Nonlinear Dynamic Inversion Flight Control Design for Guided Projectiles

Theodoulis, Spilios; Thai, Sovanna; Proff, Michael

doi:10.2514/1.g004976

Cited by 21 publications

(7 citation statements)

References 9 publications

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“…Te φ a is the height angle, and φ b is the defection angle of the projectile axis. Te translational diferential equations for the center of mass of the rocket projectile [14,27] are as follows: where v, θ a , and θ b represent the projectile centroid velocity, velocity elevation angle, and velocity defection angle, respectively; x, y, and z represent the centroid displacements; m � m 1 + m 2 represents the total projectile mass with m 1 and m 2 being the mass of the body and tail, respectively; and F x , F y , and F z represent the force components of the projectile in the three axes of the trajectory coordinate system.…”

Section: Dynamic Modelling Of Rocket Projectile With Isolated Rotatin...mentioning

confidence: 99%

“…Terefore, the shape of the two characteristic frequencies is oval, as shown in Figure 4. According to equation (27), the critical rotation speed of the tail is _ c 0 ≈ 153.3rad/s. Figure 5 shows the movement of the projectile angle of attack under the initial conditions δ 10 � 0.1rad, δ 20 � 0, v 0 � 280m/s, and θ a0 � 0.07πrad.…”

Section: Stability Analysis Of Projectile Under Magnus Momentmentioning

confidence: 99%

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Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Wang

Ding

Feng

et al. 2023

Mathematical Problems in Engineering

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A trajectory-corrected rocket projectile with an isolated rotating tail rudder provides a new concept for a low-cost trajectory correction and guidance due to its simplified guidance principle. To study the angular motion characteristics of a trajectory-corrected rocket projectile with an isolated rotating tail rudder under the action of a periodic control force, the angular motion differential equation described in the complex plane is derived based on the rigid body trajectory equation. Furthermore, the effects of the initial conditions, gravity, and an asymmetric tail on the flight stability of the projectile in an uncorrected trajectory state are studied. The critical rotational speed of the tail rudder, which makes the projectile unstable due to the Magnus moment, and the rotational speed of the tail rudder, which causes projectile resonance, are derived. The transient and steady-state solutions of the angular motion of the projectile under trajectory correction and the variation law of the velocity direction for the projectile centroid are obtained. Finally, an example is given to verify the conclusions of this study. This research has important guiding significance for trajectory analysis, guidance control, and guidance law designs for isolated rotating rudder trajectory-corrected rocket projectiles.

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Section: Dynamic Modelling Of Rocket Projectile With Isolated Rotatin...mentioning

confidence: 99%

Section: Stability Analysis Of Projectile Under Magnus Momentmentioning

confidence: 99%

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Wang

Ding

Feng

et al. 2023

Mathematical Problems in Engineering

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“…Here we describe such a controller based on the dynamic inversion (DI) principle. In typical DI controller synthesis the system is first linearized so the control input appears as an affine term in the system dynamics [71]. Here we take an alternative approach which does not require any linearization.…”

Section: B Tracking Controllermentioning

confidence: 99%

Trajectory Planning with Deep Reinforcement Learning in High-Level Action Spaces

Williams¹,

Schlossman²,

Whitten³

et al. 2021

Preprint

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This paper presentsa technique for trajectory planning based on continuously parameterized high-level actions (motion primitives) of variable duration. This technique leverages deep reinforcement learning (Deep RL) to formulate a policy which is suitable for real-time implementation. There is no separation of motion primitive generation and trajectory planning: each individual short-horizon motion is formed during the Deep RL training to achieve the full-horizon objective. Effectiveness of the technique is demonstrated numerically on a well-studied trajectory generation problem and a planning problem on a known obstacle-rich map. This paper also develops a new loss function term for policy-gradient-based Deep RL, which is analogous to an anti-windup mechanism in feedback control. We demonstrate the inclusion of this new term in the underlying optimization increases the average policy return in our numerical example.

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“…A POPULAR and important trend in the development of spinstabilized artillery ammunitions is to retrofit conventional spin-stabilized projectiles using various low-cost guidance and control techniques. A number of extant studies focus on a class of guided spin-stabilized projectiles with a dual-spin configuration (i.e., a forward part and an aft part) and steering or fixed canards [1][2][3][4][5][6][7][8][9][10]. The aft part of the projectile spins very rapidly to maintain gyroscopic stability, whereas the forward part equipped with canards spins slowly to implement trajectory control.…”

mentioning

confidence: 99%

“…The aft part of the projectile spins very rapidly to maintain gyroscopic stability, whereas the forward part equipped with canards spins slowly to implement trajectory control. Several aspects, such as flight dynamics modeling [1,2,8], stability [2,5,9], flight behavior [6,7], and guidance and control [4,10], have been discussed in the current research literature.…”

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confidence: 99%

Swerve Solution for Spin-Stabilized Projectiles with Canards: A Revisit

Chang

Wei³

2021

Journal of Spacecraft and Rockets

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The swerve response of spin-stabilized projectiles to the canard control problem is revisited in the present paper. The study is divided into three steps, including angle-of-attack response, velocity vector response of the projectile, and finally the swerving response. A complex deviation angle is used to describe the motion of the velocity vector of the projectile over the controlled trajectory. From a practical perspective, the deviation angle is usually small, and so studying the swerving motion essentially boils down to investigating the response of the deviation angle. A novel set of swerve solutions with concise expressions is obtained, taking into account the gravitational effect in a more comprehensive manner. The accuracy and effectiveness of the proposed solutions are validated using two spinstabilized projectiles with canards. The effect of the distance between the center of pressure of the canard surface and the center of mass of the projectile on swerving motion is explained from the standpoint of the velocity vector response of the projectile. The results also demonstrate that gravity plays a pivotal role in predicting the swerve response. The results of this research are expected to be supplementary to those concerning dynamic behavior of spin-stabilized projectiles concluded in current literature.

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Nonlinear Dynamic Inversion Flight Control Design for Guided Projectiles

Cited by 21 publications

References 9 publications

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Research on Angular Motion Characteristics and Stability of Trajectory‐Corrected Rocket Projectile with Isolated Rotating Tail Rudder

Trajectory Planning with Deep Reinforcement Learning in High-Level Action Spaces

Swerve Solution for Spin-Stabilized Projectiles with Canards: A Revisit

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