Introduction to UAV Systems. Mohammad H. Sadraey

Introduction to UAV Systems - Mohammad H. Sadraey


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bird can make the negative thrust during the up stroke even smaller by bending its wings during the up stroke, as shown in Figure 3.22. This largely eliminates the forces induced by the outer portions of the wings, which are the most important contributors to thrust, while preserving much of the lift produced near the wing roots.

Schematic illustration of wing articulation.

      This simplified description of how flapping wings can allow a bird to fly is as far as we are going to go in this introductory text. There are some significant differences between how birds fly and how insects fly, and not all birds fly in exactly the same way. In the early days of heavier‐than‐air flight, there were many attempts to use flapping wings to lift a human passenger. All were unsuccessful. As interest has increased in recent years in small, even tiny, UAVs, the biomechanics of bird and insect flight are being closely re‐examined and recently have been successfully emulated by machines.

      One of the important parameters in a cruising flight is the aerodynamic efficiency. This parameter is directly a function of the aircraft lift‐to‐drag ratio. One of the objectives in aerodynamic design of an air vehicle is to produce the maximum lift with a minimum drag. The aerodynamic efficiency of an air vehicle relies heavily on the section of its wing/tail; that is “airfoil.”

      Using the equations for lift and drag, one can readily prove the following relation for the maximum lift‐to‐drag ratio:

      (3.15)left-parenthesis StartFraction upper L Over upper D EndFraction right-parenthesis Subscript max Baseline equals left-parenthesis StartFraction upper C Subscript normal upper L Baseline Over upper C Subscript normal upper D Baseline EndFraction right-parenthesis Subscript max

      The lift versus drag curve is further discussed in Section 3.5. Reference [12] has derived the following expression for the maximum lift‐to‐drag coefficients ratio:

      With this relationship, one is able to evaluate the maximum lift‐to‐drag ratio of any aircraft. The only necessary information is the aircraft zero lift drag coefficient (CDo) and the induced drag correction factor (K). Graphically, the maximum L/D corresponds to the slope of the tangent to the CDCL figure (drag polar), which is shown in Figures 3.7 and 3.13. Figure 3.7 shows the two‐dimensional drag coefficient (Cd) and the moment coefficient as a function of the lift coefficient (Cl) for the NACA 23021 airfoil.

      Aerodynamic efficiency (ηE) is defined as the ratio of the difference between lift and drag over the lift:

      (3.17)eta Subscript normal upper E Baseline equals StartFraction upper L minus upper D Over upper L EndFraction

      In a cruising flight, lift is equal to the aircraft weight (L = W). Thus,

      (3.18)eta Subscript normal upper E Baseline equals StartFraction upper W minus upper D Over upper W EndFraction

      The maximum aerodynamic efficiency is

      As a conclusion, in order to increase the air vehicle maximum aerodynamic efficiency, one must: (1) decrease the aircraft zero lift drag coefficient and (2) increase the wing aspect ratio. High aspect ratio wings (long and slender) are conducive to good range and endurance. Short stubby (low AR) wings generate low aerodynamic efficiency (i.e., penalize the length of time‐on‐target during reconnaissance missions), but are good for highly maneuverable fighters.

      The wing aspect ratio for the MALE UAV General Atomics MQ‐1 Predator (see Figure 11.1) wing is about 22.5, while for the HALE UAV Northrop Grumman RQ‐4 Global Hawk (see Figure 1.4) wing is about 25. The wing aspect ratio for the small UAV AeroVironment RQ‐11 Raven (see Figure 18.11) is 3.7.

      Example 3.1

      A MALE UAV with a turbofan engine has a zero‐lift drag coefficient of 0.021 and an induced drag factor of 0.04. Determine the maximum aerodynamic efficiency of the air vehicle.

      Solution:

      from (3.16)left-parenthesis StartFraction upper C Subscript normal upper L Baseline Over upper C Subscript normal upper D Baseline EndFraction right-parenthesis Subscript max Baseline equals StartFraction 1 Over 2 StartRoot upper K upper C Subscript normal upper D Sub Subscript normal o Subscript Baseline EndRoot EndFraction equals StartFraction 1 Over 2 StartRoot 0.04 times 0.021 EndRoot EndFraction equals 17.2

      from (3.19)eta Subscript upper E max Baseline equals 1 minus StartFraction 1 Over left-parenthesis upper L slash upper D right-parenthesis Subscript max Baseline EndFraction equals 1 minus StartFraction 1 Over 17.2 EndFraction equals 0.942 equals 94.2 percent-sign

      1 Define aerodynamics.

      2 Name primary forces that act on an air vehicle.

      3 Name elements that make considerable contributions on air vehicle’s aerodynamic features.

      4 What is the primary aerodynamic function of a wing?

      5 Name two aerodynamic forces.

      6 The aerodynamic forces of lift and drag are functions of a number of factors. What are they?

      7 Define lift.

      8 Draw


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