Thrust vectoring apparatus and flying object having thrust vectoring apparatus

Patent metadata

Field	Value
Publication number	US-9663222-B2
Application number	US-201514746055-A
Country	US
Kind code	B2
Filing date	Jun 22, 2015
Priority date	Sep 17, 2014
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

The thrust vectoring apparatus has a nozzle, a jet tab arranged behind the nozzle, a rotation shaft 30 connected to the jet tab, and a gas seal member arranged on an outer circumferential surface of the rotation shaft. The rotation shaft is connected to the jet tab, and has the protrusion in the redial direction out of the rotation shaft on the rear side of the gas seal member. The protrusion restrains that the combustion gas exhausted from the nozzle flows toward the gas seal member.

First claim

What is claimed is:

1. A thrust vectoring apparatus comprising:
a nozzle having a nozzle output opening which emits a combustion gas in a rear direction;
a jet tab arranged on a rear side of the nozzle;
a rotation shaft connected to the jet tab to be rotatable around a rotation axis;
a driving mechanism configured to rotate the rotation shaft around the rotation axis; and
a gas seal member arranged on an outer circumferential surface of the rotation shaft to prevent the combustion gas from invading the driving mechanism,
wherein the jet tab is configured to rotate in a plane which intersects with a longitudinal center axis of the nozzle, by rotating the rotation shaft around the rotation axis, and to move from a standby position where the jet tab does not overlap with the nozzle output opening, to an operation position where the jet tab overlaps with the nozzle output opening,
wherein a first gap is formed between the jet tab and a surface of a rear end surface of the nozzle, and
wherein the rotation shaft has a protrusion arranged on a rear side of the gas seal member, and the protrusion protrudes in a radial direction from the rotation shaft.

2. The thrust vectoring apparatus according to claim 1 , wherein the protrusion is an annular protrusion.

3. The thrust vectoring apparatus according to claim 2 , further comprising:
a rotation shaft receiving member having a through-hole in which the rotation shaft is inserted,
wherein the gas seal member is arranged between an outer circumferential surface of the rotation shaft and the inner surface of the through-hole, and
wherein an outer diameter of the annular protrusion is larger than an inner diameter of the through-hole.

4. The thrust vectoring apparatus according to claim 1 , wherein the rear end surface of the protrusion is located in a forward direction from the outer circumferential edge of a rear end surface of the nozzle.

5. The thrust vectoring apparatus according to claim 1 , wherein the protrusion has an inclination section,
wherein the rear end surface of the inclination section is a first inclination surface which inclines in a forward direction along a radial direction from a longitudinal center axis of the nozzle.

6. The thrust vectoring apparatus according to claim 5 , wherein the protrusion has a flat section, and
wherein the flat section is located in the radial direction from the inclination section, when the jet tab is in an operation position.

7. The thrust vectoring apparatus according to claim 5 , wherein the rear end surface of the nozzle has a second inclined surface which inclines in the forward direction along the radial direction out of the nozzle, and
wherein an angle between a first surface which is perpendicular to the rotation axis and a first inclined surface is greater than an angle between the second inclined surface and a second surface which is parallel to the first surface.

8. The thrust vectoring apparatus according to claim 1 , wherein a plurality of said protrusions are provided for the rotation shaft to be apart from one after another along the longitudinal direction of the rotation shaft.

9. The thrust vectoring apparatus according to claim 1 , further comprising:
a bent passage configured to decelerate a flow of the combustion gas which goes around the protrusion and advances for the gas seal.

10. A flying object comprising:
steering wings connected to a main body of the flying object; and
a thrust vectoring apparatus,
wherein said thrust vectoring apparatus comprises:
a nozzle having a nozzle output opening which emits a combustion gas in a rear direction;

a jet tab arranged on a rear side of the nozzle;
a rotation shaft connected to the jet tab to be rotatable around a rotation axis;
a driving mechanism configured to rotate the rotation shaft around the rotation axis; and
a gas seal member arranged on an outer circumferential surface of the rotation shaft to prevent the combustion gas from invading the driving mechanism,
wherein the jet tab is configured to rotate in a plane which intersects with a longitudinal center axis of the nozzle, by rotating the rotation shaft around the rotation axis, and to move from a standby position where the jet tab does not overlap with the nozzle output opening, to an operation position where the jet tab overlaps with the nozzle output opening,
wherein a first gap is formed between the jet tab and a surface of a rear end surface of the nozzle, and
wherein the rotation shaft has a protrusion arranged on a rear side of the gas seal member, and the protrusion protrudes in a radial direction from the rotation shaft.

11. A thrust vectoring apparatus comprising:
a nozzle having a nozzle output opening configured to emit a combustion gas in a rear direction;
a jet tab arranged on a rear side of the nozzle;
a rotation shaft connected to the jet tab to be rotatable around a rotation axis;
a rotation shaft receiving member having a through-hole in which the rotation shaft is inserted;
a driving mechanism configured to rotate the rotation shaft around the rotation axis; and
a gas seal member arranged between an outer circumferential surface of the rotation shaft and an inner surface of the through-hole,
wherein the rotation shaft has an annular protrusion protruding in a radial direction out of the rotation shaft between the gas seal member and the jet tab,
wherein an outer diameter of the annular protrusion is larger than an inner diameter of the through-hole,
wherein a first gap is formed between the jet tab and the rear end surface of the nozzle, and
wherein the shortest distance between an outer circumferential edge of the rear end surface of the nozzle and the jet tab is smaller than the shortest distance between the rear end surface of the annular protrusion and the jet tab.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• FUJISAWA Fuminori
• Tani Hiroyuki
• HYUGA Daisuke

Classifications

• B64C15/02 Primary

  the jets being propulsion jets · CPC title

• F42B10/665

  characterised by using a nozzle provided with at least a deflector mounted within the nozzle · CPC title