Thrust vectoring apparatus, thrust vectoring method, and flying body

Patent metadata

Field	Value
Publication number	US-10088284-B2
Application number	US-201514694034-A
Country	US
Kind code	B2
Filing date	Apr 23, 2015
Priority date	Oct 17, 2014
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A first jet tab and a second jet tab are symmetrically arranged with respect to a symmetry plane and have a symmetrical shape with respect to the symmetry plane, and are symmetrically driven with respect to the symmetry plane by a driving section. A distance between a tip of the first jet tab and a first rotation axis is larger than a distance between the first rotation axis and the symmetry plane. A distance between a tip section of the second jet tab and a second rotation axis is larger than a distance between the second rotation axis and the symmetry plane.

First claim

What is claimed is:

1. A thrust vectoring apparatus comprising:
a nozzle having an opening of a nozzle exit from which a combustion gas is to be exhausted;
a plurality of tab sets, each of which comprises a first tab and a second tab, which are disposed outside the opening of said nozzle exit so as not to cover any part of the opening of said nozzle exit in a standby state;
for each of the plurality of tab sets, a single drive actuator configured to drive said first tab and said second tab from the standby state to a work state such that a direction of thrust by the combustion gas is vectored by covering a part of the opening of said nozzle exit by a tip section of said first tab and a tip section of said second tab; and
for each of the plurality of tab sets, a power dividing mechanism configured to transfer a power of said single drive actuator to said first tab and said second tab,
wherein said first tab is configured rotate around a first rotation axis and said second tab is configured to rotate around a second rotation axis,
wherein said first tab and said second tab are adjacent to each other such that no other tab is between said first tab and said second tab,
wherein said first tab and said second tab are disposed in symmetry with respect to a symmetrical plane between said first tab and said second tab,
wherein, in the work state, a distance between said tip section of said first tab and the first rotation axis is larger than a distance between the first rotation axis and the symmetrical plane and a distance between said tip section of said second tab and the second rotation axis is larger than a distance between the second rotation axis and the symmetrical plane,
wherein said first tab includes a first inner surface, said second tab includes a second inner surface, and said first inner surface and said second inner surface are parallel to each other and face each other when said first tab and said second tab are fully extended,
wherein said power dividing mechanism comprises:
rotation shafts connected to said first tab and said second tab, respectively; and
gears disposed on said rotation shafts, respectively,
wherein, when said single drive actuator is driven, said gears are engaged one after another such that said first tab and said second tab are driven from the standby state to the work state, and
wherein said gears are configured to rotate said first tab and said second tab toward each other.

2. The thrust vectoring apparatus according to claim 1 , further comprising:
a microprocessor; and
a non-transitory memory having stored thereon executable instructions, which when executed by the microprocessor, cause said thrust vectoring apparatus to function as a drive control section configured to issue a control signal to said single drive actuator,
wherein said single drive actuator drives said first tab and said second tab from the standby state to the work state in response to the control signal such that said tip section of said first tab and said tip section of said second tab cover the part of the opening of said nozzle exit.

3. The thrust vectoring apparatus according to claim 2 , wherein said single drive actuator drives said first tab and said second tab in symmetry with respect to the symmetrical plane.

4. The thrust vectoring apparatus according to claim 1 , wherein each of said first tab and said second tab has a proximal section, and a thickness of each of said first tab and said second tab becomes thinner toward said tip section from said proximal section.

5. The thrust vectoring apparatus according to claim 1 , wherein said plurality of tab sets is arranged so that said plurality of tab sets do not interfere with each other even if said plurality of tab sets is driven at a same time.

6. A flying object comprising:
a nozzle having an opening of a nozzle exit from which a combustion gas is to be exhausted;
a plurality of tab sets, each of which comprises a first tab and a second tab, which are disposed outside the opening of said nozzle exit so as not to cover any part of the opening of said nozzle exit in a standby state;
for each of the plurality of tab sets, a single drive actuator configured to drive said first tab and said second tab from the standby state to a work state such that a direction of thrust by the combustion gas is vectored by covering a part of the opening of said nozzle exit opening by a tip section of said first tab and a tip section of said second tab; and
for each of the plurality of tab sets, a power dividing mechanism configured to transfer a power of said single drive actuator to said first tab and said second tab,
wherein said first tab is configured rotate around a first rotation axis and said second tab is configured to rotate around a second rotation axis,
wherein said first tab and said second tab are adjacent to each other such that no other tab is between said first tab and said second tab,
wherein said first tab and said second tab are disposed in symmetry with respect to a symmetrical plane between said first tab and said second tab,
wherein, in the work state, a distance between said tip section of said first tab and the first rotation axis is larger than a distance between the first rotation axis and the symmetrical plane and a distance between said tip section of said second tab and the second rotation axis is larger than a distance between the second rotation axis and the symmetrical plane,
wherein said first tab includes a first inner surface, said second tab includes a second inner surface, and said first inner surface and said second inner surface are parallel to each other and face each other when said first tab and said second tab are fully extended,
wherein said power dividing mechanism comprises:
rotation shafts connected to said first tab and said second tab, respectively; and
gears disposed on said rotations shafts, respectively,
wherein, when said single drive actuator is driven, said gears are engaged one after another such that said first tab and said second tab are driven from the standby state to the work state, and
wherein said gears are configured to rotate said first tab and said second tab toward each other.

7. The flying object according to claim 6 , further comprising:
a microprocessor; and
a non-transitory memory having stored thereon executable instructions, which when executed by the microprocessor, cause said flying object to function as a drive control section configured to issue a control signal to said single drive actuator,
wherein said single drive actuator drives said first tab and said second tab from the standby state to the work state in response to the control signal such that said tip section of said first tab and said tip section of said second tab cover the part of the opening of said nozzle exit.

8. The flying object according to claim 6 , wherein said single drive actuator drives said first tab and said second tab in symmetry with respect to the symmetrical plane.

9. The flying object according to claim 6 , wherein each of said first tab and said second tab has a proximal section, and a thickness of each of said first tab and said second tab becomes thinner toward said tip section from said proximal section.

10. The flying object according to claim 6 , wherein said plurality of tab sets is arranged so that said plurality of tab sets do not interfere with each other even if said plurality of tab sets is driven at a same time.

11. A thrust vectoring method comprising:
disposing a plurality of tab sets outside an opening of a nozzle exit so as not to cover any part of the opening of said nozzle exit in a standby state, wherein each of said plurality of tab sets com

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• FUJISAWA Fuminori
• Tani Hiroyuki
• HYUGA Daisuke

Classifications

• F42B10/665 Primary

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

• F02K9/90

  using deflectors (F02K9/82 takes precedence) · CPC title