Fastening system for aerospace vehicles and related methods

CN115199619BActive Publication Date: 2026-08-28THE BOEING CO
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Patent Information

Application Number
CN202210343926.5
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Priority Date
2021-04-05
Filing Date
2022-04-02
Publication Date
2026-08-28
Estimated Expiration
2042-04-02

AI Technical Summary

Technical Problem

[0005]所公开实施例解决了当前系统和方法的上述以及其他缺点、不便和低效问题

Benefits of technology

[0005]所公开实施例解决了当前系统和方法的上述以及其他缺点、不便和低效问题。因此，所公开实施例包括一种用于航天运载器的紧固系统，其包括：介电螺母保持条，由介电材料形成，该介电螺母保持条具有至少一个紧固件通孔和至少一个帽接收部；抗旋转螺母保持部，一体地形成在介电螺母保持条中并与至少一个紧固件通孔相邻；帽，构造成与至少一个帽接收部相匹配；紧固件；以及抗旋转螺母，构造成配合在抗旋转螺母保持部中并且与紧固件相联接。在其他所公开实施例中，帽可以是介电材料。在又一所公开实施例中，紧固件覆盖在导电涂层中。

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Abstract

A fastening system for a space vehicle includes a dielectric nut retention strip formed of a dielectric material and having at least one fastener through hole and at least one cap receiving portion. Also included is an anti-rotation nut retention portion integrally formed in the dielectric nut retention strip adjacent the at least one fastener through hole, a cap configured to mate with the at least one cap receiving portion, a fastener covered in a conductive coating, and an anti-rotation nut configured to fit in the anti-rotation nut retention portion and coupled with the fastener.
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Claims

1. A fastening system for a space launch vehicle, comprising: A dielectric nut retainer strip, formed of dielectric material, includes at least two fastener through holes and at least two cap receiving portions; At least two anti-rotation nut retainers are integrally formed in the dielectric nut retainer strip and adjacent to the at least two fastener through holes; At least two caps are configured to match the receiving portions of the at least two caps; At least two fasteners; as well as At least two anti-rotation nuts are configured to engage in the anti-rotation nut retainer and be connected to the fastener.

2. The fastening system for a space launch vehicle according to claim 1, wherein: The cap comprises a dielectric material; and The fasteners are covered with a conductive coating.

3. The fastening system for a space launch vehicle according to claim 1, further comprising: A reinforcing member is formed in the dielectric nut retaining strip; as well as The substructure fastener, located on the dielectric nut retaining strip, is configured to engage at least a portion of the space launch vehicle substructure.

4. The fastening system for a space launch vehicle according to claim 3, wherein, The substructure fastener is configured to engage with a part of a substructure located inside the wing of a space launch vehicle.

5. The fastening system for a space launch vehicle according to claim 4, wherein, The at least two fasteners can be inserted from outside the spacecraft wing into the at least two fastener through holes of the dielectric nut retainer.

6. The fastening system for a space launch vehicle according to claim 2, wherein, The conductive coating includes an indium paste.

7. The fastening system for a space launch vehicle according to claim 2, wherein, The conductive coating includes a conductive sleeve.

8. A method for assembling the wings of a space launch vehicle, the method comprising: Insert at least two nuts into at least two nut retaining recesses formed on the dielectric nut retaining strip; The dielectric nut retaining strip is attached to the wing structure above the two fastener holes; At least two caps are applied to the dielectric nut retaining strip above the at least two nuts located in the at least two nut retaining recesses; Position the wing skin above the two fastener holes; Insert the fasteners through the wing skin into the two fastener holes; as well as The fastener is tightened to the at least two nuts.

9. The method for assembling a space launch vehicle wing according to claim 8, wherein, After applying the at least two caps to the dielectric nut retaining strip, the method further includes: A conductive coating is applied to the fastener hole and the at least two nuts.

10. The method for assembling a space launch vehicle wing according to claim 9, wherein, The conductive coating includes an indium paste.

11. The method for assembling a space launch vehicle wing according to claim 8, further comprising: The fastener is coated with a conductive coating.

12. The method for assembling a space launch vehicle wing according to claim 11, wherein, The conductive coating includes an indium paste.

13. A method for manufacturing a dielectric nut retainer strip, the method comprising: A strip of dielectric material is formed, the strip of dielectric material having a first side, the first side including at least two cap receiving portions configured as receiving caps; as well as An anti-rotation nut retainer is formed on the second side of the strip of dielectric material at each of the at least two cap receiving portions.

14. The method for manufacturing a dielectric nut retainer strip according to claim 13, further comprising: A substructure joint is formed, the substructure joint being configured to engage with a substructure of the space launch vehicle.

15. The method for manufacturing a dielectric nut retainer strip according to claim 13, further comprising: A reinforcing member is formed on at least one edge of the strip of dielectric material.

Citation Information

Patent Citations

  • Fluid-tight mechanical fastening system and associated structural assembly

    EP3260708A1

  • Fastener systems that provide EME protection

    US20130259604A1