초록 ▼

A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The

A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The first thruster serves to direct a thrust of air at an angle toward an area directly below the fuselage. The second thruster is angularly directed so as to direct the thrust of air at an angle toward the area directly below the fuselage. The propulsion system serves to propel the fuselage through the air. Each of the thrusters is a jet engine. Each of the thrusters can be angularly moveable between a vertical position and an acute angle with respect to a plane of the wings.

대표청구항 ▼

A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The

A VTOL aircraft having a fuselage, a first wing extending from one side of the fuselage, a second wing extending from an opposite side of the fuselage, a first thruster supported on the first wing, a second thruster supported on the second wing and a propulsion system connected to the fuselage. The first thruster serves to direct a thrust of air at an angle toward an area directly below the fuselage. The second thruster is angularly directed so as to direct the thrust of air at an angle toward the area directly below the fuselage. The propulsion system serves to propel the fuselage through the air. Each of the thrusters is a jet engine. Each of the thrusters can be angularly moveable between a vertical position and an acute angle with respect to a plane of the wings. one or more of the thrusters to cause a correcting thrust normal to the longitudinal axis of the projectile via a signal from the microprocessor corresponding to the acceleration data to correct for the projectile jump. 7. The jump correcting projectile method of claim 6 comprising: i) determining an initial velocity (Vi) of the projectile; ii) determining acceleration data of said projectile with the accelerometers during and after launching the projectile until it disengages from the launch platform; and transmitting said data from the accelerometers to the microprocessor; iii) determining a net normal velocity (Vn) of the projectile from the acceleration data; iv) dividing the determined net normal velocity by the initial velocity (VnVi) to calculate Vx; and v) determining the arctangent of Vx via said microprocessor to calculate any angular deviation of said projectile from the pre-launch initial target direction. 8. The jump correcting projectile method of claim 6 further comprising mounting at least one roll rate sensor along the central longitudinal axis of the projectile, said roll rate sensor being attached to said microprocessor. 9. The jump correcting projectile method of claim 6 wherein said at least one pair of accelerometers are mounted along the central longitudinal axis of the projectile at the center of gravity of the projectile.