**3.1 Experimental setup**

Using a continuously circulating low-speed wind tunnel (see **Figure 8**) owned by JAXA (Japan Aerospace Exploration Agency), we conducted a verification

**Figure 8.** *2 m x 2 m Low-speed wind tunnel.*

experiment to verify whether the DEA actuator could be used as a steering actuator under the wind received during flight. The wind tunnel used in this experiment has a measurement section of 2 m x 2 m and a maximum wind speed of 67 m / s (up to 60 m/s during continuous operation using the model).

In the preliminary study, the wind speed was set from 0 m/s to 40 m/s in order to match the actual driving conditions as much as possible. In addition, it was decided to observe the aileron driving state by changing the angle of attack from 0° to ±10° at 5° intervals at each wind speed (**Figure 9**).

The structural model of the wing used in the experiment was shaped vertically so that the surface control actuator (in this case, an aileron-like structure) can be driven by the DEA in a limited space in the wind tunnel. The body is shown in **Figure 10** [6].

The dimensions of the wings used in this experiment were 168.5 mm wide, 633 mm high and 25 mm thick, and the dimensions of the ailerons were 78.5 mm wide and 633 mm high. The wings and ailerons were made using polycarbonate resin for the frame and ABS resin for the exterior. The bottom of the model was 125 mm in diameter and 757.5 mm in length. The tip and tail are made of ABS resin,

**179**

**Figure 12.**

*System diagram of the aileron drive experiment with a DEA.*

*The Challenge of Controlling a Small Mars Plane DOI: http://dx.doi.org/10.5772/intechopen.95507*

*Link mechanism between the body and the measurement equipment.*

sion of φ100 mm.

**Figure 11.**

and the center is made of acrylic resin. For strength, the parts are reinforced with aluminum. The aileron has a hollow structure, but the total weight was about 5 kg. A DEA to control ailerons was installed inside the body. The DEA and aileron are connected by a link mechanism built into the main body (see **Figure 11**) [6], and when the DEA is displaced by 2 mm, the aileron moves 20 degrees. The DEA unit for aileron drive has a structure that adopts a diaphragm type with an outer dimen-

As shown in **Figure 12**, a load measuring device other than the main body, a high-voltage power supply, a high-voltage switch, etc. were installed outside the wind tunnel and connected to the main body with a cable so as not to obstruct the air flow in the wind tunnel [6]. A video camera was installed on the ceiling outside

**Figure 10.** *Body used in experiment.*

*The Challenge of Controlling a Small Mars Plane DOI: http://dx.doi.org/10.5772/intechopen.95507*

**Figure 11.**

*Link mechanism between the body and the measurement equipment.*

and the center is made of acrylic resin. For strength, the parts are reinforced with aluminum. The aileron has a hollow structure, but the total weight was about 5 kg. A DEA to control ailerons was installed inside the body. The DEA and aileron are connected by a link mechanism built into the main body (see **Figure 11**) [6], and when the DEA is displaced by 2 mm, the aileron moves 20 degrees. The DEA unit for aileron drive has a structure that adopts a diaphragm type with an outer dimension of φ100 mm.

As shown in **Figure 12**, a load measuring device other than the main body, a high-voltage power supply, a high-voltage switch, etc. were installed outside the wind tunnel and connected to the main body with a cable so as not to obstruct the air flow in the wind tunnel [6]. A video camera was installed on the ceiling outside

**Figure 12.**

*System diagram of the aileron drive experiment with a DEA.*

**181**

**Figure 15.**

**Figure 14.**

*(b) Laser distance sensor system.*

about 8.7 kg/f is required.

such a state and there was a risk of damage to the blade due to fatigue, the aileron drive experiment with the DEA was carried out at a wind speed of 0 m/s to 30 m/s. In order to steer 20 degrees in this environment, a DEA that can obtain a force of

*Load applied to the actuator section (by steering angle and wind speed).*

*Laser distance sensor system installed inside the body. (a) Mounting location of the laser distance sensor;* 

*The Challenge of Controlling a Small Mars Plane DOI: http://dx.doi.org/10.5772/intechopen.95507*

**Figure 13.** *Load measurement system using a load cell.*

the wind tunnel to observe the state of the enclosure, and the images were taken from the observation window.
