Download or read book Aerodynamic Characteristics Determined During Development of the Apollo Launch Escape Vehicle Configuration written by William C. Moseley (Jr.) and published by . This book was released on 1969 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1969 with total page 662 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Stability Characteristics of the Apollo Launch Escape Vehicle written by William C. Moseley (Jr.) and published by . This book was released on 1967 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Stability Characteristics of the Apollo Command Module written by William C. Moseley (Jr.) and published by . This book was released on 1967 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Static Stability and Control Characteristics of a 0 030 scale Model of a Little Joe 2 Apollo Space Vehicle at Mach Numbers from 1 57 to 4 65 written by and published by . This book was released on 1963 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Dynamic Stability Characteristics in Pitch and in Yaw for a Model of a Variable sweep Airplane Configuration Capable of Low level Supersonic Attack written by Ernest R. Hillje and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0 065 scale Model of a Four stage Rocket Configuration at Mach Numbers of 1 41 and 1 82 written by Ross B. Robinson and published by . This book was released on 1959 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Landing Characteristics of the Apollo Spacecraft with Deployed heat shield Impact Attenuation Systems written by Sandy M. Stubbs and published by . This book was released on 1966 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made to determine the landing characteristics of a 1/4-scale dynamic model of the Apollo spacecraft command module using two different active (heat shield deployed prior to landing) landing systems for impact attenuation. One landing system (configuration 1) consisted of six hydraulic struts and eight crushable honeycomb struts. The other landing system (configuration 2), consisting of four hydraulic struts and six strain straps, was lighter. Tests made on water and the hard clay-gravel composite landing surfaces simulated parachute letdown (vertical) velocities of 23 ft/sec (7.0 m/s) (full scale). Landings made on the sand landing surface simulated vertical velocities of 30 ft/sec (9.1 m/s). Horizontal velocities of from 0 to 50 ft/sec (15 m/s) were simulated. Landing attitudes ranged from -30 degrees to 20 degrees , and the roll attitudes were 0 degrees, 90 degrees, and 180 degrees.

Download or read book Stability and Control Characteristics at Mach Numbers of 2 50 3 00 and 3 71 of a Variable Wing sweep Configuration with Outboard Wing Panels Swept Back 75 written by Gerald V. Foster and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1974 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0 10 scale Model of a Three stage Configuration of the Scout Research Vehicle at Mach Numbers of 2 29 2 96 3 96 and 4 65 written by Lloyd S. Jernell and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal Stability and Control Roll Control and Hinge Moments of a Little Joe 2 Apollo Model at Mach Numbers Up to 1 20 written by and published by . This book was released on 1964 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Apollo Capsule Optimization for Improved Stability and Computational Experimental Data Comparisons written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: Numerical optimization was employed on the Apollo Command Module to modify its external shape. The Apollo Command Module (CM) that was used on all NASA human space flights during the Apollo Space Program is stable and trimmed in an apex forward (alpha of approximately 40 to 80 degrees) position. This poses a safety risk if the CM separates from the launch tower during abort. Optimization was employed on the Apollo CM to remedy the undesirable stability characteristics of the configuration. Geometric shape changes were limited to axisymmetric modifications that altered the radius of the apex (R(sub A)), base radius (R(sub O)), corner radius (R(sub C)), and the cone half angle (theta), while the maximum diameter of the CM was held constant. The results of multipoint optimization on the CM indicated that the cross-range performance can be improved while maintaining robust apex-aft stability with a single trim point. Navier-Stokes computations were performed on the baseline and optimized configurations and confirmed the Euler-based optimization results. Euler Analysis of ten alternative CM vehicles with different values of the above four parameters are compared with the published experimental results of numerous wind tunnel tests during the late 1960's. These comparisons cover a wide Mach number range and a full 180-degree pitch range and show that the Euler methods are capable of fairly accurate force and moment computations and can separate the vehicle characteristics of these ten alternative configurations.Cliff, Susan E. and Thomas, Scott D.Ames Research CenterSPACE CAPSULES; APOLLO SPACECRAFT; COMMAND MODULES; SHAPE OPTIMIZATION; NAVIER-STOKES EQUATION; EULER EQUATIONS OF MOTION; SPACE FLIGHT; STABILITY; RISK

Download or read book 76 Y ki G sei Shinpojiumu k en y shish T ky November 10 12 1999 written by Yūki-Gōsei-Shinpojiumu and published by . This book was released on 1999 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Damping and Oscillatory Stability in Pitch and Yaw of a Variable sweep Supersonic Transport Configuration at Mach Numbers from 0 40 to 1 80 written by Robert A. Kilgore and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Dynamic Stability Tests of a Half Scale Model of the Jupiter W14 Re Entry Configuration written by H. C. Dubose and published by . This book was released on 1958 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic longitudinal dynamic stability tests of a half-scale model of the Jupiter W14 re-entry configuration are reported. The pitch-damping characteristics of the model were obtained from free oscillation tests at Mach numbers from 0.45 to 1.50. The results were in general agreement with previous small scale test results indicating that an increase in Reynolds number from approximately one to ten million had no significant effect on the dynamic stability of the configuration tested. (Author).

Download or read book Effects of Wing and Tail Location on the Aerodynamic Characteristics of an Airplane for Mach Numbers from 0 25 To 4 63 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-13 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental investigations have been conducted to determine the effect of wing vertical position and horizontal-tail vertical and axial position on the static aerodynamic characteristics of a wing-body horizontal-tail configuration. The configurations investigated included the wing in a high, mid, or low position on the body with the horizontal tail in each of these vertical positions as well as in three axial positions. The closest position of the horizontal tail to the wing essentially provided on all-wing configuration. In addition, tests were made for the three wing positions with the horizontal tail removed. The tests were made in three different wind tunnels to provide data for a Mach number range from 0.25 to 4.63. The purpose of the investigation was to illustrate the strong effects of interference flow fields as a function of geometry and flight regime. An analysis of the results indicate some arrangements that might lead to aerodynamic problems and others in which the interference flow fields might be favorably exploited. The results suggest that a coplanar concept with a translating horizontal tail could potentially minimize the aerodynamic changes with Mach number and provide more optimum performance over the Mach number range. Spearman, M. L. Langley Research Center NASA-TM-84643, NAS 1.15:84643 RTOP 505-43-43-01...