Mithad Dizdarevic

6923403, Aug 2, 2005

Mar 18, 2004

10/803307

Faruk Dizdarevic - Anaheim CA, US
Mithad Dizdarevic - Anaheim CA, US

B64C001/00

244 13, 244 36, 244117 R

The “Tailed Flying Wing Aircraft” idea represents new aerodynamic concepts for large high subsonic aircraft. Large high subsonic aircraft based on these new aerodynamic concepts are having a significantly higher lift capacity and longer range, as well as a significantly lower fuel consumption of at least two times less than the aircraft based on classical fuselage concept with the same external dimensions. In addition, the aircraft based on the new concepts are having a significantly better longitudinal stability and maneuverability, as well as aerodynamic efficiency at high subsonic speed than aircraft based on “Tailless Flying Wing” concepts. The aircraft based on the “Tailed Flying Wing Aircraft” idea satisfy all safety requirements for civil aircraft. They also have simple shapes for manufacturing, hence this idea provides for new realistic advanced aerodynamic concepts for the next generations of large subsonic aircraft.

7793884, Sep 14, 2010

Dec 31, 2008

12/347997

Faruk Dizdarevic - Anaheim CA, US
Mithad Dizdarevic - Anaheim CA, US

B64C 3/00

244 36, 244117 R, 244198

“T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with fuselage that have the same passenger capacity. T-tailed deltoid main wing aircraft is satisfying all safety requirements for a passenger aircraft while having over 50% longer range than the aircraft of equivalent capacity with fuselage. Simple aerodynamic and structural solutions of T-tailed deltoid main wing aircraft are resulting with low development risks and production cost. Simple and reliable flight control systems of aircraft that are based on T-tailed deltoid main wing aerodynamic configuration allow for design of all-purpose, high-lift-capacity, and long range unmanned aircraft.

7854409, Dec 21, 2010

Apr 21, 2010

12/764925

Faruk Dizdarevic - Anaheim CA, US
Mithad Dizdarevic - Anaheim CA, US

B64C 39/12

244 45A, 244 36, 244117 R

Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft.

8056852, Nov 15, 2011

Feb 21, 2011

13/031421

Faruk Dizdarevic - Anaheim CA, US
Mithad Dizdarevic - Anaheim CA, US

B64C 1/00

244 36, 244 55, 244 45 R

The Longitudinal Flying Wing aircraft idea provides for design of large cargo and passenger aircraft in range from low to high subsonic and transonic speed. Such aircraft would have up to twice lower fuel consumption per unit of payload, higher lift capacity, and a significantly longer range, while having a significantly lower level of noise inside passenger cabin and cockpit relative to classical concept aircraft. This idea is further providing for efficient, reliable, and simple flight controls, hence it may be successfully applied for design of all-size, long range, high-lift-capacity unmanned aircraft throughout the entire range of subsonic speeds.

6578798, Jun 17, 2003

Apr 8, 2002

10/118839

Faruk Dizdarevic - Anaheim CA, 92801
Mithad Dizdarevic - Anaheim CA, 92801

B64C 2306

244199, 244198, 244 91, 244 35 R

This airlifting surface division idea provides for division of airlifting surfaces resulting in low induced and interference drag. It can be applied to aircraft wings and helicopter and windmill rotor blades to significantly reduce induced drag when compared to prior art. Also, it can be used for new concepts of large subsonic and hypersonic aircraft to significantly reduce their overall drag and external dimensions when compared to prior art, simultaneously providing for very good pitch maneuver and longitudinal stability of such aircraft.

20200156787, May 21, 2020

Nov 18, 2018

16/194366

FARUK DIZDAREVIC - Anaheim CA, US
MITHAD DIZDAREVIC - Anaheim CA, US

B64C 39/08
B64C 3/32
B64C 3/10

The present invention is a double wing aircraft with two fixed wings embodied as either a flying wing configuration or a double wing configuration having a fuselage with smaller external dimensions, larger airlifting area, thinner airfoils, and lighter airframe relative to prior art that altogether is resulting with lower drag, fuel consumption, harmful emissions, and noise, as well as higher speed and flight safety, longer range, and shorter runway when compared to prior art.