子分类：
| 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 | 带有遥控滑翔翼尾舵翼的逃逸塔整流罩助推火箭 | CN201611157918.2 | 2016-12-15 | CN106500550A | 2017-03-15 | 李德福 |
| 本发明涉及到火箭技术领域，特别涉及到带有遥控滑翔翼尾舵翼的逃逸塔、整流罩、助推火箭。其特征在于在逃逸塔、整流罩、助推火箭上分别设有一对滑翔翼，在逃逸塔、整流罩、助推火箭上均设有垂尾翼，所述垂尾翼设置在一对滑翔翼的垂直对称中心平面上，一对滑翔翼的尾部设有滑翔姿态平衡翼，垂尾翼的尾部设有尾舵翼，逃逸塔、整流罩、助推火箭上均装有遥控接收器和相应的遥控机械驱动机构以及位置信号无线发射器，通过地面控制中心可以控制逃逸塔、整流罩、助推火箭在坠落滑翔的过程中按照指定的场地降落。本发明极大地降低了逃逸塔、整流罩、助推火箭残骸的回收难度和回收成本，亦可以避免掉落在村庄时带来的危险。 | ||||||
| 2 | 一种双翼无伞末敏子弹药 | CN201611049126.3 | 2016-11-24 | CN106403730A | 2017-02-15 | 王刘星; 刘涛; 韩果; 张鹏; 高辉; 欧军; 魏树孝; 冯伦天; 马庆跃 |
| 本发明涉及一种双翼无伞末敏子弹药，包括：弹体(1)、大翼片(2)和小翼片(3)；大翼片(2)和小翼片(3)错位布置在弹体(1)的两侧，大翼片翼片(2)相对于弹体(1)轴线1/3偏左、2/3偏右，小翼片(3)与弹体(1)的连接位置位于弹体(1)顶部，小翼片(3)相对于弹体(1)轴线2/3偏左、1/3偏右。本发明的双翼无伞末敏子弹药，阻力系数提高了10％左右，转动力矩系数提高了一倍，提高了无伞末敏弹稳态扫描时间和转速。(2)与弹体(1)的连接位置位于弹体(1)顶部，大 | ||||||
| 3 | 一种高隐身性能的结构吸波弹翼 | CN201611049119.3 | 2016-11-24 | CN106403729A | 2017-02-15 | 张岩; 谢立云; 彭铮; 赵小勇; 綦龙; 方明恩; 罗剑波; 张辉; 郭靖; 罗帅; 李娟娟; 栗莉; 刘剑 |
| 本发明涉及一种高隐身性能的结构吸波弹翼，包括翼尖(1)、弹翼前缘(2)和翼面(3)；翼尖吸波材料由聚甲基丙烯酰亚胺(PMI)泡沫材料与功能化石墨烯复合而成，翼面(3)由碳纤维材料加工制成；翼尖(1)和弹翼前缘(2)分别加工完成后，粘贴在翼面(3)上组合成吸波弹翼，再在吸波弹翼外表面缠绕玻璃钢。本发明的高隐身性能的结构吸波弹翼，所采用的结构吸波材料对电磁波具有衰减效果，应用在弹翼上能有效提高导弹隐身性能，同时减小了导弹的重量，提高了导弹的突防能力。(1)与弹翼前缘(2)采用泡沫吸波材料制成，泡沫 | ||||||
| 4 | 一种铝合金舵面机械加工工艺方法 | CN201410300180.5 | 2014-06-26 | CN104128745A | 2014-11-05 | 魏建中; 耿久全 |
| 本发明提供了一种铝合金舵面机械加工工艺方法，该方法包括加工前准备铝合金板材预拉伸、精铣夹头厚度及外形、枪钻加工深孔、高速铣精铣型面和线切割加工去夹头；采用预拉伸板材，从原材料着手降低材料成型过程中产生的内部原始应力，减少后续加工中零件变形；采用外排屑深孔枪钻替代镗孔工序，有效减少加工时间，且可以加工深径比大于10倍的深孔；采用高速铣加工减少铣削加工中切削力引起的加工应力以及切削热引起的变形，免去了热处理生产的费用和时间；采用线切割替代铣加工去夹头，进一步减少加工应力，控制零件变形。该加工工艺加工效率低且零件质量难以保证，可实现舵面、弹翼类零件优质高效低成本加工。 | ||||||
| 5 | Composites made rocket motor and a manufacturing method thereof that integrates fin | JP10358089 | 1989-04-25 | JP2703622B2 | 1998-01-26 | デイノ・クラピ; ルイ・ダフィクス |
| 6 | Composite rocket motor with integrated fins and manufacture thereof | JP10358089 | 1989-04-25 | JPH01313660A | 1989-12-19 | RUI DAFUIKUSU; DEINO KURAPI |
| PURPOSE: To enable fins to be integrated with a rocket structure so as to enhance strength by making a tubular preform, fins and fin supports independently and mounting them respectively. CONSTITUTION: A tubular perform 10, fins 30 with an interior reinforced by a honeycomb structure 36 and fin supports 20 including soles 22 are made independently by fibrous cloth impregnated with polymerizable binder. The fin supports 20 are assembled with the tubular preform 10, and the assembly is polymerized. Then the fins 30 are mounted on the fin supports 20. In this way, the fins 30 are connected to the tube without the need for metal frames, therefore thickness of the tube wall is not substantially increased. Thus, the amount of fuel carried by the tube is increased. Moreover, by integrating the soles 22 of the fin supports 20 in the structure of the preform 10, the fins 30 play a role in increasing the strength of the rocket as a whole. | ||||||
| 7 | 金属部品間の低熱伝導インターフェース | JP2013558005 | 2011-10-27 | JP5886327B2 | 2016-03-16 | クリストー、キリアコス |
| 8 | Low thermal conduction interface between the metal parts | JP2013558005 | 2011-10-27 | JP2014516805A | 2014-07-17 | クリストー、キリアコス |
| 低熱伝導結合部即ち装置は、１対の対応する部品を一緒に機械的に結合するように構成されている。 前記対応する部品の一方は、発熱環境にあり得る。 前記対応する部品の一方の表面の少なくとも一部を粗面化することによって、接続の構造的な一体性を維持しながら、前記対応する部品間の接触領域が減じられ得る。 前記粗面化は、前記部品の一方の対応する面の全面、もしくは一部分のローレット加工であり得る。 これは、他方の部品と接触する面に一連の凹部を形成し得る。 これら凹部は、十分に小さいので、前記接触面のエッチングされていない領域が点在しており、前記部品間の結合の構造的な一体性が、依然として維持される。 前記結合部は、ミサイルのフィンのような航空機の操縦舵面の前縁部と、前記操縦舵面の本体部との間にあり得る。
【選択図】図１ |
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| 9 | Guided airframe | JP6517693 | 1993-03-24 | JPH06273092A | 1994-09-30 | AKIGUCHI MASAYOSHI; KUROTAKI TAKUJI |
| PURPOSE: To obtain a large lift, sufficient maneuvering performance and aerodynamic stable performance and to enhance containing capacity as a launcher by mounting large stable wings having large areas and reducing a cylindrical diameter of a canister. CONSTITUTION: Stable wings 3 having sufficiently large areas are separated from a body 1, contained in a wing containing cylinder 5 mounted at a front side of a canister 4. When the body 1 is separated from the canister 4 at the time of launching, stable wing supports 7 are inserted into the wings 3 by a thrust force of a rocket motor and a frictional force between pads 6 and the wings 3, the body 1 is coupled to the stable wings, and separated from the canister 4. Thus, since the wings 3 having sufficiently large area are mounted at the body 1, a large lift is obtained to improve aerodynamic stability. Since the wings 3 having larger areas than those of steering wings 2 are not mounted at the body 1 at the time of launching, a cylindrical diameter of the canister 4 can be reduced, and containing as the launcher can be improved. COPYRIGHT: (C)1994,JPO&Japio | ||||||
| 10 | 左右非対称設計によって造波抵抗を最小化するシステムおよび方法 | JP2013237617 | 2013-11-18 | JP6383534B2 | 2018-08-29 | プルーク, ウィリアム; ティロットソン, ブライアン ジェー. |
| 11 | System and method for minimizing wave drag through bilaterally asymmetric design | JP2013237617 | 2013-11-18 | JP2014104973A | 2014-06-09 | WILLIAM PFLUG; TILLOTSON BRIAN J |
| PROBLEM TO BE SOLVED: To provide an aircraft configuration that minimizes wave drag.SOLUTION: An air vehicle 100 having a bilaterally asymmetric configuration includes a body 104 having a longitudinal axis. The air vehicle further includes longitudinally offset engine nacelles 152, asymmetrically lengthened engine nacelles, and/or longitudinally offset protruding aerodynamic surfaces 268. | ||||||
| 12 | Launcher of the flying object | JP1848191 | 1991-03-26 | JPH0525193U | 1993-04-02 | 善之 今山; 勝彦 佐藤; 敏浩 佐藤 |
| (57)【要約】 【目的】 飛翔体の発射前の支持のために飛翔体に装着されたラグを取外し、飛翔体の飛翔距離を増大させる。 【構成】 飛翔体１を発射時まで支持しかつガイドするための上部ガイド３、下部ガイド４を装備したフレーム２と、同フレーム２を支承するための架台５と、上記飛翔体１の発射時における俯仰角を調整するための手段とによって構成された飛翔体発射装置において、一端部はそれぞれ上部と下部のガイド３，４に係合され、他端部はそれぞれ飛翔体１の外周部に離脱可能に取付けられた上部と下部のラグ７，８、及び前記上部と下部のラグを発射時に飛翔体から剥ぎ取るためのせん断刃１７をフレーム２に装着した。 | ||||||
| 13 | PENETRATOR AND SUB-CALIBER PROJECTILE | US15947238 | 2018-04-06 | US20180224251A1 | 2018-08-09 | Martin Berg |
| A penetrator and a sub-caliber ammunition or projectile accommodating said penetrator. The penetrator according to the invention is characterized by the fact that the penetrator has an interface in the front area. Via said geometric interface, a basic penetrator devised in according to the invention can be provided having different penetrator tips and completed to form an individual KE penetrator. | ||||||
| 14 | Low cost guiding device for projectile and method of operation | US15057215 | 2016-03-01 | US09587923B2 | 2017-03-07 | Gil Wurzel; Assaf Malul |
| A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger. | ||||||
| 15 | LOW COST GUIDING DEVICE FOR PROJECTILE AND METHOD OF OPERATION | US15057215 | 2016-03-01 | US20160245631A1 | 2016-08-25 | Gil WURZEL; Assaf MALUL |
| A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger. | ||||||
| 16 | Fin-stabilized, muzzle-loaded mortar projectile with sabot | US14444415 | 2014-07-28 | US09410781B1 | 2016-08-09 | Ryan Hooke; Jackie Longcore; Kyle Schaarschmidt; Joshua Gallagher |
| A muzzle-loaded, fin-stabilized mortar round includes a projectile with a discarding sabot mounted thereon. The sabot includes one or more discrete sections that are circumferentially divided into a plurality of discrete sabot increments. In the case of more than one discrete section, the plurality of discrete sections are arranged longitudinally one after another in abutting relationship. Each sabot increment includes a base portion mechanically connected to the projectile and two opposing side portions mechanically connected to circumferentially adjacent sabot increments. | ||||||
| 17 | LOW COST GUIDING DEVICE FOR PROJECTILE AND METHOD OF OPERATION | US14065467 | 2013-10-29 | US20150247715A1 | 2015-09-03 | Gil WURZEL; Assaf MALUL |
| A guiding assembly is adapted to be connected to a projectile and comprising a rear main unit adapted to be connected to the front end of the projectile, and a front main unit rotatably connected at its rear end to the front end of the rear main unit. The front main unit is adapted to rotate about a central longitudinal axis. A relative speed control unit is operable between the rear main unit and the front main unit and capable of providing spin braking force to slow the relative speed of rotation of the front main unit. An at least one guiding fin radially extends from the front main unit. The pitch angle of the fin is controllable by a return spring connected to the fin so that the pitch angle of the fin is growing as the aerodynamic pressure on the fin lowers and it is growing smaller as the aerodynamic pressure on the fin gets bigger. | ||||||
| 18 | Low-heat-transfer interface between metal parts | US13048942 | 2011-03-16 | US09012824B2 | 2015-04-21 | Kyriakos C. Christou |
| A low-heat-transfer coupling or assembly is configured to mechanically couple together a pair of mating parts, one of which may be in a heat-producing environment. By roughening at least part of the surface of one of the parts, the contact area between the mating parts can be reduced, while still maintaining the structural integrity of the connection. The roughening can be a knurling process of all or part of the mating surface on one of the parts. This can produce a series of recesses on the surface that are in contact with the other part. The recesses can be small enough, interspersed with non-etched areas of the contact surface, that structural integrity of the coupling between the parts is still maintained. The coupling may be between a leading edge of an aircraft control surface, such as a missile fin, and a body of the control surface. | ||||||
| 19 | MULTI-CALIBER FUZE KIT AND METHODS FOR SAME | US12469443 | 2009-05-20 | US20120211592A1 | 2012-08-23 | Chris E. Geswender; Cesar Sanchez; Matthew A. Zamora |
| A multi-caliber fuze kit includes a fuze housing configured for coupling with multiple projectiles. One or more canards are moveably coupled with the fuze housing. The one or more canards are adjustable between two or more canard configurations. In a first canard configuration, the one or more canards are at a first canard angle relative to a bore sight of the fuze housing, and the first canard angle is configured for use with a first projectile. In a second canard configuration, the one or more canards are at a second canard angle relative to the bore sight of the fuze housing, and the second canard angle is configured for use with a second projectile. The first and second canard angles are different. In another example, in the first canard configuration the one or more canards include a first canard shape configured to provide a first specified trajectory with the first projectile. In the second canard configuration the one or more canards include a second canard shape configured to provide a second specified trajectory with the second projectile. The first canard shape and the second canard shape are different. | ||||||
| 20 | PYROPHORIC ARROWS | US12867052 | 2009-02-17 | US20100307364A1 | 2010-12-09 | Nahum Orlev; Amir Weitz |
| An arrow-type warhead (100,200,300,400,500,600,700) comprises an envelope (102,202), a filling (108), a hardened head section (104) to promote penetration of the target and a stabilizing mechanism (106,210,302,402,502,602) to stabilize the warhead in flight, hi some embodiments the filling (108) is pyrophoric and undergoes an exothermic reaction with the envelope upon impact. In other embodiments the filling is incendiary and undergoes reaction with the envelope upon impact in an oxygen rich-environment. In yet other embodiments, the filling is explosive. In all embodiments, the warhead may be equipped with a mini-rocket propulsion mechanism (802) for propelling the warhead to the target. | ||||||
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