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A breaker strut of an aircraft landing gear, including means to adjust the length of at least one of its lower and upper portions and/or a space allowing a nesting of the lower and upper portions in the folded position of the strut. A landing gear including such a strut and/or retraction means inclu

A breaker strut of an aircraft landing gear, including means to adjust the length of at least one of its lower and upper portions and/or a space allowing a nesting of the lower and upper portions in the folded position of the strut. A landing gear including such a strut and/or retraction means including two slider-crank mechanisms which are phase shifted by a non-zero angle φ allowing a reduction of the variations of torque C applied to the undercarriage of the gear as it moves between the lowered and raised states of the latter.

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1. A breaker strut for an aircraft landing gear, the breaker strut comprising: two portions;wherein a lower one of the two portions includes an eye for articulated connection to a landing gear undercarriage about a first hinge axis;wherein an upper one of the two portions includes a first hinge for

1. A breaker strut for an aircraft landing gear, the breaker strut comprising: two portions;wherein a lower one of the two portions includes an eye for articulated connection to a landing gear undercarriage about a first hinge axis;wherein an upper one of the two portions includes a first hinge for articulated connection to at least one structural aircraft element about a second hinge axis;wherein the two portions are connected to one another by a second respective hinge about a third hinge axis parallel to the first and second hinge axes, such that the lower and upper portions are moved relative to one another between: a deployed position, in which the lower and upper portions are positioned on either side of the third hinge axis, such that the first hinge axis is contained in a plane defined by the second and third hinge axes, anda folded position, in which the lower portion is folded towards a lower face of the upper portion; andwherein at least one of the lower and upper portions of the breaker strut includes a mechanism of mutual attachment of the eye and the second hinge and the first and second hinges, respectively, which allows a distance separating the eye and second hinge and the first and second hinges, respectively, to be modified. 2. The breaker strut according to claim 1, wherein the mechanism of mutual attachment comprises at least one sliding rod, together with controlled locking and unlocking mechanisms for preventing and/or allowing motion of the sliding rod so as to lock and/or unlock the distance separating the first and second hinges. 3. A landing gear for an aircraft, comprising the at least one undercarriage which is moved between a raised state and a lowered state, together with the breaker strut according to claim 1, wherein the eye of the lower portion of the breaker strut is connected to the undercarriage. 4. An aircraft landing gear compartment accommodating the landing gear according to claim 3, the aircraft landing gear compartment comprising the at least one structural aircraft element to which the first hinge of the upper portion of the breaker strut is connected. 5. An aircraft, including the landing gear compartment according to claim 4. 6. A breaker strut for an aircraft landing gear, the breaker strut comprising: two portions;wherein a lower one of the two portions includes an eye for articulated connection to a landing gear undercarriage about a first hinge axis;wherein an upper one of the two portions includes a first hinge for articulated connection to at least one structural aircraft element about a second hinge axis;wherein the two portions are connected to one another by a second respective hinge about a third hinge axis parallel to the first and second hinge axes, such that the lower and upper portions are moved relative to one another between: a deployed position, in which the lower and upper portions are positioned on either side of the third hinge axis, such that the first hinge axis is roughly contained in a plane defined by the second and third hinge axes, anda folded position, in which the lower portion is folded towards a lower face of the upper portion, such that the first hinge axis is contained in the plane defined by the second and third hinge axes; andwherein the upper portion defines a space enabling the lower portion to be accommodated in the folded position. 7. The breaker strut according to claim 6, wherein the upper portion comprises two structures which globally have a shape of a triangle, the structures being connected respectively to either side of the lower portion, and where each of the structures comprises, at a lower apex of the triangle, the second hinge connecting the upper portion to the lower portion, and at two upper apexes of the triangle, the first hinge connecting the upper portion to the structural aircraft element. 8. The breaker strut according to claim 7, wherein the upper portion comprises a flange connecting the structures to one another. 9. The breaker strut according to claim 7, wherein each of the structures comprises an arm delimiting the space, and extending in a direction orthogonal to the first, second and third hinge axes so as to connect the lower apex to one of the other two apexes of the triangle. 10. The breaker strut according to claim 9, wherein the space traverses the upper portion so as to emerge in the lower face and in an upper face of the upper portion, and the space extends along an entire length of the arm so as to separate the structures. 11. A landing gear for an aircraft, the landing gear comprising the at least one undercarriage which is moved between a raised state and a lowered state, together with the breaker strut according to claim 6, wherein the eye of the lower portion of the breaker strut is connected to the undercarriage. 12. An aircraft landing gear compartment accommodating the landing gear according to claim 11, the aircraft landing gear compartment comprising the at least one structural aircraft element to which the first hinge of the upper portion of the breaker strut is connected. 13. An aircraft, comprising the landing gear compartment according to claim 12. 14. A breaker strut for an aircraft landing gear, the breaker strut comprising: two portions;wherein a lower one of the two portions includes an eye for articulated connection to a landing gear undercarriage about a first hinge axis;wherein an upper one of the two portions includes a first hinge for articulated connection to at least one structural aircraft element about a second hinge axis;wherein the two portions are connected to one another by a second respective hinge about a third hinge axis parallel to the first and second hinge axes, such that the lower and upper portions are moved relative to one another between: a deployed position, in which the lower and upper portions are positioned on either side of the third hinge axis, such that the first hinge axis is contained in a plane defined by the second and third hinge axes, anda folded position, in which the lower portion is folded towards a lower face of the upper portion, such that the first hinge axis is contained in the plane defined by the second and third hinge axes;wherein at least one of the lower and upper portions of the breaker strut includes a mechanism of mutual attachment of the eye and the second hinge and the first and second hinges, respectively, which allows a distance separating the eye and second hinge and the first and second hinges, respectively, to be modified, andwherein the upper portion defines a space enabling the lower portion to be accommodated in the folded position. 15. A landing gear for an aircraft, the landing gear comprising: an undercarriage; anda retraction mechanism of the undercarriage for rotating the undercarriage around a pivot axis;wherein the retraction mechanism comprises a first crank securely attached to the undercarriage, and a first linear actuator which includes a first portion coupled to the first crank and a second portion able to move relative to the first portion and having a mechanism of attachment for attaching the second portion to a structural aircraft element such that the first crank and the first linear actuator form part of a first slider-crank mechanism;wherein the retraction mechanism comprises a second crank securely attached to the undercarriage, and a second linear actuator which includes a first portion coupled to the second crank and a second portion able to move relative to the first portion and having a mechanism of attachment for attaching the second portion to a structural aircraft element such that the second crank and the second actuator form part of a second slider-crank mechanism; andwherein the first and second slider-crank mechanisms are phase-shifted relative to one another by a non-zero angle φ defined around the pivot axis. 16. A landing gear according to claim 15, wherein the second crank is offset, relative to the first crank, by the angle φ. 17. The landing gear according to claim 16, wherein the first portion of each of the linear actuators is directly connected to the corresponding crank about a hinge axis parallel to the pivot axis, and the mechanism of attachment of the second portion of each of the linear actuators allow rotation of the second portion about a hinge axis parallel to the pivot axis, and wherein the linear actuators are similar, and the respective second portions of the linear actuators are connected to the structural aircraft elements about a common hinge axis. 18. The landing gear according to claim 15, wherein the angle φ is between 70 degrees and 100 degrees. 19. An aircraft landing gear compartment accommodating the landing gear according to claim 15, wherein the second portion of the first linear actuator is attached to a first structural element of the landing gear compartment, andwherein the second portion of the second linear actuator is attached to a second structural element of the landing gear compartment. 20. An aircraft, including the landing gear compartment according to claim 19.