1. An electrical connector, comprising:
an insulating body, having at least one receiving housing formed through the insulating body;
at least one conductive member, wherein the at least one conductive member has:
a contact portion disposed in the at least one receiving housings, wherein the contact portion has a middle part higher than two ends thereof;
a pair of first retaining arms, extending downwards from one end of the contact portion, wherein a retaining hole is formed between the two first retaining arms, and each of the first retaining arms respectively has a hook portion extending towards the retaining hole; and
a second retaining arm, extending downwards from the other end of the contact portion, wherein the second retaining arm extends towards the retaining hole, and the second retaining arm has a width smaller than the retaining hole; and
at least one solder ball, correspondingly disposed in the at least one receiving housing, received in the retaining hole, and at least pressed against by the two hook portions of the pair of first retaining arms and the second retaining arm.
2. The electrical connector according to claim 1, wherein the pair of first retaining arms and the contact portion defines a first bending portion therebetween.
3. The electrical connector according to claim 2, wherein the first bending portion has a width smaller than that of the first retaining arm, and is resilient.
4. The electrical connector according to claim 3, wherein the first bending portion is elastic.
5. The electrical connector according to claim 1, wherein the second retaining arm and the contact portion define a second bending portion therebetween.
6. The electrical connector according to claim 5, wherein the second bending portion has a width smaller than the second retaining arm, and is resilient.
7. The electrical connector according to claim 6, wherein the resilient second bending is elastic.
8. The electrical connector according to claim 1, wherein when the solder ball is melted, at least 10% of the length of the second retaining arm penetrates into the solder ball.
9. The electrical connector according to claim 1, wherein a surface of the hook portion facing the retaining hole presses against the solder ball.
10. The electrical connector according to claim 1, wherein the middle part of the contact portion is two arm portions.
11. The electrical connector according to claim 1, wherein the two hook portions are bent towards the second retaining arm.
12. The electrical connector according to claim 1, wherein a stopping arm extends upwards from an intersection of the first retaining arm and the contact portion.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A wing assembly for an aircraft comprising:
a wing spar,
a wing cover and
a structural component attached to the wing spar;
wherein the wing spar has a web and a flange connected by a radius corner, and the flange is attached to the wing cover such that a gap is formed at an interface between the spar, the wing cover and the structural component;
the assembly further comprising a seal member which substantially covers the gap, and sealant provided between the seal member and at least one of the structural component, the wing cover and the wing spar; the wing spar, the wing cover, and the structural component each being in contact with at least one of the seal member and sealant so as to seal the gap.
2. An assembly according to claim 1, wherein the seal member and the sealant substantially prevent a flow of air through the gap.
3. An assembly according to claim 1, wherein the seal member comprises a projecting portion which extends over the gap.
4. An assembly according to claim 3, wherein the projecting portion is shaped to compliment a profile of the gap.
5. An assembly according to claim 1, wherein the seal member comprises a body portion and a projecting portion which tapers away from the body portion.
6. An assembly according to claim 1, wherein the seal member is substantially planar.
7. An assembly according to claim 1, wherein the seal member comprises an attachment portion which is attached to at least one of the structural component, the wing cover and the wing spar.
8. An assembly according to claim 1, wherein the seal member is attached to at least one of the structural component, the wing cover and the wing spar by an adhesive.
9. An assembly according to claim 1, wherein the sealant is an aerospace grade sealant.
10. An assembly according to claim 1, wherein the spar comprises a fibre reinforced composite material.
11. An assembly according to claim 1, wherein the wing spar is a front spar.
12. An assembly according to claim 1, wherein the wing cover is an upper wing cover or a lower wing cover.
13. An assembly according to claim 1, wherein the structural component is a wing rib.
14. An assembly according to claim 13, wherein the wing rib is at least a sealed forward rib disposed at a leading edge of the wing assembly so as to define a boundary between two compartments within the leading edge, wherein the rib and the sealed seal member are operable to substantially prevent a flow of air between the two compartments.
15. An assembly according to claim 14, wherein the at least a sealed forward rib is a plurality of sealed forward ribs spaced along the wing spar.
16. An aircraft comprising a wing assembly according to claim 1.
17. A method for sealing a gap in an aircraft wing assembly having a wing spar, a wing cover and a structural component attached to the wing spar, wherein the wing spar has a web and a flange connected by a radius comer, and the flange is attached to the wing cover such that a gap is formed at an interface between the spar, the wing cover and the structural component, the method comprising:
attaching a seal member to at least one of the structural component, the wing cover, and the wing spar so as to substantially cover the gap; and
providing sealant between the seal member and the at least one of the structural member, the wing cover and the wing spar, and wherein the spar, the wing cover and the structural component each being in contact with at least one of the seal member and sealant so as to seal the gap.
18. A wing assembly for an aircraft comprising
a wing spar, a wing cover and a structural component attached to the wing spar;
wherein the wing spar has a web and a flange connected by a radius comer, and the spar flange is attached to the wing cover such that a gap is formed at an interface between the spar, the wing cover and the structural component;
the assembly further comprising a seal member which substantially covers the gap and a portion of the seal member overlaps with the structural component, and sealant provided between the seal member and at least one of the structural component, the wing cover and the wing spar so as to seal the gap.