Deflectable Nose and Canard Controls for a Fin-Stabilized Projectile at Supersonic and Hypersonic Speeds

Landers, Michael; Hall, Les; Auman, Lamar; Vaughn, Milton E.

doi:10.2514/6.2003-3805

Cited by 23 publications

(11 citation statements)

References 9 publications

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“…The forces and moments depicted in equations (3) and (4) are total forces and moments acting on the projectile which include aerodynamic (A), gravity (G), and control forces (C). The total forces and moments are given in equations (5) and (6).…”

Section: Smart Projectile System Dynamics Modelmentioning

confidence: 99%

“…Some examples are spoilers mounted at the rear of a fin-stabilized projectile 3 and a spin-stabilized projectile with a nose capable of moving relative to the projectile body. 4,5 Other types of control mechanisms are pulse jets and thrusters 6,7 and moving internal parts to achieve trajectory alteration. [8][9][10][11] The main feature of these control mechanisms is the generation of lateral forces and moments employed to guide the projectile to an intended target.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Impact point model predictive control of a spin-stabilized projectile with instability protection

Gross

Costello

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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Most smart projectile control systems generate lateral control forces to guide the round to a target. Experience has shown that under the right combination of body orientation, translational velocity, and angular velocity, relatively low lateral control force inputs can induce instability of the round. To solve this problem, an additional control logic layer is appended to a nominal impact point flight control law to protect it from instability in these infrequent, but consequential situations. To highlight the newly developed control logic, a smart 155 mm spin-stabilized projectile equipped with a rotating paddle control mechanism is considered. For this example configuration, cross range maneuvering occasionally induces instability. Simulation results, using both rigid and multi-body nonlinear flight dynamics models, indicate that the addition of the instability protection layer in the control logic prevents projectile instability while not substantially altering target impact statistics. The nature of this protector design lends itself well to the use of a GPU to perform the calculations, greatly decreasing the computation time needed.

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Section: Smart Projectile System Dynamics Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Impact point model predictive control of a spin-stabilized projectile with instability protection

Gross

Costello

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Deflectable nose control [1,2] is one kind of missile aerodynamic control method that is similar to canard control but of higher efficiency and faster response [3,4,5]. Since the overall performances, flight quality and guidance accuracy of a deflectable nose missile are all strongly affected by nose deflection mechanism, it is necessary to have research on the designing of deflection mechanisms.…”

Section: Introductionmentioning

confidence: 99%

Design and Simulations of a Guide-screw Hand-spike Nose Deflecting Mechanism

Hu¹,

Gu²,

Sun³

et al. 2015

Procedia Engineering

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The nose deflecting mechanism is important in the development of deflectable nose control technology. In this paper, drawbacks of several existing deflection mechanisms are analyzed, and design requirements of the nose deflection mechanism are summarized. Then a Screw-Spike nose deflecting mechanism is established to meet the design requirements. After that, the relationships between nose deflecting angles and rotation of motors are deduced. At last, the ADAMS-MATLAB\Simulink cosimulations are employed to validate that the Screw-Spike mechanism which is of high precision, fast response, large achievable deflecting angles can meet the design requirements.

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“…As a result, a variety of novel control-effector concepts designed specifically for gun-launched precision munitions have been proposed. These include aerodynamic mechanisms such as canards [2,3], ram air deflectors [4,5], and moveable noses [6,7], which rely on aerodynamic effects to provide control. Others, such as gas or explosive thrusters [8,9], rely on on-board thrust mechanisms.…”

Section: Introductionmentioning

confidence: 99%

Actuator Design and Flight Testing of an Active Microspoiler-Equipped Projectile

Kim

Strickland

Gross

et al. 2017

Journal of Dynamic Systems, Measurement, and Control

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Actively controlled gun-launched projectiles require a means of modifying the projectile flight trajectory. While numerous potential mechanisms exist, microspoiler devices have been shown to be a promising control actuator for fin-stabilized projectiles in supersonic flight. These devices induce a trim force and moment generated by the boundary layer–shock interaction between the projectile body, rear stabilizing fins, and microspoilers. Previous investigations of microspoiler mechanisms have established estimates of baseline control authority, but experimental results have been restricted to cases in which the mechanism was statically deployed. This paper details the design and flight testing of a projectile equipped with a set of active microspoilers. A mechanical actuator is proposed that exhibits unique advantages in terms of robustness, simplicity, gun-launch survivability, and bandwidth compared to other projectile actuator mechanisms considered to date. A set of integrated test projectiles is constructed using this actuator design, and flight experiments are performed in which the microspoilers are oscillated near the projectile roll frequency. Data obtained from these flight tests are used in parameter estimation studies to experimentally characterize the aerodynamic effects of actively oscillating microspoilers. These predictions compare favorably with estimates obtained from computational fluid dynamics (CFD). Overall, the results presented here demonstrate that actively controlled microspoilers can generate reasonably high levels of lateral acceleration suitable for trajectory modification in many smart-weapons applications.

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Deflectable Nose and Canard Controls for a Fin-Stabilized Projectile at Supersonic and Hypersonic Speeds

Cited by 23 publications

References 9 publications

Impact point model predictive control of a spin-stabilized projectile with instability protection

Impact point model predictive control of a spin-stabilized projectile with instability protection

Design and Simulations of a Guide-screw Hand-spike Nose Deflecting Mechanism

Actuator Design and Flight Testing of an Active Microspoiler-Equipped Projectile

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