Payload adapter ring

Abstract

A lightweight spacecraft dispenser, which consists of a material made from composite materials, and of a ring structure with several payload ports. The ring structure has a surface that extends between opposite ends of the ring structure and that is at least partially spherical. The surface can be completely spherical or partially spherical between the opposite ends.

Claims

1. A lightweight spacecraft dispenser consisting of: a material made from composite materials; and a ring structure including a plurality of payload ports and a surface that extends between opposite ends of the ring structure and that is at least partially spherical.

2. The lightweight spacecraft dispenser of claim 1, wherein the ring structure is an integral composite material structure.

3. The lightweight spacecraft dispenser of claim 1, wherein the ring structure includes an adapter on an end of the ring structure.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 shows a perspective view of a lightweight spacecraft dispenser of the invention.

(2) FIG. 2 shows a perspective view of another embodiment of a lightweight spacecraft dispenser of the invention.

(3) FIG. 3 shows a view of a primary spacecraft mounted on a lightweight spacecraft dispenser of the invention.

DETAILED DESCRIPTION

(4) FIG. 1 shows a lightweight spacecraft dispenser 1 which consists of a ring structure with several payload ports 2. The ring structure has two opposite ends, and a surface 3 extends between these two opposite ends.

(5) The surface 3 of the lightweight spacecraft dispenser 1 can be at least partially spherical. In the embodiment of FIG. 1, the surface 3 of the lightweight spacecraft dispenser 1 is completely spherical.

(6) FIG. 2 shows a lightweight spacecraft dispenser 1. An adaptor 5 is placed on one of the ends of the ring structure.

(7) FIG. 3 shows a primary spacecraft 4 mounted on the lightweight spacecraft dispenser 1 of FIG. 2. In FIG. 3 it can also be seen that the adaptor 5 is connected to the primary spacecraft 4, and can have a tapered shape. FIG. 3 also shows a small satellite 6, which can be coupled in its corresponding payload port 2.

(8) According to another embodiment, the payload ports 2 comprise secondary mounts with flanges.

(9) The use of composites for manufacturing the spacecraft dispenser 1 allows for weight reduction. For instance, an ESPA configuration of a height of 1,05 m and 6 ports of 610 mm of diameter weights about 168 kg. For a configuration according to the invention (for instance, using Epoxy/M40J) the weight would be about 120 kg.

(10) By using composite materials, the dispenser 1 can provide an important mass reduction with respect to the existing ESPA ring concept dispensers. That allows a potential increase in the spacecraft masses.

(11) Also, the use of automatic manufacturing techniques (such as AFP, Automated Fiber Placement) for composites would allow for cost reduction.

(12) Although the present invention has been fully described in connection with preferred embodiments, it is apparent that modifications may be introduced within its scope, not considering this as limited by these embodiments, but by the content of the following claims.