| 出版: | Washington, D.C. : U.S. Naval Oceanographic Office |
| 出版: | Washington, D. C. : U.S. Dept. of Commerce, National Bureau of Standards ; U.S. Govt. Print. Off. |
| 附註: | "CODEN: NBTNA." |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 出版: | Washington : U.S. Naval Oceanographic Office |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 13). An analysis of the flight motions of the Reentry F spacecraft was made by using a combination of a force method and an application of the angular-rate solution of the linearized equations of motion since a trim buildup due to flight-induced asymmetries introduced an error into the ordinarily determined angle of attack. The analysis revealed that the spacecraft had little or no asymmetries prior to and during pitch-roll resonance. However, as the spacecraft emerged from resonance, a slight trim angle of attack was noted which shortly thereafter experienced a reversal in orientation and a subsequent rapid growth in the same general direction to a maximum of 0.87 (degrees). |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 24-26). Boundary layer transition on nose cones at hypersonic speeds. |
| 出版: | New York, N.Y. : New York University, School of Engineering and Science, Dept. of Meteorology and Oceanography |
| 出版: | Corvallis, Or. : U.S. Dept. of the Interior, Federal Water Quality Administration, Northwest Region, Pacific Northwest Water Laboratory |
| 出版: | Washington, D.C. : United States Dept. of the Interior, U.S. Fish and Wildlife Service, Bureau of Commercial Fisheries |
| 附註: | "June 1970." Bibliography: p. 107-108 |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 附註: | "Serial no. 91-75." |
| 出版: | Washington : U.S.Govt. Print. Off. |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 附註: | "Serial 91-76." Bibliography: p. 140-141 |
| 出版: | Washington, D.C. : Joint Publications Research Service |
| 附註: | "TRANSDEX 8409-0185-2"--Cover. "JPRS 48753." "4 September 1969." "Research & Microfilm Publications"--P. preceding t.p. Includes bibliographical references. Photocopy.New York, N.Y. :CCM Information Corp.,[197-?]18 cm. |
| 出版: | Boulder, Colo. : Environmental Research Laboratories. |
| 附註: | Includes also various numbered subseries. Includes revisions of some numbers issued under earlier title. |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | "L-1077." "L-7002." "NASA TN D-5796." "June 1970." Includes bibliographical references (p. 15). A 40-foot-nominal-diameter (12.2-meter) modified ringsail parachute was flight tested as part of the NASA Supersonic High Altitude Parachute Experiment (SHAPE) program. The 41-pound (18.6-kg) test parachute system was deployed from a 239.5-pound (108.6-kg) instrumented payload by means of a deployment mortar when the payload was at a Mach number of 2.95 and a free-stream dynamic pressure of 9.2 lb/sq ft (440 N/m²). The parachute deployed properly with the canopy inflating to a near full open condition followed immediately by a partial collapse of the canopy and subsequent oscillations of the frontal area until the system had decelerated to a Mach number of about 1.5. The parachute then attained an inflated shape that provided full drag area. During the supersonic part of the test, the average axial-force coefficient C A ,₀ varied from a minimum of about 0.24 at a Mach number of 2.7 to a maximum of 0.54 at a Mach number of 1.1. During descent under subsonic conditions, the average effective drag coefficient was 0.62 and parachute-payload oscillation angles averaged about ±10⁰ with excursions to ±20⁰.--P. [i]. Also available online in PDF and Quicktime movie format from NASA Technical Reports Server Web site. Sponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under709-12-00-01 |
| 出版: | Oak Ridge, Tenn. : Oak Ridge National Laboratory |
| 附註: | Operated by Union Carbide Corporation for the U.S. Atomic Energy Commission. "Note: This work partially funded by Defense Atomic Support Agency under subtask PEO8001." "September 1970." Includes bibliographical references (p. 231-232). The MORSE code is a multipurpose neutron and gamma-ray transport Monte Carlo code. Through the use of multigroup cross sections, the solution of neutron, gamma-ray, or coupled neutron-gamma-ray problems may be obtained in either the forward or adjoint mode. Time dependence for both shielding and criticality problems is provided. General three-dimensional geometry, as well as specialized one-dimensional geometry descriptions, may be used with an albedo option available at any material surface. A detailed discussion of the relationship between forward and adjoint flux and collision densities, as well as a detailed description of the treatment of the angle of scattering, is given in the appendices. Logical flow charts for each subroutine add to the understanding of the code. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce] |
| 附註: | Prepared at Goddard Space Flight Center. "September 1970."--Cover. Major NASA subject terms: Attitude control, digital computers, onboard equipment, spacecraft control, strapdown inertial guidance, algorithms, OAO, slewing, spacecraft stability. Includes bibliographical references (p. 13). A strapdown inertial reference system and an onboard digital computer can be used to change the attitude of a spacecraft over large angles in an arbitrary direction. A study was conducted with an advanced Orbiting Astronomical Observatory (OAO) using a three-axis control law previously proven globally stable. The control system can reorient the spacecraft to an arbitrary inertial attitude with a single command by operating the three momentum wheels simultaneously. Reorientation, therefore, becomes a simple extension of a hold or pointing mode. The time required for reorientation with this system is considerably shorter than the time required for a series of single-axis slews. The spacecraft attitude and control law are continuously updated by the onboard computer's using information provided by the strapdown inertial reference system. The use of a computer and inertial reference system with characteristics of systems presently under development demonstrates the feasibility of orientation with such a reference system. The basic system is not limited to the OAO but may be adapted for other three-axis-stabilized spacecraft. |
| 出版: | Washington, D.C. : [Springfield, Va. : National Aeronautics and Space Administration ; For sale by the Clearinghouse for Federal Scientific and Technical Information |
| 附註: | Prepared at Langley Research Center. "February 1970." Cover title. Includes bibliographical references (p. 13). The composite body consisted of a spherical nose segment, a delta-slab upper surface with blunt leading edges, wedge sides, and a conical lower surface. The tests were conducted both with and without roughness on the model for a range of angle of attack up to 400. Included is a complete tabulation of the experimental heatii rates and a discussion of the more significant findings. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 23). Three displays were evaluated on a piloted simulator, each of which provided information which could be used in thrust management. The three displays were (1) rate of change of speed, (2) potential flight-path angle, and (3) potential rate of climb. Results are presented in the form of time histories, histograms, and pilot comments. The results include comparisons of flight-path and speed control and throttle activity with and without each display and pilot comments. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and technical Information, Springfield, Va. 22151] |
| 附註: | Includes bibliographical references (p. 17). An investigation was conducted to improve the accuracy in calculating pressure distributions for various tension-shell decelerator shapes and to evaluate the effects on derived shapes resulting from the application of different pressure distributions. Pressure distributions given by Newtonian and integral-relation theory were each used to derive tension-shell shapes. Experimental pressure distributions were obtained from two windtunnel models - one model shape was derived by using a Newtonian pressure distribution and the other shape was derived by using an integral-relation pressure distribution for a Mach number of 3.0 - and were compared with theoretical pressure distributions. The tests were conducted at a Mach number of 3.0, at zero angle of attack, and at a Reynolds number of 10.4 X 106 based on maximum model diameter. Tension-shell shapes were also derived by using the experimental pressure distributions and were compared with both the Newtonianderived shape and the integral-relation-derived shape for a Mach number of 3.0 |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | "L-6962." "NASA TN D-5770." "April 1970." Includes bibliographical references (p. 12). Four ejectors mounted in each pod under each wing and powered with compressed air were used to simulate vertical-lift, fan-type jet engines. Data were obtained through an angle-of-attack range to show the effects of engine-pod location, ground-plane movement, flaps, tail size and location, and l0⁰ of sideslip on the aerodynamic characteristics of the model, and the effects of configuration changes on the jet and free-stream interference increments.--P. [i]. Also available online in PDF from NASA Technical Reports Server Web site. Sponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under721-01-11-05-23 |
| 出版: | Washington, DC : National Aeronautics and Space Administration |
| 附註: | "L-1080." "L-7023." "NASA TN D-5840." "August 1970." Includes bibliographical references (p. 13). Deployment and performance characteristics of 5-Foot diameter (1.5m) Attached Inflatable Decelerators (AID) from Mach Numbers 2.2-4.4. Deployment characteristics and steady-state performance data were obtained over the Mach number range from 2.2 to 4.4 and at angles of attack from 0 degrees to 10 degrees. All attached inflatable decelerator (AID) models deployed successfully and exhibited flutter-free performance after deployment. Shock loads commonly associated with inflation of parachutes during deployment were not experienced. Force and moment data and ram-air pressure data were obtained throughout the Mach number range and at angles of attack from 0 degrees to l0 degrees. The high drag coefficient of 1.14 was in good agreement with the value predicted by the theory used in the design and indicated other AID shapes may be designed on a rational basis with a high degree of confidence.--NTIS Web site. Also available online in PDF and Quicktime movie format from NASA Technical Reports Server Web site. Sponsored by the National Aeronautics and Space Administration (NASA); performed by the NASA Langley Research Center under124-07-23-01 |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 28-29). Heat transfer in convergent-divergent nozzles with different values of wall roughness. |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151] |
| 附註: | Includes bibliographical references (p. 12). Drag characteristics of toroid-membrane and wide-angle conical shells used as towed decelerators. System requirements: Adobe Acrobat Reader. [electronic resource] |
| 出版: | Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Office of Technical Services, Dept. of Commerce] |
| 附註: | Prepared at Ames Research Center. "January 1970."--Cover. Major NASA subject terms: Aerodynamics; Atmospheric Entry Simulation; Hypersonic Forces; Mars Probes; Ballistic Ranges; Blunt Bodies; Cones; Dynamic Stability; Spheres. Includes bibliographical references (p. 10 - 11). Five spherically blunted cones were tested in free flight, in still air, to determine their aerodynamic characteristics. Three of these models, by design, had drag Coefficients invariant with angle of attack (< 15 degree) and lift-curve slopes near zero. Each of these three models was statically stable but the dynamic stability was found to depend on cone half-angle and , nose bluntness. The lift-curve slopes and dynamic stability of the lwo high-drag bodies, 55 degree and 60 degree half-angle blunted cones, were invariant with angle of attack (<16 degree) and equal in magnitude. These two models were both statically and dynamically stable. |
| 出版: | Washington, D.C. : [For sale by the Clearinghouse for Federal Scientific and technical Information, Springfield, Va. 22151] : National Aeronautics and Space Administration |
| 附註: | Includes bibliographical references (p. 123-124). Integral equations to calculate free streamline flow behind axisymmetric bodies at zero and small angles of attack. |
| 出版: | Washington : U.S. National Bureau of Standards : For sale by the Supt. of Docs., U.S. Govt. Print. Off. |
| 附註: | Includes bibliographical references (p. 20). |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 附註: | "Serial 91-57." Hearings on S. 1151, 1889, 2059, 2230, 2396, 2825, 3102, 3176, 3492; H.R. 1049 and 4813 |
| 出版: | Washington : U.S. Govt. Print. Off. |
| 附註: | "Serial no. 91-20." |
| 出版: | Washington : For sale by the Supt. of Docs., U.S. Govt. Print. Off |
| 出版: | Washington, D.C. : U.S. Dept. of the Interior, Fish and Wildlife Service, Bureau of Commercial Fisheries |
| 附註: | "April 1970." Includes bibliographical references (p. 25-26). |