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 (“T/V”) module and a second T/V module, and an electronics mo

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 (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V 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 T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

대표청구항 ▼

1. A folding airframe, the folding airframe comprising: a plurality of integrated hinges, each of said plurality of integrated hinges defining a fold line;a locking mechanism configured to lock the folding airframe in a deployed position, wherein the locking mechanism comprises a rod configured to a

1. A folding airframe, the folding airframe comprising: a plurality of integrated hinges, each of said plurality of integrated hinges defining a fold line;a locking mechanism configured to lock the folding airframe in a deployed position, wherein the locking mechanism comprises a rod configured to attach to an edge of the folding airframe via at least one clip when in the deployed position,wherein the edge of the folding airframe defines a recess configured to receive at least a portion of said rod when in the deployed position; andat least one passive retention device for securing one or more flight components to the folding airframe, wherein said one or more flight components are configured to eject from the folding airframe upon a sudden impact. 2. The folding airframe of claim 1, wherein said at least one passive retention device is a permanent magnet. 3. The folding airframe of claim 1, wherein one or more magnets are positioned at each fold line to increase airframe rigidity when in the deployed position. 4. The folding airframe of claim 1, wherein the folding airframe does not comprise a control surface. 5. The folding airframe of claim 1, wherein the folding airframe is fabricated using expanded polypropylene foam. 6. A folding airframe, the folding airframe comprising: a plurality of integrated hinges, each of said plurality of integrated hinge defining a fold line; a locking mechanism configured to lock the folding airframe in a deployed position, wherein the locking mechanism comprises a rod configured to attach to an edge of the folding airframe via at least one magnet when in the deployed position; andat least one passive retention device for securing one or more flight components to the folding airframe, wherein said one or more flight components are configured to eject from the folding airframe upon a sudden impact. 7. The folding airframe of claim 6, wherein said at least one passive retention device is a permanent magnet. 8. The folding airframe of claim 6, wherein one or more magnets are positioned at each fold line to increase airframe rigidity in the deployed position. 9. The folding airframe of claim 6, wherein the folding airframe does not comprise a control surface. 10. The folding airframe of claim 6, wherein the folding airframe is fabricated using expanded polypropylene foam. 11. An aerial vehicle comprising: one or more flight components;a folding airframe, the folding airframe having (1) an integrated hinge defining a fold line, and (2) a locking mechanism configured to lock the folding airframe in a deployed position, wherein the locking mechanism comprises a rod configured to attach to an edge of the folding airframe via at least one clip when in the deployed position, wherein the edge of the folding airframe defines a recess configured to receive at least a portion of said rod when in the deployed position; and one or more passive retention devices for securing said one or more flight components to said folding airframe, wherein said one or more flight components are configured to eject from the folding airframe upon a sudden impact. 12. The aerial vehicle of claim 11, wherein the folding airframe is fabricated using a low-cost material. 13. The aerial vehicle of claim 11, wherein the folding airframe is fabricated using expanded polypropylene foam. 14. The aerial vehicle of claim 11, wherein at least one of said one or more passive retention devices is a permanent magnet. 15. The aerial vehicle of claim 11, wherein at least one of said one or more flight components is an electronics module. 16. The aerial vehicle of claim 11, wherein at least one of said one or more flight components is a thrust-vectoring module. 17. The aerial vehicle of claim 16, wherein said 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 position of the electric motor. 18. The aerial vehicle of claim 11, wherein the folding airframe does not comprise a control surface. 19. The aerial vehicle of claim 11, wherein the locking mechanism comprises a second rod configured to attach to a second edge of the folding airframe when in the deployed position. 20. The aerial vehicle of claim 11, wherein the rod is stored within the folding airframe when the folding airframe is not in a deployed position.