公开(公告)号：US1266490A

公开(公告)日：1918-05-14

申请号：US19079917

申请日：1917-09-11

申请人： LEO P KELLER ,  KREMER ALFRED

发明人： KREMER ALFRED

CPC分类号： B64D27/023

公开(公告)号：US1024287A

公开(公告)日：1912-04-23

申请号：US1910594028

申请日：1910-11-25

申请人： SASSIL EUGENE H

发明人： SASSIL EUGENE H

CPC分类号： B64D27/023

公开(公告)号：US20240051671A1

公开(公告)日：2024-02-15

申请号：US17885597

申请日：2022-08-11

申请人： Venus Aerospace Corp.

发明人： Andrew Thomas DUGGLEBY ,  Nicholas D. CARDWELL ,  Christian BAILEY

IPC分类号： B64D27/02 ,  B64D41/00 ,  B64D37/00 ,  F02C6/00 ,  F02C7/36 ,  F02K9/42 ,  H02K7/108 ,  H02K7/116 ,  H02K7/18 ,  H02K11/00

CPC分类号： B64D27/023 ,  B64D41/00 ,  B64D37/00 ,  F02C6/00 ,  F02C7/36 ,  F02K9/425 ,  H02K7/108 ,  H02K7/116 ,  H02K7/1823 ,  H02K11/0094 ,  F05D2220/70

摘要： An integral propulsion and auxiliary power generation system includes a rocket engine, a liquid propellant supply system, an auxiliary electrical system, and a transmission system. The liquid propellant supply system is configured to supply a liquid fuel and a liquid oxidizer to the rocket engine. The liquid propellant supply system includes a gas generator configured to burn a mixture of the liquid fuel and the liquid oxidizer to generate a combustion gas stream, and a gas turbine configured to convert the kinetic energy of the combustion gas stream into mechanical energy. The auxiliary electrical system includes a power generator configured to convert mechanical energy into electrical energy and an electric load device electrically coupled to the power generator. The transmission system is configured to mechanically couple the gas turbine and the power generator to selectively transfer mechanical energy between the gas turbine and the power generator.

公开(公告)号：US20240010348A1

公开(公告)日：2024-01-11

申请号：US18371207

申请日：2023-09-21

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Ivan SIDOROVICH PARADISO ,  Daniel ALECU

IPC分类号： B64D27/24 ,  B64D27/02

CPC分类号： B64D27/24 ,  B64D27/023 ,  B64D2027/026 ,  B64D2041/002

摘要： Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

公开(公告)号：US11794914B2

公开(公告)日：2023-10-24

申请号：US17379285

申请日：2021-07-19

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Ivan Sidorovich Paradiso ,  Daniel Alecu

IPC分类号： B64D27/24 ,  B64D27/02 ,  B64D41/00 ,  F01D13/02 ,  F01D15/10 ,  F02C3/30

CPC分类号： B64D27/24 ,  B64D27/023 ,  B60L2200/10 ,  B64D2027/026 ,  B64D2041/002 ,  B64D2221/00 ,  F01D13/02 ,  F01D15/10 ,  F02C3/30 ,  F05D2220/50 ,  F05D2220/76 ,  F05D2270/09 ,  H02J2310/44

摘要： Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

公开(公告)号：US11713114B2

公开(公告)日：2023-08-01

申请号：US17196643

申请日：2021-03-09

申请人： Textron Innovations Inc.

发明人： Troy Cyril Schank

IPC分类号： B64C29/00 ,  B64D27/02 ,  B64D27/12

CPC分类号： B64C29/0025 ,  B64D27/023 ,  B64D27/12 ,  B64C2211/00 ,  B64D2027/026

摘要： A vertical-takeoff-and-landing (“VTOL”) aircraft including a non-VTOL aircraft equipped for forward takeoff and flight and a modular boom system interoperably coupled to the non-VTOL aircraft. The modular boom system includes a first modular boom and a second modular boom. The first modular boom includes a first rocket-turbine engine. The first modular boom is mounted to a first wing of the non-VTOL aircraft. The second modular boom includes a second rocket-turbine engine. The second modular boom is mounted to a second wing of the non-VTOL aircraft.

公开(公告)号：US20180319486A1

公开(公告)日：2018-11-08

申请号：US15768052

申请日：2016-10-14

申请人： NEWROCKET LTD.

发明人： Moti ELYASHIV ,  Reuben RAZ ,  Zohar SCHLAGMAN

IPC分类号： B64C27/00 ,  B64D27/02 ,  F02K9/95 ,  F02K9/24 ,  F02K9/46 ,  F02K9/70 ,  F02K9/72

CPC分类号： B64C27/006 ,  B64D27/023 ,  F02K9/24 ,  F02K9/46 ,  F02K9/70 ,  F02K9/72 ,  F02K9/95 ,  F05D2270/09

摘要： There is provided, in accordance some embodiment, a method for enhancing autorotation performance of a rotary-wing aircraft in emergency events. The method comprises an action of receiving a request for emergency thrust from a user interface. The method comprises an action of sending a start command to an emergency engine coupled to a rotary-wing aircraft following the request. The method comprises an action of thrusting the rotary-wing aircraft coupled to the emergency engine in a direction substantially of a longitudinal axis of the rotary-wing aircraft, thereby enhancing autorotation performance of the rotary-wing air-craft in an emergency event.

公开(公告)号：US20160208743A1

公开(公告)日：2016-07-21

申请号：US14908349

申请日：2013-10-18

申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

发明人： Shozo HIDAKA ,  Atsushi MORIWAKI ,  Kensuke FUTAHASHI ,  Shuhei HOSAKA ,  Masaaki NAGASE ,  Kohei KOJIMA ,  Mitsuru INADA

IPC分类号： F02K9/86 ,  B64D31/00 ,  B64D27/02

CPC分类号： F02K9/86 ,  B64D27/023 ,  B64D31/00 ,  F02K9/80 ,  F02K9/94 ,  F05D2250/75

摘要： A thrust control valve equipped with: a valve element, in which a gas injection passage, through which an operating gas is injected, is formed, with a valve-seating surface being formed in the gas injection passage; and a valve stem, which is provided in the interior of the gas injection passage and has a seated surface that makes contact with the valve-seating surface. A guide surface which makes contact with the inner circumferential surface of the gas injection passage of the valve element is formed on the outer circumferential surface of the valve stem. The guide surface is formed downstream from the seated surface in the direction of flow of the operating gas. A V-groove through which the operating gas flows is formed at the tip of the valve stem, downstream from the seated surface in which the guide surface is formed.

摘要翻译： 一种推力控制阀，配备有：阀元件，其中形成有注入工作气体的气体注入通道，在气体注入通道中形成有阀座表面; 以及阀杆，其设置在气体注入通道的内部并具有与阀座表面接触的就座表面。 在阀杆的外周面上形成有与阀体的气体注入通道的内周面接触的引导面。 引导表面沿着工作气体的流动方向从就座表面的下游形成。 操作气体流过的V形槽形成在阀杆的尖端处，在形成有引导表面的就座表面的下游。

公开(公告)号：US20160144968A1

公开(公告)日：2016-05-26

申请号：US14933235

申请日：2015-11-05

申请人： Naomi Kikuchi

发明人： Naomi Kikuchi

IPC分类号： B64D27/18 ,  B64C3/10 ,  B64D27/02

CPC分类号： B64C3/10 ,  B64D27/023 ,  B64D27/12

摘要： Provided is a fuel-efficient method of flying an aircraft for flying an aircraft. The present invention relates to a method of flying an aircraft 1 having a fuselage 2, primary wings 3, and high-power engines 6 serving as driving units for generating a thrust. The method of flying an aircraft comprising: determining a combination of said primary wings 3 and high-power engines 6 so that a total wing area of said primary wings 2 is proportionally correlated to an power output of said high-power engines 6, generating a comparatively large lifting power using said primary wings 3 having large wing areas, elevating said aircraft 1 to a high altitude, and flying said aircraft 1 at high speeds and altitudes using said high-power engine 6.

摘要翻译： 提供了一种飞行飞机飞行器的节能方法。 本发明涉及一种飞机1的飞行器1，其具有作为用于产生推力的驱动单元的机身2，主翼3和大功率发动机6。 飞行飞行器的方法包括：确定所述主翼3和大功率发动机6的组合，使得所述主翼2的总机翼面积与所述大功率发动机6的功率输出成比例地相关，产生 使用具有大翼面积的所述主翼3的相对大的提升力，将所述飞机1升高到高空，并且使用所述大功率发动机6以高速和高度飞行飞行器1。

公开(公告)号：US09079661B2

公开(公告)日：2015-07-14

申请号：US13516878

申请日：2010-12-20

申请人： Marco Prampolini ,  Yohann Coraboeuf

发明人： Marco Prampolini ,  Yohann Coraboeuf

IPC分类号： B64C30/00 ,  B64D27/20 ,  B64C3/10 ,  B64C5/08 ,  B64C5/10 ,  B64C23/06 ,  B64G1/14 ,  B64D27/02

CPC分类号： B64C30/00 ,  B64C3/10 ,  B64C5/08 ,  B64C5/10 ,  B64C23/076 ,  B64D27/023 ,  B64D27/20 ,  B64D27/26 ,  B64D2027/026 ,  B64G1/14 ,  Y02T50/12 ,  Y02T50/164 ,  Y02T50/44 ,  Y02T90/44

摘要： The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).

摘要翻译： 本发明涉及一种超快速空中飞行器以及超快速空中飞行器的空中移动方法，其中，空中交通工具由涡轮喷气发动机（TB1，TB2），冲击器（ST1， ST2）和火箭发动机，其可以被制成流线型以减少在巡航阶段期间底座的阻力，并且其中车辆具有装配有活动翅片（a1，a2）的哥特式三角翼（A），其在两个外端处 三角翼的后缘（A）。