Vibration isolation module having reduced nonlinear effects

Patent metadata

Field	Value
Publication number	US-9726248-B2
Application number	US-201415033600-A
Country	US
Kind code	B2
Filing date	Oct 23, 2014
Priority date	Oct 31, 2013
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

An isolation module between a vibration generating device, such as a satellite launcher, and a structure to be isolated, such as the structure carrying a satellite, comprising: at least two fastening parts, and a connecting means. The first fastening part, called the frame, comprises at least two parallel radial branches, and the second fastening part, called the support, comprises at least one radial branch extending between the two branches of the frame. The connecting means is made from an elastomer material and includes at least one pair of identical elastomer pads, being mounted in series between the frame and the support.

First claim

The invention claimed is:

1. An isolation module between a satellite launcher, which is a vibration-generating device, and a satellite structure to be isolated, the isolation module comprising:
at least two fastening parts intended to be fastened respectively on the vibration-generating device and the structure to be isolated,
an elastomeric connecting means interposed between the two fastening parts, allowing at least one degree of freedom in translation along a longitudinal axis between the two fastening parts,
wherein a first fastening part, comprises a frame that includes;
two lower branches, one within the continuous extension of the other,
two upper branches one within the continuous extension of the other; and
a longitudinal branch extending in the longitudinal plane of symmetry, the frame forming an H,
the two upper branches and two lower branches of the frame being symmetrical with each other with respect to a plane perpendicular to the longitudinal axis,

wherein a second fastening part, comprises a support, the support includes;
two aligned median branches, one extending toward the other without meeting, the support forming a C,

wherein each of the support median branches extend between two branches of the frame,
the frame and the support each have a longitudinal plane of symmetry perpendicular to the radial axis, and in which,
the elastomeric connecting means comprise at least one pair of identical elastomer pads, in which each pad extends along the longitudinal axis between a first end and a second end, a first pad having the first end supported on a lower branch of the frame and the second end supported on the median branch of the support and the second pad having the first end supported on the upper branch of the frame and the second end supported on the median branch of the support, the two pads of the pair being thus mounted in parallel between the frame and the support and being active along the longitudinal axis in opposite directions, so that when one pad works under tension, the other pad of the pair works under compression, and vice-versa, a stiffness of the module being symmetrical, whether a force applied thereto along the longitudinal axis is oriented in one direction or the opposite direction, and

each pad is dimensioned so that a contact surface S 1 of one end in contact with a radial branch and a free contact surface S 2 satisfy the relationship:

S
1

S
2

≤
3.

2. The isolation module according to claim 1 , in which the assembly formed by the two fastening parts has a relative stiffness comprised between 5% and 30% of the total stiffness of the module.

3. The isolation module according to claim 2 , in which the relative stiffness is contributed by a single one of the two fastening parts.

4. The isolation module according to claim 2 , in which the relative stiffness is comprised between 20% and 30% of the total stiffness of the module.

5. The isolation module according to claim 1 , comprising a plurality of pairs of elastomer pads.

6. The isolation module according to claim 1 , in which each fastening part comprises a fastening surface, suitable for placing in contact directly or indirectly with one or other of the vibration-generating device and the structure to be isolated, the fastening surface of the frame being parallel to the fastening surface of the support.

7. The isolation module according to claim 6 , in which the fastening surfaces of the two fastening parts are perpendicular to a fastening axis parallel to the longitudinal axis.

8. The isolation module according to claim 6 , in which the fastening surfaces of the two fastening parts are perpendicular to a fastening axis that is inclined with respect to the longitudinal axis.

9. The isolation module according to claim 8 , in which the angle of inclination of the fastening axis with respect to the longitudinal axis is 40°.

10. The isolation module according to claim 9 , in which the fastening location of the frame respectively on one or other of the vibration-generating device and the structure to be isolated and the fastening location of the support respectively on one or other of the structure to be isolated and the vibration-generating device are aligned along the longitudinal axis.

11. The isolation module according to claim 10 , in which the frame comprises two lower branches one within the continuous extension of the other and two upper branches one within the continuous extension of the other, extending on either side of two longitudinal branches, the two lower branches having an opening, and in which the support is in the shape of a T, and comprises two median branches extending on either side of a central longitudinal branch passing through the opening of the frame so that the median branches extend between the branches of the frame.

12. The isolation module according to claim 1 , in which the vibration-generating device is a launcher for an artificial satellite and the structure to be isolated is the structure carrying an artificial satellite.

13. The isolation module according to claim 12 , in which the satellite launcher comprises a circular launcher interface ring and in which the carrying structure comprises a circular satellite interface ring, a plurality of isolation modules being mounted between the interface rings, the frame of each module being rigidly fastened respectively on one or other of the launcher interface ring or the satellite interface ring and the support of each module being rigidly fastened respectively on one or other of the satellite interface ring or the launcher interface ring, each module being arranged so that its longitudinal axis is parallel to the longitudinal axis of the other modules.

14. An isolation module between a satellite launcher, which is a vibration-generating device, and a satellite structure to be isolated, the isolation module comprising:
at least two fastening parts intended to be fastened respectively on the vibration-generating device and the structure to be isolated,
an elastomeric connecting means interposed between the two fastening parts, allowing at least one degree of freedom in translation along a longitudinal axis between the two fastening parts,
wherein a first fastening part, includes a frame of at least two parallel radial branches comprised of two lower branches and two upper branches, the two lower branches and the two upper branches disposed at a distance from each other along the longitudinal axis,
wherein a second fastening part is a support which comprises at least one radial branch called a median branch, the median branch extending between the two radial branches of the frame, the two radial branches of the frame being symmetrical with each other with respect to a plane perpendicular to the longitudinal axis,
wherein one of the two lower branches of the frame is disposed within the continuous extension of the other and one of the two upper branches is disposed within the continuous extension of the other, extending on either side of two longitudinal branches, the two lower branches having an opening, and in which the support is in the shape of a T, and comprises two median branches extending on either side of a central longitudinal branch passing through the opening of the frame so that the median branches extend between the branches of the frame,
wherein each of

Assignees

• Airbus Defence & Space Sas

Inventors

• Camarasa Patrick
• Dhieux Emmanuel

Classifications

• F16F3/12 Primary

  the steel spring being in contact with the rubber spring {(F16F1/12 takes precedence)} · CPC title

• F16F2230/00

  Purpose; Design features · CPC title

• F16F15/08

  with rubber springs {(grommet- or bushing-type resilient mountings F16F1/3732, F16F1/38); with springs made of rubber and metal (arrangement of internal-combustion or jet-propulsion units B60K5/12; mounting of propulsion plants on vessels B63H21/30; mounting of vehicle drivers' cabs B62D33/0604)} · CPC title

• F16F1/40

  consisting of a stack of similar elements separated by non-elastic intermediate layers {(F16F9/306 takes precedence; laminated constructions to protect buildings against abnormal external influences, e.g. earthquakes, E04H9/022)} · CPC title

• B64G1/641

  Interstage or payload connectors (docking systems B64G1/646) · CPC title