Aircraft system with assisted taxi, take off, and climbing

Patent metadata

Field	Value
Publication number	US-11084602-B2
Application number	US-201816201613-A
Country	US
Kind code	B2
Filing date	Nov 27, 2018
Priority date	Nov 27, 2017
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

An aircraft system with assisted taxi, take-off and climbing, comprising: a main air vehicle capable of performing autonomously the cruising and landing phases of a flight, an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during the taxing and take-off phases of a flight. Main and auxiliary air vehicles are adapted to be detachably connectable, so that the auxiliary air vehicle can assist the main air vehicle when both are attached to each other during taxing, take-off and climbing. The auxiliary air vehicle is an unmanned air vehicle and it is further configured to fly and land when it is detached from the main air vehicle. Aircraft operations cost and aircraft production cost are reduced, by optimizing the design (sizing) and capabilities of some systems of an aircraft.

First claim

The invention claimed is:

1. An aircraft system with assisted take-off and climbing, comprising:
a main air vehicle capable of performing autonomously the cruising and landing phases of a flight,
an auxiliary air vehicle lighter than the main air vehicle and configured to assist the main air vehicle during taxiing and take-off phases of a flight,
wherein the main and auxiliary air vehicles are configured to be detachably connectable, so that the auxiliary air vehicle assists the main air vehicle when both are attached to each other during taxiing, take-off and climbing, and
wherein the auxiliary air vehicle is an unmanned air vehicle and is further configured to fly and land when the auxiliary air vehicle is detached from the main air vehicle.

2. The aircraft system according to claim 1 ,
wherein the main air vehicle has a nose landing gear and main landing gear including left and right landing gear, and
wherein the main and auxiliary air vehicles are configured so that the auxiliary air vehicle is detachably connectable to a belly of the main air vehicle and between the left and right landing gear.

3. The aircraft system according to claim 1 , wherein the auxiliary air vehicle has a landing gear, and wherein the main and auxiliary air vehicles are configured such that when they are both connected during taxing and take-off, the landing gear of both air vehicles are extended and on the ground, and wherein the auxiliary air vehicle partially supports a weight of the main air vehicle.

4. The aircraft system according to claim 1 , wherein the main air vehicle is configured to carry a payload, and wherein a maximum thrust of a power plant of the main air vehicle is selected such that when the main air vehicle carries a full load, the main air vehicle can only take-off with assistance of the auxiliary air vehicle.

5. The aircraft system according to claim 1 , wherein the main and auxiliary air vehicles have respective fuel systems, or electric energy storage/power generation devices, and wherein both air vehicles are configured such that, when they are connected to each other, fuel, or electric energy, from the auxiliary air vehicle is transferrable to the main air vehicle.

6. The aircraft system according to claim 1 , wherein the auxiliary air vehicle is an autonomously or remotely operated vehicle.

7. The aircraft system according to claim 1 , wherein the auxiliary air vehicle comprises extendable lifting and control surfaces, and wherein the auxiliary air vehicle is configured such that its extendable lifting and control surfaces are retracted while the auxiliary air vehicle is coupled with the main air vehicle, and the lifting and control surfaces are deployed when the auxiliary air vehicle is detached from the main air vehicle.

8. The aircraft system according to claim 1 , wherein the auxiliary air vehicle is controllable from the main air vehicle when both are attached to each other.

9. The aircraft system according to claim 1 , wherein a powerplant of the auxiliary air vehicle comprises at least one of at least one turbofan engine or at least one electric engine.

10. The aircraft system according to claim 9 , wherein the auxiliary air vehicle comprises one turbofan engine and a vectorized exhaust nozzle coupled with the turbofan engine.

Assignees

• Airbus Operations Sl

Inventors

• Casado-Montero Carlos
• Linde Ayllon Javier

Classifications

• B64F1/10 Primary

  using self-propelled vehicles · CPC title

• B64D5/00 Primary

  Aircraft transported by aircraft, e.g. for release or reberthing during flight · CPC title

• B64F1/227

  for direct connection to aircraft, e.g. tow tractors without towing bars · CPC title

• B64C25/08

  non-fixed, e.g. jettisonable · CPC title