
Shuttle avionics visual display
SAV-D system is composed of display description language (DDL) and its language processor. Language provides for the description of displays in terms of static and variable references for text, special symbols, lines, and circles. SAV-D permits use of high-order English-like language to describe complete displays with increased speed and ease of coding, debugging, and modification. It also allows one to specify static and variable attribute, such as location, flash, dash, character size, and intensity.
Yoshimura, A. A.↗