N85-10071*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. ACTIVE CONTROL TECHNOLOGY EXPERIENCE WITH THE SPACE SHUTTLE IN THE LANDING REGIME Final Report Bruce G. Powers Oct. 1984 12 p refs Presented at the AGARD Flight Mech. Panel Symp. on Active Control Systems, Toronto, 15-18 Oct. 1984 (NASA-TM-85910; H-1260; NAS 1.15:85910) Avail: NTIS HC A02/MF A01 CSCL 01C The shuttle program took on the challenge of providing a manual landing capability for an operational vehicle returning from orbit. Some complex challenges were encountered in developing the longitudinal flying qualities required to land the orbiter manually in an operational environmental. Approach and landing test flights indicated a tendency for pilot-induced oscillation near landing. Changes in the operational procedures reduced the difficulty of the landing task, and an adaptive stick filter was incorporated to reduce the severity of any pilot-induced oscillatory motions. Fixed-base, moving-base, and in-flight simulations were used for the evaluations, and in general, flight simulation was the only reliable means of assessing the low-speed longitudinal flying qualities problems. Overall, the orbiter control system and operational procedures have produced a good capability for routinely performing precise landings in a large, unpowered vehicle with a low lift-to-drag ratio. 09 RESEARCH AND SUPPORT FACILITIES (AIR) Author A method and apparatus for producing molecular oxygen in the excited singlet delta oxygen electronic state for use as an excited species reactant in a high energy, continuous-wave, chemically pumped laser. In this invention, small amounts of sodium hydroxide and hydrogen peroxide are continuously mixed, reacted, cooled and then combined with chlorine to form a mixture which is injected into a mixing chamber as very fine droplets to provide an efficient means for effecting a reaction which produces excited molecular oxygen. Author (GRA) N85-10073# Systems Control, Inc., West Palm Beach, Fla. HELIPORT SNOW AND ICE CONTROL METHODS AND GUIDELINES Final Report J. B. McKinley and R. B. Newman Aug. 1984 61 p refs (Contract DTFA01-80-C-10080) (DOT/FAA-PM-84-22) Avail: NTIS HC A04/MF A01 Guidelines for snow and ice control on heliports are presented for the purpose of both enhancing the operational utility of heliports, and employing the unique capabilities of the rotorcraft to the maximum extent. These guidelines consider manual methods of snow and ice control such as plowing and chemical application, and automated methods through pavement heating systems. Cost and design considerations are provided for each system. Benefit/ cost decision guidelines are provided with estimated annual operating cost data for 32 U.S. cities, and six snow and ice control methods. In addition, selection guidelines provide a methodology to assist heliport planners and designers with the selection of the most appropriate snow and ice control system. Author N85-10074*# National Aeronautics and Space Administration. Ames Research Center, Moffett Field, Calif. YO-3A ACOUSTICS RESEARCH AIRCRAFT SYSTEMS MANUAL J. L. Cross Jul. 1984 38 p (NASA-TM-85968; A-9776; NAS 1.15:85968) Avail: NTIS HC A03/MF A01 CSCL 14B The flight testing techniques, equipment, and procedures employed during air-to-air acoustic testing of helicopters using the NASA YO-3A Acoustic Research Aircraft are discussed. The research aircraft instrumentation system is described as well as hardware installation on the test aircraft and techniques used during the tests. Emphasis is placed on formation flying, position locations, test matrices, and test procedures. M.A.C. N85-10075# National Aerospace Lab., Tokyo (Japan). Seigou Nakamura, Koichi Suzuki, Masataka Shirai, Akira Koike, Avail: NTIS HC A05/MF A01 The current data processing system of the NAL 2m x 2m Transonic Wind Tunnel is described. The system is based on dual ECLIPSE S/140 processors with a core memory of 128 KW x 2 at 16 bits/word. An outline of the main processing stages through which the test data cascade is first given, and then a description is given of the way in which force and moment data as well as pressure and temperature data are collected, processed, stored and displayed at each processing stage. Part of the hardware system used for the test data acquisition is also described when thought helpful in delineating the process of data reduction. Author N85-10076# Naval Civil Engineering Lab., Port Hueneme, Calif. HANGAR DESTRATIFICATION INVESTIGATION Technical Note, FY82 - FY83 J. Ashley Apr. 1984 42 p (AD-A145049; NCEL-TN-1692) Avail: NTIS HC A03/MF A01 CSCL 13/1 Measurements made in military hangars indicated that stratification, the existence of a layer of hot air in a structure's overhead, is a typical phenomenon. Five destratification concepts (three commercial and two Navy-developed) were evaluated to determine the effectiveness and the adaptability of each concept for hangar applications. Only the Navy-developed concepts were found practical for hangar applications. Destratifier design and application guidelines were developed and are presented in the report. GRA N85-10077# Strategic Air Command, Offutt AFB, Nebr. Aircraft AIRCRAFT CHOCKS Final Engineering Report (AD-A145135; SAC/LGME-P-425) Avail: NTIS HC A04/MF A01 CSCL 01/5 A tire chock is the most common means to restrain an aircraft while it is parked. However, during certain ground operations, the chock is unable to restrain the aircraft. An analysis was done on the restrain capabilities of the current chocks used for the B-52 and -135 aircraft. From this analysis, safety factors and operating limitations were established. In addition, criteria was developed for chock improvements as they are related to the various engineers on the B-52G, B-52H, KC-135A, KC-135E and KC-135R. Author (GRA) N85-10078# Seville Training Systems Corp., Pensacola, Fla. TRAINING EFFECTIVENESS EVALUATION AND UTILIZATION DEMONSTRATION OF A LOW COST COCKPIT PROCEDURES TRAINER Final Report, Jun. 1978 - Jul. 1982 P. W. Caro, W. E. Corley, W. D. Spears, and A. S. Blaiwes Jun. 1984 84 p (Contract N61339-78-C-0113) (AD-A145179; SEVILLE-TR-83-25; NAVTRAEQUIPC-78-C-0113-3) Avail: NTIS HC A05/MF A01 CSCL 05/9 The purpose of this study was to evaluate a prototype low cost cockpit procedures trainer (LCCPT) for the SH-3H aircraft. During Phase I of the study, pilots trained in the LCCPT were compared in subsequent SH-3H performance with a historical control group trained in Device 2C44, a much more expensive conventional cockpit procedures trainer. The LCCPT and 2C44 groups performed equally well in the SH-3H. For tasks practiced in the LCCPT, transfer of device training to SH-3H performance was 95 percent as estimated through a curve fitting technique. During Phase II, the adaptability of the LCCPT to student-directed instruction was evaluated. The students developed required levels of proficiency, and they appeared able to identify weaknesses in their performance and to direct their practice toward overcoming them. N85-10079# DCS Corp., Alexanderia, Va. GRA ANALYSIS OF ON-BOARD CIG (COMPUTER IMAGE GENERATOR) APPLICATIONS FOR AIRCREW TRAINING Final Technical Report, 1 Jul. 1983 - 30 Apr. 1984 D. B. Coblitz Orlando, Fla. NTEC Apr. 1984 107 p (Contract N60921-82-D-A075) (AD-A145214; DCS-LT0010; NAVTRAEQUIPC-IH-353) Avail: NTIS HC A06/MF A01 CSCL 09/2 This report presents the results of a study examining the potential use of on-board Computer Image Generation (CIG) for Naval aircrew training. Three criteria determine whether on-board CIG may be applied to a particular training task. The displays available in the cockpit must be suitable, generation of adequate imagery must be feasible, and the training problem must be appropriate. To determine each of these factors, surveys in each area were conducted. An analysis of the survey results is presented. The development and use of on-board CIG based training systems was concluded to be feasible and would enhance operational readiness. The report includes specific recommendations as regards training tasks that would benefit most from application of on-board CIG and would also be technically feasible. Three approaches to such application are: Utilization of existing and planned on-board hardware in training modes; Development of a training computer image generator as a pod to be mounted temporarily on a weapon station for training missions; Long term merging of training and tactical considerations in the development phase of a new weapon systems and avionics. All three approaches should be pursued in parallel. Author (GRA) (approximately 60 bombing runs) and the remainder had none. The pilots were given 80 training trials in the simulator under specific training conditions. Three factors were manipulated in training; those being level of detail in the visual scene, number of visual scenes, and augmented feedback in the form of artificial visual guidance. Differential transfer effects were assessed on the basis of performances on 30 transfer trials in the simulator. The transfer phase used a variety of visual scenes and varying levels of detail but no augmented feedback. All subjects flew the same set of conditions in the transfer phase. The scene-content issue is one of the most crucial for modern training simulators. These data are the first to show that scene content affects learning of flight skills. Simulator training of air-to-ground attack should be conducted with visual scenes that have features similar to those of our landscape. Variety was raised as a training issue. Augmented feedback proved to be helpful to inexperienced and more experienced pilots with their dive altitude control. It appears to be useful at least for primary and intermediate instruction. There is no evidence in this report that pilots with no experience in air-to-ground attack should be treated differently during training to pilots who have some experience in air-to-ground attack. GRA N85-10081# Department of the Air Force, Washington, D.C. AIRCRAFT CABIN PRESSURIZATION CONTROL SYSTEM TESTER Patent Application K. J. Werling, inventor (to Air Force) Filed 19 Jun. 1984 16 p (AD-D011225; US-Patent-Appl-SN-622047) Avail: NTIS HC A02/MF A01 CSCL 14/2 This patent application discloses an aircraft cabin pressure control system tester, including a first tester component having a vacuum pressure-sensing gage which indicates the static atmosphere in inches of Hg and a second tester component having a differential pressure-sensing gage which indicates the pressure/ vacuum in inches of H2O. When the components of the tester are connected respectively in communication with lines connecting the controller of the system to static atmosphere ports and a pressure regulator valve, the tester can be used to determine which one, if any, of the pressure controller, air compressor and regulator valve of the pressure control system is faulty. GRA 12 ASTRONAUTICS (GENERAL) For extraterrestrial exploration see 91 Lunar and Planetary Exploration. N85-10082# Science Council of Japan, Tokyo. National Committee on Space Research. SPACE RESEARCH IN JAPAN. NATIONAL REPORT Atsuhiro Nishida, ed., Yoshiaki Ogawara, ed., Mikio Shimizu, ed., and Kazuo Takayanagi, ed. Inst. of Space and Astronautical Science May 1984 83 p refs Presented at the 25th Meeting of the ICSU Comm. on Space Res., Graz, Austria, 25 Jun. - 7 Jul. 1984 Original contains color illustrations Avail: NTIS HC A05/MF A01 Satellite observations; rocket observations; SEPAC (space experiments with particle accelerators); balloon observations; scientific activities in space research; and bibliography of space science are discussed. For individual titles, see N85-10083 through N85-10086. In its Space Res. in Japan May 1984 p 25-39 (For primary document see N85-10082 01-12) Avail: NTIS HC A05/MF A01 The Institute of Space and Astronautical Science (ISAS) sounding rocket experiments were carried out during the periods of August to September, 1982, January to February and August to September, 1983 and January to February, 1984 with sounding rockets. Among 9 rockets, 3 were K-9M, 1 was S-210, 3 were S-310 and 2 were S-520. Two scientific satellites were launched on February 20, 1983 for solar physics and on February 14, 1984 for X-ray astronomy. These satellites were named as TENMA and OHZORA and designated as 1983-011A and 1984-015A, respectively. Their initial orbital elements are also described. A payload recovery was successfully carried out by S-520-6 rocket as a part of MINIX (Microwave Ionosphere Non-linear Interaction Experiment) which is a scientific study of nonlinear plasma phenomena in conjunction with the environmental assessment study for the future SPS project. Near IR observation of the background sky shows a more intense flux than expected possibly coming from some extragalactic origin and this may be related to the evolution of the universe. US-Japan cooperative program of Tether Experiment was done on board US rocket. Author N85-10085# Science Council of Japan, Tokyo. SEPAC (SPACE EXPERIMENTS WITH PARTICLE ACCELERATORS) In its Space Res. in Japan May 1984 p 40-44 (For primary document see N85-10082 01-12) Avail: NTIS HC A05/MF A01 Space Experiments with Particle Accelerators: SEPAC was carried out by the Spacelab-1 (STS-9) on November 28 to December 8, 1983, which was one of the first international cooperative scientific experiments using the Space Shuttle. The purpose of SEPAC experiment is to carry out active and interactive experiments on and in the Earth's upper atmosphere and magnetosphere, outer space being used as a gigantic laboratory to perform the variety of experiments of space plasma physics. In particular, the following were immediate scientific objectives to study: vehicle charge build up and its neutralization; beam plasma physics; and beam atmosphere interactions. N85-10086# Science Council of Japan, Tokyo. BALLOON OBSERVATIONS Author C02 In its Space Res. in Japan May 1984 p 45-51 (For primary document see N85-10082 01-12) Avail: NTIS HC A05/MF A01 Seventeen balloon observations were carried out in May to June and September to October, 1982, and eight observations were made in August to Septem.ber in 1983. These balloons were launched from the Sanriku Balloon Center (39.2 N, 141.8 E), in Japan, which was established in 1971. The flight operations were conducted by the balloon team of the institute of Space and Astronautical Science. Besides these observations, five balloon observations were carried out at Alice Springs in May, 1983, in Collaboration with Australian group. Two flights were performed at the time of eclipse, June, 1983, in Indonesia in collaboration with balloon groups in Lapan, Indonesia. Balloon observations were made in the fields of astrophysics, cosmic ray physics, geophysics and atmospheric science. The observations were made for scientists of other institutions and universities as well as for the research groups of ISAS. Author N85-10088# Committee on Commerce, Science, and Transportation (U. S. Senate). SOVIET SPACE PROGRAMS, 1976-1980, WITH SUP- Marcia S. Smith, Alfred Hellman, and Christopher H. Dodge Soviet manned space programs are discussed. The Soviet quest for a permanently manned presence in space is reviewed. Also included is information concerning the physiological and psychological findings to the extended duration of Soviet manned flights. R.J.F. preliminary design studies to proceed with a common and consistent set of natural environment criteria requirements. B.W. 15 LAUNCH VEHICLES AND SPACE VEHICLES Includes boosters; manned orbital laboratories; reusable vehicles; and space stations. N85-10090 Bayerische Akademie der Wissenschaften, Munich (West Germany). Geodaetische Kommission. DIAGNOSIS AND THERAPY OF GEODETIC SATELLITE NETWORKS OF DOPPLER TYPE Ph.D. Thesis - Stuttgart Univ. [DIAGNOSE UND THERAPIE VON GEODAETISCHEN SATELLITENNETZEN VON TYP DOPPLER] Alfred Kleusberg 1984 111 p refs In GERMAN (Ser-C-293; ISBN-3-7696-9343-4; ISSN-0065-5325) Copyright. Avail: Issuing Activity The different sources of errors influencing the accuracy of geodetic point determination are localized and qualitatively described in an analysis of Doppler satellite networks. The error quantities for absolute and relative coordinates determined by Doppler measurements are given. Possibilities to enhance the accuracy in the reference system, ephemerides determination, and evaluation of Doppler measurements are discussed. For ephemerid determination, the rotational and translational equations of motions to be integrated for satellites of any structure are given. The gravitational part of the force acting on satellites is described by a representation of the gravitational potential using Cartesian basic functions. The models for Doppler measurement evaluation are based on a free Doppler network compensation. The a priori knowledge about ephemerides, refraction, etc., is taken into account in this compensation. Author (ESA) The potential of the observation equipment in remote sensing satellites is described. United States meteorology, land use and oceanography satellites and the major US Earth observation programs are listed. Imaging satellite systems are described such as: visible light and near infrared, thermal IR window, and microwave window. It is concluded that a geometrical resolution between 10 and 40 m can be expected. In order to reduce the data flow from the satellite system the input side of the system (the object-sensor interaction) has to be known. Satellites with synthetic aperture radar are increasingly important, but satellites can never fully replace observations with aircraft and drones. Author (ESA) N85-10095# Massachusetts Inst. of Tech., Cambridge. Current concepts for directed-energy ballistic missile defense in space are described and assessed. Its purpose is to provide Members of Congress, their staffs, and the public with a readable introduction to the so-called Star Wars technologies that some suggest might form the basis of a future nationwide defense against Soviet nuclear ballistic missiles. Since these technologies are a relatively new focus for U.S. missile defense efforts, little information about them has been readily available outside the expert community. Author (GRA) N85-10083# Science Council of Japan, Tokyo. In its Space Res. in Japan May 1984 p 3-24 (For primary document see N85-10082 01-12) Avail: NTIS HC A05/MF A01 N85-10084# Science Council of Japan, Tokyo. ROCKET OBSERVATIONS In its Space Res. in Japan May 1984 p 25-39 (For primary document see N85-10082 01-12) Avail: NTIS HC A05/MF A01 16 SPACE TRANSPORTATION Includes passenger and cargo space transportation, e.g., shuttle operations; and rescue techniques. For related information see also 03 Air Transportation and Safety and 85 Urban Technology and Transportation. N85-10096* Chrysler Corp., New Orleans, La. TRACKING ICAN AERODYNAMICS LABORATORY LOWSPEED WIND TUNNEL USING 0.0405-SCALE SPACE SHUTTLE ORBITER MODEL 16-0 (TEST OA-309) B. A. Marshall (Rockwell International Corp., Downey, Calif.) and M. E. Nichols (Rockwell International Corp., Downey, Calif.) Sep. 1984 118 p ref (Contract NAS9-16283) (NASA-CR-167692; NAS 1.26:167692; DMS-DR-2519) Avail: NTIS HC A06 CSCL 22B An experimental investigation (Test OA-309) was conducted using 0.0405-scale Space Shuttle Orbiter Model 16-0 in the North American Aerodynamics Laboratory 7.75 x 11.00-foot Lowspeed Wind Tunnel. The primary purpose was to locate and study any flow conditions or vortices that might have caused damage to the Advanced Flexible Reusable Surface Insulation (AFRSI) during the Space Transportation System STS-6 mission. A secondary objective was to evaluate vortex generators to be used for Wind Tunnel Test OS-314. Flowfield visualization was obtained by means of smoke, tufts, and oil flow. The test was conducted at Mach numbers between 0.07 and 0.23 and at dynamic pressures between 7 and 35 pounds per square foot. The angle-of-attack range of the model was -5 degrees through 35 degrees at 0 or 2 degrees of sideslip, while roll angle was held constant at zero degrees. The vortex generators were studied at angles of 0, 5, 10, and 15 degrees. Author N85-10401*# Rockwell International Corp., Downey, Calif. STRUCTURAL ANALYSIS OF THE SPACE SHUTTLE ORBITER Henry R. Grooms and James H. Johnson, Jr. In NASA. Langley Research Center Res. in Struct. and Dyn., 1984 Oct. 1984 p 369-383 refs (For primary document see N85-10377 01-39) Avail: NTIS HC A18/MF A01 CSCL 22B 17 SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING Includes telemetry; space communications networks; astronavigation; and radio blackout. For related information see also 04 Aircraft Communications and Navigation and 32 Communications. N85-10097# National Bureau of Standards, Boulder, Colo. Electromagnetic Fields Div. AN ERROR ANALYSIS FOR THE USE OF PRESENTLY AVAILABLE LUNAR RADIO FLUX DATA IN BROADBEAM ANTENNASYSTEM MEASUREMENTS William C. Daywitt Feb. 1984 39 p refs (PB84-218361; NBS-TN-1073) Avail: NTIS HC A03/MF A01; also available SOD CSCL 09F Simple, precise expressions for lunar diameter, average brightness temperature, flux density, and shape factor are presented. An analysis of the relationship between these parameters and corresponding errors are included. For broadbeam (HPBW > d) antennas, results show that flux density and shape factor can be determind with errors less than 13 percent and 0.4 percent respectively at frequencies below 10 GHz. Extension of the analysis to higher frequencies is indicated. Author (GRA) 18 SPACECRAFT DESIGN, TESTING AND A sequence of single axismodels and a series of reduced state linear observers of minimum order are used to reconstruct inaccessible variables pertaining to the modular attitude control of a rigid body flexible suspension model of a flexible spacecraft. The single axis models consist of two, three, four, and five rigid bodies, each interconnected by a flexible shaft passing through the mass centers of the bodies. Modal damping is added to each model. Reduced state linear observers are developed for synthesizing the inaccessible modal state variables for each modal model. M.A.C. N85-10099# Spectra Research Systems, Inc., Huntsville, Ala. (AD-A145080; SRS-TR84-015-CU40; AFRPL-TR-84-040) Avail: NTIS HC A05/MF A01 CSCL 13/8 Very large and accurate reflective surfaces are required for future space applications such as solar rocket propulsion, radar, laser power transmission and relay, solar energy collection, telescopes, and others. Present techniques used to construct highly accurate reflectors are limited in application to diameters of a few meters. Metallized thin film membranes have the potential to satisfy the requirements of most future applications with minimum weight systems. The objective of this research was to identify materials, construction and control techniques to improve the surface accuracy of inflatable reflectors. Film joining and forming, support structure design options, surface accuracy measurement system options and electrostatic surface configuration control techniques were investigated. Prototype models were designed, built, and tested to demonstrate film forming techniques, support structure deployment, and electrostatic membrane configuration control utilizing segmented charge plates and an electron gun. A laser ray-tracing technique was employed to measure surface accuracies. These demonstrations verified the feasibility of the concepts. Author (GRA) N85-10872# Committee on Appropriations (U. S. Senate). In its Department of Housing and Urban Development and Certain Independent Agencies Appropriations for Fiscal Year 1985, Pt. 2 1984 p 1233-1241 Washington GPO (For primary document see N85-10870 01-84) Avail: Committee on Appropriations 19 SPACECRAFT INSTRUMENTATION For related information see also 06 Aircraft Instrumentation and 35 Instrumentation and Photography. No abstracts in this category. |