System for rolling landing gear

Patent metadata

Field	Value
Publication number	US-11230372-B1
Application number	US-202117196719-A
Country	US
Kind code	B1
Filing date	Mar 9, 2021
Priority date	Mar 9, 2021
Publication date	Jan 25, 2022
Grant date	Jan 25, 2022

Abstract

A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.

First claim

What is claimed is:

1. A system for rolling landing gear, the system comprising:
a skid component attached to an aircraft, wherein the skid component further comprises:
a first skid tube oriented laterally to a longitudinal axis of the aircraft;
a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube;

a first wheel journaled on a first rotational fulcrum;
a second wheel journaled on a second rotational fulcrum;
a first biasing means attaching the first rotational fulcrum to the first skid tube; and
a second biasing means attaching the second rotational fulcrum to the second skid tube;
wherein the first biasing means, and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and the second skid tube, and wherein each of the first biasing means and the second biasing means further comprise at least a leaf spring.

2. The system of claim 1 , wherein the at least a leaf spring includes at least a fiberglass prestressed leaf spring.

3. The system of claim 1 , wherein the at least a leaf spring includes at least a carbon prestressed leaf spring.

4. The system of claim 1 , wherein the at least a leaf spring has two ends and a central section, wherein the fulcrum is attached to the central section, and wherein the two ends are affixed to the first skid tube.

5. The system of claim 1 , wherein the first skid tube has a first recess and the first wheel is in the first recess, and wherein the second skid tube has a second recess and the second wheel is in the second recess.

6. The system of claim 1 , wherein the first and second biasing means includes an upper recess.

7. The system of claim 1 , wherein the first biasing means and the second biasing means extend the first wheel and the second wheel upon a reduction in a downward force.

8. The system of claim 1 , wherein the system is configured to enable a rolling takeoff.

9. The system of claim 1 , wherein the system is configured to enable a rolling landing.

10. The system of claim 1 further comprising a crosstube connecting the second skid tube to the first skid tube.

11. The system of claim 1 , wherein the first and second biasing means include a first quantity of carbon prestressed leaf springs and a second quantity of fiberglass prestress leaf springs, and the first quantity is greater than the second quantity.

12. The system of claim 11 , wherein the first quantity is more than twice the second quantity.

13. The system of claim 1 , wherein the recoil force separates first skid tube and second skid tube from a ground below as a function of a threshold landing force.

14. The system of claim 13 , wherein the threshold landing force is 1.4 times a force exerted on the aircraft by gravity.

15. The system of claim 13 , wherein the threshold landing force is less than or equal to a rating force of the first wheel and second wheel.

Assignees

• Beta Air Llc

Inventors

• Griffin Riley Clinton
• Clark Kyle B
• Verna Raffaello

Classifications

• B64C25/66

  Convertible alighting gear; Combinations of different kinds of ground or like engaging elements · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C25/62

  Spring shock-absorbers; Springs · CPC title

• B64C25/52 Primary

  Skis or runners · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title