Flight investigation of methods for implementing noise-abatement landing approaches
Flight tests and simulation of steep noise reducing landing approaches with jet transport
Fry, E. B.↗
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Results for “test approach”
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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A test of the independence of the approach and avoidance gradients.
Test of independence of approach and avoidance gradients using shock-food pairings in rats
Donahoe, J. W.↗
Descent-speed testing of a hazard detection system for safe landing on Mars
In a previous paper we described an approach for testing a prototype system designed to detect hazards during the terminal descent phase of a mission to Mars. The system under development at the Jet Propulsion Laboratory (JPL) utilizes a scanning laser radar and an inertial measurement unit to map the landing zone, identify hazards, and thenguide the vehicle to a safe landing site. The test approach consisted of a placing this system on a rocket sled, accelerating the sled to typical descent speeds, and mapping a simulated Martian terrain. The data would then be processed to identify hazards and locate a safe landing site. Since ref. 1 was written several such tests have been performed. In this paper we provide an update on the testing methodology and we present preliminary results from one of the tests.
hazard↗
Approach and landing test network interface processor interface control document
The design requirements are established for all external or interproject interfaces to the Network Interface Processor located in Building 30 at the Lyndon B. Johnson Space Center, Houston, Texas. In addition to external interfaces, software/hardware and special interfaces are also described.
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Communications and tracking subsystem approach and landing test phase task 501 RF path console acceptance test report
The RF downlink S-band path in the RF path console was tested under quality assurance inspection. The UHF RF paths were also tested. The acceptance test plans, procedures, and results of the acceptance tests are included.
Doland, G. D.↗
Description of a Computer Program Written for Approach and Landing Test Post Flight Data Extraction of Proximity Separation Aerodynamic Coefficients and Aerodynamic Data Base Verification
A computer program written to calculate the proximity aerodynamic force and moment coefficients of the Orbiter/Shuttle Carrier Aircraft (SCA) vehicles based on flight instrumentation is described. The ground reduced aerodynamic coefficients and instrumentation errors (GRACIE) program was developed as a tool to aid in flight test verification of the Orbiter/SCA separation aerodynamic data base. The program calculates the force and moment coefficients of each vehicle in proximity to the other, using the load measurement system data, flight instrumentation data and the vehicle mass properties. The uncertainty in each coefficient is determined, based on the quoted instrumentation accuracies. A subroutine manipulates the Orbiter/747 Carrier Separation Aerodynamic Data Book to calculate a comparable set of predicted coefficients for comparison to the calculated flight test data.
Homan, D. J.↗
Space Shuttle Orbiter Approach and Landing Test Evaluation Report. Captive-Active Flight Test Summary
Captive-active tests consisted of three mated carrier aircraft/Orbiter flights with an active manned Orbiter. The objectives of this series of flights were to (1) verify the separation profile, (2) verify the integrated structure, aerodynamics, and flight control system, (3) verify Orbiter integrated system operations, and (4) refine and finalize carrier aircraft, Orbiter crew, and ground procedures in preparation for free flight tests. A summary description of the flights is presented with assessments of flight test requirements, and of the performance operations, and of significant flight anomalies is included.
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Approach and landing test program status
This paper discusses captive-active tests of the Shuttle Orbiter's landing capability. Tests include: free-flight, in which a flare maneuver was undertaken to evaluate the control stick steering mode; separation, in which the pilot pitches up and rolls at a 20 deg bank angle; up and away flight, to test vehicle handling and stability; 2nd rollout, to test the anti-skid system and braking. Attention is given to bare airframe handling qualities, stressing the role of the pilot in controlling the craft.
Haise, F. W., Jr.↗
USDA Application Test System (ATS) session: The application test system, an approach for technology transfer
There are no author-identified significant results in this report.
David, F. C.↗
Formal verification and testing: An integrated approach to validating Ada programs
An integrated set of tools called a validation environment is proposed to support the validation of Ada programs by a combination of methods. A Modular Ada Validation Environment (MAVEN) is described which proposes a context in which formal verification can fit into the industrial development of Ada software.
Cohen, Norman H.↗
A differential approach to microcomputer test battery development and implementation
The present microcomputer-based performance test battery emphasizes psychometric theory and utility for repeated-measures applications during extended exposure to various environmental stressors. In the menu that has been defined at the current state of this system's development, there are more than 30 'qualified' mental tests which stabilize in less than 10 min and possess test-retest reliabilities greater than 0.7 for a three-minute test/work period. The battery encompasses tests of cognition, information processing, psychomotor skill, memory, mood, etc. Several of the tests have demonstrated sensitivity to chemoradiotherapy, sleep loss, hypoxia, amphetamines, thermal stress, sensory deprivation, altitude, fatigue, and alcohol use. Recommendations are presented for 6-, 12-, and 22-min batteries.
Kennedy, R. S.↗
A new approach to equipment testing
Considerable controversy has arisen during the recent discussions over a new version of the RTCA DO160C/ED 14C Section 22 document at the European Committee for Aviation Electronics. Section 22 is concerned with lightning waveform tests to equipment. Investigations of some of these controversies with circuit analysis and measurements indicate the impedance characteristics required of the transient generators and the possibility of testing to a voltage limit even for current waveforms.
Hardwick, C. J.↗
A hybrid approach to test-analysis-model development for large space structures
The present FEM reduction method for the generation of test-analysis-models (TAMs) in test-analysis correlation addresses contentions that the current modal TAM is hypersensitive to differences between test model shapes and analysis mode shapes, thereby generating large off-diagonal terms within the orthogonality and cross-orthogonality matrices employed in test-analysis mode-shape correlation. A hybrid TAM methodology is accordingly developed which combines the exact representation of the FEM target modes from the modal TAM with the more accurate TAM representation of the residual modes; the superior residual dynamics representation of the hybrid TAM is demonstrated for a detailed representation of a large space structure.
Kammer, D. C.↗
A Novel Approach to Hardness Testing
This paper gives a description of the application of a simple rebound time measuring device and relates the determination of relative hardness of a variety of common engineering metals. A relation between rebound time and hardness will be sought. The effect of geometry and surface condition will also be discussed in order to acquaint the student with the problems associated with this type of method.
Spiegel, F. Xavier↗
Free Enterprise: Contributions of the Approach and Landing Test (ALT) Program to the Development of the Space Shuttle Orbiter
The space shuttle orbiter was the first spacecraft designed with the aerodynamic characteristics and in-atmosphere handling qualities of a conventional airplane. In order to evaluate the orbiter's flight control systems and subsonic handling characteristics, a series of flight tests were undertaken at NASA Dryden Flight Research Center in 1977. A modified Boeing 747 Shuttle Carrier Aircraft carried the Enterprise, a prototype orbiter, during eight captive tests to determine how well the two vehicles flew together and to test some of the orbiter s systems. The free-flight phase of the ALT program allowed shuttle pilots to explore the orbiter's low-speed flight and landing characteristics. The Enterprise provided realistic, in-flight simulations of how subsequent space shuttles would be flown at the end of an orbital mission. The fifth free flight, with the Enterprise landing on a concrete runway for the first time, revealed a problem with the space shuttle flight control system that made it susceptible to pilot-induced oscillation, a potentially dangerous control problem. Further research using various aircraft, particularly NASA Dryden's F-8 Digital-Fly-By-Wire testbed, led to correction of the problem before the first Orbital Test Flight.
Merlin, Peter W.↗
Flyby Anomaly Test Integrating Multiple Approaches (FATIMA)
FATIMA is a mission concept for a small satellite to investigate the flyby anomaly - a possible velocity increase that has been observed in some earlier satellites when they have performed gravitational swingy maneuvers of the earth.
gravitation↗
Compact, Lightweight, Ceramic Matrix Composite (CMC) Based Acoustic Liners for Reducing Subsonic Jet Aircraft Engine Noise
Recent developments have reduced fan and jet noise contributions to overall subsonic aircraft jet-engine noise. Now, aircraft designers are turning their attention toward reducing engine core noise. The NASA Glenn Research Center and NASA Langley Research Center have teamed to investigate the development of a compact, lightweight acoustic liner based on oxide/oxide ceramic matrix composite (CMC) materials. The NASA team has built upon an existing oxide/oxide CMC sandwich structure concept that provides monotonal noise reduction. Oxide/oxide composites have good high temperature strength and oxidation resistance, which could allow them to perform as core liners at temperatures up to 1000C (1832F), and even higher depending on the selection of the composite constituents. NASA has initiated the evaluation of CMC-based liners that use cells of different lengths (variable-depth channels) or effective lengths to achieve broadband noise reduction. Reducing the overall liner thickness is also a major goal, to minimize the volume occupied by the liner. As a first step toward demonstrating the feasibility of our concepts, an oxide/oxide CMC acoustic testing article with different channel lengths was tested. Our approach, summary of test results, current status, and goals for the future are reported.
testing↗
Design and Testing of an Approach to Automated In-Flight Safety Risk Management for sUAS Operations
Explore the source record for details and available documents.
safety management↗