Side thruster module

Abstract

A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a thrust generated from the first thruster in the longitudinal direction into the radial direction. A large number of thrusters can be mounted at the side thruster module thus to generate a high thrust, and the side thruster module can be slim in the radial direction perpendicular to the longitudinal direction.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention.

In the drawings:

FIG. 1 is a sectional view showing a side thruster module according to a first embodiment of the present invention;

FIG. 2 is a sectional view of a first thruster of FIG. 1;

FIG. 3 is a sectional view of a body skin that forms a first-row conversion nozzle taken along line III-III of FIG. 1;

FIG. 4 is a sectional view of a body skin that forms a second-row conversion nozzle taken along line IV-IV of FIG. 1;

FIG. 5 is a sectional view of a second thruster of FIG. 1;

FIG. 6 is a sectional view showing a state that a first-row injection nozzle is jointed to a body skin, which is taken along line VI-VI of FIG. 1;

FIG. 7 is a sectional view showing a state that a second-row injection nozzle is jointed to a body skin, which is taken along line VII-VII of FIG. 1; and

FIG. 8 is a view showing a body skin of FIG. 1.

Claims

1. A side thruster module, comprising: a cavity-type body skin extending in a longitudinal direction;a first thruster arranged in the body skin and extending in a longitudinal direction; anda conversion nozzle arranged in the body skin and extending in a radial direction perpendicular to the longitudinal direction, for converting a direction of a_thrust generated from the first thruster in the longitudinal direction into the radial direction.

2. The side thruster module of claim 1, wherein the first thruster comprises: a cavity-type combustion tube;a propellant arranged in the combustion tube for generating a thrust at the time of combustion; andan igniter jointed to the combustion tube for igniting the propellant.

3. The side thruster module of claim 2, wherein the combustion tube is formed by filament-winding a composite material on an outer circumference of a cavity-type alloy steel.

4. The side thruster module of claim 3, wherein the cavity-type alloy steel is a titanium alloy, and the composite material is a carbon fiber.

5. The side thruster module of claim 2, wherein the propellant is a solid propellant, and the first thruster further comprises a liner attached to an inner wall of the combustion tube for jointing the solid propellant to the inner wall.

6. The side thruster module of claim 1, wherein the conversion nozzle is integrally formed at the body skin, and the conversion nozzle includes: a length portion opened in the longitudinal direction and connected to the first thruster; anda radius portion opened in the radial direction and connected to the length portion and outside.

7. The side thruster module of claim 6, wherein the conversion nozzle is provided in plural, and the conversion nozzles adjacent to each other in the longitudinal direction have the radius portions of different lengths so that the first thrusters jointed to the conversion nozzles be stacked in the radial direction.

8. The side thruster module of claim 1, wherein the conversion nozzle is integrally formed at an inner circumference of the body skin, and further comprising a jointing portion formed between the conversion nozzle and the first thruster for jointing therebetween.

9. The side thruster module of claim 8, wherein the jointing portion includes: a male screw thread formed on one of an inner circumferential surface of an inlet of the conversion nozzle and an outer circumferential surface of an outlet of the first thruster; anda female screw thread formed on another of an inner circumferential surface of an inlet of the conversion nozzle and an outer circumferential surface of an outlet of the first thruster, and jointed to the male screw thread.

10. The side thruster module of claim 1, wherein the first thruster and the conversion nozzle are arranged in a circumferential direction of the body skin in plural, and a weight reduction hole for reducing a weight of the body skin is formed between the adjacent conversion nozzles of the body skin.

11. The side thruster module of claim 2, further comprising a conversion nozzle closure jointed to an outlet of the conversion nozzle for sealing the conversion nozzle and a combustion tube connected to the conversion nozzle.

12. The side thruster module of claim 1, further comprising a second thruster arranged in the body skin so as to be extending in the radial direction for generating a thrust in the radial direction through a jointing groove of the body skin.

13. The side thruster module of claim 12, wherein the second thruster comprises: a cavity-type combustion tube;a propellant arranged in the combustion tube for generating a thrust at the time of combustion;an igniter jointed to the combustion tube for igniting the propellant; andan injection nozzle jointed to an outlet of the combustion tube for outwardly injecting a thrust generated by a combustion of the propellant through the jointing groove of the body skin.

14. The side thruster module of claim 13, wherein the combustion tube is formed by filament-winding a composite material on an outer circumference of a cavity-type alloy steel.

15. The side thruster module of claim 14, wherein the cavity-type alloy steel is a titanium alloy, and the composite material is a carbon fiber.

16. The side thruster module of claim 13, wherein the propellant is a solid propellant, and the second thruster further comprises a liner attached to an inner wall of the combustion tube for jointing the solid propellant to the inner wall.

17. The side thruster module of claim 13, further comprising a jointing portion formed between an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove, for jointing the injection nozzle to the jointing groove.

18. The side thruster module of claim 17, wherein the jointing portion includes: a male screw thread formed on one of an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove; anda female screw thread formed on another of an outer circumferential surface of the injection nozzle and an inner circumferential surface of the body skin that defines the jointing groove, and jointed to the male screw thread.

19. The side thruster module of claim 13, further comprising an injection nozzle closure jointed to an outlet of the injection nozzle for sealing the combustion tube.

20. The side thruster module of claim 12, wherein the second thruster is arranged in a circumferential direction of the body skin in at least two rows, and the second thrusters of adjacent two rows are arranged in a zigzag form.