AIRCRAFT LANDING GEAR ASSEMBLY

• US 20170203833A1
• Filed: 01/16/2017
• Published: 07/20/2017
• Est. Priority Date: 01/19/2016
• Status: Active Grant

• Current Assignee: Safran Landing Systems UK Limited (Safran SA)
• Original Assignee: Safran Landing Systems UK Limited (Safran SA)
• Inventors: Schmidt, Robert Kyle
• Granted Patent: US 10,457,383 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 25/10 retractable, foldable, or the like
• CPC Class Codes: B64C 25/26 Control or locking systems therefor
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies
• CPC Class Codes: B64C 25/58 Arrangements or adaptations of shock-absorbers or springs shimmy-dampers B64C25/50

Abstract

An aircraft landing gear assembly includes a structural member coupled to another part by a joint including engagement formations or a relatively high friction coating arranged such that the joint inhibits pivotal movement of the structural member when the structural member is compressively loaded in an axial manner.

Claims

1. An aircraft landing gear assembly comprising:

a first part and a second part, the first and second parts being movably mounted with respect to one another;

a structural member pivotally coupled to the first part via a first joint, the structural member having a load reacting condition in which it inhibits relative movement between the first and second parts by reacting a compressive load applied to it by the parts,

the first joint including a first bearing associated with the first part and a second bearing surface associated with the structural member, the joint being arranged such that the first bearing surface mechanically couples with the second bearing surface during said compressive loading so as to define a load path between the first and second bearing surfaces by each bearing surface engaging a respective bearing counter-face; and

one or more springs,

wherein the first and second bearing surfaces each define male and/or female engagement formations arranged to engage with the respective first and second counter-faces to inhibit pivotal movement of the structural member relative to the first part when the first and second bearing surfaces are engaged in an interlocking condition with the respective first and second counter-faces, the one or more springs being arranged to urge the first and second bearing surfaces to assume a spaced condition in which they are relatively spaced from the respective first and second counter-faces so as to permit said pivotal movement of the structural member relative to the first part.

2. The landing gear assembly according to claim 1, wherein the structural member is pivotally coupled to the second part via a second joint and the second joint includes a third bearing surface associated with the second part and a fourth bearing surface associated with the structural member the second joint being arranged such that the third bearing surface mechanically couples with the fourth bearing surface during said compressive loading by each engaging with a bearing counter-face,

wherein the third and fourth bearing surfaces each define male and/or female engagement formations arranged engage with the respective third and fourth counter-faces to inhibit pivotal movement of the structural member relative to the second part when the third and fourth bearing surfaces are engaged in an interlocking condition with the respective third and fourth counter-faces, the assembly further comprising one or more resilient biasing members arranged to urge the third and fourth bearing surfaces to assume a spaced condition in which they are relatively spaced from the respective third and fourth counter-faces so as to permit said pivotal movement of the structural member relative to the second part.

3. The landing gear assembly according to claim 1, wherein the structural member comprises a two bar linkage pivotally coupled at a central region between its ends by a third joint, the third joint including a fifth bearing surface associated with a first bar of the structural member and a sixth bearing surface associated with a second bar of the structural member, the third joint being arranged such that the fifth bearing surface mechanically couples with the sixth bearing surface during said compressive loading by each engaging with a bearing counter-face,

wherein the fifth and sixth bearing surfaces each define male and/or female engagement formations arranged engage with the respective fifth and sixth counter-faces to inhibit pivotal movement of the first bar of the structural member relative to the second bar of the structural when the fifth and sixth bearing surfaces are engaged in an interlocking condition with the respective fifth and sixth counter-faces, the assembly further comprising one or more resilient biasing members arranged to urge the fifth and sixth bearing surfaces to assume a spaced condition in which they are relatively spaced from the respective fifth and sixth counter-faces so as to permit said pivotal movement of the first bar of the structural member relative to the second bar of the structural member.

4. The landing gear assembly according to claim 1, wherein the engagement formations of the bearing surfaces and the counter-faces are provided only at the regions which engage during compressive loading of the structural member.

11. The aircraft landing gear assembly according to claim 1, wherein each spring can comprise a generally annular, radially compliant spring disposed between a pair of smooth race surfaces, each race surface being arranged in parallel with a respective bearing surface or counter-face and at least one race within each pair being recessed with respect to the respective bearing surface or counter-face it such that a gap exists to house the deformed spring when the bearing surfaces engage the counter-faces.

12. The aircraft landing gear assembly according to claim 1, wherein the first bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel first lugs associated with the first part, the second bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel second lugs associated with the structural member, and the first and second counter-faces are defined by a pivot pin mounted within the coaxial holes defined by the first and second lugs.

13. The aircraft landing gear assembly according to claim 2, wherein the third bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel third lugs associated with the second part, the fourth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel fourth lugs associated with the structural member and the third and fourth counter-faces are defined by a pivot pin mounted within the coaxial holes defined by the third and fourth lugs.

14. The aircraft landing gear assembly according to claim 3, wherein the fifth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel fifth lugs associated with the first bar of the structural member, the sixth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel sixth lugs associated with the second bar of the structural member and the fifth and sixth counter-faces is defined by a third pivot pin mounted within the coaxial holes defined by the fifth and sixth lugs.

15. The aircraft landing gear assembly according to claim 1, wherein the first part comprises a main strut and the second part comprises the airframe of an aircraft or a stay arm.

5. An aircraft landing gear assembly comprising:

a first part and a second part, the first and second parts being movably mounted with respect to one another; and

a structural member pivotally coupled to the first part via a first joint, the structural member having a load reacting condition in which it inhibits relative movement between the first and second parts by reacting a compressive load applied to it by the parts,

the first joint including a first bearing surface associated with the first part and a second bearing surface associated with the structural member, the joint being arranged such that the first bearing surface mechanically couples with the second bearing surface during said compressive loading so as to define a load path between the first and second bearing surfaces by each bearing surface engaging a respective bearing counter-face,

wherein at least one of the first bearing surface and the first counter-face and at least one of the second bearing surface and the second counter-face is defined by a layer of first material having a coefficient of friction which is relatively high in comparison to that of a second material from which at least one of the structural member, the first part and the second part is formed.

6. The aircraft landing gear assembly according to claim 5, wherein the structural member is pivotally coupled to the second part via a second joint and the second joint can include a third bearing surface associated with the second part and a fourth bearing surface associated with the structural member the second joint being arranged such that the third bearing surface mechanically couples with the fourth bearing surface during said compressive loading by each engaging with a bearing counter-face,

wherein at least one of the third bearing surface and the third counter-face and at least one of the fourth bearing surface and the fourth counter-face is defined by a layer of third material having a coefficient of friction which is relatively high in comparison to that of the second material from which at least one of the structural member, the first part and the second part is formed.

7. The aircraft landing gear assembly according to claim 5, wherein the structural member comprises a two bar linkage pivotally coupled at a central region between its ends by a third joint, the third joint including a fifth bearing surface associated with a first bar of the structural member and a sixth bearing surface associated with a second bar of the structural member, the third joint being arranged such that the fifth bearing surface mechanically couples with the sixth bearing surface during said compressive loading by each engaging with a bearing counter-face,

wherein at least one of the fifth bearing surface and the fifth counter-face and at least one of the sixth bearing surface and the sixth counter-face is defined by a layer of fourth material having a coefficient of friction which is relatively high in comparison to that of the second material from which at least one of the structural member, the first part and the second part is formed.

8. The aircraft landing gear assembly according to claim 5, wherein one or more of the high coefficient of friction layers comprise a coating applied to the part in question.

9. The aircraft landing gear assembly according to claim 5, wherein one or more of the high coefficient of friction layers are each be defined on a bush which defines one of the bearing surfaces.

10. The aircraft landing gear assembly according to claims 5, wherein one or more springs can be provided and arranged to urge the first and second bearing surfaces to assume a spaced condition in which they are relatively spaced from the respective first and second counter-faces so as to enable relatively unrestricted pivotal movement of the structural member relative to the first part in comparison when the first bearing surface mechanically couples with the second bearing surface during said compressive loading.

16. The aircraft landing gear assembly according to claim 5, wherein each spring can comprise a generally annular, radially compliant spring disposed between a pair of smooth race surfaces, each race surface being arranged in parallel with a respective bearing surface or counter-face and at least one race within each pair being recessed with respect to the respective bearing surface or counter-face it such that a gap exists to house the deformed spring when the bearing surfaces engage the counter-faces.

17. The aircraft landing gear assembly according to claim 5, wherein the first bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel first lugs associated with the first part, the second bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel second lugs associated with the structural member, and the first and second counter-faces are defined by a pivot pin mounted within the coaxial holes defined by the first and second lugs.

18. The aircraft landing gear assembly according to claim 6, wherein the third bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel third lugs associated with the second part, the fourth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel fourth lugs associated with the structural member and the third and fourth counter-faces are defined by a pivot pin mounted within the coaxial holes defined by the third and fourth lugs.

19. The aircraft landing gear assembly according to claim 7, wherein the fifth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel fifth lugs associated with the first bar of the structural member, the sixth bearing surface is defined by an inner generally cylindrical face of a hole formed through each of one or more parallel sixth lugs associated with the second bar of the structural member and the fifth and sixth counter-faces is defined by a third pivot pin mounted within the coaxial holes defined by the fifth and sixth lugs.

20. The aircraft landing gear assembly according to claim 5, wherein the first part comprises a main strut and the second part comprises the airframe of an aircraft or a stay arm.