Wing module for air vehicle with non-zero angular displacement pivot axes for first wing and second wing elements

A wing system for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system comprising at least one wing deployment module, each wing deployment module comprising:

• a set of wing elements, including at least a first said wing element having a first wing element longitudinal axis, and a second said wing element having a second wing element longitudinal axis;
• each said wing deployment module configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration;
• wherein in the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another;
• and
• wherein in the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis
• and wherein for each said wing deployment module:
• each said first wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said first wing element about a first module pivot axis by a non-zero first module angular displacement, and
• pivoting said first wing element about a first wing element pivot axis by a non-zero first wing element angular displacement;
• and
• each said second wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said second wing element about a second module pivot axis by a non-zero second module angular displacement;
• the wing system including a first said wing deployment module configured for being mounted to the air vehicle at a port side of the fuselage section, and a second said wing deployment module configured for being mounted to the air vehicle at a starboard side of the fuselage section.

A wing system for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system comprising at least one wing deployment module, each wing deployment module comprising:

• a set of wing elements, including at least a first said wing element having a first wing element longitudinal axis, and a second said wing element having a second wing element longitudinal axis;
• each said wing deployment module configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration;
• wherein in the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another;
• and
• wherein in the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis
• and wherein for each said wing deployment module:
• each said first wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said first wing element about a first module pivot axis by a non-zero first module angular displacement, and
• pivoting said first wing element about a first wing element pivot axis by a non-zero first wing element angular displacement;
• and
• each said second wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said second wing element about a second module pivot axis by a non-zero second module angular displacement;
• the wing system including one of:
• wherein for each said wing deployment module, the first wing element is configured as a horizontal stabilizer, and the second wing element is configured as a vertical stabilizer;
• or
• wherein for each said wing deployment module, the first wing element is configured as a horizontal stabilizer, and the second wing element is configured as a vertical stabilizer, and, wherein for each said wing deployment module, the first wing element comprises an actuable elevator, and the second wing element comprises an actuable rudder.

A wing system configured as an empennage for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system comprising:

• at least one wing deployment module, each wing deployment module comprising:
• a set of wing elements, including at least a first said wing element configured as a horizontal stabilizer and having a first wing element longitudinal axis, and a second said wing element configured as a vertical stabilizer having a second wing element longitudinal axis;
• each said wing deployment module configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration;
• wherein in the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another;
• wherein in the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis;
• wherein each said first wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said first wing element about a module pivot axis by a non-zero module angular displacement, and
• pivoting said first wing element about a first wing element pivot axis by a non-zero first wing element angular displacement;
• wherein each said second wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
• pivoting said second wing element about said module pivot axis by said non-zero module angular displacement.