Rectification structure body and flying vehicle

Patent metadata

Field	Value
Publication number	US-11299252-B2
Application number	US-201816639188-A
Country	US
Kind code	B2
Filing date	Sep 12, 2018
Priority date	Feb 23, 2018
Publication date	Apr 12, 2022
Grant date	Apr 12, 2022

Abstract

A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.

First claim

The invention claimed is:

1. A rectification structure body of a flying vehicle, the rectification structure body comprising:
a rectification section having a rectification surface configured to rectify airflow from a travelling direction and a back surface opposite to the rectification surface;
a heat input control section connected to the back surface; and
a vacuum thermal insulation section connected to the heat input control section,
wherein the heat input control section is sandwiched between the back surface and the vacuum thermal insulation section,
wherein the vacuum thermal insulation section comprises:
a first plate forming a first surface of the vacuum thermal insulation section where the heat input control is arranged;
a second plate provided so as to face the first plate on an opposite side of the vacuum thermal insulation section; and
a further plate forming a side surface of the vacuum thermal insulation section connected to an end of the first surface,

wherein the first plate, the second plate, and the further plate form a rigid body,
wherein the heat input control section is arranged so as to be separated by a predetermined distance from the side surface such that heat added to the rectification section moves to the heat input control section and further to the second plate via the first plate, ends of first plate, and the further plate, and
wherein the heat input control section is arranged at a center of the first surface.

2. The rectification structure body of a flying vehicle according to claim 1 ,
wherein the rectification section comprises:
a rectification plate having the rectification surface; and
a strengthening section connected to the rectification plate and having the back surface,

the strengthening section is a hollow rigid body.

3. The rectification structure body of a flying vehicle according to claim 2 , wherein the strengthening section is a lattice structure body.

4. The rectification structure body of a flying vehicle according to claim 1 , wherein the heat input control section is a hollow rigid body.

5. The rectification structure body of a flying vehicle according to claim 4 , wherein the heat input control section is a honeycomb structure body or a lattice structure body.

6. The rectification structure body of a flying vehicle according to claim 1 , wherein a plurality of the heat input control sections is connected to the vacuum thermal insulation section.

7. The rectification structure body of a flying vehicle according to claim 1 , further comprising a thermal insulation material between the vacuum thermal insulation section and the rectification section.

8. A flying vehicle comprising the rectification structure body according to claim 1 .

9. The flying vehicle according to claim 8 , further comprising a ramjet engine, wherein the ramjet engine comprises an inlet having the rectification structure body.

10. The flying vehicle according to claim 8 , further comprising a wing having the rectification structure body.

11. The rectification structure body of a flying vehicle according to claim 1 , wherein the heat moves from the heat input control section to the second plate via the first plate, the ends of the first plate, and the further plate faster than through any other path.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• YOSHIDA Rikako
• Nishikawa kosuke

Classifications

• B64U50/15

  using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors · CPC title

• F02K1/822 Primary

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• B64C1/38 Primary

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64D27/20

  within, or attached to, fuselages · CPC title

• B64D27/16

  of jet type · CPC title