WO1994020364A1

WO1994020364A1 - Launching vehicle

Info

Publication number: WO1994020364A1
Application number: PCT/US1994/002171
Authority: WO
Inventors: Dov Raviv
Original assignee: Arnowitz, Leonard, A.
Priority date: 1993-03-02
Filing date: 1994-03-01
Publication date: 1994-09-15
Also published as: AU6251994A; IL104925A; IL104925A0

Abstract

A launching vehicle for a payload (16) comprising at least one solid rocket motor stage (10) and a restartable final stage (14) preceded only by one or more solid rocket motor stages (12) the restartable final stage (14) being operative for satellizing a payload (16) and having a thrust which is at least equal to the earth weight of the payload (16).

Description

LAUNCHING VEHICLE

FIELD OF THE INVENTION

The present invention relates generally to the launching of payloads into low-earth, geostationary and geostationary transfer orbits around the earth and more particularly to a modular family of launch vehi- cles for this purpose.

BACKGROUND OF THE INVENTION

Various configurations and designs of launch vehicles are represented in the literature. It is well known to employ a configuration consisting of three or more solid fuel stages or consisting of a plurality of initial solid fuel rocket stages followed by a small liquid or bi-propellant powered stage for positioning or orbit transfer.

SUMMARY OF THE INVENTION

The present invention seeks to provide an improved launching vehicle. There is thus provided a launching vehicle for a payload comprising at least one solid rocket motor stage and a restartable final stage, preceded only by one or more solid rocket motor stages, the restartable final stage being operative for satellizing a payload and having a thrust which is at least equal to the earth weight of the payload. Preferably, the final stage is also operative for shaping the orbit of the payload. The final stage should have a thrust of at least 10,000 newtons and preferably has a thrust of at least 30,000 newtons. Preferably, the final stage provides an incremental velocity to the payload of at least 1000 m/sec during satellization. There is also provided a launching vehicle for a payload comprising a two stage solid fueled rocket, the second stage being operative for satelliz- ing a payload.

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BRIEF DESCRIPTION OF THE DRAWINGS

The present invention will be more fully appreciated and understood from the following detailed description, taken in conjunction with the drawings in which: Fig. 1 is a simplified illustration of a three stage launch vehicle constructed and operative in accordance with a preferred embodiment of the present invention; Figs. 2A and 2B are simplified illustrations of two alternative embodiments of a two stage launch vehicle constructed and operative in accordance with a preferred embodiment of the present invention; Fig. 3 is a simplified illustration of a four stage launch vehicle constructed and operative in accordance with a preferred embodiment of the present invention; and Fig. 4 is a simplified illustration of the satellization and subsequent operation of a restartable liquid final stage of the launch vehicles shown in Figs. 1 - 3.

DETAILED DESCRIPTION OF A PREFERRED EMBODIMENT

Reference is now made to Fig. 1, which illus- trates a launch vehicle constructed and operative in accordance with a preferred embodiment of the present invention. The launch vehicle preferably comprises first and second solid fueled initial stages 10 and 12, followed by a restartable final stage 14 which is operative for satellization of a payload 16. The term "satellization" is used to mean insertion of the pay- load into an earth orbit. Fig. 2A illustrates an alternative embodiment of a launch vehicle in which a single initial solid fueled stage 20 is provided together with a restartable final stage 22 which is operative for satellization of a payload 24. Fig. 2B illustrates a further alternative embodiment of a launch vehicle in which a pair of solid fueled stages 26 and 28 are operative for satellization of a payload 29. It is a particular feature of this embodiment that satellization is realized by a two stage solid fueled launch vehicle.

Reference is now made to Fig. 3, which illus- trates a further alternative embodiment of a launch vehicle constructed and operative in accordance with a preferred embodiment of the present invention. The launch vehicle preferably comprises first, second and third solid fueled initial stages 30, 32 and 34, fol- lowed by a restartable final stage 36 which is opera- tive for satellization of a payload 38. Fig. 4 illustrates the operation of the launch vehicles of Figs. 1 - 3. One or more initial stages provide initial thrust, while satellization is produced by a restartable stage, which produces a delta V of greater than 1000 m/sec for satellization. There- after, for transferring orbits or adjusting the orbit, the restartable stage is operated again to provide one or more additional burns. It will be appreciated by persons skilled in the art that the present invention is not limited by what has been particularly shown and described hereina- bove. Rather the scope of the present invention is defined only by the claims which follow:

Claims

C L A I M S

1. A launching vehicle for a payload comprising at least one solid rocket motor stage and a restartable final stage, preceded only by one or more solid rocket motor stages, the restartable final stage being opera- tive for satellizing a payload and having a thrust which is at least equal to the earth weight of the payload.

2. A launching vehicle according to claim 1 and wherein the final stage is also operative for shaping the orbit of the payload.

3. A launching vehicle according to either of claims 1 and 2 and wherein said final stage has a thrust of more than 10,000 newtons.

4. A launching vehicle according to claim 3 and wherein said final stage has a thrust of at least 30,000 newtons.

5. A launching vehicle according to any of the preceding claims and wherein said final stage provides an incremental velocity to the payload of at least 1000 m/sec .