초록 ▼

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electroni

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust vectoring module and a second thrust vectoring module, and an electronics module. The electronics module provides commands to the two thrust vectoring modules. The two thrust vectoring modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as thrust vectoring modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

대표청구항 ▼

1. An aircraft comprising: an airframe, said airframe having a first section and a second section, wherein the first section is foldably connected to the second section;a thrust vectoring module, wherein said thrust vectoring module is attached to the airframe by a first non-destructive integrated b

1. An aircraft comprising: an airframe, said airframe having a first section and a second section, wherein the first section is foldably connected to the second section;a thrust vectoring module, wherein said thrust vectoring module is attached to the airframe by a first non-destructive integrated breakaway mount, andwherein said thrust vectoring module is independently articulable with respect to a portion of the airframe to which it is attached; andan electronics module attached to the airframe by a second non-destructive integrated breakaway mount. 2. The aircraft of claim 1, wherein the electronics module is configured to provide commands to the thrust vectoring module based at least in part on instructions received from a user. 3. The aircraft of claim 2, wherein the thrust vectoring module is magnetically connected to the airframe. 4. The aircraft of claim 3, wherein the aircraft is an unmanned aerial vehicle. 5. The aircraft of claim 4, wherein the thrust vectoring module comprises (i) a propeller, (ii) an electric motor configured to rotate the propeller to generate a thrust vector, and (iii) a positioning device configured to direct the thrust vector by adjusting the electric motor's position. 6. The aircraft of claim 5 further comprising one or more fins. 7. The aircraft of claim 6 further comprising one or more landing skids. 8. The aircraft of claim 7, wherein at least one of said one or more landing skids is connected to (i) at least a portion of said first section, and (ii) at least a portion of said second section. 9. An aircraft for unmanned aviation, comprising: an airframe having one or more fixed wing portions;a plurality of fins attached to the airframe;at least a first thrust vectoring module and a second thrust vectoring module, wherein said first thrust vectoring module and said second thrust vectoring module are attached to at least one of said one or more fixed wing portions by a non-destructive integrated breakaway mount,wherein each of said first thrust vectoring module and said second thrust vectoring module is independently articulable with respect to a portion of the fixed wing portion to which it is attached; andan electronics module configured to provide commands to said first thrust vectoring module and said second thrust vectoring module. 10. The aircraft of claim 9, wherein the electronics module is configured to provide commands to said first thrust vectoring module and said second thrust vectoring module based at least in part on instructions received from a user. 11. The aircraft of claim 10, wherein the electronics module is attached to the airframe by a non-destructive integrated breakaway mount. 12. The aircraft of claim 11, wherein the electronics module is magnetically attached to the airframe. 13. The aircraft of claim 9, wherein said first thrust vectoring module and said second thrust vectoring module each comprise (i) a propeller, (ii) an electric motor configured to rotate the propeller to generate a thrust vector, and (iii) a positioning device configured to direct the thrust vector by adjusting the electric motor's position. 14. The aircraft of claim 13, wherein said first thrust vectoring module and said second thrust vectoring module are magnetically attached to at least one of said one or more fixed wing portions. 15. The aircraft of claim 13 further comprising one or more landing skids. 16. An aerial vehicle comprising: a disposable frame;a thrust vectoring module, wherein said thrust vectoring module is attached to the disposable frame by a first non-destructive integrated breakaway mount; andwherein said thrust vectoring module is independently articulable with respect to a portion of the disposable frame to which it is attached;an electronics module attached to the disposable frame by a second non-destructive integrated breakaway mount, wherein said electronics module is configured to provide commands to the thrust vectoring module based at least in part on instructions received from a user. 17. The vehicle of claim 16, wherein the disposable frame is foldable. 18. The vehicle of claim 17, wherein the vehicle is an unmanned aerial vehicle. 19. The vehicle of claim 18 further comprising one or more landing skids. 20. The vehicle of claim 19 further comprising one or more fins.