# Survey on Unmanned Aerial Vehicle for Mars Exploration: Deployment Use Case
## 2 Space Exploration through Different Methods/Vehicles
### Space Exploration through UAVs
#### 2.1.4 Designing Mars UAV  
The Mars UAV is based on a vehicle system; however, it has been adapted to match the thrust requirements of Mars' thin atmosphere. The Mars UAV system was created to create a model that could resist Mars conditions, such as dust storms and temperature shifts during night and day. When the UAV is expected to fly out of sight of the operator or to perform complex manoeuvres for which the control response from manual operation is insufficient, autonomy is required. The benefits of Mars UAV systems over helicopter vehicles motivated the development of the Mars UAV. When performing manoeuvres, the helicopter requires a complicated system to regulate the pitch of the rotors. On the other hand, UAVs can change their orientation simply by changing the rotor speeds. All three movements, roll, pitch, and yaw, may be accomplished simply by delivering appropriate signals to the motors to alter rotor speeds without any mechanisms or mechanical control. The negative of the Mars UAV system is that huge rotors require a significant amount of actuation effort to accelerate up or slow down, resulting in a delayed reaction time. The variable pitch is employed for very large rotors because motors cannot rapidly accelerate up or down. The idea of flying UAVs on Mars is to show that with significant rotor blade design optimisation, enough lift can be created to fly a lightweight UAV in the thin atmosphere. The design also emphasises making the flight and operation autonomous and mapping the surrounding terrain and path planning to help the ground-based rover go beyond its existing capabilities. The Mars UAV will be used in high tip Mach numbers and low Reynolds numbers. To minimise the development of unwanted shock waves, it is critical to maintain subsonic speed at the rotor's tip in a generic rotor design. \begin{table}
\begin{tabular}{c c c c c c c c c} \hline \hline
**References** & **Venus** & **Wang Area** & **Chord** & **Mass (kg)** & **Wang Span** & **Horizontal** & **Vertical** & **Power** \\  & **UAV** & **(m\({}^{2}\))** & **Length** & **Mass (m)** & **Tail Area** & **Tail Area** & **Tail Area** & **Supply** \\ \hline
[36, 39] & Large & \multirow{2}{*}{\(1.6\)} & \multirow{2}{*}{\(0.37\)} & \multirow{2}{*}{\(15\)} & \multirow{2}{*}{\(4.38\)} & \multirow{2}{*}{\(0.32\)} & \multirow{2}{*}{\(0.22\)} & \multirow{2}{*}{\(\text{Solar}\)} \\ (2002) & drone & & & & & & & \\ \hline
[36, 39] & Small & \multirow{2}{*}{\(1.2\)} & \multirow{2}{*}{\(0.4\)} & \multirow{2}{*}{\(10\)} & \multirow{2}{*}{\(3\)} & \multirow{2}{*}{\(0.12\)} & \multirow{2}{*}{\(0.06\)} & \multirow{2}{*}{\(\text{Solar}\)} \\ (2002) & drone & & & & & & & \\ \hline
[37] (2005) & Aircraft & \multirow{2}{*}{\(16.2\)} & \multirow{2}{*}{\(1.8\)} & \multirow{2}{*}{-} & \multirow{2}{*}{\(9\)} & \multirow{2}{*}{\(2.33\)} & \multirow{2}{*}{\(0.45\)} & \multirow{2}{*}{\(\text{Solar}\)} \\  & flight & & & & & & & \\ \hline
[40, 41] & \multirow{2}{*}{VAMP AV} & \multirow{2}{*}{-} & \multirow{2}{*}{-} & \multirow{2}{*}{\(900\)} & \multirow{2}{*}{\(55\)} & \multirow{2}{*}{-} & \multirow{2}{*}{-} &
\begin{tabular}{c} Solar and \\ ASRG \\ \end{tabular} \\ \hline
[19] (2015) & SESPA & - & \(0.4\) & - & \(3\) & - & - & Solar \\ \hline \hline \end{tabular}
\end{table} 
Table 2: Comparison between the parameters of Venus UAVs. If not anticipated beforehand, the produced shock waves significantly impact the rover's lift-generating capabilities. Because the air density on Mars is so low, rotating the rotor is greater while keeping the tip speeds subsonic is advantageous. The vehicle's hovering will be controlled in the same way any UAV flying under Earth settings. The suggested controller, specifically developed to manage the co-axial rotors, will handle the roll, pitch, and yaw movement instructions. The lower gravity value will assist the vehicle in remaining stable while flying and prevent tiny instabilities produced by unstable phugoids [43]. The suggested rotor blade size is 1.12 m, and when placed co-axially, two rotors spin in opposing directions.