Multi-stage reduction of impact forces

Patent metadata

Field	Value
Publication number	US-2018099741-A1
Application number	US-201715782660-A
Country	US
Kind code	A1
Filing date	Oct 12, 2017
Priority date	Oct 12, 2016
Publication date	Apr 12, 2018
Grant date	—

Abstract

Multi-stage reduction of impact forces are disclosed. An example apparatus to reduce impact energy of an aircraft during landing includes a rotatable landing leg having a proximal end near an axis of rotation and a distal end opposite the proximal end, a first flexible portion of the proximal end, where the first flexible portion is to engage a first engaging portion at a first rotation angle of the rotatable landing leg, and a second flexible portion of the distal end, where the second flexible portion is to engage a second engaging portion at a second rotation angle of the rotatable landing leg.

First claim

What is claimed is:

1 . An apparatus to reduce impact energy of an aircraft during landing, the apparatus comprising:
a rotatable landing leg having a proximal end near an axis of rotation and a distal end opposite the proximal end; a first flexible portion of the proximal end, the first flexible portion to engage a first engaging portion at a first rotation angle of the rotatable landing leg; and a second flexible portion of the distal end, the second flexible portion to engage a second engaging portion at a second rotation angle of the rotatable landing leg.

2 . The apparatus as defined in claim 1 , further including a third flexible portion at the proximal end to engage a third engaging portion when the rotatable landing leg rotates towards a frame of the aircraft.

3 . The apparatus as defined in claim 1 , further including an antenna disposed within the rotatable landing leg.

4 . The apparatus as defined in claim 1 , wherein the first flexible portion includes a snap, and wherein the first engaging portion includes a detent to retain the snap.

5 . The apparatus as defined in claim 1 , wherein the second flexible portion includes a finger, wherein an end of the finger is to contact and slide against a surface of the aircraft at the second rotation angle.

6 . The apparatus as defined in claim 5 , wherein the finger is curved towards the surface.

7 . The apparatus as defined in claim 6 , wherein the second flexible portion further includes a curved contact portion opposite the end of the finger to contact a landing surface prior to the finger contacting a frame of the aircraft.

8 . The apparatus as defined in claim 1 , wherein engagement between the second flexible portion and the second engagement portion has an associated force that exceeds a force associated with engagement between the first flexible portion and the first engagement portion.

9 . The apparatus as defined in claim 1 , wherein the first and second engaging portions include first and second surfaces, respectively, of a frame of the aircraft.

10 . An aircraft comprising:
at least one surface of the aircraft; a landing leg that is rotatable about a pivot, the landing leg including a first flexible portion proximate the pivot and a second flexible portion proximate a distal end of the landing leg; a first engaging portion of the at least one surface to engage the first flexible portion at a first angle of rotation of the landing leg; and a second engaging portion of the at least one surface to engage the second flexible portion at a second angle of rotation of the landing leg.

11 . The aircraft as defined in claim 10 , further including an antenna disposed within the landing leg.

12 . The aircraft as defined in claim 10 , wherein the first flexible portion includes a snap, and wherein the first engagement portion includes a detent.

13 . The aircraft as defined in claim 12 , wherein the snap is to disengage from the detent when the landing leg is rotated past the first angle of rotation.

14 . The aircraft as defined in claim 10 , wherein engagement between the second flexible portion and the second engagement portion has an associated force that exceeds a force associated with engagement between the first flexible portion and the first engagement portion.

15 . The aircraft as defined in claim 10 , wherein the landing leg is spring-loaded.

16 . The aircraft as defined in claim 10 , wherein the second flexible portion includes a finger that is curved towards the at least one surface.

17 . A method comprising:
defining a first flexible portion onto a landing leg, the first flexible portion to be placed near a pivot of the landing leg, wherein the first flexible portion is to engage a first engaging portion of a frame of an aircraft when the landing leg is rotated at a first angular rotation relative to the frame; and defining a second flexible portion onto the landing leg proximate a distal portion of the landing leg, wherein the second flexible portion is to engage a second engaging portion of the frame when the landing leg is rotated at a second angular rotation relative to the frame.

18 . The method as defined in claim 17 , further including assembling an antenna to be disposed within the landing leg.

19 . The method as defined in claim 17 , further including assembling the landing leg to the frame.

20 . The method as defined in claim 19 , further including assembling a spring to be operatively coupled between the landing leg and the frame.

Assignees

• Intel Corp

Inventors

• Oberndorfer Fabian
• Doth Klaus
• Stobbe Martin

Classifications

• B64C25/06

  fixed · CPC title

• B64C25/10

  retractable, foldable, or the like · CPC title

• B64C25/62 Primary

  Spring shock-absorbers; Springs · CPC title

• B64U30/20

  Rotors; Rotor supports · CPC title

• B64U60/50

  with landing legs · CPC title