Missed our webinar on improving UAV Performance? Click here to watch the recording.

This section doesn’t currently include any content. Add content to this section using the sidebar.

Image caption appears here

Add your deal, information or promotional text

This section doesn’t currently include any content. Add content to this section using the sidebar.

Image caption appears here

Add your deal, information or promotional text

The Best Coaxial Rotor Design for UAVs

Report by Jean Schmitt

Many UAVs are designed with dual motor or coaxial propulsion systems. There are several variables to consider when designing such systems, such as relative propeller size, speed, and inter-rotor distance. Making the right design decisions allows you to build the highest performing UAV possible - in terms of thrust, torque and efficiency.

We recently completed a study comparing various dual motor and coaxial rotor configurations. We compared the effect of inter-rotor distance, propeller size and relative propeller speed on total thrust and torque generated as well as propeller and propulsion system efficiency. We believe that these results are pertinent to all unmanned aircraft designers, as they can inform better vehicle designs resulting in higher efficiency and performance.

coaxial drone

Introduction

This report summarizes our findings on physical interactions between rotors during coaxial tests with a focus on the influence of the front rotor on the rear rotor. We quantified the effects of distance between rotors, rotation speed, and propeller diameter.

We used two Flight Stand 50 test stands for the tests, which measure up to 50 kgf of thrust and 30 Nm of torque, as well as RPM, voltage, current, mechanical power, electrical power, propeller efficiency, motor efficiency, and overall propulsion system efficiency. During the coaxial tests, two Flight Stands were placed back to back on a rail system, with a brushless motor and propeller mounted on each of the stands’ force measurement units (FMUs).

The two propellers were set-up to rotate in opposite directions so that the torques of the motors would compensate one another and balance the structure. In a UAV, this coaxial set-up helps to avoid in-flight vertical axis rotation caused by torque. The rear propeller was inverted to make sure that the airflow generated was in the same direction as the airflow generated by the front propeller (figure 1).

For the tests where distance between rotors was varied, the distance was measured between the two FMUs.

coaxial rotor setup
Figure 1: The coaxial testing set-up

How Propeller Speed and Rotor Separation Affect Thrust and Torque Generation

We first studied the effects of rotation speed and rotor separation distance on the thrust and torque produced by rotor 2 (R2) in the rear position. We anticipated that the performance of R2 would be affected by rotor 1 (R1) since it is located directly in the airflow generated by R1.

We completed the first set of tests with R1 rotating at two different speeds: 1600 and 2200 RPM. We also repeated the tests at four different separation distances: 10, 30, 50 and 70 mm. The results are shown in figure 2 and 3.

drone speed thrust graph

Figure 2: R2 thrust vs. speed at four coaxial separations and two R1 speeds

Figure 2 shows the evolution of R2 thrust as a function of R2 speed, at various R1 speeds and separation distances. As you can see, two groups of curves form, each representing a different R1 speed. The thrust of R2 was lower at all separation distances and R2 speeds when R1 was rotating at the faster 2200 RPM.

uav torque speed graph

Figure 3: R2 torque vs. speed at four coaxial separations and two R1 speeds

Figure 3 shows the evolution of R2 torque as a function of R2 speed, at the same R1 speeds and separation distances as the previous test. Again, two groups of curves form, defined by R1 speed. As with thrust, the torque of R2 was lower when R1 was rotating at 2200 RPM. 

For both thrust and torque, it does not appear that the distance between rotors has a significant effect on the thrust generated by R2. In general, we can conclude that an increase in the front rotor (R1) rotation speed reduces the amount of thrust and torque generated by the rear rotor (R2).

Further reading: Brushless Motor Power and Efficiency Analysis

Impact of Front Propeller Size on Thrust and Torque Generation

In the previous section we learned that an increase in R1 rotation speed leads to a decrease in the thrust and torque produced by R2. We wanted to see how this phenomenon was affected by changing the size of the front propeller.

40 inch propeller thrust vs speed

47" propeller thrust vs. speed

Figure 4: R2 thrust vs. speed with 40” front propeller (top) and 47” front propeller (bottom)

Figure 4 shows the thrust generated by R2 as a function of R2 speed, at four different R1 speeds. The top graph shows results for a 40" front propeller and the bottom graph a 47" front propeller. As anticipated, the 47” propeller generated more thrust than the 40” propeller at all R1 and R2 speeds.

A decrease in R2 thrust was observed with both propeller sizes as R1 speed increased from 1600 to 2200 RPM. We observed a similar decline in torque (data not shown). The decline in R2 thrust appeared to be greater for the 47” R1 propeller, demonstrated by the greater spread between points at 1600 RPM and 2200 RPM.

To determine whether this difference was significant, we calculated the difference in R2 thrust between R1 speeds 1600 and 2200 RPM, for all R2 speeds. R2 is always equipped with a 47” propeller.

uav rotor thrust at different separation distances

Figure 5: R2 thrust difference vs. R2 speed

At all four R2 speeds, the difference in R2 thrust between R1 at 1600 and 2200 RPM was larger for the 47” propeller. Interestingly, the difference is most noticeable at 1600 and 2200 RPM at either end of the R2 speed spectrum. In general, it appears that the larger 47” R1 propeller has a greater impact on R2 thrust. 

We have two hypotheses for why this might be happening.

Hypothesis 1: the airflow generated by the front propeller applies a force on the rear propeller. This resistive load, which is oriented opposite to the force generated by the thrust of R1 (figure 6), is measured by the FMU. As a consequence, the resistive load is subtracted from the raw thrust value that is recorded.

There is 100% overlap between the two propellers when R1 is equipped with a 47” propeller, which declines to 72% overlap when R1 has a 40” propeller. In other words, only 72% of the R2 propeller surface is covered by the 40” propeller. It thus appears that the bigger the overlap, the greater the decline in thrust will be, perhaps due to a greater resistive load.

coaxial rotor mechanism

Figure 6: The thrust and resistive forces experienced by R1 and R2

Hypothesis 2: R1 generates turbulence, and the induced drag counters the thrust and the torque generated by R2. We know this drag exists because of the windmilling effect observed when throttle is applied to R1 but not R2. The faster R1 rotates, the more drag is generated and a more significant loss of thrust will be observed.

When throttle is applied to the front rotor, causing it to rotate, the rear propeller will turn without any throttle. The faster R1 rotates, the higher airspeed from R1 will act on R2 and drag it to rotate at higher and higher speeds. The torque is negative because what is measured is the resistive torque in the motor, which aims at braking the rotation of the propeller. It is induced by the drag generated by the airflow from R1.

Such a reaction can be seen when there is no electrical power input: R2 self-rotates and becomes kind of a wind-turbine (figure 7).

uav rotor aerodynamics

Figure 7:  Aerodynamic forces causing windmilling in a rotor blade (source: semanticscholar.org)

The 3D plot in figure 8 shows how R2 torque evolves as R1 and R2 speeds are varied. The blue and yellow sheets were interpolated from the data points shown. 

The blue plot shows the evolution of the torque at a 10 mm separation distance between rotors whereas the yellow plot shows torque at a 25 mm distance. This chart demonstrates the presence of negative torque when little or no throttle is applied to R2.

torque in coaxial rotors graph

Figure 8: Evolution of the R2 torque depending on the rotors speed (10mm blue 25mm yellow)

Propeller efficiency

Propeller efficiency is one of the main indicators of rotor performance as it measures the amount of thrust generated relative to the power input.

We studied how propeller efficiency evolved in relation to rotation speed and separation distance between rotors. In figure 9, R2 propeller efficiency is plotted against R2 speed on the x-axis. Each curve represents a different combination of R1 speed (1600 vs. 2200 RPM), and separation distance (10, 30, 50 or 70 mm). Measurements were taken at R2 speeds 1200, 1400, 1600, 1800, 2000 and 2200 RPM, and the curves are interpolated based on these points.

propeller efficiency graph

Figure 9: R2 propeller efficiency as a function of speed and separation distance

As we can see, two groups of curves form, separated by R1 rotation speed. At all R2 speeds and separation distances, R2 has a higher propeller efficiency for the higher R1 speed of 2200 RPM.

For the curves where R1 rotates at 2200 RPM, there is a decline in R2 propeller efficiency over the full range of R2 speeds. When R1 is at 1600 RPM, there is a peak in R2 efficiency around R2 at 1450 RPM, followed by a gradual decline parallel to the other set of curves for the higher R1 speed.

At high speeds, inter-rotor distance plays a negligible effect on R2 propeller efficiency. At lower speeds for both R1 and R2, the smaller separation distance is associated with higher efficiency. This difference is more prominent at low R1 and R2 speeds compared to when R1 speed is high and R2 speed is low. The effect becomes visible when R2 rotates at and below ~1750 RPM.

The propeller efficiency is calculated as the thrust generated divided by the mechanical power of the propeller (propeller rotation speed multiplied by the torque).

propeller efficiency formula

Where:

ηp = the propeller efficiency (gf/W)
Fth = the thrust force (gf)
𝒯= the torque (N.m)
ω = the rotation speed (rad/s)

Conclusion

In conclusion, this study allowed us to observe the effects of several variables on the performance of coaxial rotor systems. We learned that the front rotor has a considerable impact on the rear rotor.

Our study provided several key takeaways: 

  1. In a coaxial setup, the rear propeller’s performance is impacted by more aerodynamic effects than the front propeller.
  2. In a coaxial setup, the greater the overlap between propellers (%), the more loss of thrust will be observed in the rear propeller.
  3. A negative thrust and torque, as well as a self-rotation effect, can be observed in the rear propeller under the influence of the front propeller.
  4. The coaxial distance between the propellers has limited impact on the performance of the rear propeller. 
  5. The fluid velocity, generated by the front propeller and related to its rotation speed, has a dominant effect on the rear propeller’s performance.
  6. Due to the drag effect on the rear propeller, the downwind rotor can rotate at the same speed with a smaller amount of torque, therefore making it more efficient compared to a single-motor operation.

Further reading: How to Test Brushless Motors

 

Please let us know in the comments what you would like us to study next!

Leave a comment

Comments will be approved before showing up.

Search