1. Introduction

1.1. The introduction to the drone and its single-axis camera control

Drones, also known as unmanned aerial vehicles (UAVs), are a type of aircraft that can be controlled remotely without a pilot onboard. The history of drones began after the First World War when simple prototypes is used as weapons. [1] During the late twentieth century, an autonomous control system is added to aid operations. Currently equipped with advanced technologies such as global positioning systems (GPS), [2] cameras, and sensors [3], drones has the indigenous abilities for navigation, data collection, videography, or some specific mission objectives.

Figure 1. (a) NASA uses drones for launch detection. image credit NASA [4] Images used in accordance with image use policy, “NASA content (images, videos, audio, etc.) are generally not copyrighted and may be used for educational or informational purposes without needing explicit permissions”. [5] (b) the detail of the one-gimbal drone’s camera.

Figure 1. (a) NASA uses drones for launch detection. image credit NASA [4] Images used in accordance with image use policy, “NASA content (images, videos, audio, etc.) are generally not copyrighted and may be used for educational or informational purposes without needing explicit permissions”. [5] (b) the detail of the one-gimbal drone’s camera.

The drone is becoming increasingly important in a wide range of industries, including agriculture construction [6,7], journalism, [8] and filmmaking [9], among others; and drones of various sizes and shapes have been designed for a wide range of applications proving drones to be a growingly important technological advancement and an increasingly vital tool for modern society.

Cameras are a very common payload for drones, as they enable users to capture images and videos from a unique perspective which would be different from that obtained by traditional cameras on the ground. As the basis of robot perception, cameras serve as eyes for aerial photography and videography, surveying and mapping, and inspection and monitoring of infrastructure and facilities. [10] Thus, cameras are a crucial component of modern drones, and their performance will also directly impact the performance of the drone.

Error caused by camera mounting devices is considered one of the main factors affecting camera performance. Sources of noise affect the performance of the camera leading to pointing deviation and vibrations. Various camera mounting devices are available, as described by Carmona [11], who has designed a complex platform-style mechanical structure that can stabilize the camera and absorb vibrations. Unfortunately, complex mechanical structures can be relatively cumbersome for drones that aim to be small and affordable. Danh [12] described a dual-axis gimbal that stabilizes the camera, but the design still requires an excellent control structure to support system operations. One widely-accepted solution is to use a single-axis gimbal and electrical control structure to mount the camera, as explained in Gasparovic’s article [13] where the advantages of the gimbal are clearly outlined.

1.3. The rest-to-rest model of the drone’s gimbal and six controls

The movement of a drone’s camera gimbal is mathematically modeled as rest-to-rest rotation of a rigid body system, which means that its velocities and acceleration at the beginning and end points are zero (quiescent conditions) over a specified, limited time. The rest-to-rest rigid-body system adheres to classical Newtonian translation mechanics and rotation in accordance with Euler’s moment equations [26] represented as a double integrator in equation (1) when motion is expressed in coordinates of an inertial reference frame. The rotation equation of the reorientation system is the focus of control and optimization.

$$I\ddot{\theta }=T_q=u$$

(1)

Table 1. Proximal variable definitions.

Table 1. Proximal variable definitions.

Valuables	Definitions	Valuables	Definitions
$\theta$	Angle	$J$	the quadratic cost functional
$\omega$	Angular velocity	$F$	The dynamic cost function
$\ddot{\theta }$	Rotational acceleration	$f$	The dynamic constraint
$I$	The inertia of moment	$T_q$	System torque
$t_0$	The initial time	$t_f$	The final time
u	Control function of time

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

The boundary condition for the rest-to-rest maneuver is characterized by starting from a stationary position and ending with a new orientation with zero velocity. The expected duration of the maneuver is scaled or normalized to unity. The boundary condition in this problem is expressed in equation (2). In addition, the performance of the controller is also evaluated using the quadratic cost displayed in equation (3). The control architecture tuned the relevant parameters and appropriate values were selected to minimize the quadratic cost.

$$\left\{\begin{array}{c}\begin{array}{c}\theta \left(0\right)=0\\ \omega \left(0\right)=0\end{array}\\ \begin{array}{c}\theta \left(1\right)=1\\ \omega \left(1\right)=0\end{array}\end{array}\right.$$

(2)

$$J=\frac{1}{2}{\int }_{t_0}^{t_f}{u}^{2}dt={\int }_{t_0}^{t_f}Fdt$$

(3)

There are six control architectures compared are:

• Open loop quadratic-cost control. [27,28]
• Proportional plus velocity feedback control.
• Real-time optimal control. [29]
• Proportional plus velocity feedback with a double-integrator patching filter. [30]
• Gain-(re)tuned P+V controller with a double-integrator patching.
• Proportional plus velocity controller with a control law inversion patching filter.

Table 2. Acronym definitions.

Table 2. Acronym definitions.

Topic	Definitions
RTOC	Real-Time optimal control
P+V	Proportional plus velocity control
HzMAT	Hamiltonian Minimization, Adjoint equations, Terminal transversality of the endpoint Lagrangian
Kp and Kv	Proportional and velocity gains for P+V control

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

The main controller architectures compared in this manuscript are the proportional plus velocity (P+V) controller with and without patching filters; double-integrator quadratic cost control (DQC) as both open-loop optimal control and real-time optimal control (RTOC) with feedback. [31]

The proportional plus velocity (P+V) feedback controller is similar to the well-known proportional, integral, derivative (PID) controller, and to proportional, derivative (PD) control. Proportional plus velocity control contains an amplifier to adjust the state variables towards the target and does not necessitate an integrator to stabilize oscillations. The controller is simple to operate and easy to build. Compared to the open loop controller, the proportional plus velocity controller has better robustness to uncertainty. However, the controller has two parameters $K_{p}and{K}_v$ introducing tasks to tune effectively. Accuracy and precision are sought without inclusion of analytic minimization of quadratic costs.

The optimal-control algorithm is based on Pontryagin’s minimize principle, which converts the optimal control problem into a multipoint boundary value problem (BVP) where adjoint equations are used to incorporated constraints [32,33,34] as described in equations (4) – (9). The Hamiltonian minimization condition is expressed in equation (5). The adjoint equations are listed in equation (6). The terminal transversality condition of the endpoint Lagrangian is displayed in equation (7) and proves useful to provide additional boundary values aiding analytic solvability. The Hamiltonian final value condition does similarly.

$$H=F+{\lambda }^{T}f(x,u)$$

(4)

$$\frac{\partial H}{\partial u}=0$$

(5)

$$\frac{\partial H}{\partial x}=-\dot{{\lambda }_x}$$

(6)

$$\overline{E}=E+{\nu }^{T}e$$

(7)

$$\frac{\partial E}{\partial X_f}={\lambda }_x\left(t_f\right)$$

(8)

$$H\left(t_f\right)=-\frac{\partial E}{\partial t_f}$$

(9)

The advantage of using the optimal-control algorithm resides in the influence of the quadratic cost and running time mandates. The final control result minimizes the cost while strictly enforcing the running time. Augmenting optimal-control results in the open-loop controller with feedback leads to a real-time system.

Table 3. Table of proximal variable definitions.

Table 3. Table of proximal variable definitions.

Variables	Definitions	Valuables	Definitions
$H$	Hamiltonian	$F$	Dynamic cost function
$\lambda$, $\nu$	Lagrange multipliers	$f$	Dynamic constraint
${\lambda }_x$	Lagrange multiplier for $x$	$\dot{{\lambda }_x}$	Lagrange multiplier derivative for $x$
x	System states	$u$	Control (a function of time)
$\overline{E}$	Total end-point cost functional	$E$	Static cost function
$e$	Static constraint function	$t_f$	Final time

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

2. Materials and Methods

2.1. The HzMAT optimal to the rest-to-rest orientation system

Based on Equation (3), the quadratic cost function is considered, and identify that the F in Equation (4) represents a dynamic cost in the system which is generated by the quadratic cost. Therefore, the dynamics or running cost presents the link relation between the quadratic cost and dynamic system constraint. Equation (10) is the quadratic cost function:

$$F=\frac{1}{2}{u}^2$$

(10)

The f in the Hamiltonian condition is a dynamic constraint in the system. External control in the dynamics depends on the costate, state, and time. The costate represents the sensitivity of the system to perturbations and the states represent the current physical state of the system. Additionally, time is also a critical factor in external control since the time determines the duration of the control action and influences the overall performance of the system. Equation (11) displays the relationship between the dynamics and these factors.

$$\dot{x}=f\left(x,u,t\right)=f(x,\lambda ,t)$$

(11)

Equation (11) provides insight into the relationship between the dynamic’s constraint and states. Equation (12) shows that the detail of dynamic constraint, represented by f in the Hamiltonian, influences the evolution of the state variables over time. The dynamic constraint is simplified by expressing the constraints as a set of equations that maintain the simplest structure, consisting of a first derivative and a derivative-free function.

$$\left\{\overline{x}\right\}=\left\{\begin{array}{c}\theta \\ \omega \end{array}\right\}$$

(12)

$$\left\{\dot{\overline{x}}\right\}=\left\{\begin{array}{c}\omega \\ \tau /I\end{array}\right\}=\left\{\begin{array}{c}\omega \\ u\end{array}\right\}$$

(13)

For each state variable in the system, there is a corresponding costate variable, which represents the sensitivity of the system’s performance to perturbations in that state variable. Therefore, the Hamiltonian condition function is a combination of dynamic cost and dynamic constraints by Lagrangian, which include both the state and costate variables.

$$H=F+{\lambda }^{T}f\left(x,u\right)=\frac{1}{2}{u}^2+\left\{\begin{array}{cc}{\lambda }_{\theta }& {\lambda }_{\omega }\end{array}\right\}\left\{\begin{array}{c}\omega \\ u\end{array}\right\}=\frac{1}{2}{u}^2+{\lambda }_{\theta }\omega +{\lambda }_{\omega }u$$

(14)

Based on Equation (5), the result of the partial derivative of the Hamiltonian condition functions with respect to the control value is calculated.

$$u+{\lambda }_{\omega }=0$$

(15)

Therefore, referring to Equation (6), the adjoint equations in this condition are available. Equations (15) and (16) obtained by taking the partial derivative of the $\theta$ and $\omega$ using the Hamiltonian function are:

$$\frac{\partial H}{\partial \theta }=0=-\dot{{\lambda }_{\theta }}$$

(16)

$$\frac{\partial H}{\partial \omega }={\lambda }_{\theta }=-\dot{{\lambda }_{\omega }}$$

(17)

Table 4. Table of proximal variable definitions.

Table 4. Table of proximal variable definitions.

Variable	Definition
$\tau$	The torque from the controller
${\lambda }_{\theta }$	The Lagrangian about $\theta$
${\lambda }_{\omega }$	The Lagrangian about $\omega$
$\dot{{\lambda }_{\theta }}$	The derivative about the $\theta$ lagrangian
$\dot{{\lambda }_{\omega }}$	The derivative about the $\omega$ lagrangian

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

Equations (15) and (16) establish the relationship between the Lagrangian and constant through integral operation, while equations (17) and (18) demonstrate the obtained result:

$${\lambda }_{\theta }=a$$

(18)

$${-\lambda }_{\omega }=at+b=u$$

(19)

where a and b are both constant.

By combining Equations (17) and (18), a straightforward relationship between control and time can be derived in Equation (20).

$$u=\dot{\omega }=at+b$$

(20)

Integrate these equations and obtain the optimal control for both velocity v and angle $\theta$.

$$\omega =\frac{1}{2}a{t}^2+bt+c$$

(21)

$$\theta =\frac{1}{6}a{t}^3+\frac{1}{2}b{t}^2+ct+d$$

(22)

where a, b, c, and d are unknown constants.

Equations may contain unknown constants, therefore constructing a solvable equation needs to base on time and control. The solution to the equation requires the specification of boundary conditions. After satisfying these conditions, a time-optimal control under the given conditions is available.

Due to the boundary condition in Equation (2), the control function with respect to time from Equation (19) to (21) is displayed in Equation (23), (24) and (25):

$$u=6-12t$$

(23)

$$\omega =-6t^2+6t$$

(24)

$$\theta =-2t^3+3t^2$$

(25)

Table 5. Table of proximal variable definitions.

Table 5. Table of proximal variable definitions.

Variable	Definition
t	Time (dimensionless)
a, b, c	Constants of integration

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

2.2. The introduction of six control architectures

2.2.1. Open loop controller with the result of the HzMAT optimal analysis

By utilizing the optimal analysis result from the HzMAT with equation (22) as input, the ideal output for both theta and angular velocity can be derived through double integrator translation control. The control architecture is depicted in Figure 3:

Figure 2. Open-loop controller structure.

Figure 2. Open-loop controller structure.

Figure 3. P+V feedback controller structure.

Figure 3. P+V feedback controller structure.

2.2.2. P+V feedback controller

Due to the feedback system, an ideal target (shown in Figure 4) is set and the error between the target and the output theta can be calculated. The error is then multiplied by $K_p$ and added to Kv times the output speed, forming the system input. After passing through the double integrator, the system provides output values for both theta and speed, which are then fed back into the input, completing the feedback loop.

Figure 4. RTOC controller structure.

Figure 4. RTOC controller structure.

The values of K_v and K_p used in this system are tuned based on the analysis of oscillation. the system’s steady state can be set as $K_p={{\omega }_n}^2$ and $K_v=2*\zeta *{\omega }_n$. Where ${\omega }_n$ is the angular speed obtained from oscillation analysis, and $\zeta$ is a parameter related to the system’s running time.

Table 6. Table of proximal variable definitions for Figure 3 and 4.

Table 6. Table of proximal variable definitions for Figure 3 and 4.

Variable	Definition
${\theta }_d$	The desired angle
$\theta$	The position output
Kv	A proportional value for P+V control
Kp	A proportional value for P+V control
x	System states
$\dot{x}$	The derivative of states
$\omega$	The velocity output
$\widehat{\omega }$	The actual velocity (the velocity output with the noise)
$\widehat{\theta }$	The actual angle (the position output with the noise)
$n_{\theta }$	The noise from the position sensor
$n_w$	The noise from the velocity sensor

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

2.2.3. Real-time optimal controller (RTOC)

RTOC is a real-time controller (shown in Figure 5) that utilizes the HzMAT optimization with different boundary conditions. The HzMAT analysis can provide reference equations like equations (20), (21), and (22). Various final boundary conditions can help to solve the values of a, b, c, and d. These values will be utilized to determine the control u and subsequently calculate the output position and speed of the system. But in this manuscript, time, position, and velocity limitations keep the same for easy comparison.

Figure 5. P+V feedback controller with double integrator patching filter.

Figure 5. P+V feedback controller with double integrator patching filter.

2.2.4. P+V feedback control with double-integrator patching filter.

In the P+V feedback controller, a patching filter is introduced to optimize the basic target and enhance the system’s input to approach the ideal target. In the patching filter, there is a simple double integrator (shown in Figure 6) that closely represents the dynamics of the open-loop plant. The K_p and K_v parameters remain unchanged.

Figure 6. P+V controller with Control law inversion patching filter structure.

Figure 6. P+V controller with Control law inversion patching filter structure.

Table 7. Table of proximal variable definitions for Figure 5 and Figure 6.

Table 7. Table of proximal variable definitions for Figure 5 and Figure 6.

Variable	Definition
s	Complex variable for Laplace Transform
${\theta }_d^{*}$	The desired transformed angle
${\tau }^{*}$	The desired torque input
$\omega$	The velocity output
$\theta$	The position output
$\widehat{\omega }$	The actual velocity (the velocity output with the noise)
$\widehat{\theta }$	The actual angle (the position output with the noise)
$n_{\theta }$	The noise from the position sensor
$n_w$	The noise from the velocity sensor

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

2.2.5. Gain-tuning P+V controller with double-integrator patching.

This control architecture still utilizes the P+V feedback control structure, complemented by a double integrator patching filter. However, the K_p and K_v parameters have been updated with brand-new values that are tested to improve the system’s ability to approach the ideal target. After careful selection and tuning, the K_p and K_v are set to 400 and 3, respectively.

2.2.6. P+V controller with Control law inversion patching filter.

This controller architecture is like the previous structure, with the primary difference being the use of a control law inversion patching filter. To achieve the HzMAT optimal control with the P+V controller, the input must be designed to be close to the final output.

Table 8. variables definitions.

Table 8. variables definitions.

Variables	Definitions	Variables	Definitions
${\theta }_d$	The desired angle	$X_d\left(s\right)$	The input of the control structure (angle)
$\theta$	The actual angle	$U^{*}\left(s\right)$	The output of the control structure (control)
$u^{*}$	The desired control	Kv	A proportional value for P+V control
u	The actual control	Kp	A proportional value for P+V control

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

As a reminder, the closed-loop control law is displayed in the equation (25):

$$u=K_p\left({\theta }_d-\theta \right)-K_v\omega$$

(26)

Also, equation (25) can be written as equation (26) and (27). Equation (27) represents the ideal outcome of equation (26).

$${\theta }_d=\frac{u}{K_p}+\theta +\frac{K_v}{K_p}\omega$$

(27)

$${\theta }_d\left(t\right)=\frac{u*}{K_p}+{\theta }^{*}\left(t\right)+\frac{K_v}{K_p}{\omega }^{*}\left(t\right)\forall tϵ[t_0,t_f]$$

(28)

For the double integrator plant, equation (28) is the same as equation (27):

$${\theta }_d\left(t\right)=\frac{1}{K_p}(u^{*}+K_v\int u^{*}\left(t\right)dt+K_p\iint \left(u^{*}\left(t\right)dt\right)dt)$$

(29)

Equation (28) may be written in the s-domain based on Laplace Transform as

$$X_d\left(s\right)=\frac{1}{K_p}(U^{*}\left(s\right)+\frac{K_v}{s}{U}^{*}\left(s\right)+\frac{K_p}{s}{U}^{*}\left(s\right))$$

(30)

Therefore, an alternative patching filter is shown in the equation (30):

$$\frac{X_d\left(s\right)}{U^{*}\left(s\right)}=\frac{1}{K_p}\left[\frac{s^2+K_{v}s+K_p}{s^2}\right]$$

(31)

The control structure is displayed in Figure 7:

Figure 7. MATLAB® integration solver iteration with time on the abscissa and position and velocity on the ordinant. (a) the trajectory under the ode1 and step 0.01. (b) the trajectory under the ode4 and step 0.01. (c) the trajectory under the ode4 and step 0.0001.

Figure 7. MATLAB® integration solver iteration with time on the abscissa and position and velocity on the ordinant. (a) the trajectory under the ode1 and step 0.01. (b) the trajectory under the ode4 and step 0.01. (c) the trajectory under the ode4 and step 0.0001.

Table 9. Table of proximal variable definitions for Figure 7.

Table 9. Table of proximal variable definitions for Figure 7.

Variable	Definition
s	Complex variable for Laplace Transform
Kv	A proportional value for P+V control
Kp	A proportional value for P+V control
$\widehat{\omega }$	The actual velocity (the velocity output with the noise)
$\widehat{\theta }$	The actual angle (the position output with the noise)
$n_{\theta }$	The noise from the position sensor
$n_w$	The noise from the velocity sensor

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

2.3. The MATLAB® solver selection

In the Simulink system, the solver plays a crucial role in determining the trajectory of the position and speed variables. Thereby the solver affects the accuracy and precision of the results. Therefore, selecting the appropriate solver and step size carefully for the analysis of the controllers’ performance is essential.

For the purposes of this manuscript, using an open-loop controller to evaluate the solver is convenient. When ode1 with a step size of 0.01 is tested, the resulting trajectory appears in Figure 8 (a). To obtain more accurate results, using a different solver as a comparison is significant, such as ode4 with a step size of 0.01 whose trajectory is displayed in Figure 8 (b). To further improve the accuracy and precision of the results, reducing the step size to 0.0001 is also an option, The objective trajectory with a step size of 0.0001 is shown in Figure 8 (c).

Figure 8. MATLAB® simulations with no noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the open loop. (b) The trajectory from the P+V controller. (c) The trajectory from the RTOC.

Figure 8. MATLAB® simulations with no noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the open loop. (b) The trajectory from the P+V controller. (c) The trajectory from the RTOC.

The conclusion based on the trajectory of ode1 with a step size of 0.01 is obvious that the final angular speed fails to satisfy the rest-to-rest condition. As a result, ode1 may not be the optimal choice for our analysis. After switching to the ode4 solver, the final boundary condition appears to be better satisfied in Figure 8 (b). Switching to the ode4 solver with a step size of 0.0001 did not significantly improve the final boundary condition. However, the running time increased significantly.

Table 10. The performances of the open-loop system with different solvers and step length.

Table 10. The performances of the open-loop system with different solvers and step length.

Solver and step length	End position	End velocity	Computational runtime	Quadratic cost (vehicle fuel usage)
Ode1 solver with 0.01 step length	1.0296	$0.06$	1.1338	6.0012
Ode4 solver with 0.01 step length	1	$2.2204\times {10}^{-16}$	1.0502	6
Ode4 solver with 0.0001 step length	1	$6.8196\times {10}^{-17}$	4.3162	6

${}^1$Such tables are distributed throughout the manuscript to increase the ease of reading, while a combined, master table of definitions is included in the appendices.

To find a compromise between accuracy and efficiency, using the ode4 solve with a step size of 0.01 is an ideal option for the simulation. This should provide reasonably accurate results while also maintaining a manageable running time.

3. Trajectory of the result from six architectures without any uncertainty

Figure 9. MATLAB® simulations with no noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the P+V controller with double-integrator patching filter (b) The trajectory from the tuning parameter P+V controller with double integrator filter. (c) The trajectory from the P+V controller with law inversion filter.

Figure 9. MATLAB® simulations with no noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the P+V controller with double-integrator patching filter (b) The trajectory from the tuning parameter P+V controller with double integrator filter. (c) The trajectory from the P+V controller with law inversion filter.

Table 11. The performances of six control architectures without parameter variations.

4. Analysis of six control architectures with some uncertainties

Figure 10. MATLAB® simulations with noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the open loop with noise. (b) The trajectory from the P+V controller with noise. (c) The trajectory of RTOC with noise.

Figure 10. MATLAB® simulations with noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the open loop with noise. (b) The trajectory from the P+V controller with noise. (c) The trajectory of RTOC with noise.

Figure 11. MATLAB® simulations with noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the P+V controller with double-integrator patching filter with noise. (b) The trajectory from the tuning parameter P+V controller with double integrator filter with noise. (c) The trajectory from the P+V controller with law inversion filter with noise.

Figure 11. MATLAB® simulations with noise with time on the abscissa and position and velocity on the ordinant. (a) The trajectory from the P+V controller with double-integrator patching filter with noise. (b) The trajectory from the tuning parameter P+V controller with double integrator filter with noise. (c) The trajectory from the P+V controller with law inversion filter with noise.

Table 12. The performances of six control architectures with errors.

5. Monte Carlo analysis

Figure 12. MATLAB® simulations with noise with the angle on the abscissa and the angular velocity on the ordinant. (a) Monte Carlo figure from the open loop (b) Monte Carlo figure from the single P+V controller (c) Monte Carlo figure from the RTOC.

Figure 12. MATLAB® simulations with noise with the angle on the abscissa and the angular velocity on the ordinant. (a) Monte Carlo figure from the open loop (b) Monte Carlo figure from the single P+V controller (c) Monte Carlo figure from the RTOC.

Figure 13. MATLAB® simulations with noise with the angle on the abscissa and the angular velocity on the ordinant. (a) Monte Carlo figure from the P+V controller with double-integrator patching filter (b) Monte Carlo figure from the tuning parameter P+V controller with double integrator filter (c) Monte Carlo figure from the P+V controller with law inversion filter.

Figure 13. MATLAB® simulations with noise with the angle on the abscissa and the angular velocity on the ordinant. (a) Monte Carlo figure from the P+V controller with double-integrator patching filter (b) Monte Carlo figure from the tuning parameter P+V controller with double integrator filter (c) Monte Carlo figure from the P+V controller with law inversion filter.

Table 13. The performances of six control architectures with errors in Monte Carlo analysis.

6. Discussions

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