| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 带有可抛放的隐形外壳的执行器 | CN201510153691.3 | 2015-04-02 | CN104973249A | 2015-10-14 | K.W.迪特里希; J.佩雷斯-桑切斯 |
| 本发明涉及一种用于飞机(100)的执行器(10)。该执行器(10)具有执行器本体(12)和至少部分地包围执行器本体(12)的隐形外壳(14)。隐形外壳(14)固定在执行器本体(12)处并且实施为在支承执行器(10)的飞机(100)的飞行期间与飞机(100)分离并且与执行器本体(12)分离。 | ||||||
| 2 | 推力反向器的同步系统 | CN201380064759.X | 2013-12-10 | CN104854336A | 2015-08-19 | 文森特·佩隆 |
| 本发明公开了一种用于涡轮喷气发动机机舱的推力反向器装置(1)，其包括至少两个罩(11，12)，每个罩相对于固定结构平移移动安装在上游闭合位置和下游开启位置之间，所述上游闭合位置保证所述机舱的空气动力学的连续性，所述下游开启位置打开机舱内的通道，所述推力反向装置包括至少一个同步线缆(2)，所述同步线缆(2)在两个活动罩之间延伸，从而具有第一端部(111)，以及第二端部(121)，所述第一端部(111)固定在第一罩的上游点，所述第二端部(121)固定在第二罩的下游点，上游和下游固定点相对于固定中间区域(3)确定，其中线缆从两个罩之间穿过固定中间区域(3)。 | ||||||
| 3 | JPS493679B1 - | JP7823869 | 1969-10-02 | JPS493679B1 | 1974-01-28 | |
| 4 | Getarntes Fluggerät | EP12004166.0 | 2012-05-31 | EP2532588B1 | 2016-06-29 | Dornwald, Jochen; Bichler, Bartholomäus |
| 5 | Exterior aircraft light unit and aircraft comprising the same | EP14180964.0 | 2014-08-14 | EP2985229B1 | 2017-11-15 | Jha, Anil Kumar; Hessling Von Heimendahl, Andre; Beermann, Franz-Josef; Schoen, Christian; Lueder, Sascha |
| An exterior aircraft light unit (2) includes a mounting structure (4), an LED (18) arranged on the mounting structure (4), and an optical system (6), arranged on the mounting structure (4) for creating an output light emission distribution of the exterior aircraft light unit (2). The optical system (6) has, in a first cross-sectional plane extending through the LED (18), a first concave reflector (8) and a second concave reflector (10), each of the first and second concave reflectors (8, 10) having a proximate end positioned adjacent to the mounting structure (4) and a distal end positioned removed from the mounting structure (4), with the first and second concave reflectors (8, 10) being arranged on opposite sides of the LED (18) in the first cross-sectional plane, and a refractive optical element (16) arranged between the first and second concave reflectors (8, 10) in the first cross-sectional plane. The distal ends of both the first and second concave reflectors (8, 10) have back-tapered shapes, with the first and second concave reflectors (8, 10) curving towards each other at their distal ends. | ||||||
| 6 | Exterior aircraft light unit and aircraft comprising the same | EP14180964.0 | 2014-08-14 | EP2985229A1 | 2016-02-17 | Jha, Anil Kumar; Hessling Von Heimendahl, Andre; Beermann, Franz-Josef; Schoen, Christian; Lueder, Sascha |
An exterior aircraft light unit (2) includes a mounting structure (4), an LED (18) arranged on the mounting structure (4), and an optical system (6), arranged on the mounting structure (4) for creating an output light emission distribution of the exterior aircraft light unit (2). The optical system (6) has, in a first cross-sectional plane extending through the LED (18), a first concave reflector (8) and a second concave reflector (10), each of the first and second concave reflectors (8, 10) having a proximate end positioned adjacent to the mounting structure (4) and a distal end positioned removed from the mounting structure (4), with the first and second concave reflectors (8, 10) being arranged on opposite sides of the LED (18) in the first cross-sectional plane, and a refractive optical element (16) arranged between the first and second concave reflectors (8, 10) in the first cross-sectional plane. The distal ends of both the first and second concave reflectors (8, 10) have back-tapered shapes, with the first and second concave reflectors (8, 10) curving towards each other at their distal ends.
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| 7 | SYSTÈME DE SYNCHRONISATION POUR DISPOSITIF D'INVERSION DE POUSSÉE | EP13818281.1 | 2013-12-10 | EP2932078A1 | 2015-10-21 | PEYRON, Vincent |
| Thrust reverser device (1) for a turbojet engine nacelle comprising at least two cowls (11, 12) each one mounted with the ability to move translationally with respect to a fixed structure between an upstream closed position in which it provides the aerodynamic continuity of the nacelle, and a downstream open position in which it opens a passage in the nacelle, the device comprising at least one synchronization cable (2) stretched between the two mobile cowls so as to have a first end (111) attached to an upstream point of a first cowl, a second end (121) attached to a downstream point of the second cowl, and the upstream and downstream attachment points being determined relative to a fixed central zone (3) where the cable passes between the two cowls. | ||||||
| 8 | Getarntes Fluggerät | EP12004166.0 | 2012-05-31 | EP2532588A1 | 2012-12-12 | Dornwald, Jochen; Bichler, Bartholomäus |
Ein Fluggerät 10 mit geringer Radarsignatur weist eine erste Seite 12 auf, auf der Turbinenöffnung 14, 16 und Nutzlast- oder Fahrwerkschächte 20, 24, 26 angeordnet sind. Eine zweite Seite 30 des Fluggeräts ist derart ausgeführt, dass sie eine geringere Radarsignatur als die erste Seite 12 aufweist.
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| 9 | 항공기 구조 부품 및 동적 구성품의 내 탄환 손상 설계 방법 | KR1020120041738 | 2012-04-20 | KR1020130118664A | 2013-10-30 | 현영진; 원태훈 |
| PURPOSE: A ballistic damage-resistance design method for structure material and dynamic components of an aircraft is provided to perform ballistic damage-resistance design of the structure material of the aircraft through acquisition of the ballistic damage-resistance design basic data and analysis of test result. CONSTITUTION: A ballistic damage-resistance design target item is defined (S100). Material, a tool and specimen shape are designed (S200). Bullet shot test and damage database are constructed (S300). Sizing of the structure is performed (S400). It is evaluated whether ballistic damage-resistance requirement is satisfied (S500). When the requirement is satisfied, the ballistic damage-resistance design is completed (S600). [Reference numerals] (S100) Define a ballistic damage-resistance design target item; (S200) Design material, a tool, and specimen shape; (S300) Construct a bullet shot test and damage database; (S400) Perform the sizing of the structure (analyze the damage of a ballistic damage-resistance bullet); (S500) Satisfy the requirement?; (S600) Complete the ballistic damage-resistance design | ||||||
| 10 | 항공기의 건 보어사이팅 조정장치 | KR1020010013698 | 2001-03-16 | KR1020020073830A | 2002-09-28 | 박서신; 김병구 |
| PURPOSE: A gun bore sighting adjusting apparatus of an aircraft is provided to install many fuel tanks in a bay of a bulkhead, and to prevent mixture of remaining or fuel gas and pressure oil in firing by mounting a manual gun bore sighting adjuster in the limit space close to the fuel tanks. CONSTITUTION: A gun bore sighting adjusting device of an aircraft is composed of an outer eccentric cam inserted in the inner periphery of a through hole in the front of a bulkhead(10); an inner eccentric cam inserted to the outer eccentric cam with fitting the end of a gun system; an index plate(60) assembled with the front of the outer eccentric cam, and rotated in adjusting the gun bore sighting with forming an index groove; and a fixing member(70) fastened in the bulkhead, and inserted to the index groove to fix the index plate. Many fuel tanks are mounted in the bay by installing the manual gun bore sighting adjuster in the limit space of the bulkhead. | ||||||
| 11 | 기관총의 보관덮개 | KR1020140003956 | 2014-01-10 | KR1020150083757A | 2015-07-20 | 문성현 |
| 본발명의일 실시예에따른보관덮개가개시된다. 본발명의일 실시예에따른본 발명은, 여러개의총신이돌아가면서발사되는기관총(미니건)의뒤에기관총을좌우, 상하로움직일수 있게해주는운동형반구를붙여놓고, 그기관총의총신오른쪽과왼쪽, 앞쪽과아래에적의총탄이나다른기타무기들로부터기관총을보호할 수있는보관덮개를제공한다. 포함한다. | ||||||
| 12 | 스텔스 항공기 | KR1020120047856 | 2012-05-07 | KR1020120136283A | 2012-12-18 | 돈왈트,요헨; 비츨러,바르솔로메우스 |
| PURPOSE: A stealth aircraft is provided to optimize a stealth property by always facing a clean second face to radar threat. CONSTITUTION: A stealth aircraft(10) comprises a turbine and bays(20,24). The turbine propels an aircraft having at least one turbine holes(14,16). Other components of the aircraft are received inside the aircraft through the bays. The aircraft is designed to have a small radar signature. The turbine holes and the bays are arranged on a first face(12) of the aircraft. A second face(30) of the aircraft has the small radar signature smaller than the first face. | ||||||
| 13 | 항공기의 계통 배치구조 | KR1020010010120 | 2001-02-27 | KR1020020069744A | 2002-09-05 | 신상준 |
| PURPOSE: Arrangement structure of a system for an aircraft is provided to improve stability of the aircraft, and to arrange systems optimally by separating a fuel system, a hydraulic system and a gun system fundamentally. CONSTITUTION: A bulkhead(100) is installed horizontally in a fuselage of an aircraft, and plural webs(200) are mounted vertically in the bulkhead to separate systems. Plural bays(300) are formed between the bulkhead and the web, and a gun system(400) is installed in the front bay through the web. A fuel system and a hydraulic system are installed in the rear bays, and isolated from the gun system completely. Plural discharge passages(500) are formed in the bulkhead placed in the rear part of a gun(430) to discharge remaining gas in firing the gun. Stability of the aircraft is improved with preventing mixture of gun gas, fuel gas and oil by isolating and arranging systems optimally. | ||||||
| 14 | JUNGLE FIGHTER AIRCRAFT CONVERSION KIT | PCT/US2006017973 | 2006-05-09 | WO2007114831A2 | 2007-10-11 | HARDING DAVID K |
| A jungle fighter aircraft conversion kit comprised of a gattling gun works (1) that is mounted at the nose cone (3) under portion of an aircraft (2), avionics grayboxes (8), vibration trays (5), a hood (9) for enclosure and a machine gun (10). The gattling gun works (1) is designed for repeat fire power in intermittent operations while the air vents (4) in the gattling machine gun works (1) are designed for cooling the weapon. The grayboxes (8) are located within the gattling works weapon (1) and are designed for control within the cockpit (7) of the aircraft. Both the weapon and the grayboxes (8) have vibration trays (5) mounted at each equipment base. The machine gun (10) is preferably compact and lightweight and similar in design to those used by United States secret service agents. | ||||||
| 15 | Effector with ejectable stealth shell | US14676047 | 2015-04-01 | US09950781B2 | 2018-04-24 | Kay W. Dittrich; Juan Perez-Sanchez |
| An effector for an aircraft has an effector body and a stealth sheath enclosing the effector body at least in part. The stealth shell is attached to the effector body and embodied so as to be separated from the aircraft and from the effector body during flight of the aircraft carrying the effector. | ||||||
| 16 | Exterior aircraft light unit and aircraft comprising the same | US14825898 | 2015-08-13 | US09789975B2 | 2017-10-17 | Anil Kumar Jha; Andre Hessling Von Heimendahl; Franz-Josef Beermann; Christian Schoen; Sascha Lueder |
| An exterior aircraft light unit includes a mounting structure, an LED arranged on the mounting structure, and an optical system, arranged on the mounting structure for creating an output light emission distribution of the exterior aircraft light unit. The optical system has, in a first cross-sectional plane extending through the LED, a first concave reflector and a second concave reflector, each of the first and second concave reflectors having a proximate end positioned adjacent to the mounting structure and a distal end positioned removed from the mounting structure, with the first and second concave reflectors being arranged on opposite sides of the LED in the first cross-sectional plane, and a refractive optical element arranged between the first and second concave reflectors in the first cross-sectional plane. The distal ends of both the first and second concave reflectors that curve towards each other and have back-tapered shapes. | ||||||
| 17 | FANG MOUNT | US15008208 | 2016-01-27 | US20170211903A1 | 2017-07-27 | Jesse DAVISON; David DIERKS; Jarrett O'HARA; Russell MENSCH; Chris FELLEGY; Chris KNIFFIN |
| An IDAS compatible weapons mounting platform for a helicopter, such as the UH-1, that allows two weapon stores, including Hellfire, to mount to each side of the aircraft. The platform is compatible with a broad array of weapons, such as the Hellfire and other smart weapons, and increases the total weapon payload to 1,000 lbs per aircraft side, while having positive safety margins throughout the flight profile. | ||||||
| 18 | Stealth Aerial Vehicle | US15182074 | 2016-06-14 | US20160368603A1 | 2016-12-22 | Jochen DORNWALD; Bartholomaeus BICHLER |
| An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side. | ||||||
| 19 | SYNCHRONIZATION SYSTEM FOR A THRUST REVERSER | US14716908 | 2015-05-20 | US20150260125A1 | 2015-09-17 | Vincent PEYRON |
| The present disclosure provides a thrust reverser device for a turbojet engine nacelle which includes at least two cowls each mounted with the ability to move translationally with respect to a fixed structure between an upstream closed position and a downstream open position. In the upstream position, the two cowls provide aerodynamic continuity of the nacelle, and in the downstream open position, they open a passage in the nacelle. The thrust reverser device further includes at least one synchronization cable extended between the two mobile cowls so as to have a first end attached to an upstream point of one of the two cowls, and a second end attached to a downstream point of the another cowl. In particular, the upstream and downstream attachment points are determined relative to a fixed central zone where the cable passes between the two cowls. | ||||||
| 20 | Jungle fighter aircraft conversion kit | US11265924 | 2005-11-03 | US20060249013A1 | 2006-11-09 | David Harding |
| A jungle fighter aircraft conversion kit comprised of a gattling gun works (1) that is mounted at the nose cone (3) under portion of an aircraft (2), avionics grayboxes (8), vibration trays (5), a hood (9) for enclosure and a machine gun (10). The gattling gun works (1) is designed for repeat fire power in intermittent operations while the air vents (4) in the gattling machine gun works (1) are designed for cooling the weapon. The grayboxes (8) are located within the gattling works weapon (1) and are designed for control within the cockpit (7) of the aircraft. Both the weapon and the grayboxes (8) have vibration trays (5) mounted at each equipment base. The machine gun (10) is preferably compact and lightweight and similar in design to those used by United States secret service agents. | ||||||
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