LIGHTWEIGHT PASSIVE ATTENUATOR FOR SPACECRAFT

Abstract

A lightweight passive attenuator (1) for spacecraft includes two omega cross-section rings (2), placed symmetrically and defining a gap therebetween, and being the main load path of the light passive attenuator (1). A plurality of damper elements (3) are placed in the gap defined between the two omega cross-section rings (2), and not in the main load path of the light passive attenuator (1), such that the omega cross-section rings (2) and the damper elements (3) are assembled at their ends by attachment elements. The omega cross-section rings (2) have a protruding central part (5) with a plurality of holes (6) for connection with adjacent structures (7, 8) of the spacecraft.

Claims

1. A lightweight passive attenuator for spacecraft, comprising: two omega cross-section rings, placed symmetrically and defining a gap therebetween, the gap being a main load path of the lightweight passive attenuator, and a plurality of damper elements placed in the gap defined between the two omega cross-section rings and out of the main load path of the lightweight passive attenuator, wherein the omega cross-section rings and the damper elements are assembled at ends by attachment means, and the omega cross-section rings have a protruding central part with a plurality of holes for connection with adjacent structures of the spacecraft.

2. The lightweight passive attenuator for spacecraft according to claim 1, wherein the omega cross-section rings are metallic.

3. The lightweight passive attenuator for spacecraft, according to claim 1, wherein the damper elements contain elastomers.

4. The lightweight passive attenuator for spacecraft, according to claim 3, wherein the damper elements are made of aluminium and vulcanized elastomer.

5. The lightweight passive attenuator for spacecraft, according to claim 1, wherein parts of the omega cross-section rings that connect the ends to the protruding central parts have a variable thickness with a thinner central portion, and the thickness at their ends is less than the thickness at the protruding central parts.

6. The lightweight passive attenuator for spacecraft, according to claim 1, comprising 36 of the damper elements of approximately 10?.

7. The lightweight passive attenuator for spacecraft, according to claim 1, wherein the omega cross-section rings and the damper elements are assembled by bolts.

8. The lightweight passive attenuator for spacecraft, according to claim 1, wherein one of the omega cross-section rings has at least two venting holes.

Description

BRIEF DESCRIPTION OF DRAWINGS

[0023] FIG. 1 shows a general perspective view of the light passive attenuator for spacecraft of the invention.

[0024] FIG. 2 shows a top view of the light passive attenuator for spacecraft of the invention.

[0025] FIG. 3 is a detail of FIG. 2, without one of the omega cross-section rings, showing damper elements of the invention.

[0026] FIG. 4 is a detailed assembly view of the light passive attenuator for spacecraft of the invention.

[0027] FIG. 5 is a cross section of an omega cross-section ring of the invention.

[0028] FIG. 6 is a perspective view of a damper element of the invention.

[0029] FIG. 7 is a plan view of a damper element of the invention.

[0030] FIG. 8 is a view of the working principle of the light passive attenuator of the invention.

[0031] FIG. 9 shows the spring and damper elements of the invention.

[0032] FIG. 10 shows an assembly of the light passive attenuator of the invention with the adjacent structures.

[0033] FIGS. 11 and 12 show the assembly of the lower omega cross-section ring with the adjacent structure.

[0034] FIG. 13 shows the assembly of the upper omega cross-section ring with the adjacent structure, and the final assembly of the light passive attenuator of the invention.

[0035] FIG. 14 shows the results of a stiffness test at subscale level.

[0036] FIG. 15 shows the results of a sine vibration test at full scale level.

[0037] FIG. 16 shows the results of a sine vibration test at full scale level with and without LPA.

[0038] FIGS. 17 and 18 show shock test results with and without the light passive attenuator (LPA) of the invention.

DETAILED DESCRIPTION OF THE INVENTION

[0039] FIG. 1 shows a perspective view of the he light passive attenuator 1 for spacecraft of the invention. It is mainly formed by two omega cross-section rings 2 placed symmetrically. Between the two omega-cross rings 2 there is a gap, where a plurality of damper elements 3 are placed.

[0040] The two omega cross-section rings 2 are the main load path of the light passive attenuator 1 and are in charge of providing the stiffness.

[0041] The two omega cross-section rings 2 are continuous elements which are assembled face to face. The damper elements 3 are placed in parallel with the omega cross-section rings 2, i.e., they are not in the main load path of the light passive attenuator 1. The dynamic payload isolation is obtained by a combination of elastic and damping elements (see FIGS. 8 and 9, which show the spring 9 and damper 10 elements of the light passive attenuator 1).

[0042] The omega cross-section rings 2 and the damper elements 3 are assembled at their ends by means of attachment means 4 (see for instance FIGS. 11 to 13).

[0043] An omega cross-section ring 2 is represented in FIG. 5. It has a protruding central part 5 with a plurality of holes 6 for connection with the adjacent structures 7, 8 of the spacecraft.

[0044] The omega cross-section rings 2 are preferably metallic and the damper elements 3 may contain elastomers to improve the isolation performance. The damper elements 3 may be made of aluminium and vulcanized elastomer working in double shear (see FIGS. 6 and 7).

[0045] Preferably, there are 36 damper elements 3 of approximately 10? (see FIGS. 3, 6 and 7).

[0046] According to an embodiment, the omega cross-section rings 2 and the damper elements 3 are assembled at their ends by means of bolts (see FIG. 4).

[0047] According to another embodiment, one of the omega cross-section rings 2 has at least two venting holes 11 (see FIG. 4).

[0048] In FIG. 5 it can be seen that the parts of the omega cross-section rings 2 that connect their ends to their protruding central parts 5 can have a variable thickness with a thinner central portion, and the thickness at their ends can be less than the thickness at their protruding central parts 5.

[0049] FIGS. 11 to 13 show the assembly process of the light passive attenuator components, and of the light passive attenuator 1 with the adjacent structures 7, 8.

[0050] The first step (FIG. 11) consists in the assembly of the lower omega cross-section ring 2 with the adjacent structure 8.

[0051] The second step (FIG. 12) consists in the assembly of the damper elements 3 and the upper omega cross-section ring 2 with the lower omega cross-section ring 2.

[0052] The third step (FIG. 13) consists in the assembly of the upper adjacent structure 7 with the upper omega cross-section ring 2.

[0053] Several tests have been carried out to check the correct performance of the light passive attenuator 1 for spacecraft of the invention. Specifically, shock tests and sine vibration tests have been carried out, comparing the transmission with and without the light passive attenuator 1 to evaluate its efficiency.

[0054] FIG. 14 shows the results of a stiffness test at subscale level. There is good stiffness linearity of the light passive attenuator 1 with respect to load level in spite of the elastomer beyond the limit load (LL).

[0055] FIG. 15 shows the results of a sine vibration test at full scale level. As it can be seen, there is a good stability of the stiffness and damping with respect to load level. Good damping is obtained (low amplification factor Q value <10; see the table below):

TABLE-US-00001 Level (g) 1st Lateral Frequency (Hz) Amplification Q 0.1 43.6 8.1 0.4 43.0 8.0 0.8 42.4 8.0 1.2 41.7 7.8 0.1 43.6 8.1

[0056] FIG. 16 shows the results of a sine vibration test at full scale level with and without LPA 1. As it can be seen, there is a good reduction of the amplification at the first mode (factor of reduction >2).

[0057] FIGS. 17 and 18 show shock test results with and without the light passive attenuator (LPA) of the invention. The shock filtering efficiency is proven by test (9 dB in radial and axial accelerations).

[0058] Accordingly, the light passive attenuator 1 of the invention has the following features: [0059] Very simple design, manufacturing and installation. [0060] Payload domain up to 6400 kg with lateral frequency higher than 6 Hz. [0061] Low height (less than 75 mm) and low mass (less than 75 kg). [0062] Linear stiffness up to the limit load of the elastomer and beyond. [0063] It does not induce overfluxes to the adjacent structures. [0064] Good reduction of the amplification of the main modes (factor of reduction>2). [0065] Good shock attenuation (?9 dB in radial and axial).

[0066] The light passive attenuator 1 is preferably placed at the 1780 mm interface diameter. However, its concept could be easily scaled to other interface diameter of the launcher.

[0067] Although the present invention has been fully described in connection with preferred embodiments, it is evident that modifications may be introduced within the scope thereof, not considering this as limited by these embodiments, but by the contents of the following claims.