# US 11,299,252 B2 · Rectification structure body and flying vehicle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,299,252 B2 - Document ID: US11299252B2 - Status: Granted - Kind: B2 - Application number: 16/639,188 - Filed: 2018-09-12 - Published: 2020-07-30 - Granted: 2022-04-12 - Earliest claimed: 2018-02-23 - Assignees: Mitsubishi Heavy Industries, Ltd. - Applicants: Mitsubishi Heavy Industries, Ltd. - Inventors: Rikako Yoshida; Kosuke Nishikawa - Web page: https://patentgrep.com/patent/US11299252B2 ## CPC - B64C 1/38: Constructions adapted to reduce effects of aerodynamic or other external heating - F02K 1/822: {Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors} - B64C 3/36: Structures adapted to reduce effects of aerodynamic or other external heating - B64D 27/16: of jet type - B64D 27/20: within, or attached to, fuselages - B64U 50/15: using combustion exhausts other than turbojets or turbofans, e.g. using rockets, ramjets, scramjets or pulse-reactors - F02K 7/10: characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines - F05D 2250/283: honeycomb - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64C: AEROPLANES; HELICOPTERS - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 2) The rectification structure body of a flying vehicle according to claim 2, wherein the strengthening section is a lattice structure body. ### Claim 4 (depends on 1) The rectification structure body of a flying vehicle according to claim 1, wherein the heat input control section is a hollow rigid body. ### Claim 5 (depends on 4) 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. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) 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. ### Claim 8 (depends on 1) A flying vehicle comprising the rectification structure body according to claim 1. ### Claim 9 (depends on 8) The flying vehicle according to claim 8, further comprising a ramjet engine, wherein the ramjet engine comprises an inlet having the rectification structure body. ### Claim 10 (depends on 8) The flying vehicle according to claim 8, further comprising a wing having the rectification structure body. ### Claim 11 (depends on 1) 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.