Autonomous unmanned aerial vehicle

Patent metadata

Field	Value
Publication number	US-11535375-B2
Application number	US-201816628731-A
Country	US
Kind code	B2
Filing date	Jul 6, 2018
Priority date	Jul 6, 2017
Publication date	Dec 27, 2022
Grant date	Dec 27, 2022

Abstract

An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

First claim

What is claimed is:

1. An autonomous unmanned aerial vehicle comprising:
an engine assembly, wherein the engine assembly is located in a body, and the engine assembly provides motion to a front propeller and a rear propeller,
the front propeller, wherein the front propeller is located in a front of the body, wherein the front of the body is connected to the engine assembly,
the rear propeller, wherein the rear propeller is connected to the engine assembly and the rear propeller is located at a rear of the body, the rear propeller is configured to rotate in a same direction or opposite direction to the front propeller,
3 wings, wherein the 3 wings enable vertical take-off and vertical landing of the autonomous unmanned aerial vehicle, a plurality of sharp ends of the 3 wings are used as a landing gear, and the landing gear are installed on the body with constant 120 degree spacing,
a liquid hydrogen tank installed in a center of the rear propeller,
a balloon is wrapped around the liquid hydrogen tank, wherein the balloon is inflated with hydrogen in the liquid hydrogen tank, and the balloon enables suspension of the autonomous unmanned aerial vehicle in air,
a multispectral camera, wherein the multispectral camera is installed in a center of the front propeller, and
a stabilized platform, wherein the stabilized platform carries the multispectral camera.

2. The autonomous unmanned aerial vehicle according to claim 1 , further comprising a balloon ejection unit, wherein the balloon ejection unit is located at an end portion of the liquid hydrogen tank, wherein the balloon ejection unit releases the balloon during the vertical landing of the autonomous unmanned aerial vehicle.

3. The autonomous unmanned aerial vehicle according to claim 2 , further comprising a mono block hybrid engine, wherein the mono block hybrid engine operates the engine assembly with an internal combustion engine during a lift off and when the autonomous unmanned aerial vehicle is operated in a friendly zone, and the mono block hybrid engine operates with electricity without noise in a mission area.

4. The autonomous unmanned aerial vehicle according to claim 3 , wherein the autonomous unmanned aerial vehicle comprises a wing body, wherein the wing body is mounted on the body with constant 120 degree spacing.

5. The autonomous unmanned aerial vehicle according to claim 4 , wherein the autonomous unmanned aerial vehicle comprises a wing end, wherein the wing end is mounted on an end portion of the wing body, and, the wing end is positioned in a same direction as the wing body when the autonomous unmanned aerial vehicle is taking off and when the unmanned aerial vehicle is gaining altitude, the wing end expands when the autonomous unmanned aerial vehicle is gliding wherein the wing end turns 180° in an opposite direction as the wing body to increase a gliding capacity of the autonomous unmanned aerial vehicle.

6. The autonomous unmanned aerial vehicle according to claim 5 , wherein the autonomous unmanned aerial vehicle comprises a gyro unit attached to the front propeller, wherein the gyro unit provides reference to an inertial navigational system of the autonomous unmanned aerial vehicle, and the gyro unit enables correct positioning of the autonomous unmanned aerial vehicle and an autonomous flight of the autonomous unmanned aerial vehicle.

7. The autonomous unmanned aerial vehicle according to claim 6 , wherein the autonomous unmanned aerial vehicle comprises a plurality of MEMPS microphones located on the autonomous unmanned aerial vehicle to eliminate and/or reduce a noise of the engine assembly by an acoustic interference method as the rear propeller rotates with a same rotation speed as the front propeller with 180 degrees phase so as to create a different noise.

8. The autonomous unmanned aerial vehicle according to claim 7 , wherein the autonomous unmanned aerial vehicle operates as follows,
the autonomous unmanned aerial vehicle is operated with a remote control or the autonomous unmanned aerial vehicle is operated autonomously,
the autonomous unmanned aerial vehicle takes off by the internal combustion engine, wherein the internal combustion engine is located in the engine assembly,
a plurality of ends of the wing ends are opened 20-60° and the autonomous unmanned aerial vehicle takes off while working with an electric engine,
the wing ends extend 180° in a lateral axis while the autonomous unmanned aerial vehicle continues to operate with the electric engine,
after reaching a target point, the wing ends are retracted and the autonomous unmanned aerial vehicle is reversed,
the balloon is inflated with hydrogen wherein hydrogen is stored in the liquid hydrogen tank,
the autonomous unmanned aerial vehicle ascends together with the balloon, wherein the balloon is inflated with hydrogen,
the balloon is ejected after the autonomous unmanned aerial vehicle rises to an altitude wherein a sound of the internal combustion engine in the engine assembly is not heard,
the internal combustion engine is operated and the autonomous unmanned aerial vehicle is returned back to an original location of the autonomous unmanned aerial vehicle.

9. The autonomous unmanned aerial vehicle according to claim 8 , further comprising the liquid hydrogen tank, wherein hydrogen in the liquid hydrogen tank explodes as a bomb in an event of an attack or a danger.

10. The autonomous unmanned aerial vehicle according to claim 9 , further comprising,
a hollow cylindrical power transmission shaft connected at a hub of an internal combustion engine output shaft and a plurality of rotary body bearings in the engine assembly of the body,
a control rack, wherein the control rack comprises three non-hollow cylindrical shafts born linearly on the plurality of rotary body bearings, wherein the plurality of rotary body bearings are connected to a rack power transmission hub,
the rack power transmission hub in a cylindrical form, wherein the cylindrical form of the rack power transmission hub is operated in a manner to allow a radial movement in the engine assembly, wherein the rack power transmission hub is in a form of a disk connected with the hollow cylindrical power transmission shaft to a rack linear actuator,
a rack gear train, wherein the rack gear train comprises 3 rack gears on the shaft connected to 3 control racks, and 3 cogwheels, wherein the 3 control racks and the 3 cogwheels are connected to the front propeller and the 3 control racks are positioned to act together with the 3 cogwheels,
the plurality of rotary body bearings are mounted to the engine assembly to allow a radial movement of the plurality of rotary body bearings and the engine assembly,
a conic cam in a form of the hollow cylindrical power transmission shaft having the conic cam at an end portion of the hollow cylindrical power transmission shaft, wherein the conic cam is mounted to allow for a linear movement relative to the engine assembly, and the conic cam and the engine assembly are connected to the plurality of rotary body bearings so as to rotate together with the plurality of rotary body bearings,
a conic cam follower, wherein the conic cam follower contacts the conic cam and the conic cam follower has a moveable ball at an end of the conic cam follower to enable movement,
a cam follower shaft as a cylindrical shaft mounted linearly moveable to a cogwheel of the rack gear train, wherein the cogwheel of the rack gear train is connected to the front propeller and the cam follower shaft in turn is connected to the conic cam follower,
a cam follower gear in the form of a cogwheel connected to the cam follower shaft,
a propeller closing gear is placed as axially offset compared to

Assignees

• Univ Istanbul Teknik
• Mitos Mikrodalga Goruntuleme Sistemleri Muhendislik Sanayi Ve Ticaret Ltd Sirketi
• Mitos Mikrodalga Gorun Iuleme Sistemler Muhendislhk Sanayi Ve Ticaret Ltd Sirketi

Inventors

• Canli Guray Ali
• Akduman Ibrahim
• Kurtoglu Ismail
• Cayoren Mehmet
• Yavuz Gundogdu Pelin
• Ozkol Ibrahim
• Ercan Hasan
• Tamyurek Muhammet Tarik

Classifications

• Y02T90/40

  Application of hydrogen technology to transportation, e.g. using fuel cells · CPC title

• B64D27/04

  of piston type · CPC title

• B64C3/10

  Shape of wings · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title