Coupled landing gear and methods of use
A coupled landing gear apparatus for an aircraft including at least a nose gear disposed forward of a neutral point of an aircraft by a first distance and at least a main gear disposed aft of the neutral point of the aircraft by a second distance. The at least a nose gear and the at least a main gear are in communication with one another.
1. A blended wing body (BWB) aircraft with coupled landing gear apparatus, comprising:
a fixed-wing aircraft body having no demarcation between wings and a main body of the BWB aircraft at a leading edge of the wings;
at least a nose gear disposed forward of a neutral point of the BWB aircraft by a first distance, wherein the at least a nose gear comprises at least a nose hydraulic cylinder; and
at least a main gear disposed aft of the neutral point of the BWB aircraft by a second distance, wherein the at least a main gear comprises at least a main hydraulic cylinder;
wherein the at least a nose gear and the at least a main gear are hydraulically linked in hydraulic communication with one another, such that when the main hydraulic cylinder collapses the nose hydraulic cylinder extends while the coupled landing gear is on the ground during takeoff of the BWB aircraft, causing the front of the BWB aircraft to be raised and the rear of the BWB aircraft to be lowered and wherein:
the main hydraulic cylinder and the nose hydraulic cylinder are locked in a level position below a predetermined speed; and
the main hydraulic cylinder comprises a larger total piston surface area than a total piston surface area of the nose hydraulic cylinder, wherein the distance from the nose gear to a center of gravity of the fixed-wing aircraft body is larger than a distance of the main gear to the center of gravity of the fixed-wing aircraft body to produce hydro-mechanical equilibrium.
2. The BWB aircraft of claim 1 , wherein an extension of the nose hydraulic cylinder of the at least a nose gear, with respect to the BWB aircraft, increases an angle of attack of the BWB aircraft during take-off.
3. The BWB aircraft of claim 1 , wherein a communication between the at least a nose gear and the at least a main gear comprises an electromechanical communication.
4. The BWB aircraft of claim 1 , wherein the at least a nose gear and the at least a main gear are in communication through a longitudinal member.
5. The BWB aircraft of claim 1 , further comprising a controller configured to control an actuator connected to the at least a nose gear and control the at least a main gear to vary the angle of attack of the BWB aircraft.
6. The BWB aircraft of claim 1 , wherein the at least a nose gear and the at least a main gear are arranged in a tricycle arrangement.
7. The BWB aircraft of claim 1 , wherein the at least a nose gear and the at least a main gear are configured to move in opposition.
8. A method of using a coupled landing gear for a blended wing body (BWB) aircraft, the method comprising:
disposing a fixed-wing aircraft body having no clear demarcation between wings and a main body of the BWB aircraft at a leading edge of the wings;
disposing at least a nose gear forward of neutral point of the aircraft by a first distance, wherein the at least a nose gear comprises at least a nose hydraulic cylinder;
disposing at least a main gear aft of the neutral point of the BWB aircraft by a second distance, wherein the at least a main gear comprises at least a main hydraulic cylinder, and
wherein the at least a nose gear and the at least a main gear are hydraulically linked in hydraulic communication with one another, such that when the main hydraulic cylinder collapses the nose hydraulic cylinder extends while the coupled landing gear is on the ground during takeoff of the BWB aircraft, causing the front of the BWB aircraft to be raised and the rear of the BWB aircraft to be lowered and wherein:
the main hydraulic cylinder and nose hydraulic cylinder are locked in a level position below a predetermined speed; and
the main hydraulic cylinder comprises a larger total piston surface area than a total piston surface area of the nose hydraulic cylinder, wherein the distance from the nose gear to a center of gravity of the fixed-wing aircraft body is larger than a distance of the main gear to the center of gravity of the fixed-wing aircraft body to produce hydro-mechanical equilibrium.
9. The method of claim 8 , wherein an extension of the nose hydraulic cylinder of the at least a nose gear, with respect to the BWB aircraft, increases an angle of attack of the BWB aircraft during take-off.
10. The method of claim 8 , wherein a communication between the at least a nose gear and the at least a main gear comprises an electromechanical communication.
11. The method of claim 8 , wherein the at least a nose gear and the at least a main gear are in communication through a longitudinal member.
12. The method of claim 8 , further comprising controlling, by a controller, an actuator connected to the at least a nose gear and the at least a main gear to vary an angle of attack of the BWB aircraft.
13. The method of claim 8 , wherein the at least a nose gear and the at least a main gear are arranged in a tricycle arrangement.
14. The method of claim 8 , wherein the at least a nose gear and the at least a main gear are configured to move in opposition.