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 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 An Investigation of the Dynamic Stability and Control Characteristics for a Transport Cruising at a Mach Number of 3 written by Lawrence W. Brown and published by . This book was released on 1964 with total page 50 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 Stability Investigation of a Blunted Cone and a Blunted Ogive with a Flared Cylinder Afterbody at Mach Numbers from 0 30 to 2 85 written by Lucille C. Coltrane and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Damping and Oscillatory Stability in Pitch and Yaw of Gemini Configurations at Mach Numbers from 0 50 to 4 63 written by Bruce R. Wright and published by . This book was released on 1966 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Longitudinal Stability Characteristics of Preliminary Configurations for Scout D at Mach Numbers 0 20 to 4 63 written by Robert J. Keynton and published by . This book was released on 1971 with total page 140 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 Aerodynamic Characteristics in Pitch and Sideslip of a 1 15 scale Model of the Scout Vehicle at a Mach Number of 2 01 written by Ross B. Robinson and published by . This book was released on 1961 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: