Aerospace and Electronic Systems Magazine September 2016 - 47


Fu, Zhang, and Yu
Table 1.

Energy-Loop Control
The energy-based controller to guarantee energy tracking is written as:
(40)
where Kds > 0 and Dr = 25.46V 2 + 337.21V 2a 2 + 80.20V 2a. The
objective function of energy tracking is introduced as:
(41)
where es = V - Vd. Using (2) and (40), ϒs = 0 is derived to ensure
that V → Vd. In accordance with (2), the desired energy function
of energy-loop is:
(42)
The time derivative of (42) is:
(43)
Thus,

Reference Pitch Angle Description
Level

Time (s)

Pitch Angle (deg)

Velocity
(m/s)

1

0 < t ≤110

0

80

2

110 < t ≤150

-5×(t-110)/40

80

3

150 < t ≤190

-5

80

4

190 < t ≤230

-5+10×(t-190)/40

80

5

230 < t ≤260

-5

80

6

260 < t ≤300

5-10×(t-260)/40

80

7

300 < t ≤340

0

80

8

340 < t ≤380

-6×(t-340)/40

80

9

380 < t ≤420

-6

80

10

420 < t ≤450

-6+3×(t-420)/30

80

11

450 < t ≤500

-3

80

holds.

Outer-Loop Control

Table 2.

With respect to the tracking error in z-position, the outer-loop controller to achieve the altitude stabilization is introduced as:

Reference Altitude Description

(44)

Level

Time (s)

Altitude (m)

Velocity
(m/s)

(45)

1

0 < t ≤110

1,000

80

2

110 < t ≤190

1000-500×(t-110)/80

80

3

190 < t ≤300

500+400×(t-190)/110

80

4

300 < t ≤380

900

80

5

380 < t ≤500

900-900×(t-380)/120

80

where K1, K2, K3, K4 Î R.
Remark 4. Energy-based control design formulates the UAV
control in the form of the energy equation following the principle
of conservation of energy. The control design is applied to track
the reference trajectory and keep energy balance without the need
of gain-scheduling.

Table 3.

SIMULATION AND RESULTS ANALYSIS

The Initial Parameters for Simulation

SIMULATION SCENARIOS

Parameter

The proposed approach is validated by numerical simulation conducted in the MATLAB/Simulink environment with a PC that is
configured with a 2 GHz Intel Core i7-4510U processor with 8
Gigabytes Random Access Memory. The landing phase is explicitly considered in the simulation study, where the reference signals
of the pitch angle and altitude are indicated in Table 1 and Table 2,
respectively. The UAV follows the initial conditions as shown in
Table 3. For aircraft presented as intruders in this study, it is required to follow the original trajectory with a constant airspeed
of 60 m/s. The initial parameters of BBO algorithm are given as:
SEPTEMBER 2016

Value

Initial x position

1,000 m

Initial z position

1,000 m

Initial velocity along x-axis

80 m/s

Initial velocity along z-axis

0 m/s

Initial pitch angle
Initial pitch rate
Airspeed

IEEE A&E SYSTEMS MAGAZINE

1.627 deg
0
80 m/s
47



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