초록 ▼

Aircraft having subsonic and supersonic flight capabilities which utilize travelling tail units with circular arc motions, connected with the rear fuselage by means of two arm-frames that swing upward and rearward and vice versa, to generally increase stability and control of aircraft during low-spe

Aircraft having subsonic and supersonic flight capabilities which utilize travelling tail units with circular arc motions, connected with the rear fuselage by means of two arm-frames that swing upward and rearward and vice versa, to generally increase stability and control of aircraft during low-speed flight and to reduce accidents at zero altitude operations.

대표청구항 ▼

An aircraft having a travelling tail unit which is movable in longitudinal direction of aircraft by means of circular arc motions comprising: a fuselage (1), a pair of fixed wings (2) with ailerons, landing flaps, slats, jet engines (3; 23; 33) mounted on said aircraft, a startbooster jet engine (13

An aircraft having a travelling tail unit which is movable in longitudinal direction of aircraft by means of circular arc motions comprising: a fuselage (1), a pair of fixed wings (2) with ailerons, landing flaps, slats, jet engines (3; 23; 33) mounted on said aircraft, a startbooster jet engine (13) accommodated inside of the aft end of said fuselage, a tail unit being composed of a tail unit-chassis (4a; 4b) having a longitudinal and airflow suitable shape and at least two tail surfaces, the parts of said tail unit forming a common monocoque construction, a. the said tail unit being substantially moved along the path of a circular arc upwards and rearwards into the rearward position increasing the effective tail unit lever for low-speed flight and particularly for takeoff and landing operations, b. the said tail unit being substantially moved along the path of a circular arc forwards and downwards into the forward position for high-speed flight, c. the said tail unit in its forward high-speed flight position being placed in a horizontal distance behind the trailing edges of said wings, from which forward position the said tail unit is moved rearwards into the position for low-speed flight and vice versa (FIG. 1; FIG. 2; FIG. 4 and FIG. 5), d. the said tail unit-chassis being connected with the aft end of said fuselage by means of two front swivel arms (11 with positions 11a and 11b) and two hind swivel arms (12 with positions 12a and 12b), e. the said two front swivel arms (11) being with each other connected by means of crossbeams (26) into a front swivel arm-frame (FIG. 12), and the said two hind swivel arms (12) being with each other connected by means of crossbeams (26) into a hind swivel arm-frame (analogous to FIG. 12), both said frames having rigid frame corners, f. the said swivel arm-frames lying with their frame planes substantially transversally to the direction of flight, g. the said swivel arm-frames having hinges on their corners, particularly each said swivel arm-frame having two lower hinges (24) on its two lower corners connecting said swivel arm-frame with the aft end of said fuselage and two upper hinges (25) on its two upper corners connecting said swivel arm-frame with said tail unit-chassis (FIG. 2; FIG. 5 and FIG. 9 to FIG. 12), h. the said tail unit-chassis in its forward high-speed flight position (4a) being joined in an airflow suitable manner to said aft end of said fuselage, i. the said tail unit-chassis in its forward high-speed flight position (4a) being used as an airflow suitable fairing for said startbooster jet engine (13) when it is stopped during high-speed flight (FIG. 2; FIG. 3 and FIG. 5 to FIG. 9), whereas said tail unit-chasses moved into its rearward low-speed flight position (4b) uncovers the air intake (14) and propelling nozzle of said startbooster jet engine, which put into operation (15) increases the takeoff thrust or the zoom away thrust of the air-craft (FIG. 10), increases the propulsion redundancy, makes thE design of the main jet engines simpler, especially for supersonic aircraft, and being specially adpated to zero altitude conditions, reduces the fuel consumption, and makes the exhaust emissions on airfields cleaner, j. the said tail unit being moved rearwards and forwards by means of actuators (21 and 22) coupled with at least one of said swivel arm-frames (FIG. 10 and FIG. 11), k. the said tail unit having control linkages continuously connecting the flight control means with the contol surfaces of said tail unit (FIG. 11 and FIG. 12), and each said control linkage is transmitting a separate control command to a separate control surface, l. the said startbooster jet engine (13) having its air intake through the inner opening of said front swivel arm-frame, and its propelling nozzle positioned inside of the inner opening of said hind swivel arm-frame (FIG. 9 and FIG. 10), m. the said tail unit arrangement having a crossbond (20) consisting of two rods in X-shape and being horizontally inserted into the front end of the upper cutout of the rear fuselage, diagonally connecting the left front end of the fuselage cutout with the right and rear fuselage side wall, and the right front end of the fuselage cutout with the left and rear fuselage side wall, penetrating the inner opening of said front swivel arm-frame (FIG. 1; FIG. 4; FIG. 10 and FIG. 12), whilst said cross-bond is increasing the torsional stiffness of said fuselage aft end, n. the said fuselage (1) having a channel (16) in its rear bottom side.