Self-tightening rotor

1. An aerial vehicle comprising:

(a) a first rotor comprising a first receptacle with a first passage extending through the first receptacle, a first plurality of rotor blades coupled to the first receptacle, a first insert having a first cap and a first body, and a first screw thread carried by the first insert, wherein at least a portion of the first insert is positioned in the first passage, the first cap is wider than at least a portion of the first passage, and the first cap extends from the first receptacle;

(b) a first support element coupled to a first motor, the first support element comprising a second screw thread, wherein the first motor is configured to rotate the first support element in a first direction;

(c) a second rotor comprising a second receptacle with a second passage extending through the second receptacle, a second plurality of rotor blades coupled to the second receptacle, a second insert having a second cap and a second body, and a third screw thread carried by the second insert, wherein at least a portion of the second insert is positioned in the second passage, the second cap is wider than at least a portion of the second passage, and the second cap extends from the second receptacle; and

(d) a second support element coupled to a second motor, the second support element comprising a fourth screw thread, wherein the second motor is configured to rotate the second support element in a second direction opposite the first direction;

wherein the first rotor is coupled to the first support element via a first mating connection between the first screw thread and the second screw thread, the first mating connection being tightened by rotation of the first support element in the first direction, and wherein the first plurality of rotor blades produces lift for the aerial vehicle when the first support element rotates in the first direction; and

wherein the second rotor is coupled to the second support element via a second mating connection between the third screw thread and the fourth screw thread, the second mating connection being tightened by rotation of the second support element in the second direction, and wherein the second plurality of rotor blades produces lift for the aerial vehicle when the second support element rotates in the second direction.

2. The aerial vehicle of claim 1 wherein the first support element is a drive shaft and the first screw thread is a male screw thread.

3. The aerial vehicle of claim 1 wherein the first screw thread is a female screw thread positioned in the first insert.

4. The aerial vehicle of claim 1 wherein the first receptacle is cylindrical.

5. The aerial vehicle of claim 1 wherein the first body is cylindrical.

6. The aerial vehicle of claim 1 wherein the first cap is a conical cap.

7. The aerial vehicle of claim 1 wherein the first body is integral with the first cap.

8. The aerial vehicle of claim 1 wherein at least one rotor blade of the first plurality of rotor blades is integral with the first receptacle.

9. The aerial vehicle of claim 1 wherein the first receptacle and the first plurality of rotor blades are formed from one or more plastic materials, and the first insert is formed from one or more metallic materials.

10. The aerial vehicle of claim 1 wherein the first plurality of rotor blades consists of two rotor blades.

11. An aerial vehicle comprising:

(a) a first rotor comprising a first receptacle with a first passage extending through the first receptacle, a first plurality of rotor blades coupled to the first receptacle, a first insert having a first conical cap and a first body, and a first fastening feature positioned in the first insert, wherein at least a portion of the first insert is positioned in the first passage, and the first conical cap extends from the first receptacle;

(b) a first drive shaft coupled to a first motor, the first drive shaft comprising a second fastening feature, wherein the first motor is configured to rotate the first drive shaft in a first direction;

(c) a second rotor comprising a second receptacle with a second passage extending through the second receptacle, a second plurality of rotor blades coupled to the second receptacle, a second insert having a second conical cap and a second body, and a third fastening feature positioned in the second insert, wherein at least a portion of the second insert is positioned in the second passage, and the second conical cap extends from the second receptacle; and

(d) a second drive shaft coupled to a second motor, the second drive shaft comprising a fourth fastening feature, wherein the second motor is configured to rotate the second drive shaft in a second direction opposite the first direction;

wherein the first rotor is coupled to the first drive shaft via a first mating connection between the first fastening feature and the second fastening feature, the first mating connection being tightened by rotation of the first drive shaft in the first direction, and wherein the first plurality of rotor blades produces lift for the aerial vehicle when the first drive shaft rotates in the first direction; and

wherein the second rotor is coupled to the second drive shaft via a second mating connection between the third fastening feature and the fourth fastening feature, the second mating connection being tightened by rotation of the second drive shaft in the second direction, and wherein the second plurality of rotor blades produces lift for the aerial vehicle when the second drive shaft rotates in the second direction.

12. The aerial vehicle of claim 11 wherein each of the first fastening feature and the second fastening feature comprises a screw thread.

13. The aerial vehicle of claim 11 wherein the aerial vehicle is an unmanned aerial vehicle.

14. The aerial vehicle of claim 11 wherein the first body is cylindrical.

15. The aerial vehicle of claim 11 wherein the first body is integral with the first conical cap.

16. An aerial vehicle, comprising:

(a) an aerial vehicle body;

(b) a first drive unit carried by the aerial vehicle body, and including a first drive shaft, the first drive shaft carrying a first male screw thread;

(c) a second drive unit carried by the aerial vehicle body, and including a second drive shaft, the second drive shaft carrying a second male screw thread;

(d) a first rotor comprising a first receptacle with a first passage extending through the first receptacle, a first plurality of rotor blades coupled to the first receptacle, a first insert having a first cap and a first body, and a first female screw thread positioned in the first insert, wherein the first insert is positioned at least partially in the first passage and extends from the first receptacle; and

(e) a second rotor comprising a second receptacle with a second passage extending through the second receptacle, a second plurality of rotor blades coupled to the second receptacle, a second insert having a second cap and a second body, and a second female screw thread positioned in the second insert, wherein the second insert is positioned at least partially in the second passage and extends from the second receptacle;

wherein the first drive shaft is configured to cause rotation of the first rotor in a first direction to produce a first propulsive force for the aerial vehicle using the first plurality of rotor blades, and the second drive shaft is configured to cause rotation of the second rotor in a second direction opposite the first direction, to produce a second propulsive force for the aerial vehicle using the second plurality of rotor blades; and wherein

the first rotor is configured to be coupled to the first drive shaft via a first mating connection between the first female screw thread and the first male screw thread, wherein the first mating connection is configured to be tightened by rotation of the first rotor relative to the first drive shaft in the second direction; and wherein

the second rotor is configured to be coupled to the second drive shaft via a second mating connection between the second female screw thread and the second male screw thread, wherein the second mating connection is configured to be tightened by rotation of the second rotor relative to the second drive shaft in the first direction.

17. The aerial vehicle of claim 16 wherein the first cap is a conical cap.

18. The aerial vehicle of claim 16 wherein the first cap and the first body are integral.

19. The aerial vehicle of claim 16 , further comprising one or more third rotors.

20. The aerial vehicle of claim 16 wherein the first drive unit comprises a motor.