	US 8,328,128 C1 (13,149th)
	Aircraft
Burkhard Wiggerich, Arnsberg (DE)
Filed by Burkhard Wiggerich, Arnsberg (DE)
Assigned to NORDIC UNMANNED AS, Sandnes (NO)
Reexamination Request No. 90/019,956, May 12, 2025.
Reexamination Certificate for Patent 8,328,128, issued Dec. 11, 2012, Appl. No. 12/306,346, Dec. 23, 2008.
PCT Filed Mar. 31, 2007, PCT No. PCT/DE2007/000592 § 371(c)(1), (2), (4) Date Dec. 23, 2008, PCT Pub. No. WO2008/000203, PCT Pub. Date Jan. 3, 2008.
Claims priority of application No. 10 2006 029 603 (DE), filed on Jun. 26, 2006.
Ex Parte Reexamination Certificate issued on Jan. 21, 2026.
Int. Cl. B64U 50/19 (2023.01); B64U 10/16 (2023.01); B64U 10/80 (2023.01); B64U 30/24 (2023.01); B64U 30/299 (2023.01); B64U 101/70 (2023.01)

CPC B64U 50/19 (2023.01) [B64U 10/16 (2023.01); B64U 30/24 (2023.01); B64U 10/80 (2023.01); B64U 30/299 (2023.01); B64U 2101/70 (2023.01)]

AS A RESULT OF REEXAMINATION, IT HAS BEEN DETERMINED THAT:

Claims 9 and 10 are cancelled.

Claim 1 is determined to be patentable as amended.

Claims 2-8 and 11-20, dependent on an amended claim, are determined to be patentable.

New claims 21 and 22 are added and determined to be patentable.

1. An aircraft, comprising:

autonomous attitude and position control provided by at least three drive units, each of said drive units having:

a first rotor ; [ ,]

a first rotary speed-controlled electric motor configured for driving said first rotor in a rotation direction during operation of the aircraft ; [ ,]

at least one second rotor ; [ , and ]

at least one second rotary speed-controlled electric motor configured for driving said at least one second rotor during operation of the aircraft in a rotation direction opposite to said rotation of said first rotor of said respective drive unit ; [ ,]

said first rotary speed-controlled electric motor and said at least one second rotary speed-controlled electric motor having rotary speeds being variable on an individual basis; and

a support for said drive units, said support including a number of supporting arms extending radially outward from and secured only to a central base body without the drive units being secured to each other, at least one of said drive units being fitted to each respective one of said supporting arms [ ,

wherein said first and second rotors of each of said drive units are disposed coaxially, and

wherein the attitude and position control is provided by individually controlling a rotary speed of each of the at least one first rotary speed-controlled electric motor and the at least one second rotary speed-controlled electric motor in each of said drive units] .

[ 21. An aircraft, comprising:

autonomous attitude and position control provided by at least three drive units, each of said drive units having:

a first rotor,

a first rotary speed-controlled electric motor configured for driving said first rotor in a rotation direction during operation of the aircraft,

at least one second rotor, and

said first rotary speed-controlled electric motor and said at least one second rotary speed-controlled electric motor having rotary speeds being variable on an individual basis;

a collision protection device for said rotors, wherein said collision protection device includes a first rotor protection ring and a second rotor protection ring extending along an outer circumference of the aircraft; and

a number of holding crossmembers interconnecting said rotor protection rings.]

[ 22. The aircraft according to claim 21, wherein said holding crossmembers are detachably fitted to said supporting arms.]