Name: An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (en Inglés)
SKU: 59924124
Price: 74440.00 COP
Availability: InStock
Author: Nason, Martin L. ; Nasa Technical Reports Server (Ntrs) ; Et Al
ISBN: 9781289032036

portada An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (en Inglés)

An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (en Inglés)

Formato

Libro Físico

Autor

Nasa Technical Reports Server (Ntrs)

Martin L. Nason

Editorial

Bibliogov

Idioma

Inglés

N° páginas

Encuadernación

Tapa Blanda

Dimensiones

24.6x18.9x0.3 cm

Peso

0.11 kg.

ISBN13

9781289032036

Categorías

Política y gobierno

An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (en Inglés)

Nasa Technical Reports Server (Ntrs) (Autor) · Martin L. Nason (Autor) · Bibliogov · Tapa Blanda

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Reseña del libro "An Evaluation of the Roll-Rate Stabilization System of the Sidewinder Missile at Mach Numbers from 0.9 to 2.3 (en Inglés)"

A linear stability analysis and flight-test investigation has been performed on a rolleron-type roll-rate stabilization system for a canard-type missile configuration through a Mach number range from 0.9 to 2.3. This type damper provides roll damping by the action of gyro-actuated uncoupled wing-tip ailerons. A dynamic roll instability predicted by the analysis was confirmed by flight testing and was subsequently eliminated by the introduction of control-surface damping about the rolleron hinge line. The control-surface damping was provided by an orifice-type damper contained within the control surface. Steady-state rolling velocities were at all times less than 1 radian per second between the Mach numbers of 0.9 to 2.3 on the configurations tested. No adverse longitudinal effects were experienced in flight because of the tendency of the free-floating rollerons to couple into the pitching motion at the low angles of attack and disturbance levels investigated herein after the introduction of control-surface damping.