Abstract: A mobile nest for unmanned aerial vehicles (UAVs) includes a cuboid-shaped frame, staging pads, charging electronics, and exterior siding. The cuboid-shaped frame includes vertical supports positioned at corners of the cuboid-shaped frame. The staging pads are adapted for landing, launching, and charging the UAVs. The staging pads are mounted to pivot about two or more of the vertical supports. Each of the staging pads rotates into the cuboid-shaped frame when stowed and rotates out of the cuboid-shaped frame when deployed for launching or landing the corresponding one of the UAVs. The charging electronics are disposed within the cuboid-shaped frame and coupled to the staging pads to charge the UAVs when the UAVs are positioned on the staging pads. The exterior siding is mounted to the cuboid-shaped frame to provide a weather barrier that protects the UAVs from weather when the UAVs are stowed within the mobile housing structure.

Abstract: An example unmanned aerial vehicle includes a power source, a processor module having one or more processors, and a plurality of boom arms, each boom arm being couplable to a printed circuit board (PCB) and a plurality of propellers. In the example UAV, a PCB of each boom arm includes a power hub electrically couplable to the power source and to corresponding propellers of the boom arm, and a signal hub electrically couplable to at least one processor of the processor module and to the corresponding propellers. Further, in the example UAV, the power hub of each PCB is configured to transfer power from the power source to the corresponding propellers, and wherein the signal hub of each PCB is configured to transfer signals from the processor module to the corresponding propellers such that the processor module controls the plurality of propellers.

Abstract: An example unmanned aerial vehicle includes a power source, a processor module having one or more processors, and a plurality of boom arms, each boom arm being couplable to a printed circuit board (PCB) and a plurality of propellers. In the example UAV, a PCB of each boom arm includes a power hub electrically couplable to the power source and to corresponding propellers of the boom arm, and a signal hub electrically couplable to at least one processor of the processor module and to the corresponding propellers. Further, in the example UAV, the power hub of each PCB is configured to transfer power from the power source to the corresponding propellers, and wherein the signal hub of each PCB is configured to transfer signals from the processor module to the corresponding propellers such that the processor module controls the plurality of propellers.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.