Mounting system for mechanical-shock resistant printed circuit board (PCB)

Patent metadata

Field	Value
Publication number	US-10617028-B2
Application number	US-201816218961-A
Country	US
Kind code	B2
Filing date	Dec 13, 2018
Priority date	Mar 19, 2015
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A shock resistant fuselage system includes first and second fuselage side walls, each of the first and second fuselage side walls having a plurality of guide posts, and a printed circuit board (PCB) rigidly attached to at least one of the first and second fuselage side walls, the PCB having a plurality of guide slots, each of the plurality of guide posts slideably seated in a respective one of the plurality of guide slots so that elastic deformation of the PCB is guided by the guide slots between the first and second fuselage side walls.

First claim

What is claimed is:

1. A shock resistant fuselage system, comprising:
a frame having a plurality of guide posts and at least one fixed post;
a printed circuit board (PCB) rigidly attached to the frame, the PCB having a plurality of guide slots and at least one mounting hole, wherein at least one guide post of the plurality of guide posts is slideably seated in a respective one of the plurality of guide slots, and wherein at least one fixed post is fixedly seated in a respective one of the at least one mounting hole; and
a plurality of electrical components mounted to the PCB are arranged such that each of the plurality of electrical components are mounted with their major longitudinal axis oriented perpendicularly to a major longitudinal axis of the frame;
wherein elastic deformation of the PCB is guided by the guide slots.

2. The system of claim 1 , wherein the frame comprises one or more fuselage side walls.

3. The system of claim 2 , wherein the one or more fuselage side walls are first and second fuselage side walls of a unitary fuselage clam shell.

4. The system of claim 1 , wherein the frame is a unitary section of a fuselage.

5. The system of claim 1 , wherein a major longitudinal axis of each of the plurality of guide slots extends parallel to the major longitudinal axis of the frame.

6. The system of claim 1 , wherein the PCB is rigidly attached to the frame at a front of the PCB board.

7. The system of claim 1 , wherein the PCB is rigidly attached to the frame at a rear of the PCB board.

8. A shock resistant fuselage system, comprising:
a frame having a plurality of guide posts and at least one fixed post;
a printed circuit board (PCB) rigidly attached to the frame, the PCB having a plurality of guide slots and at least one mounting hole, wherein at least one guide post of the plurality of guide posts is slideably seated in a respective one of the plurality of guide slots, and wherein at least one fixed post is fixedly seated in a respective one of the at least one mounting hole; and
a plurality of electrical components mounted to the PCB such that a larger proportion of larger electrical components of the plurality of electrical components are mounted at a PCB front end than a PCB rear end;
wherein elastic deformation of the PCB is guided by the guide slots.

9. The system of claim 8 , wherein the frame comprises one or more fuselage side walls.

10. The system of claim 9 , wherein the one or more fuselage side walls are first and second fuselage side walls of a unitary fuselage clam shell.

11. The system of claim 8 , wherein the frame is a unitary section of a fuselage.

12. The system of claim 8 , wherein a major longitudinal axis of each of the plurality of guide slots extends parallel to the major longitudinal axis of the frame.

13. The system of claim 8 , wherein the PCB is rigidly attached to the frame at a front of the PCB board.

14. The system of claim 8 , wherein the PCB is rigidly attached to the frame at a rear of the PCB board.

15. The system of claim 8 , wherein
the plurality of electrical components mounted to the PCB are arranged such that electrical components having relatively less sensitivity to PCB deformation are positioned in an area of the PCB having relatively less deformation.

16. The system of claim 8 , wherein electrical components having relatively larger widths are mounted distal from the at least one mounting hole.

17. The system of claim 16 , wherein electrical components having relatively smaller widths are mounted closer to the at least one mounting hole than the electrical components having relatively larger widths.

18. The system of PCB claim 8 wherein elastic deformation of the PCB is larger in an area of the PCB proximate the at least one fixed post.

19. The system of claim 8 wherein the at least one mounting hole is disposed at a central mounting point of the PCB.

20. The system of claim 8 wherein the at least one mounting hole is disposed at a center of mass of the PCB.

Assignees

• Aerovironment Inc

Inventors

• Nicoloff William John

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• H05K7/1422 Primary

  Printed circuit boards receptacles, e.g. stacked structures, electronic circuit modules or box like frames · CPC title

• H05K2201/2045

  Protection against vibrations · CPC title

• H05K1/0271 Primary

  Arrangements for reducing stress or warp in rigid printed circuit boards, e.g. caused by loads, vibrations or differences in thermal expansion · CPC title

• H05K5/0034

  having an overmolded housing covering the PCB · CPC title