Written in EnglishRead online
|Statement||Richmond P. Boyden, Cuyler W. Brooks, Jr., and Edwin E. Davenport|
|Series||NASA technical memorandum ; 74058|
|Contributions||Brooks, Cuyler W., joint author, Davenport, Edwin E , joint author, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office|
|The Physical Object|
|Pagination||81 p. :|
|Number of Pages||81|
Download Transonic static and dynamic stability characteristics of a finned projectile configuration
The item Transonic static and dynamic stability characteristics of a finned projectile configuration, Richmond P. Boyden, Cuyler W.
Brooks, Jr., and Edwin E. Davenport represents a specific, individual, material embodiment of a distinct intellectual or artistic creation found in Indiana State Library. Get this from a library. Transonic static and dynamic stability characteristics of a finned projectile configuration.
[Richmond P Boyden; Cuyler W Brooks, Jr.; Edwin E Davenport; United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.]. ANALYSIS OF STATIC AND DYNAMIC AEROELASTIC CHARACTERISTICS OF AIRPLANE IN TRANSONIC FLOW interference of the elements is also modeled (Fig.
Fig. Possible airplane configuration (Blwf code) A viscous-inviscid interaction procedure is in the frame of the boundary layer theory. The calculation of the external inviscid steady flow.
Dynamic stability A bullet is said to be dynamically stable, if an angle of yaw, induced at the muzzle, is damped out with time, or with other words if the angle of yaw decreases as the bullet travels on.
It can be shown that this is true, if the dynamic stability condition is fulfilled. Aug 01, · A projectile is stabilised using either gyroscopic or aerodynamic stability. But subcalibre projectiles with sabot have both spin and fins. Separate stability criteria are researched generally for each type of projectile.
In this paper a stability criterion which can be used for all such bodies has been developed through the Liapunov second 3rdrailphotography.com by: 4. Dynamic stability of unguided projectile with 6-DOF trajectory modeling the problems of static and dynamic stability by giving initial perturbations, effect of spin on thrust misalignment, and.
Aug 27, · What is the difference between Dynamic and Static Stability (of Aircrafts). • Static stability of an aircraft describes the tendency of and aircraft to retain its original position when subjected to unbalanced forces or moments acting on the aircraft.
• Dynamic stability describes the form of motion an aircraft in static stability undergoes. The flow field of a cruciform finned guided projectile with and without fin slot was simulated by the mean of CFD(computational fluid dynamic) numerical method.
The characteristics of pressure field distribution without and different widths slots were calculated and compared. The influence of fin slot to the aerodynamic characteristics such as drag, lift, roll moment, pitch moment static Author: Hua Dong Sun, Jian Qiao Yu, Yue Song Mei, Chong Liang.
Statics and the dynamics of a particle, (New York, McGraw-Hill book company, inc., ), by W. MacMillan (page images at HathiTrust) Statics, (Boston, Ginn, ), by Joseph Henry Kindle and Harry Leroy Miller (page images at HathiTrust). This report describes a new multi-disciplinary computational study undertaken to compute the flight trajectories and simultaneously predict the unsteady free flight aerodynamics of a spinning.
More Abbreviations Explanation A projectile is said to be dynamically stable, if its yawing motion of nutation and Transonic static and dynamic stability characteristics of a finned projectile configuration book is damped out with time, which means that an angle of yaw induced at the muzzle (the initial yaw) decreases.
A dynamic stability factor s d can be defined from the linearized theory of gyroscopes (assuming only a small angle of yaw) and the above dynamic stability. Sep 14, · Computational drag and magnus force reduction for a transonic spinning projectile using passive porosity.
when a porous surface is applied on a projectile in a transonic flow. This conclusion coincides with those drawn in studies, it is a critical parameter Cited by: 2.
An experimental study to determine the flow and the subsonic static and dynamic stability characteristics of aircraft operating at high angles-of-attack ALEX GOODMAN, CLINTON BROWN and.
Transonic Aerodynamic and Scaling Issues for Lattice Fin Projectiles Tested in a Ballistics Range,” Wind Tunnel Tests of a Grid Finned Projectile Configuration,” AIAA.
Paper No. – Sun, Y. Numerical Analysis of Static and Dynamic Performances of Grid Fin Controlled Missiles,”. The effect of asymmetric vortex wake characteristics on a slender delta wing undergoing wing rock motion.
Coupled static and dynamic stability parameters. Computation of the roll characteristics of a long L/D finned projectile and comparison with range data.
For the investigated projectile at M = this occurred for clearances h/d > 1, where h is the clearance between the projectile and the ground and d is the projectile diameter. Experiments and numerical simulations established the trends for lift, drag and aerodynamic moment .Cited by: 3. COMPUTATIONAL STUDY OF THE AERODYNAMIC CHARACTERISTICS OF AXI-SYMMETRIC BODIES IN TRANSONIC FLOW1 Eddy Priyono2 and Harijono Djojodihardjo3 Departmentof Aeronautics and Astronautics, Bandung Institute of Technology Jl.
Ganesha 10 Bandung, Indonesia e-mail: [email protected] Wind Tunnel Measurements of the Magnus Induced Surface Pressures on a Spinning Artillery Projectile Model in the Transonic Speed Regime [Miles C. Miller] on Author: Miles C. Miller. basic projectile dynamic model followed by judicious simpliﬁca-tions to these equations that result in the projectile linear theory equations.
The solution of the projectile linear theory equations is used to shed light on intuitive and subtle factors that inﬂuence swerve response of Cited by: projectile. The critical aerodynamic behavior occurs in the transonic speed regime, Two dimensional inlets with extended compression surfaces, used to improve the angle-of-attack performance of the inlets for wingless configurations, were also investigated.
The twin axisymmetric two dimensional inlet types without internal flow are covered, and the boost configuration of an air-breathing missile is simulated.
Structural Dynamic Model The VSB airframe is represented by a finite element structural dynamic reduced order model, composed by beam and plate elements connected by nodes to represent the body, the fin spars and the fin surfaces, respectively.
Such an approach is sufficient for the aeroelastic stability analysis of the 3rdrailphotography.com: Roberto Gil Annes da Silva, José Guido Damilano, João Luiz F. Azevedo. projectile flight dynamic modeling is described. At the core of the method is an unsteady, time accurate computational fluid dynamics simulation that is tightly coupled to a rigid body dynamics simulation.
A set of n short time snippets of simulated projectile motion at m different Mach numbers is computed and employed as baseline data. For. U.S. Army Ballistic Research Laboratory: Stability characteristics as determined by yaw card measurements for four 20mm projectiles for the VRFWS-I; HEIT M, HEIT XM, TPT M, TPT ME2 /, also by Maynard J.
Piddington and U.S. Atomic Energy. Although there are still some discrepancies, generally a good correspondence is obtained between the semi-analytical results and the FE results.
The dynamic stability of the base-excited cylindrical shell is studied using numerical continuation of periodic solutions with the Cited by: Investigation of Transonic Flow Behavior around a Three-Dimensional Turret Using Particle Image Velocimetry Carlos Caballero.
College of Engineering, University of Florida. Light distortions produced by flow density gradients, commonly referred as aero-optic aberrations, remain one of. The figures below show a plot of the inverse of the gyroscopic stability factor versus the dynamic stability for the M projectile with the dynamic stability bound, 5 Ì Ò.
L 5_ @:2 F 5 × ;, overlaid. The figure on the left is for the standard firing (constant pd/V) and the. Aug 27, · From Introduction: "Although the aerodynamic characteristics of the components of such configurations may be well known, the mutual interference resulting from combining the wings, as well as the wings and body, may be so great that is desirable to study the aerodynamic properties of the complete configurations.
Two methods of handling this problem are presented in this report. The first Cited by: 4. The example projectile used in these configuration optimization studies was the 30 mm-diameter Army-Navy Finner (ANF) projectile.
A schematic of this projectile is shown in Fig. This projectile was selected because of its routine use in academic literature and its well-characterized aerodynamic 3rdrailphotography.com: Dooroo Kim, Laura Strickland, Matthew Gross, Jonathan Rogers, Mark Costello, Frank Fresconi, Ilmars.
The load acting on a cylindrical shell, with added periodic stiffeners, under a transient pressure pulse propelling a pullet (gun case) has been experimentally studied.
This study is based on two modes of velocities, the first is subcritical mode and the second is supercritical mode. The stiffeners are added to the gun tube of an experimental gun facility, of 14 mm bore diameter.
The radial Cited by: 2. Jul 25, · Note presenting linearized equations of motions which are derived for both conventional aircraft having mirror symmetry and spinning projectiles or missiles with rotational and mirror symmetry. The equations for aircraft are compared with those for missiles and shortcomings in the currently accepted theories are pointed out.
The dynamic-stability requirements for spin-stabilized projectiles Cited by: 9. Static lift, drag, and pitching moment were measured as functions of body angle of attack in the High Speed Water Tunnel over a range of flow velocities.
Every model configuration was tested at 30 fps, and repre sentative runs were made at velocities of 20 and 40 fps. Additional drag. A measure of a projectile's ability to coast. It is defined as Cb = M/CdA where M is the projectile's mass and CdA is the Drag Form Factor (q.v.).
At any given velocity and air density, the deceleration of a rocket from drag is inversely proportional to this value. Intuitively, it is the principle Ballistic Recovery. Abstract: Multi-transonic accretion for a spinning black hole has been compared among different disc geometries within post Newtonian pseudo potential framework.
The variation of stationary shock characteristics with black hole spin has been studied in details for all the disc models and compared for adiabatic as well as for isothermal 3rdrailphotography.com by: 5. The present conference on applied aerodynamics discusses the flowfield for the propeller disks of a twin-pusher canard configuration, the effects of canard-wing flowfield interactions on longitudinal stability and potential deep-stall trim, the progress of wing vortex flows to vortex breakdown, flow visualization by IR imaging, wind tunnel.
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection An investigation of the transonic pressure drag coefficient for axi-symmetric bodies.
View Notes - Computing Project 1 (Projectile) from CEE at Arizona State University. Arizona State University CEE Dynamics The Mechanics Project CP 1Projectile Computing ProjectAuthor: Dienf. is addressed as the dynamic stability of these structures.
In this paper the dynamic stability of two thin-walled structures (a slender beam and a cylindrical shell) with top mass will be investigated. Both structures are not buckled in the static situation. An additional harmonic base excitation, however, may cause a dynamic.
namic force and moment coefficients of the Basic Finner missile in the High Speed Water Tunnel on the angular oscillating and linear oscillating dynamic balances and free flight studies2 in the Controlled Atmosphere Launching Tank.
The Basic Finner configuration has been tested in the Bureau of. pst – static pressure in the wind tunnel test section, the test section is with solid walls, while for transonic tests, a section with porous walls is inserted into the wind tunnel configuration.
difference between the test section static pressure and the dynamic pressure. Computational and Experimental Investigation S. Stupar, J Cited by: 1. Full text of "Modern Exterior Ballistics The Launch And Flight Dynamics Of Symmetric Projectiles 2nd Ed.
R. Mc Coy" See other formats.stability, but using non-zero spring stiffness on the guiding force has a stabilizing effect. This work also showed that the use of the finite element method and Floquet theory is an effective combination to analyze stability in gyroscopic systems with stationary friction loads.Oct 01, · title = "Computational study of large-disturbance oscillations in unsteady supersonic combustion around projectiles", abstract = "Unsteady combustion around a spherical projectile in supersonic flows is numerically studied using the simplified two-step chemical reaction model consisting of the induction and the exothermic 3rdrailphotography.com by: