Aeronautics and astronautics – Spacecraft – Spacecraft formation – orbit – or interplanetary path
Patent
1997-02-06
1999-01-19
Jordan, Charles T.
Aeronautics and astronautics
Spacecraft
Spacecraft formation, orbit, or interplanetary path
244161, B64G 164
Patent
active
058606246
DESCRIPTION:
BRIEF SUMMARY
DESCRIPTION
1. Technical Field
The invention relates to an adaptor designed for installation on a launcher carrying structure when the launcher is intended to simultaneously carry in juxtaposed manner at least two payloads, such as satellites.
Such an adaptor can be used on any type of launcher, when it is wished to simultaneously carry several heavy satellites in juxtaposed manner beneath the nose cone of the same launcher.
2. Prior Art
In order to reduce satellite launching costs, ever more frequently consideration is given, when their size permits, to simultaneously carrying several satellites on the same launcher.
Means making it possible to simultaneously carry several satellites on the same launcher and then separate the satellites therefrom are already operational. For example, U.S. Pat. No. 3,380,687 and U.S. Pat. No. 5,199,672 illustrate means for placing beneath the nose cone of a launcher in order to simultaneously support there a relatively large number of small satellites.
In the case of heavy and relatively large satellites, none of the known means make it possible to completely eliminate collision risks when the satellites separate from the launcher. Thus, such satellites are conventionally juxtaposed on a carrying structure in the form of a plate or platform and their separation from the latter takes place perpendicular thereto. The ejection of a satellite inevitably then produces collision risks with the neighbouring satellite or satellites, when the distance separating them is relatively small.
DE-A-42 43562 proposes installing very small payloads on the same launcher. In one of the embodiments described, the loads are placed on the carrying structure by means of an adaptor making it possible to incline the load before it is separated from the launcher. More specifically, the means comprises a part mounted in tilting manner on the carrying structure, a guidance part carried by the tilting part and a carrying part to which is fixed the load. The flight stresses are taken up by the guidance of the carrying part on the guidance part. Prior to launch, a tilting mechanism controls the tilting of the three parts with respect to the carrying structure. The operation of an explosive bolt, initially connecting the guidance part to the carrying part, has the effect of ejecting the load and said latter part under the action of ejection springs.
The arrangement described in DE-A-42 43562 makes it possible to avoid collision risks between small loads carried by the same launcher during the launch of said loads. However, it is completely inappropriate for the launching of heavy satellites incorporating fragile elements. Thus, the tilting control mechanism supports all the stresses and loads which are then exerted by the ejection springs. Therefore the mechanism must be dimensioned in such a way that said stresses have no effect on the orientation of the load during its ejection. In the case of a heavy load, this dimensioning will lead to the application of a considerable shock or impact to each load during tilting prior to ejection. Such a shock is unacceptable because it may damage and/or misadjust certain components of the satellite.
Moreover, the means described in DE-A-42 43562 makes it necessary to eject a carrying part with the satellite. This increases the weight of the latter and therefore accentuates the previous disadvantage. In general terms, such a weight increase is highly prejudicial, particularly as it occurs on each of the satellites carried by the launcher.
DESCRIPTION OF THE INVENTION
The invention relates to an adaptor for interposing between the carrying structure placed beneath the nose cone of a launcher and each of the payloads, so as to permit, for a small size and without damaging or misadjusting the vehicle-borne systems and without any risk of collision during separation, the simultaneous carriage of at least two juxtaposed, relatively large and heavy payloads.
According to the invention, this result is obtained by means of a payload adaptor to be installed on a carrying
REFERENCES:
patent: 3380687 (1968-04-01), Wrench et al.
patent: 3420470 (1969-01-01), Meyer
patent: 3547375 (1970-12-01), Mackey
patent: 3903803 (1975-09-01), Losey
patent: 3907225 (1975-09-01), Welther
patent: 4632339 (1986-12-01), Yuan
patent: 4679752 (1987-07-01), Wittmann et al.
patent: 4776539 (1988-10-01), Byers et al.
patent: 4860974 (1989-08-01), Barnett et al.
patent: 5040748 (1991-08-01), Torre et al.
patent: 5199672 (1993-04-01), King et al.
patent: 5411226 (1995-05-01), Jones et al.
patent: 5529264 (1996-06-01), Bedegrew et al.
patent: 5743492 (1998-04-01), Chan et al.
Chevalier Guy
Obry Daniel
Pimont Raymond
Aerospatiale - Societe Nationale Industrielle
Ducker, Jr. Charles R.
Jordan Charles T.
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