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41. 发明专利

JP2007516400A Rotation missile to launch a light pulse 有权
公开(公告)号：JP2007516400A
公开(公告)日：2007-06-21
申请号：JP2006516340
申请日：2004-07-01
申请人：エムべーデーアーフランスMBDA France
发明人：ベルナールテネゼ , フランベルヌー , ファビエンヌレオン
IPC分类号： F42B10/26 , F41G7/30 , F42B15/01 , G01S1/70
CPC分类号： F41G7/305 , H04B10/1121
摘要：本発明は光パルスを照射する回転ミサイルに関し、ミサイル(２)のその長手方向の軸(Ｌ−Ｌ)を中心とする回転運動(３)が停止した際、上記光パルスを遮断するように為されていることを特徴とする。
【選択図】図１

42. 发明专利

JPH10184455A MISSILE 失效
公开(公告)号：JPH10184455A
公开(公告)日：1998-07-14
申请号：JP34198096
申请日：1996-12-20
申请人： NISSAN MOTOR
发明人： SHIRAISHI TAKASHI
IPC分类号： F42B10/26 , B64C15/02 , F02K9/30 , F02K9/80
摘要： PROBLEM TO BE SOLVED: To reduce the heat load against a thrust deflecting plate as well as to improve in propulsive efficiency by installing plural pieces of rocket nozzles in the tail part of a motor case, and rotatably installing the thrust deflecting plate deflecting a jet of combustion gas jetted out of these rocket nozzles in the vicinity of each rocket nozzle. SOLUTION: When a solid propellant is ignited, a missile 1 flies up by jetting the combustion gas from each nozzle 3 installed in the tail part of a motor case 2. In this missile 1, since a thrust deflection plate 4 is rotatably installed in the vicinity of the outside of each rocket nozzle 3, when attitude control is not carried out, the thrust deflecting plate 4 is not exposed directly to the combustion gas, especially a tip part (an end at the center side of rotation) of this thrust deflecting plate 4 will not be exposed to the combustion gas irrespective of the presence of attitude control action. Moreover, in this missile 1, when the attitude control is not conducted, the thrust deflecting plate 4 will in no case hinder a flow of the combustion gas, and thus there is no thrust loss due to the thrust deflecting plate 4.

43. 发明专利

JPH07127999A ACTUATOR FOR SPIN MISSILE 失效
公开(公告)号：JPH07127999A
公开(公告)日：1995-05-19
申请号：JP27696593
申请日：1993-11-05
申请人： MITSUBISHI ELECTRIC CORP
发明人： NAKANO EIICHI
IPC分类号： F42B10/26 , F15B11/15 , F42B10/64 , F42B15/00
摘要： PURPOSE:To provide a small, low-cost actuator to be used in a spin missile in which its operating range is high. CONSTITUTION:This actuator is comprised of a cylinder, a piston 2, a shaft 3 integrally assembled with the piston 2, an operating wing 8 of which angle is changed by the shaft 3, valves 4a, 4b for adjusting a pressure within the cylinder, a pressurizing source 9 for supplying pressure to the valves 4a, 4b, and a solenoid 5 for driving the valves 4a, 4b. The solenoid 5 and the valves 4a, 4b are driven at a predetermined position of a spin position of a missile, a pressurizing side and a pressure reducing side of a cylinder which is divided into two segments by the piston 2 are reversed from each other and then the operating vane 8 performs a repeating operation. With such an arrangement as above, a complex control can be eliminated, a range of the actuator is increased, a simplified structure reduces the size and cost of the actuator.

44. 发明专利

JPH05157498A RUDDER WING 失效
公开(公告)号：JPH05157498A
公开(公告)日：1993-06-22
申请号：JP32454691
申请日：1991-12-09
申请人： MITSUBISHI HEAVY IND LTD
发明人： ARAKAWA HARUHIKO
IPC分类号： B64C9/02 , F42B10/26 , F42B15/00
摘要： PURPOSE:To obtain a rudder wing which is free from tip stall and has no decrease in dynamic lift caused by a gap at a wing root part by shaping the rudder wing mounted on a body with a circular cross section to have a planar form with an advancing angle and to mount with a forward tilted hinge line for driving. CONSTITUTION:A rudder wing to be mounted on a body with a circular cross section such as flying object, which has a rudder wing 1 with an advancing angle and a forward tilted hinge line 2 causes no tip stall at a wing tip 4 up to a large rudder angle while a gap 6 is reduced between a rear part of the hinge line 2 at a wing root part 5 and the body 3. Thus, a dynamic lift and a rolling moment can be retained thereby allowing a higher tip opening and a stable rolling control. With the control of the tip stall, increase in resistance can be lowered thereby achieving an increase in the cruising range.

45. 发明专利

JPH04273999A MISSILE 失效
公开(公告)号：JPH04273999A
公开(公告)日：1992-09-30
申请号：JP3286291
申请日：1991-02-27
申请人： MITSUBISHI HEAVY IND LTD
发明人： HORIUCHI KAZUO
IPC分类号： B64C1/26 , F42B10/26 , F42B10/64
摘要： PURPOSE:To provide a missile in which a main wing is projected only at an upper part and a lower part of a barrel, a rolling means is provided so as to enable changing in any direction in longitudinal or lateral directions to be rapidly attained with low flying resistance. CONSTITUTION:The present invention provides a missile characterized in that the same is comprised of a main wing 2 projected in a radial direction as viewed from a barrel axis only at an upper part and a lower part of a barrel 1 of the missile and a rolling means for rolling the missile in response to a requirement during its flying operation.

46. 发明专利

JPH04270899A CRUISING MISSILE 失效
公开(公告)号：JPH04270899A
公开(公告)日：1992-09-28
申请号：JP3087091
申请日：1991-02-26
申请人： MITSUBISHI HEAVY IND LTD
发明人： KANEKO RYUICHI
IPC分类号： B64C13/18 , F42B10/26 , F42B15/01
摘要： PURPOSE:To permit the maintenance of the up-and-down of a picture caught by an imager in constant by a method wherein a cruising missile is provided with a guiding device, mounted on a fuselage through a roll bearing, and a control means, controlling the flight of the fuselage so as to be capable of bank-to-turn during flying. CONSTITUTION:A cruising missile is constituted of a fuselage section 2 and a guiding section 1, equipped with an imager (visible light or infrared ray camera) and a radio altimeter 5 and connected to the fuselage section 2 through a roll bearing 3. During the flight of the missile, an attitude angle in roll with respect to space is controlled by a roll driving device 6, mounted on the fuselage section 2, so as to keep it in constant. In this case, the roll rate and the roll attitude angle of the fuselage section 2 are detected by an inertia device 7 mounted on the fuselage section 2 and the roll driving device 6 is controlled based on the detections. On the other hand, the fuselage section 2 is controlled in the turning flight of the same so that an inertia force is exerted on the fuselage 2 toward the downward of the axis of the same at all times similarly as the case of a conventional aeroplane (this control is called as 'bank-to-turn').

47. 发明专利

JPS5721798A Flying object 失效
公开(公告)号：JPS5721798A
公开(公告)日：1982-02-04
申请号：JP9471780
申请日：1980-07-11
申请人： Tokyo Shibaura Electric Co
发明人： KOTAKE HISAYUKI
IPC分类号： F42B15/01 , F42B10/26 , F42B15/00

48. 发明专利

JPS5418220B2 失效
公开(公告)号：JPS5418220B2
公开(公告)日：1979-07-05
申请号：JP4422573
申请日：1973-04-20
IPC分类号： B22D19/06 , B22D23/10 , B23D61/12 , B23D65/00 , B23K20/00 , B23P15/38 , B32B15/02 , F42B10/26

49. 发明专利

JP2021156501A 飛翔体审中-公开
公开(公告)号：JP2021156501A
公开(公告)日：2021-10-07
申请号：JP2020057449
申请日：2020-03-27
申请人：株式会社日本製鋼所
发明人：阿曽良之 , 松山孝男 , 三浦啓晶 , 藤岡一美 , 松尾亜紀子 , 笠原弘貴
IPC分类号： F42B10/26 , F42B10/22
摘要：【課題】翼を設けることなく安定に飛翔することができる飛翔体を提供する。【解決手段】飛翔体100は、胴体1と、複数の溝2と、を有する。胴体1は、円錐形状を有する部材として構成される。複数の溝2は、錐体形状の先端1Aと、底面1Bと、の間の胴体1の側面の所定の位置である溝の先端部2Aから、錐体形状の底面1Bへ向けて延在するように形成されている。【選択図】図1

50. 发明专利

KR102237987B1 KR102237987B1 - Multi axis diriving device and projectile comprising the same 有权
公开(公告)号：KR102237987B1
公开(公告)日：2021-04-08
申请号：KR1020200020188A
申请日：2020-02-19
申请人： 국방과학연구소
发明人： 김광태 , 김홍철 , 김용철 , 최성호 , 이용선 , 이충희
IPC分类号： F42B10/04 , F42B10/26 , F42B10/64 , F42B10/66 , F42B15/01 , G01B7/30
CPC分类号： F42B10/04 , F42B10/26 , F42B10/64 , F42B10/66 , F42B15/01 , G01B7/30
摘要： 일 실시 예에 따른 다축 구동 장치는, 모듈 하우징; 상기 모듈 하우징에 대하여 회전 가능하게 연결되는 제 1 회전 구동축; 상기 제 1 회전 구동축에 연결되는 제 1 날개; 상기 모듈 하우징에 고정되는 제 1 고정자와, 상기 제 1 회전 구동축과 일체로 회전 가능한 제 1 회전자를 포함하는 제 1 구동 파트; 상기 제 1 날개의 회전 각도를 감지하기 위한 제 1 회전각 센서; 상기 모듈 하우징에 대하여 회전 가능하게 연결되는 제 2 회전 구동축; 상기 제 2 회전 구동축에 연결되는 제 2 날개; 상기 모듈 하우징에 고정되는 제 2 고정자와, 상기 제 2 회전 구동축과 일체로 회전 가능한 제 2 회전자를 포함하는 제 2 구동 파트; 및 상기 제 2 날개의 회전 각도를 감지하기 위한 제 2 회전각 센서를 포함하고, 상기 제 1 회전 구동축의 연장선과 상기 제 2 회전 구동축의 연장선은 서로 직교할 수 있다.

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