# Optimization of Trajectory Correction Scheme for Guided Mortar Projectiles

Authors: Yongwei Zhang; Min Gao; Suochang Yang; Dan Fang
Journal: International Journal of Aerospace Engineering
 (2015)

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## Abstract

Guidance with traditional trajectory correction scheme usually starts from the trajectory apex time to reduce drag penalties early in flight; however, this method cannot get the max trajectory correction capability of canards according to our analysis. This paper presents an optimized trajectory correction scheme by taking different control phases of canards in ballistic ascending segment and ballistic descending segment. Simulation indicates that the optimized trajectory correction can improve the trajectory correction capability greatly. The result of an example trajectory and Monte Carlo simulations with the predictive guidance law and the trajectory tracking guidance law testifies the effectiveness of the optimized trajectory correction scheme.


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## Body

## 1. Introduction

Firing accuracy of the guided projectiles can be dramatically improved by outfitting with a suitable trajectory correction system. The commonly used tools are impulse thrusters [1–3], inertial loads [4, 5], drag brakes [6, 7], fixed canards [8–10], and moveable canards [11–15].Research and development on the use of canards have been going on for decades. Rogers and Costello [11] have presented a design of a canard-controlled mortar projectile using a bank-to-turn concept; the smart mortar is equipped with a set of two reciprocating fixed-angle roll canards and a set of two reciprocating fixed-angle maneuver canards. An active control system is designed to perform trajectory corrections and Monte Carlo simulations demonstrate the control system effectiveness in reducing dispersion error. Cooper et al. [13] have extended standard projectile linear theory to account for aerodynamic asymmetries caused by actuating canards, and the extended linear-projectile theory offers a tool to address flight stability of projectiles with aerodynamic configuration asymmetries. Spagni et al. [14] have characterized the system equilibrium point manifold in terms of a minimal vector of scheduling variables for a class of reciprocating canard-guided artillery munitions, giving rise to a discussion concerning the canard size and position for maneuverability optimization. Theodoulis et al. [15] have presented a complete design concerning the guidance and autopilot modules for a class of spin-stabilized fin-controlled projectiles.The guidance usually starts from the trajectory correction apex time to reduce drag penalties early in flight in the studies of guided projectiles with canards [11–15]; however, this trajectory correction scheme cannot get the max trajectory correction capability of canards according to our analysis.In this paper, an optimized trajectory correction scheme is put forward to maximize the trajectory correction capability and improve firing accuracy of guided mortar projectiles. Section2 presents the trajectory model of the guided mortar projectile. Section 3 presents the analysis and optimization of trajectory correction capability. Section 4 puts forward the optimized trajectory correction scheme. Section 5 describes the result of simulations, and conclusion is provided in Section 6.


## 2.
6-DOF Trajectory Model

The mortar projectile configuration used in this study is a representative 120 mm mortar projectile, 0.9 m long, fin-stabilized. The initial velocity is 280 m/s; the projectile weight, mass center location from the nose tip, roll inertia, and pitch inertia are 15.0 kg, 0.387 m, 0.0261 kg-m2, and 0.70 kg-m2, respectively. Figure 1 shows schematic of the guided mortar projectile; the canards are mounted on the nose of the guided mortar projectile.Figure 1
Schematic of the guided mortar projectile.Figure2 shows schematic of canards, which are driven by one actuator. Figures 2(a) and 2(b) show schematic of canards with no deflection, and Figures 2(c) and 2(d) show schematic of canards with a negative deflection angle, as shown in Figure 2; the negative deflection angle produces positive roll acceleration. The range of canards deflection angle is set as −15~15 deg. to ensure the fight stability of the guided mortar projectile.Figure 2
Schematic of canards.
(a)
Canards with no deflection angle viewed from projectile top
(b)
Canards with no deflection angle viewed from projectile left
(c)
Canards with negative deflection angle viewed from projectile top
(d)
Canards with negative deflection angle viewed from projectile leftFigure3 shows schematic of forces on the guided mortar projectile and the forces applied on the guided mortar projectile including weight force and aerodynamic force; the deflection angle of canards is adjusted to change the aerodynamic force for trajectory correction in flight.Figure 3
Schematic of forces on guided mortar projectiles.In Figure3, α is the attack angle, G is the weight force, and F is the aerodynamic force.The numerical simulation is based on a rigid body six-degree-of-freedom model typically utilized in flight dynamic analysis of mortar projectiles [3, 16]. The translational kinetic differential equations are given by(1)dVdt=Gx2+Fx2,Vdθdt=Gy2+Fy2,-Vcos⁡θdψvdt=Gz2+Fz2.The applied forces in (1) consist of weight force (G) and aerodynamic force (F), expressed in aeroballistic reference frame. V, ψv, and θ are the velocity, trajectory azimuth angle, and trajectory incline angle, respectively.The rotational kinetic differential equations are given by(2)Jx4dωx4dtJy4dωy4dtJz4dωz4dt=Mx4+Mx4′My4+My4′Mz4+Mz4′-0Jx4-Jz4ωx4ωz4Jy4-Jx4ωx4ωy4+0-Jz4ωz4dγdtJy4ωy4dγdt.The applied moments in (2) contain contributions from steady air loads, denoted by M, and unsteady air loads, denoted by M′, expressed in quasibody reference frame. Jx4, Jy4, and Jz4 are components of the transverse moment of inertia. ωx4, ωy4, and ωz4 are components of the angular rate vector; γ is the Euler roll angle.The translational kinematic equations are given by(3)dxdt=Vcos⁡θcos⁡ψv,dydt=Vsin⁡θ,dzdt=-Vcos⁡θsin⁡ψv.In (3), x, y, and z are position vector components of the center of mass, expressed in the inertial reference frame.The rotational kinematic equations are given by(4)dϑdt=ωz4,dψdt=1cos⁡ϑωy4,dγdt=ωx4-ωy4tan⁡ϑ.In (4), ϑ is the pitch angle and ψ is the yaw angle.The angles in (1)~(4) have the relation expressed as follows:(5)β=arcsin⁡cos⁡θsin⁡ψ-ψv,α=ϑ-arcsin⁡sin⁡θcos⁡β,γv=⁡arcsin⁡tan⁡θtan⁡β.In (5), α is the attack angle and β is the sideslip angle.Equations (1)~(5) constitute the rigid body six-degree-of-freedom model for guided mortar projectiles, which can be solved by the fourth-order Runge-Kutta algorithm.


## 3. Analysis and Optimization of Trajectory Correction Capability

### 3.1. Analysis of Trajectory Correction Capability

The guided mortar projectile is fin-stabilized, which will roll slowly in the flight progress, and Figure4 plots the roll rate of the guided mortar projectile. The canards used in the guided mortar projectiles are a pair of proportional electrokinetic canards, the control method of the canards lets the deflection angle of canards follow a sinusoidal signal of the projectile roll angle, and the strength and direction of aerodynamic force accused by canards are changed through the change of the amplitude and phase of the sinusoidal signal. The control progress of canards deflection angle is shown in Figure 5.Figure 4
Roll rate versus time.Figure 5
Schematic of canards deflection angle.As shown in Figure5, δt is the canards deflection angle, δ0 is the amplitude of canards deflection angle, ϕ is the phase of the sinusoidal signal, which is named as canards control phase, and γ is the roll angle. The variables in Figure 5 have the following relation:(6)δt=δ0·sin⁡γ+π2-ϕ.As shown in (6), trajectory correction capability will be influenced by the factors like canards control amplitude δ0, canards control phase ϕ, and control start time t0. To investigate the correction performance of canards, some simulations of the guided mortar have been done by numerical integration of the equations described above using a fourth-order Runge-Kutta algorithm. The mortar projectile is launched at sea level toward a target on the ground with altitude and cross range equal to zero at a range of 2000 m. The traditional method to characterize trajectory correction capability is exerting control normal force in a given roll orientation from a given time [17], so the method to calculate trajectory correction capability in this study is as follows: firstly, set the launching elevation angle, simulate the uncontrolled trajectory, and make sure that the range of uncontrolled trajectory equals 2000 m. Secondly, set the same launching elevation angle and simulate the controlled trajectory with different parameters such as different control start times, different canards control phases, and different canards control amplitudes. Thirdly, calculate the trajectory correction capability through comparing the impact point of the controlled trajectory to the impact point of the uncontrolled trajectory. For example, the launching elevation angle is set as 78.86 deg. to simulate the uncontrolled trajectory; on the other hand, canards control amplitude is set as 15 deg., the canards control phase is set as 180 deg., and control start time is set as 20 s for the controlled trajectory. The contrast of the controlled trajectory and uncontrolled trajectory is shown in Figure 6; the range correction capability is about 154 m according to the method of calculating trajectory correction capability described above.Figure 6
Altitude versus range.The simulations with different control parameters were done with the method described above; in these simulations,δ0 is set as max value (15 deg.) to get the max trajectory correction capability and ϕ is set as 180 deg. or 270 deg. to get the change laws of range and cross range correction capability. The launching elevation angle is 78.86 deg.; the simulation result of range and cross range correction capability is shown in Figure 7.Figure 7
Trajectory correction capability versus control start time.As shown in Figure7, range correction capability and cross range correction capability have different change laws. The range correction capability increases as the control start time increases when the control start time is earlier than the trajectory apex time (23.3 s), while the range correction capability decreases as the control start time increases when the control start time is later than the trajectory apex time. At the same time, the cross range correction capability decreases as the control start time increases whether the control start time is earlier than the trajectory apex time or not.The behavior of range correction capability and cross range correction capability has a physical reason. Supposing that the canards control phase is set as 180 deg., the projectile will subject aerodynamic force causing canards deflection, denoted byF, the direction of F is nearly perpendicular to the velocity direction of the projectile, F can be decomposed into Fx and Fy, as shown in Figure 8, in ballistic ascending segment, Fx is negative, which will shorten the projectile range, while Fy is positive, which will extend the projectile range, the impact of Fx and Fy is contradictory, the impact of Fx is bigger than the impact of Fy, and a range correction capability loss will be caused; the earlier the control start time, the bigger the range correction capability loss; therefore the range correction capability increases as the control start time increases in the ballistic ascending segment. In ballistic descending segment, Fx is positive, which will extend the projectile range, and Fy is positive, which will also extend the projectile range; then the range correction distance is mainly influenced by the time to go; therefore, the range correction decreases gradually with the increase of control start time in ballistic descending segment. In the horizontal plane, Fz is the only component decomposed from F, so the cross range correction capability is mainly influenced by the time to go; hence the cross range correction capability decreases gradually with the decrease of time to go. Therefore, the range correction capability and cross range correction capability have the change trends shown in Figure 7. The max range correction capability is 166 m, and the max cross range correction capability is 912 m.Figure 8
Schematic of aerodynamic force caused by canards deflection.


### 3.2. Optimization of Trajectory Correction Capability

As discussed above, range correction capability increases as the control start time increases in ballistic ascending segment because a range correction capability loss will be caused when the control start time is earlier than the trajectory apex time. An optimized canards control method is put forward to increase the range correction capability; this method is setting different canards control phases in ballistic ascending segment and ballistic descending segment for range correction. Take extending projectile range as an example, the canards control phase is set as 0 deg. in ballistic ascending segment, and the canards control phase is set as 180 deg. in ballistic descending segment, the aerodynamic force on the projectile caused by canards deflection is shown in Figure9, in ballistic ascending segment, F is decomposed into Fx and Fy, Fx is positive, which will extend the projectile range, while Fy is negative, which will shorten the projectile range, and the impact of Fx and Fy is contradictory: the impact of Fx is bigger than the impact of Fy; then the range correction capability loss can be avoided.Figure 9
Schematic of aerodynamic force caused by canards deflection (optimized method).The optimized method to increase the range correction capability is expressed in the following equations.The method to extend projectile range is(7)ϕ=0t<tapex,ϕ=πt≥tapex.The method to shorten projectile range is(8)ϕ=πt<tapex,ϕ=0t≥tapex.Taking extending range as an example, δ0 is set as the max value (15 deg.), and the control start time is set as 0 s; the launching elevation angle is 78.86 deg. The simulation result of range correction capability with traditional method and optimized method is shown in Figure 10. The range correction capability with optimized method decreases as the control start time increases; the max range correction capability is improved from 166 m to 1253 m with the optimized method. Then trajectory correction capability with optimized method is shown in Figure 11, the range correction capability and cross range correction capability have the same change laws, range and cross range correction capability decreases as the control start time increases, the max range correction capability is 912 m, and the max range correction capability is 1253 m.Figure 10
Contrast of range correction capability with traditional method and optimized method.Figure 11
Trajectory correction capability versus control start time (using the optimized method).


## 3.1. Analysis of Trajectory Correction Capability

The guided mortar projectile is fin-stabilized, which will roll slowly in the flight progress, and Figure4 plots the roll rate of the guided mortar projectile. The canards used in the guided mortar projectiles are a pair of proportional electrokinetic canards, the control method of the canards lets the deflection angle of canards follow a sinusoidal signal of the projectile roll angle, and the strength and direction of aerodynamic force accused by canards are changed through the change of the amplitude and phase of the sinusoidal signal. The control progress of canards deflection angle is shown in Figure 5.Figure 4
Roll rate versus time.Figure 5
Schematic of canards deflection angle.As shown in Figure5, δt is the canards deflection angle, δ0 is the amplitude of canards deflection angle, ϕ is the phase of the sinusoidal signal, which is named as canards control phase, and γ is the roll angle. The variables in Figure 5 have the following relation:(6)δt=δ0·sin⁡γ+π2-ϕ.As shown in (6), trajectory correction capability will be influenced by the factors like canards control amplitude δ0, canards control phase ϕ, and control start time t0. To investigate the correction performance of canards, some simulations of the guided mortar have been done by numerical integration of the equations described above using a fourth-order Runge-Kutta algorithm. The mortar projectile is launched at sea level toward a target on the ground with altitude and cross range equal to zero at a range of 2000 m. The traditional method to characterize trajectory correction capability is exerting control normal force in a given roll orientation from a given time [17], so the method to calculate trajectory correction capability in this study is as follows: firstly, set the launching elevation angle, simulate the uncontrolled trajectory, and make sure that the range of uncontrolled trajectory equals 2000 m. Secondly, set the same launching elevation angle and simulate the controlled trajectory with different parameters such as different control start times, different canards control phases, and different canards control amplitudes. Thirdly, calculate the trajectory correction capability through comparing the impact point of the controlled trajectory to the impact point of the uncontrolled trajectory. For example, the launching elevation angle is set as 78.86 deg. to simulate the uncontrolled trajectory; on the other hand, canards control amplitude is set as 15 deg., the canards control phase is set as 180 deg., and control start time is set as 20 s for the controlled trajectory. The contrast of the controlled trajectory and uncontrolled trajectory is shown in Figure 6; the range correction capability is about 154 m according to the method of calculating trajectory correction capability described above.Figure 6
Altitude versus range.The simulations with different control parameters were done with the method described above; in these simulations,δ0 is set as max value (15 deg.) to get the max trajectory correction capability and ϕ is set as 180 deg. or 270 deg. to get the change laws of range and cross range correction capability. The launching elevation angle is 78.86 deg.; the simulation result of range and cross range correction capability is shown in Figure 7.Figure 7
Trajectory correction capability versus control start time.As shown in Figure7, range correction capability and cross range correction capability have different change laws. The range correction capability increases as the control start time increases when the control start time is earlier than the trajectory apex time (23.3 s), while the range correction capability decreases as the control start time increases when the control start time is later than the trajectory apex time. At the same time, the cross range correction capability decreases as the control start time increases whether the control start time is earlier than the trajectory apex time or not.The behavior of range correction capability and cross range correction capability has a physical reason. Supposing that the canards control phase is set as 180 deg., the projectile will subject aerodynamic force causing canards deflection, denoted byF, the direction of F is nearly perpendicular to the velocity direction of the projectile, F can be decomposed into Fx and Fy, as shown in Figure 8, in ballistic ascending segment, Fx is negative, which will shorten the projectile range, while Fy is positive, which will extend the projectile range, the impact of Fx and Fy is contradictory, the impact of Fx is bigger than the impact of Fy, and a range correction capability loss will be caused; the earlier the control start time, the bigger the range correction capability loss; therefore the range correction capability increases as the control start time increases in the ballistic ascending segment. In ballistic descending segment, Fx is positive, which will extend the projectile range, and Fy is positive, which will also extend the projectile range; then the range correction distance is mainly influenced by the time to go; therefore, the range correction decreases gradually with the increase of control start time in ballistic descending segment. In the horizontal plane, Fz is the only component decomposed from F, so the cross range correction capability is mainly influenced by the time to go; hence the cross range correction capability decreases gradually with the decrease of time to go. Therefore, the range correction capability and cross range correction capability have the change trends shown in Figure 7. The max range correction capability is 166 m, and the max cross range correction capability is 912 m.Figure 8
Schematic of aerodynamic force caused by canards deflection.


## 3.2. Optimization of Trajectory Correction Capability

As discussed above, range correction capability increases as the control start time increases in ballistic ascending segment because a range correction capability loss will be caused when the control start time is earlier than the trajectory apex time. An optimized canards control method is put forward to increase the range correction capability; this method is setting different canards control phases in ballistic ascending segment and ballistic descending segment for range correction. Take extending projectile range as an example, the canards control phase is set as 0 deg. in ballistic ascending segment, and the canards control phase is set as 180 deg. in ballistic descending segment, the aerodynamic force on the projectile caused by canards deflection is shown in Figure9, in ballistic ascending segment, F is decomposed into Fx and Fy, Fx is positive, which will extend the projectile range, while Fy is negative, which will shorten the projectile range, and the impact of Fx and Fy is contradictory: the impact of Fx is bigger than the impact of Fy; then the range correction capability loss can be avoided.Figure 9
Schematic of aerodynamic force caused by canards deflection (optimized method).The optimized method to increase the range correction capability is expressed in the following equations.The method to extend projectile range is(7)ϕ=0t<tapex,ϕ=πt≥tapex.The method to shorten projectile range is(8)ϕ=πt<tapex,ϕ=0t≥tapex.Taking extending range as an example, δ0 is set as the max value (15 deg.), and the control start time is set as 0 s; the launching elevation angle is 78.86 deg. The simulation result of range correction capability with traditional method and optimized method is shown in Figure 10. The range correction capability with optimized method decreases as the control start time increases; the max range correction capability is improved from 166 m to 1253 m with the optimized method. Then trajectory correction capability with optimized method is shown in Figure 11, the range correction capability and cross range correction capability have the same change laws, range and cross range correction capability decreases as the control start time increases, the max range correction capability is 912 m, and the max range correction capability is 1253 m.Figure 10
Contrast of range correction capability with traditional method and optimized method.Figure 11
Trajectory correction capability versus control start time (using the optimized method).


## 4. Optimization of Trajectory Correction Scheme

A predictive guidance law and a trajectory tracking guidance law are introduced for the guidance of the guided mortar projectiles, and the optimization of trajectory correction scheme is done for the two guidance laws [18, 19].


### 4.1. Optimization of Trajectory Correction Scheme for the Predictive Guidance Law

The schematic of predictive guidance is shown in Figure12; the position of the target in inertial reference frame is T, while the position of the predictive impact point in inertial reference frame is I; then the predictive impact point deviation between the predictive impact point and the target is (ΔL, ΔH), where ΔL is longitudinal impact point deviation and ΔH is horizontal impact point deviation. The objective of predictive guidance scheme is making ΔL and ΔH equal to zero through the control of the canards.Figure 12
Schematic of predictive guidance.In Figure12, ε denotes the angle between the TI direction and the downrange direction. The calculation method of ε is(9)ε=atan⁡ΔHΔL.The predictive impact point deviation can be calculated through (10), which is based on the perturbation theory:(10)ΔL=∂L∂xΔx+∂L∂yΔy+∂L∂VxΔVx+∂L∂VyΔVy,ΔH=∂H∂zΔz+∂H∂VzΔVz,Δx=x-x0,Δy=y-y0,Δz=z-z0,ΔVx=Vx-Vx0,ΔVy=Vy-Vy0,ΔVz=Vz-Vz0.In (10), L is the range function of nominal trajectory, H is the cross range function of nominal trajectory, x0, y0, and z0 are position vector components of nominal trajectory, Vx0, Vy0, and Vz0 are velocity vector components of nominal trajectory, x, y, and z are position vector components of actual trajectory, and Vx, Vy, and Vz are velocity vector components of actual trajectory.The position and velocity vector components of nominal trajectory (x0, y0, z0, Vx0, Vy0, and Vz0) and differential coefficients (∂L/∂x, ∂L/∂y, ∂L/∂Vx, and ∂L/∂Vy) can be computed and loaded on the onboard computer before flight; the position and velocity vector components of actual trajectory can be acquired by the inertial measurement unit (IMU), or global position system (GPS) receiver. The predictive impact point deviation can be computed online with (10) in flight.The canards will deflect according to the predictive impact point deviation; the method of traditional trajectory correction scheme to compute canards control parameters is(11)δ0=kΔL2+ΔH2,ϕ=ε.In (11), k is the coefficient, which is set as 0.5 in this paper.As discussed in Section3, different canards control phases should be set in ballistic ascending segment and ballistic descending segment to improve the range correction capability. An optimized method of trajectory correction scheme is put forward based on the optimized method of range correction capability:(12)δ0=kΔL2+ΔH2,ϕ=π-εt<tapex,ϕ=εt≥tapex.As shown in (12), unlike the traditional trajectory correction scheme, the canards control phase of the optimized trajectory correction scheme has different calculation methods in ballistic ascending segment and ballistic descending segment, canards control phase equal π-ε in ballistic ascending segment, and canards control phase equal ε in ballistic descending segment.


### 4.2. Optimization of Trajectory Correction Scheme for the Trajectory Tracking Guidance Law

The trajectory tracking guidance law compares the position of actual trajectory to the position of nominal trajectory to get a position error vector in the inertial frame. The trajectory error is converted to the quasibody reference frame using(13)eXeYeZ=cos⁡ϑcos⁡ψ-sin⁡ϑcos⁡ψsin⁡ψsin⁡ϑcos⁡ϕ0-cos⁡ϑsin⁡ψsin⁡ϑsin⁡ψcos⁡ψx-x0y-y0z-z0.In (13), eX, eY, and eZ are trajectory error vector components in the quasibody reference frame.The magnitude and phase angle of the trajectory error are denoted byΓ and ε′ and are defined by(14)Γ=eY2+eZ2,ε′=atan⁡eZeY.The canards will deflect according to the trajectory error, and the method of traditional trajectory correction scheme to compute canards control parameters is(15)δ0=k′Γ,ϕ=ε′.In (15), k′ is the coefficient, which is set as 0.5 in this paper.As discussed in Section3, different canards control phases should be set in ballistic ascending segment and ballistic descending segment to improve the range correction capability. An optimized method of trajectory correction scheme is put forward based on the optimized method of range correction capability:(16)δ0=k′Γ,ϕ=π-ε′t<tapex,ϕ=ε′t≥tapex.


## 4.1. Optimization of Trajectory Correction Scheme for the Predictive Guidance Law

The schematic of predictive guidance is shown in Figure12; the position of the target in inertial reference frame is T, while the position of the predictive impact point in inertial reference frame is I; then the predictive impact point deviation between the predictive impact point and the target is (ΔL, ΔH), where ΔL is longitudinal impact point deviation and ΔH is horizontal impact point deviation. The objective of predictive guidance scheme is making ΔL and ΔH equal to zero through the control of the canards.Figure 12
Schematic of predictive guidance.In Figure12, ε denotes the angle between the TI direction and the downrange direction. The calculation method of ε is(9)ε=atan⁡ΔHΔL.The predictive impact point deviation can be calculated through (10), which is based on the perturbation theory:(10)ΔL=∂L∂xΔx+∂L∂yΔy+∂L∂VxΔVx+∂L∂VyΔVy,ΔH=∂H∂zΔz+∂H∂VzΔVz,Δx=x-x0,Δy=y-y0,Δz=z-z0,ΔVx=Vx-Vx0,ΔVy=Vy-Vy0,ΔVz=Vz-Vz0.In (10), L is the range function of nominal trajectory, H is the cross range function of nominal trajectory, x0, y0, and z0 are position vector components of nominal trajectory, Vx0, Vy0, and Vz0 are velocity vector components of nominal trajectory, x, y, and z are position vector components of actual trajectory, and Vx, Vy, and Vz are velocity vector components of actual trajectory.The position and velocity vector components of nominal trajectory (x0, y0, z0, Vx0, Vy0, and Vz0) and differential coefficients (∂L/∂x, ∂L/∂y, ∂L/∂Vx, and ∂L/∂Vy) can be computed and loaded on the onboard computer before flight; the position and velocity vector components of actual trajectory can be acquired by the inertial measurement unit (IMU), or global position system (GPS) receiver. The predictive impact point deviation can be computed online with (10) in flight.The canards will deflect according to the predictive impact point deviation; the method of traditional trajectory correction scheme to compute canards control parameters is(11)δ0=kΔL2+ΔH2,ϕ=ε.In (11), k is the coefficient, which is set as 0.5 in this paper.As discussed in Section3, different canards control phases should be set in ballistic ascending segment and ballistic descending segment to improve the range correction capability. An optimized method of trajectory correction scheme is put forward based on the optimized method of range correction capability:(12)δ0=kΔL2+ΔH2,ϕ=π-εt<tapex,ϕ=εt≥tapex.As shown in (12), unlike the traditional trajectory correction scheme, the canards control phase of the optimized trajectory correction scheme has different calculation methods in ballistic ascending segment and ballistic descending segment, canards control phase equal π-ε in ballistic ascending segment, and canards control phase equal ε in ballistic descending segment.


## 4.2. Optimization of Trajectory Correction Scheme for the Trajectory Tracking Guidance Law

The trajectory tracking guidance law compares the position of actual trajectory to the position of nominal trajectory to get a position error vector in the inertial frame. The trajectory error is converted to the quasibody reference frame using(13)eXeYeZ=cos⁡ϑcos⁡ψ-sin⁡ϑcos⁡ψsin⁡ψsin⁡ϑcos⁡ϕ0-cos⁡ϑsin⁡ψsin⁡ϑsin⁡ψcos⁡ψx-x0y-y0z-z0.In (13), eX, eY, and eZ are trajectory error vector components in the quasibody reference frame.The magnitude and phase angle of the trajectory error are denoted byΓ and ε′ and are defined by(14)Γ=eY2+eZ2,ε′=atan⁡eZeY.The canards will deflect according to the trajectory error, and the method of traditional trajectory correction scheme to compute canards control parameters is(15)δ0=k′Γ,ϕ=ε′.In (15), k′ is the coefficient, which is set as 0.5 in this paper.As discussed in Section3, different canards control phases should be set in ballistic ascending segment and ballistic descending segment to improve the range correction capability. An optimized method of trajectory correction scheme is put forward based on the optimized method of range correction capability:(16)δ0=k′Γ,ϕ=π-ε′t<tapex,ϕ=ε′t≥tapex.


## 5. Results and Discussion

To investigate the correction performance of canards and verify the effectiveness of the optimized trajectory correction scheme, some simulations of the guided mortar projectiles have been done by numerical integration of the equations described above using a fourth-order Runge-Kutta algorithm. In these simulations, the trajectory correction performance of the optimized trajectory correction scheme will be compared with the traditional trajectory correction scheme for the predictive guidance law and the trajectory tracking guidance law.


### 5.1. Results and Discussion for Guided Mortar Projectiles with the Predictive Guidance Law

It can be known from (11) and (12) that the method of traditional trajectory correction scheme to compute canards control parameters is identical with the optimized method if the guidance starts at the trajectory apex time. So the optimized method is used in both cases but with different guidance start times.Traditional Trajectory Correction Scheme. Equation (12) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as the trajectory apex time [11–15].Optimized Trajectory Correction Scheme. Equation (12) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as 5 s. The control start time is set as 5 s because the control system needs a few time to complete initialization and the GPS receiver needs time to search satellites and start location.


#### 5.1.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Table 1
Initial conditions for example simulation.
State
Unit
Unperturbed value
Perturbed value
launching elevation angle
deg
78.86
78.26
Launching azimuth angle
deg
−0.13
0.80
Initial velocity
m/s
280
285
Wind
m/s
0
3
Wind direction
deg
0
135Figures13 and 14 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 52.4 m and −44.0 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are −0.3 m and 0.0 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 13
Altitude versus range.Figure 14
Deflection versus range.Figures15 and 16 show the change of the predicted impact point deviation. It can be known from Figure 15 that the predicted longitudinal impact point deviation before trajectory correction is about 185 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted longitudinal impact point deviation reduces from about 185 m at the trajectory apex time to 58.3 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted longitudinal impact point deviation starts to reduce at 5 s; it reduces from about 185 m at 5 s to about 0 m at 15 s. It can be known from Figure 16 that the predicted horizontal impact point deviation before trajectory correction is about −170 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at the trajectory apex time to −50 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at 5 s to about 0 m at 13 s. As shown in Figures 15 and 16, the optimized trajectory correction scheme has a bigger trajectory correction capability through taking different calculation methods of canards control phase in ballistic ascending segment and ballistic descending segment, so it can correct the big dispersion error successfully; however, the big dispersion error is not corrected absolutely with the traditional trajectory correction scheme because trajectory correction needs to start after trajectory apex time to avoid range correction capability loss, which leads to a smaller trajectory correction capability.Figure 15
The change of longitudinal impact point deviation.Figure 16
The change of horizontal impact point deviation.Figure17 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme; the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 315 deg. Figure 18 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle maintains at about 15 deg. during 5~8.7 s and reduces gradually after 8.7 s due to the decrease of predicted impact point deviation; notably, the control phase maintains at about −87.5 deg. before 23.7 s and changes to about 267.5 deg. at 23.7 s; the quick change of the control phase is determined by the optimized trajectory correction scheme, as shown in (12).Figure 17
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 18
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


#### 5.1.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. Table 3 lists signal noise and bias standard deviations used in these simulations.Table 2
Initial conditions and disturbances.
Parameter
Unit
Mean value
Std. deviation
launching elevation angle
deg
78.86
0.35
Launching azimuth angle
deg
−0.13
0.30
Initial velocity
m/s
280
3
Wind
m/s
0
2Table 3
Signal noise and bias standard deviations.
Signal
Unit
Noise std. deviation
Bias std. deviation
x
m
8
4
y
m
8
4
z
m
8
4
v
x
m/s
0.4
0.2
v
y
m/s
0.4
0.2
v
z
m/s
0.4
0.2
γ
deg
5
3Figure19 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 19(a), and the CEP of the uncontrolled mortar projectiles is 111.0 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 19(b) and 19(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 20.5 m, while the CEP of projectiles with the optimized trajectory correction scheme is 6.2 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 19
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


### 5.2. Results and Discussion for Guided Mortar Projectiles with the Trajectory Tracking Guidance Law

It can be known from (15) and (16) that the method of traditional trajectory correction scheme to compute canards control parameters is identical with the optimized method if the guidance starts at the trajectory apex time. So the optimized method is used in both cases but with different guidance start times.Traditional Trajectory Correction Scheme. Equation (16) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as the trajectory apex time [11–15].Optimized Trajectory Correction Scheme. Equation (16) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as 5 s.


#### 5.2.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Figures20 and 21 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 67.3 m and −67.7 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are 1.1 m and −1.8 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 20
Altitude versus range.Figure 21
Deflection versus range.Figure22 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme, the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 320 deg. Figure 23 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle increases from 0 deg. to 15 deg. during 5~26 s and reduces gradually after 37.5 s.Figure 22
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 23
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


#### 5.2.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. The signal noise and bias standard deviations used in these simulations are listed in Table 3.Figure24 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 24(a), and the CEP of the uncontrolled mortar projectiles is 109.3 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 24(b) and 24(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 35.1 m, while the CEP of projectiles with the optimized trajectory correction scheme is 16.1 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 24
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


## 5.1. Results and Discussion for Guided Mortar Projectiles with the Predictive Guidance Law

It can be known from (11) and (12) that the method of traditional trajectory correction scheme to compute canards control parameters is identical with the optimized method if the guidance starts at the trajectory apex time. So the optimized method is used in both cases but with different guidance start times.Traditional Trajectory Correction Scheme. Equation (12) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as the trajectory apex time [11–15].Optimized Trajectory Correction Scheme. Equation (12) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as 5 s. The control start time is set as 5 s because the control system needs a few time to complete initialization and the GPS receiver needs time to search satellites and start location.


### 5.1.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Table 1
Initial conditions for example simulation.
State
Unit
Unperturbed value
Perturbed value
launching elevation angle
deg
78.86
78.26
Launching azimuth angle
deg
−0.13
0.80
Initial velocity
m/s
280
285
Wind
m/s
0
3
Wind direction
deg
0
135Figures13 and 14 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 52.4 m and −44.0 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are −0.3 m and 0.0 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 13
Altitude versus range.Figure 14
Deflection versus range.Figures15 and 16 show the change of the predicted impact point deviation. It can be known from Figure 15 that the predicted longitudinal impact point deviation before trajectory correction is about 185 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted longitudinal impact point deviation reduces from about 185 m at the trajectory apex time to 58.3 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted longitudinal impact point deviation starts to reduce at 5 s; it reduces from about 185 m at 5 s to about 0 m at 15 s. It can be known from Figure 16 that the predicted horizontal impact point deviation before trajectory correction is about −170 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at the trajectory apex time to −50 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at 5 s to about 0 m at 13 s. As shown in Figures 15 and 16, the optimized trajectory correction scheme has a bigger trajectory correction capability through taking different calculation methods of canards control phase in ballistic ascending segment and ballistic descending segment, so it can correct the big dispersion error successfully; however, the big dispersion error is not corrected absolutely with the traditional trajectory correction scheme because trajectory correction needs to start after trajectory apex time to avoid range correction capability loss, which leads to a smaller trajectory correction capability.Figure 15
The change of longitudinal impact point deviation.Figure 16
The change of horizontal impact point deviation.Figure17 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme; the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 315 deg. Figure 18 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle maintains at about 15 deg. during 5~8.7 s and reduces gradually after 8.7 s due to the decrease of predicted impact point deviation; notably, the control phase maintains at about −87.5 deg. before 23.7 s and changes to about 267.5 deg. at 23.7 s; the quick change of the control phase is determined by the optimized trajectory correction scheme, as shown in (12).Figure 17
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 18
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


### 5.1.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. Table 3 lists signal noise and bias standard deviations used in these simulations.Table 2
Initial conditions and disturbances.
Parameter
Unit
Mean value
Std. deviation
launching elevation angle
deg
78.86
0.35
Launching azimuth angle
deg
−0.13
0.30
Initial velocity
m/s
280
3
Wind
m/s
0
2Table 3
Signal noise and bias standard deviations.
Signal
Unit
Noise std. deviation
Bias std. deviation
x
m
8
4
y
m
8
4
z
m
8
4
v
x
m/s
0.4
0.2
v
y
m/s
0.4
0.2
v
z
m/s
0.4
0.2
γ
deg
5
3Figure19 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 19(a), and the CEP of the uncontrolled mortar projectiles is 111.0 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 19(b) and 19(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 20.5 m, while the CEP of projectiles with the optimized trajectory correction scheme is 6.2 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 19
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


## 5.1.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Table 1
Initial conditions for example simulation.
State
Unit
Unperturbed value
Perturbed value
launching elevation angle
deg
78.86
78.26
Launching azimuth angle
deg
−0.13
0.80
Initial velocity
m/s
280
285
Wind
m/s
0
3
Wind direction
deg
0
135Figures13 and 14 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 52.4 m and −44.0 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are −0.3 m and 0.0 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 13
Altitude versus range.Figure 14
Deflection versus range.Figures15 and 16 show the change of the predicted impact point deviation. It can be known from Figure 15 that the predicted longitudinal impact point deviation before trajectory correction is about 185 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted longitudinal impact point deviation reduces from about 185 m at the trajectory apex time to 58.3 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted longitudinal impact point deviation starts to reduce at 5 s; it reduces from about 185 m at 5 s to about 0 m at 15 s. It can be known from Figure 16 that the predicted horizontal impact point deviation before trajectory correction is about −170 m, for the controlled trajectory with traditional trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at the trajectory apex time to −50 m before impact, and for the controlled trajectory with optimized trajectory correction scheme, the predicted horizontal impact point deviation reduces from about −170 m at 5 s to about 0 m at 13 s. As shown in Figures 15 and 16, the optimized trajectory correction scheme has a bigger trajectory correction capability through taking different calculation methods of canards control phase in ballistic ascending segment and ballistic descending segment, so it can correct the big dispersion error successfully; however, the big dispersion error is not corrected absolutely with the traditional trajectory correction scheme because trajectory correction needs to start after trajectory apex time to avoid range correction capability loss, which leads to a smaller trajectory correction capability.Figure 15
The change of longitudinal impact point deviation.Figure 16
The change of horizontal impact point deviation.Figure17 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme; the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 315 deg. Figure 18 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle maintains at about 15 deg. during 5~8.7 s and reduces gradually after 8.7 s due to the decrease of predicted impact point deviation; notably, the control phase maintains at about −87.5 deg. before 23.7 s and changes to about 267.5 deg. at 23.7 s; the quick change of the control phase is determined by the optimized trajectory correction scheme, as shown in (12).Figure 17
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 18
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


## 5.1.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. Table 3 lists signal noise and bias standard deviations used in these simulations.Table 2
Initial conditions and disturbances.
Parameter
Unit
Mean value
Std. deviation
launching elevation angle
deg
78.86
0.35
Launching azimuth angle
deg
−0.13
0.30
Initial velocity
m/s
280
3
Wind
m/s
0
2Table 3
Signal noise and bias standard deviations.
Signal
Unit
Noise std. deviation
Bias std. deviation
x
m
8
4
y
m
8
4
z
m
8
4
v
x
m/s
0.4
0.2
v
y
m/s
0.4
0.2
v
z
m/s
0.4
0.2
γ
deg
5
3Figure19 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 19(a), and the CEP of the uncontrolled mortar projectiles is 111.0 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 19(b) and 19(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 20.5 m, while the CEP of projectiles with the optimized trajectory correction scheme is 6.2 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 19
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


## 5.2. Results and Discussion for Guided Mortar Projectiles with the Trajectory Tracking Guidance Law

It can be known from (15) and (16) that the method of traditional trajectory correction scheme to compute canards control parameters is identical with the optimized method if the guidance starts at the trajectory apex time. So the optimized method is used in both cases but with different guidance start times.Traditional Trajectory Correction Scheme. Equation (16) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as the trajectory apex time [11–15].Optimized Trajectory Correction Scheme. Equation (16) is adopted to relate the predictive impact point deviation with canards control phase and amplitude, and the control start time is set as 5 s.


### 5.2.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Figures20 and 21 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 67.3 m and −67.7 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are 1.1 m and −1.8 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 20
Altitude versus range.Figure 21
Deflection versus range.Figure22 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme, the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 320 deg. Figure 23 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle increases from 0 deg. to 15 deg. during 5~26 s and reduces gradually after 37.5 s.Figure 22
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 23
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


### 5.2.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. The signal noise and bias standard deviations used in these simulations are listed in Table 3.Figure24 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 24(a), and the CEP of the uncontrolled mortar projectiles is 109.3 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 24(b) and 24(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 35.1 m, while the CEP of projectiles with the optimized trajectory correction scheme is 16.1 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 24
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


## 5.2.1. Example Trajectory

An example trajectory is simulated to demonstrate trajectory correction performance. A ballistic case using unperturbed initial conditions shown in Table1 is used as the nominal trajectory; perturbed initial conditions shown in Table 1 are used to simulate the uncontrolled trajectory and demonstrate trajectory correction performance.Figures20 and 21 compare the trajectory response obtained using the different trajectory correction schemes. The two figures show the nominal trajectory, the uncontrolled trajectory, the controlled trajectory with traditional trajectory correction scheme, and the controlled trajectory with optimized trajectory correction scheme. The longitudinal and horizontal impact point deviations are 190.6 m and −171.9 m in the uncontrolled case, the longitudinal and horizontal impact point deviations of the controlled trajectory with traditional trajectory correction scheme are 67.3 m and −67.7 m, the longitudinal and horizontal impact point deviations of the controlled trajectory with optimized trajectory correction scheme are 1.1 m and −1.8 m, and the optimized trajectory correction scheme has a better trajectory correction performance.Figure 20
Altitude versus range.Figure 21
Deflection versus range.Figure22 plots the deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme, the amplitude of canards deflection angle maintains at 15 deg. during the trajectory correction progress because the impact point deviation is not corrected absolutely throughout the trajectory correction progress, and the control phase maintains at about 320 deg. Figure 23 plots the deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme; the amplitude of canards deflection angle increases from 0 deg. to 15 deg. during 5~26 s and reduces gradually after 37.5 s.Figure 22
The deflection angle and control phase histories of the controlled trajectory with traditional trajectory correction scheme.Figure 23
The deflection angle and control phase histories of the controlled trajectory with optimized trajectory correction scheme.


## 5.2.2. Dispersion Simulations

Dispersion simulations were performed to test control system robustness and effectiveness in eliminating error due to launch perturbations and atmospheric winds. All initial conditions were modeled as Gaussian random variables, with mean values and standard deviations given in Table2. Wind direction is a uniform random variable between 0 and 2π. The signal noise and bias standard deviations used in these simulations are listed in Table 3.Figure24 shows the impact point distribution using the Monte Carlo method with a statistical sample of 200 simulations. The cases of the uncontrolled mortar projectiles as well as of the guided mortar projectiles with traditional trajectory correction scheme and optimized trajectory correction scheme are shown, the impact point distribution of the uncontrolled mortar projectiles is big, as shown in Figure 24(a), and the CEP of the uncontrolled mortar projectiles is 109.3 m. Impact point distribution of the controlled projectiles reduces greatly, as shown in Figures 24(b) and 24(c). The mortar projectiles with the traditional trajectory correction scheme have a CEP of 35.1 m, while the CEP of projectiles with the optimized trajectory correction scheme is 16.1 m. Note that the optimized trajectory correction achieves significantly greater CEP reduction, reflecting the higher trajectory correction authority inherent in this method.Figure 24
Impact point distribution.
(a)
Uncontrolled mortar projectiles
(b)
Controlled mortar projectiles with traditional trajectory correction scheme
(c)
Controlled mortar projectiles with optimized trajectory correction scheme


## 6. Conclusion

This paper presents an optimized trajectory correction scheme by taking different calculation methods of canards control phase in ballistic ascending segment and ballistic descending segment. Simulation indicates that the optimized trajectory correction scheme can improve the trajectory correction capability greatly. The simulation of an example trajectory and Monte Carlo simulations with the predictive guidance law and the trajectory tracking guidance law were done to investigate the correction performance of canards and verify the effectiveness of the optimized trajectory correction scheme. In the simulations with the predictive guidance law, the result of the example trajectory shows that the optimized trajectory correction scheme has better trajectory correction performance for the ballistics case with big dispersion error, and the result of Monte Carlo simulations shows that the uncontrolled mortar projectiles have a CEP of 111.0 m, the CEP was improved to 20.5 m with the traditional trajectory correction scheme, and, as a contrast, the CEP was improved to 6.2 m with the optimized trajectory correction scheme. In the simulations with the trajectory tracking guidance law, the result of the example trajectory shows that the optimized trajectory correction scheme has better trajectory correction performance for the ballistics case with big dispersion error, and the result of Monte Carlo simulations shows that the uncontrolled mortar projectiles have a CEP of 109.3 m, the CEP was improved to 35.1 m with the traditional trajectory correction scheme, as a contrast, and the CEP was improved to 16.1 m with the optimized trajectory correction scheme. The result of the example trajectory and Monte Carlo simulations with the predictive guidance law and the trajectory tracking guidance law testifies the effectiveness of the optimized trajectory correction scheme. The trajectory correction performance of the optimized trajectory correction scheme with other launching elevation angles will be studied in the future work.



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*Source: 618458-2015-12-29.xml*