Tilt-frame UAV for agricultural air sampling with a propeller-thrust-governing system that facilitates VTOL capability

1. An aircraft, which is capable of vertical takeoff and landing, comprising:

a fuselage;

a probe-deployment mechanism located at a front end of the fuselage, wherein:

the probe-deployment mechanism is configured to deploy a sample-gathering probe; and

when the aircraft is pitched up, the front end of the fuselage sits higher than a rear end of the fuselage to allow the probe-deployment mechanism to extend higher;

a main wing coupled to a middle section of the fuselage;

a right motor and associated right propeller coupled to a right side of the main wing;

a right propeller-thrust-governing system (PTGS) located in proximity to the right propeller;

a left motor and associated left propeller coupled to a left side of the main wing;

a left PTGS located in proximity to the left propeller; and

a pitch motor and associated pitch propeller located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage;

wherein:

each PTGS comprises a pair of adjustable butterfly flaps located in an airflow of an associated propeller;

each pair of butterfly flaps includes a front flap and a rear flap; and

the front flap and rear flap open in opposing directions.

2. The aircraft of claim 1 , wherein the probe-deployment mechanism includes an extendable boom, which extends the sample-gathering probe away from the aircraft.

3. The aircraft of claim 1 , wherein the sample-gathering probe is configured to sample volatile organic compounds (VOCs).

4. The aircraft of claim 1 , wherein the aircraft further comprises one or more landing supports, which support the aircraft after a vertical landing so that the front end of the fuselage sits higher than the rear end of the fuselage, which facilitates extending the sample-gathering probe above and away from the aircraft.

5. The aircraft of 4 , wherein the one or more landing supports include the following three landing supports:

a right leg extending from the middle section of the fuselage;

a left leg extending from the middle section of the fuselage; and

a tail support extending from the rear end of the fuselage.

6. The aircraft of claim 1 , further comprising:

wherein the right and left PTGSs are adjustable to reduce and/or redirect thrust from the associated right and left propellers.

7. The aircraft of claim 6 , wherein by reducing and/or redirecting thrust from the left and right propellers, the left and right PTGSs control a roll-axis rotation and a yaw-axis rotation for the aircraft during horizontal flight.

8. The aircraft of claim 1 , wherein: the left motor, the right motor and the pitch motor comprise a tri-motor system,

the left and right motors generate thrust and control roll-axis and yaw-axis rotations for the aircraft, and

the pitch motor controls a pitch-axis rotation for the aircraft.

9. The aircraft of claim 1 , wherein the right and left propellers are fixedly attached to the main wing so that the angles of the right and left propellers cannot change with respect to the fuselage.

10. The aircraft of claim 1 , wherein the pitch motor comprises a variable-speed motor.

11. The aircraft of claim 1 , wherein the aircraft comprises an unmanned aerial vehicle (UAV).

12. The aircraft of claim 1 , wherein:

the front flap of each pair of butterfly flaps controls yaw motion of the aircraft; and

the rear flap of each pair of butterfly flaps controls roll motion of the aircraft.