Method of preloading an aircraft assembly, a preloading tool and an aircraft assembly

Patent metadata

Field	Value
Publication number	US-10112699-B2
Application number	US-201615190335-A
Country	US
Kind code	B2
Filing date	Jun 23, 2016
Priority date	Jun 23, 2015
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A method of preloading an aircraft assembly involving a step of operating an extendible preloading tool to move a landing gear strut to decrease the distance between first and second link attachment joints for attachment of a preloading linkage. A tool and aircraft assembly are also provided.

First claim

The invention claimed is:

1. A method of preloading an aircraft assembly for fitting a preloading linkage, the aircraft assembly comprising:
a strut mounting joint;
a landing gear strut movably coupled to the strut mounting joint so as to be movable between a deployed condition, for take-off and landing, and a stowed condition for flight, the landing gear strut including a first link attachment joint arranged to be coupled to a first fitting of the preloading linkage;
a second link attachment joint arranged to be coupled to a second fitting of the preloading linkage; and
a first tool attachment joint mechanically coupled to the landing gear strut to define a load path between the first tool attachment joint and the strut;
the method comprising:
actuating a variable length preloading tool coupled between the first tool attachment joint and an anchor point having a known spatial relationship with respect to the aircraft assembly to cause the tool to change from:
a first extension state in which the landing gear strut is in a default, deployed position and where the distance between the first link attachment joint and the second link attachment joint is a default distance, to
a second extension state in which the landing gear strut is moved from the default, deployed position and where the distance between the first and second link attachment joints substantially corresponds to the preloaded distance between the first and second fittings of the preloading linkage.

2. The method according to claim 1 , whereby the relative displacement between the first and second tool attachment joints as the tool is actuated between the first and second extension states is relatively large in comparison to the relative displacement between the first and second link attachment joints.

3. The method according to claim 1 , whereby the ratio of tool displacement to link attachment joint displacement is at least 5:1.

4. The method according to claim 1 , further comprising a step of providing the preloading tool and coupling it to the first and second tool attachment joints.

5. An aircraft assembly comprising: a strut mounting joint;
a landing gear strut movably coupled to the strut mounting joint so as to be movable between a deployed condition, for take-off and landing, and a stowed condition for flight, the landing gear strut including a first link attachment joint arranged to be coupled to a first fitting of a preloading linkage;
a second link attachment joint arranged to be coupled to a second fitting of the preloading linkage;
a first tool attachment joint mechanically coupled to the landing gear strut to define a load path between the first tool attachment joint and the strut; and
a preloading tool for preloading the aircraft assembly prior to fitting the preloading linkage, the preloading tool comprising:
a first fitting arranged to be coupled to the first tool attachment joint and a second fitting arranged to be coupled to an anchor point having a known spatial relationship with respect to the aircraft assembly; and
an actuator operable to control the distance between the first and second fittings such that the tool is actuatable between
a first extension state in which the landing gear strut is in a default, deployed position and where the distance between the first link attachment joint and the second link attachment joint is a default distance, and
a second extension state in which the landing gear strut is moved from the default, deployed position and where the distance between the first and second link attachment joints substantially corresponds to the preloaded distance between the first and second fittings of the preloading linkage.

6. The aircraft assembly according to claim 5 , wherein the first tool attachment joint is provided on an element of the aircraft assembly.

7. The aircraft assembly according to claim 5 , wherein the second tool attachment joint is provided on an element of the aircraft assembly.

8. The aircraft assembly according to claim 5 , wherein the first and second tool attachment joints are defined by conventional, operational landing gear assembly joints.

9. The aircraft assembly according to claim 5 , wherein the tool comprises a component of the assembly.

10. The aircraft assembly according to claim 9 , wherein the actuator comprises an electro-mechanical actuator or a manual mechanical actuator which can be driven to an exact extension state that results in the required amount of relative displacement between the first and second tool attachment joints to achieve the predefined distance between the first and second link attachment joints.

11. The aircraft assembly according to claim 5 , wherein the tool includes a gearing mechanism arranged to provide a ratio of at least 1.1:1.

12. The aircraft assembly according to claim 5 , wherein the tool includes a meter or gauge which provides a visual reading corresponding to its extension state, in order to assist an operator in actuating the tool to the required extension state in cases where the required extension state does not correspond to a maximum extension state.

13. The aircraft assembly according to claim 5 , wherein the tool includes a load cell arranged to measure the amount of load required to relieve the preloading following fitting of the second stay, which can be used to measure the amount of load required to relieve the preloading following fitting of the second stay.

14. The aircraft assembly according to claim 5 , wherein the preloading linkage comprises a stay.

Assignees

• Safran Landing Systems Uk Ltd

Inventors

• Simonneaux Yann
• Paddock Andrew

Classifications

• B64C25/12 Primary

  sideways · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C25/10 Primary

  retractable, foldable, or the like · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title