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1. 发明授权

US4004416A Infra-red suppressor for use with turbo-shaft engine 失效
标题翻译：用于涡轮轴发动机的红外线抑制器
公开(公告)号：US4004416A
公开(公告)日：1977-01-25
申请号：US19576
申请日：1970-03-16
申请人： Armand F. Amelio , Kenneth M. Rosen
发明人： Armand F. Amelio , Kenneth M. Rosen
IPC分类号： F02K1/82 , F02K3/04
CPC分类号： F02K1/825
摘要： An infra-red radiation suppressor adapted to be positioned to alter the flow of the exhaust gases of a turbo-shaft engine and sized to block view into the engine outlet and including self-pumping ejector means to cool the visible surfaces of the suppressor.BACKGROUND OF THE INVENTION1. Field of InventionThis invention relates to infra-red radiation suppression and more particularly to an infra-red radiation suppressor which is adapted to be mounted to block the view into the outlet of a turbo-shaft engine and to intercept and alter the flow of exhaust gases thereof and which includes self-pumping ejector mechanisms to provide cooling of the exposed suppressor parts.2. Description of the Prior ArtDuring military combat it is common practice to utilize infra-red radiation seeking missiles and other destructive vehicles to seek out and destroy upon contact military flight vehilces which use propulsion mechanisms, such as turbo-jet or turbo-shaft engines or rockets, which operate at a sufficiently high temperature that the metal parts thereof emit significant infra-red radiation. The radiation emitted by the exhaust gases is largely attenuated by the atmosphere. In any case it has been found to be of less significance than that emitted by the exposed metal parts.The infra-red radiation threat is fully described in U.S. Pat. No. 3,210,934, to which reference may be made.Protection against this threat is accomplished by blocking the view into the engine outlet to prevent the infra-red radiation seeking devices from detecting the infra-red radiation emitting parts therewithin and by cooling exposed parts to prevent them from reaching the critical infra-red radiation emitting temperature which can be detected by the oncoming missile.In the prior art, such as in U.S. Pat. No. 3,210,934, this exposed part cooling function is performed by apparatus which either needs a pressure source for the cooling fluid or which is ram-air responsive. The disadvantage of such systems is that devices which require pressure sources for providing pressurized cooling fluid to the exposed vehicle parts either require a separate pumping source with its attendant added weight and complication to the flight vehicle system, or require that pressurized engine compressor bleed air be utilized for this purpose, thereby reducing the power generating capability of the engine so bled. The devices which are ram-air responsive must not only be capable of being positioned so that some part thereof is in impinging contact with atmosphere to develop the ram-air effect, and this is not possible or practical in power generating devices which are positioned internally within the flight vehicle and, further, such ram-air responsive devices are inoperative when the flight vehicle is not moving forward at a substantial velocity. Accordingly, such ram-air responsive devices could not be utilized if the flight vehicle were a helicopter, which is capable of operating in many directions other than forward and which is further capable of operating in the hover mode, which mode is very important in many military situations.It will therefore be seen that the prior art devices either add weight and complication to the overall system when a separate cooling fluid power source is utilized, or reduce the engine power generating capability when an engine generated pressure source, such as turbo-jet or turbo-shaft compressor, is bled to provide this cooling fluid. Further, ram responsive infra-red radiation suppressors are ineffective on helicopters during flight modes other than forward flight and the all-important military hover mode.In addition, it has been suggested in the prior art that infra-red radiation suppressor parts be made completely porous so as to be able to use transpiration cooling, that is, the forced passage of cooling air through the various pores in the suppressor wall members. While transpiration cooling is accepted as an efficient method of cooling from a theoretical thermodynamic standpoint, film cooling is only slightly less efficient and has many advantages. Transpiration cooling is particularly unsuited for helicopter operation. The helicopter often lands and takes-off from unprepared areas and foreign matter, including dust and debris, fill the air and are injected into the engine and pass therefrom into the suppressor. The debris will attempt to pass with the air through the small 40 micron pores of the transpiration cooled suppressor members, thereby clogging these pores with foreign matter. With transpiration cooling, even if a complete clogging of all the pores is not encountered, localized infra-red radiating hot spots in the walls would be encountered in the localized clogged portions. In helicopter use, an attempt to keep the pores of a transpiration cooled suppressor absolutely clean in service would present very substantial maintenance problems. A further disadvantage of transpiration cooling is that the porous parts involved cannot be fabricated by conventional methods, as can the solid sheet metal parts of our suppressor. In addition, in a transpiration cooled system, it would be necessary, in some suppressor stations, to be discharging cooling air into a high static pressure region, and this would require the use of a positive pressure source. Still further, the partially clogged pores, or the partially clogged porous wall, offers increased resistance to cooling air flow therethrough and hence a greater positive pressure is required to cause the cooling air to pass through these restricted pores, therefore, transpiration cooling produces the undersirable need of an extremely high capacity pressure source capable of generating high pressure. To complicate the problem, we are not able to produce an even cooling effect over the entire surface of the suppressor due to irregular pore clogging problems. Contrary to the clogging problems presented by the transpiration cooled suppressor, the ejector slots of our suppressor are sufficiently large that they are not subject to clogging.In addition, the prior art has taught infra-red radiation prevention by passing cooling air between closely positioned double walls of the suppressor parts to produce convection cooling thereof. Since there is substantial resistance to the flow of cooling air between two closely spaced walls of this type, very substantial air pressure is required to cause the air to flow therethrough with sufficient velocity to effectively cool the passage defining parts.Contrary to the transpiration cooling and the convection cooling of the prior art, we are using primarily film cooling. Since film cooling produces a cooling air film between the suppressor parts and the hot exhaust gases to prevent heating of the suppressor parts, less air is used in such a system because it requires less air to prevent heating of suppressor parts by film cooling than it does to convectively cool suppressor parts which are directly scrubbed by the hot exhaust gases.SUMMARY OF THE INVENTIONA primary object of the present invention is to provide an infra-red radiation suppressor for use with a turbine engine, such as a turbo-shaft engine, which both blocks view into the outlet of the turbine engine from all vantage points, which is mounted independently of the engine so as not to change the operating characteristics thereof and so as to be free from absorbing the vibrations and physical distortion therefrom, which includes no moving parts, and which includes a self-pumping, passive cooling system for the exposed suppressor parts to prevent them from reaching critical infra-red radiation emitting temperatures.In accordance with the present invention, an infra-red radiation suppressor is provided for use with a flight vehicle which is operable during all modes of operation of the flight vehicle and which requires no cooling fluid pressure generating mechanism, with its attendant added weight, added complication and reduced reliability, and which does not depend upon engine generated pressure to cool the suppressor.In accordance with the present invention, such a suppressor is provided and is made of sheet metal parts, all of which are capable of fabrication and repair by the use of conventional sheet metal fabricating methods and apparatus.In accordance with still a further aspect of the present invention, such a suppressor is provided which defines an annular exhaust gas passage for the engine exhaust gases, which passage increases in cross-sectional area from its forward or upstream end to its after or downstream end so as to constitute a diffuser.It is still a further object of the present invention to provide such an infra-red radiation suppressor which requires minimum cooling fluid flow and which is not prone to flow separation of the cooling fluid film and the adjacent exhaust gas flow from the suppressor parts over which it is flowing.In accordance with a further aspect of the present invention, such an infra-red radiation suppressor is provided and includes an inner body or central plug enveloped within an outer casing such that these parts are supported in spaced relation to define an annular exhaust gas passageway therebetween and such that the selected curvature of the outer surface of the central plug, the inner surface of the outer casing and the midstream path of the annular passageway interact to induce the flow of a cooling air blanket along the outer surface of the central plug and to prevent flow separation of that cooling air blanket and the adjacent exhaust gas flow from the outer surface of the central plug.In accordance with a further aspect of the present invention, an infra-red suppressor is provided which utilizes the ejector principle at at least one station in the suppressor.In accordance with still a further aspect of the present invention, such a suppressor is provided which includes a self-pumping boundary layer control, film cooling slot at substantially the maximum diameter station of the central plug, which slot is defined between wall members in the central plug which cooperate to define a converging passage culminating in the slot, the length of which passage is approximately 10 times the exit height of the slot, thereby cooling the convergent passage defining walls by convection cooling, and so that the cooling air passing through the slot is uniform and positively accelerated to prevent local flow separation of the cooling air from the slot walls upstream of the slot exit and from the central plug wall downstream of the slot exit.
摘要翻译：一种红外辐射抑制器，其适于被定位成改变涡轮轴发动机的排气的流量，并且其尺寸被设计成阻挡视图进入发动机出口，并且包括用于冷却抑制器的可见表面的自泵送喷射器装置。

2. 发明授权

US4966526A Mechanically actuated slot for circulation control rotor 失效
标题翻译：用于循环控制转子的机械致动槽
公开(公告)号：US4966526A
公开(公告)日：1990-10-30
申请号：US379305
申请日：1989-07-13
申请人： Armand F. Amelio , William C. Fischer, Jr.
发明人： Armand F. Amelio , William C. Fischer, Jr.
IPC分类号： B64C27/46 , B64C27/32 , B64C27/467
CPC分类号： B64C27/325
摘要： A circulation control rotor system for aircraft in which compressed air is directly supplied at generally constant pressure to plenums in the rotor blades and discharged through area controlled slots, the area controlling means involving camming surfaces and being actuated by cyclic, collective, aircraft vibration and flight stability inputs.
摘要翻译：一种用于航空器的循环控制转子系统，其中压缩空气以一般恒定的压力直接供应到转子叶片中的通风室并通过区域控制的槽排出，该区域控制装置涉及凸轮表面并由循环，集体，飞机振动和飞行稳定性输入。

3. 发明授权

US6134879A Suppression system for a gas turbine engine 失效
标题翻译：燃气轮机的抑制系统
公开(公告)号：US6134879A
公开(公告)日：2000-10-24
申请号：US454167
申请日：1989-12-21
申请人： Robert C. Frawley , Armand F. Amelio , Richard S. Barnard
发明人： Robert C. Frawley , Armand F. Amelio , Richard S. Barnard
IPC分类号： B64D33/04 , F02K1/82 , F02K1/44
CPC分类号： B64D33/04 , F02K1/825 , Y02T50/672
摘要： A suppression system for a gas turbine engine uses a tapered exhaust manifold with a plurality of exhaust nozzles acting in conjunction with a plurality of mixing cells to produce cooling of an exhaust gas stream upon exit from an aircraft. The cooling air is supplied to the mixing cells in such a way that the walls of the cells are inherently maintained at a desired temperature without the use of dedicated cooling apparatus such as finned head exchangers, film cooling slots, etc. This approach allows the typically conflicting requirements of low IR signature and low radar cross section to be simultaneously satisfied in an efficient, light weight and low cost manner. The exhaust gas suppression system is preferably disposed in the tail section of a helicopter aircraft, having nozzles pointing in an essentially downward direction to reduce the threat from an over flying aircraft while minimizing the ability of ground based systems to acquire a direct line of sight on any hot surfaces or to detect the exhaust cavity using radar.
摘要翻译：用于燃气涡轮发动机的抑制系统使用具有多个排气喷嘴的锥形排气歧管，多个排气喷嘴与多个混合室结合起来，以在从飞机出来时产生排气流的冷却。将冷却空气以这样的方式供应到混合室，使得电池的壁固有地保持在期望的温度，而不使用专用冷却装置，例如翅片式头部交换器，薄膜冷却槽等。这种方法允许通常低IR签名和低雷达横截面的冲突要求以有效，重量轻，成本低的方式同时满足。排气抑制系统优选地设置在直升机飞行器的尾部中，其具有指向基本上向下的方向的喷嘴，以减少来自飞行飞行器的威胁，同时使基于地面的系统获得直接视线的能力最小化任何热表面或使用雷达检测排气腔。

4. 发明授权

US5165232A Dual charge engine start accumulator 失效
标题翻译：双重充电发动机起动蓄能器
公开(公告)号：US5165232A
公开(公告)日：1992-11-24
申请号：US812091
申请日：1991-12-23
申请人： Armand F. Amelio , James J. Manzolli , William F. Lange , Robert C. Eisenberg
发明人： Armand F. Amelio , James J. Manzolli , William F. Lange , Robert C. Eisenberg
IPC分类号： B64D41/00 , F02C7/27
CPC分类号： F02C7/27 , B64D41/00 , F05D2220/50 , Y02T50/44 , Y02T50/671
摘要： There is provided by the present invention an accumulator system for turb engine start-ups that has comparable weight and bulk to a conventional auxiliary power unit system but which has instantaneous second start capability.
摘要翻译：本发明提供了一种用于涡轮发动机起动器的蓄能器系统，其具有与常规辅助动力单元系统相当的重量和体积，但具有瞬时第二启动能力。

5. 发明授权

US4304094A Engine air particle separator for use with gas turbine engine 失效
标题翻译：用于燃气轮机的发动机空气分离器
公开(公告)号：US4304094A
公开(公告)日：1981-12-08
申请号：US95135
申请日：1979-11-16
申请人： Armand F. Amelio
发明人： Armand F. Amelio
IPC分类号： F02C7/055 , F02C7/052 , F02C7/042
CPC分类号： F02C7/052
摘要： An engine air particle separator for use with a turbine engine and providing a first engine air flow path to the engine inlet in which foreign particles are separated from the air entering engine, and a second direct flow path for air to the engine inlet presenting minimum pressure drop and such that the ram air flows directly into the engine inlet. The second flow path includes actuatable blow-in doors which are actuated by a pneumatic door actuator mechanism operable to cause the doors to close upon the admission of air at operating pressure to the mechanism. Mechanism is provided to prevent the doors from opening when actuating air pressure is applied to the door actuator mechanism but falls below a preselected limit and to permit the doors to open in response to spring bias and ram pressure acting thereagainst when the air at actuating pressure is withdrawn.
摘要翻译：一种发动机空气颗粒分离器，用于与涡轮发动机一起使用，并且向发动机入口提供第一发动机空气流动路径，其中外来颗粒与进入发动机的空气分离，以及用于空气到发动机入口的第二直接流动路径，其具有最小压力使得冲压空气直接流入发动机入口。第二流路包括可致动的吹入门，其由气动门致动器机构致动，该气动门致动器机构可操作以在入口处的空气在机构的操作压力下使门关闭。提供机构以防止当致动空气压力施加到门致动器机构但是低于预定极限时允许门打开，并且允许门响应于当致动压力下的空气为起动时的弹簧偏压和压头作用而打开门取消。

6. 发明授权

US5544449A Aircraft duplex hinge assembly 失效
标题翻译：飞机双面铰链总成
公开(公告)号：US5544449A
公开(公告)日：1996-08-13
申请号：US139257
申请日：1993-10-20
申请人： Armand F. Amelio , David N. Susek
发明人： Armand F. Amelio , David N. Susek
IPC分类号： B64C1/14 , E05D3/06 , E05D3/12 , E05D11/00
CPC分类号： B64C1/1446 , B64C1/1407 , E05D3/12 , E05D11/1007 , E05Y2900/502 , Y10T16/5409 , Y10T16/547
摘要： An aircraft duplex hinge assembly (10 or 10') configured for use in aircraft, especially helicopters, having a compound curvature airframe (130) configuration wherein the edges of access panels (100) and the corresponding airframe apertures have a beveled configuration. The duplex hinge assembly (10 or 10') includes dual hinge mechanisms (20) and a latching mechanism (50) to deactivate the duplex hinge mechanism (10) with the access panel (100) in the closed position. The dual hinge mechanisms (20) include a primary mounting bracket (22) secured in combination with the airframe (130), a secondary mounting bracket (24) secured in combination with the access panel (100), and an interconnecting member (26) having a straight segment (30), an arcuate segment (32), and a protective flat segment (34). The straight and protective flat segments (30, 34) are mounted in rotatable combination with the primary and secondary mounting brackets (22, 24), respectively, and the protective flat segment (34) protects the access panel (100) from damage during opening and closing. One embodiment of the duplex hinge assembly (10) further includes an aft locking subassembly (40) that functions as the primary means for maintaining the access panel (100) in the closed position. Another embodiment of the duplex hinge assembly (10') includes a stabilizing member (60) secured in combination with the interconnecting members (26) and operative to stabilize the hinge mechanisms (20) and the access panel during opening and closing sequencing. Optionally, either embodiment of the duplex hinge assembly (10 or 10') may include a panel support assembly (70) that is operative to support and maintain the access panel (100) in a partially or fully open position.
摘要翻译：配置用于具有复合曲率机体（130）配置的飞机尤其是直升机的飞机双重铰链组件（10或10'），其中检修面板（100）的边缘和对应的机身孔具有斜面构型。双重铰链组件（10或10'）包括双重铰链机构（20）和闭锁机构（50），以使接近面板（100）处于关闭位置来停用双重铰链机构（10）。所述双铰链机构（20）包括与所述机架（130）组合固定的主安装支架（22），与所述检修面板（100）组合固定的辅助安装支架（24）和互连构件（26）具有直段（30），弧形段（32）和保护平面段（34）。直的和保护的平坦段（30,34）分别与主要和次要安装支架（22,24）可旋转地组装安装，并且保护平面段（34）在开启期间保护检修面板（100）免受损坏并关闭。双重铰链组件（10）的一个实施例还包括作为用于将检修面板（100）保持在关闭位置的主要装置的后部锁定子组件（40）。双相铰链组件（10'）的另一实施例包括与互连构件（26）组合固定的稳定构件（60），并且可操作以在打开和关闭排序期间稳定铰链机构（20）和检修面板。可选地，双面铰链组件（10或10'）的任一实施例可以包括面板支撑组件（70），其可操作以支撑和维持接近面板（100）处于部分或完全打开位置。

7. 发明授权

US5433070A Flexible engine inlet duct mounting system 失效
标题翻译：灵活的发动机入口管道安装系统
公开(公告)号：US5433070A
公开(公告)日：1995-07-18
申请号：US118064
申请日：1993-09-08
申请人： Armand F. Amelio
发明人： Armand F. Amelio
IPC分类号： F02C7/04 , F02K1/80 , F02C7/20
CPC分类号： F02C7/04 , F02K1/80 , Y10T137/0536
摘要： A flexible engine inlet duct mounting system for integrating an engine inlet duct in combination with an engine system to minimize or eliminate turbulence-inducing structural discontinuities therebetween wherein non-turbulent intake airflow is provided to the engine system. The mounting system includes a mechanical support assembly that constrains the relative motion between the aft ends of the inlet duct and the engine system, and a dual seal assembly that accommodates such relative motion while concomitantly maintaining seals between the inlet duct and the engine system. The duct support assembly includes an annular duct support member and an annular spherical adaptor member having interacting ends that have complementary arcuate configurations which constrain the relative motion of the aft ends of the inlet duct to in-plane displacements about a duct pivot point coincident with the engine system centerline.
摘要翻译：一种柔性发动机入口管道安装系统，用于将发动机入口管道与发动机系统相结合，以最小化或消除其间引起的紊流引起的结构不连续性，其中非湍流入口气流被提供给发动机系统。安装系统包括限制入口管道和发动机系统的后端之间的相对运动的机械支撑组件，以及容纳这种相对运动同时保持入口管道和发动机系统之间的密封的双重密封组件。管道支撑组件包括环形管道支撑构件和环形球形适配器构件，其具有相互作用的端部，该相互作用端部具有互补的弓形构造，其将入口管道的后端部的相对运动限制在围绕与管道枢转点重合的管道枢转点的平面内位移发动机系统中心线。

8. 发明授权

US5779288A Low profile latch mechanism 失效
标题翻译：薄型闩锁机构
公开(公告)号：US5779288A
公开(公告)日：1998-07-14
申请号：US118066
申请日：1993-09-08
申请人： Armand F. Amelio
发明人： Armand F. Amelio
IPC分类号： B64D29/08 , E05C5/04
CPC分类号： E05C5/04 , B64D29/06 , Y10T292/1099 , Y10T292/218
摘要： A low profile latch mechanism for an access panel that minimizes external structural discontinuities while concomitantly providing external access to engage and/or disengage the latch mechanism for closing and/or opening of the access panel. The latch mechanism includes an insert member mounted in rotatable combination with the internal surface of the access panel, a captured floating nut mounted in nonrotatable combination with the internal surface of a frame segment, a safety lock member mounted for axial displacement within the captured floating nut, and a removable key member. The removable key member is insertable through an access aperture in the access panel to engage the insert member for rotation thereof to threadingly engage the captured floating nut to close the access panel. The safety lock member is biased to engage the insert member to lock the low profile latch mechanism in the fully engaged state upon removal of the key member. The removable key member is inserted through the access aperture to mechanically disengage the safety lock member from the insert member to initiate the disengagement procedure. Counter-rotation of the key member causes the insert member to threadingly disengage from the capture floating nut, which causes the access panel to be biased to a partially open position wherein the access panel may be fully opened manually.
摘要翻译：一种用于进入面板的薄型闩锁机构，其最小化外部结构不连续性，同时伴随地提供外部接近以接合和/或解除用于闭合和/或打开检修面板的闩锁机构。所述闩锁机构包括与所述检修面板的内表面可旋转地组合安装的插入件，与框架部分的内表面安装成不可旋转组合的捕获浮动螺母，安装在所捕获的浮动螺母内的轴向位移的安全锁定构件，以及可拆卸的键构件。可拆卸的键构件可通过检修面板中的进入孔插入，以接合插入构件以使其旋转，以与被捕获的浮动螺母螺纹接合以闭合检修面板。安全锁定构件被偏置以接合插入构件，以在移除键构件时将低轮廓闩锁机构锁定在完全接合状态。可拆卸的键构件通过进入孔插入以使安全锁定构件与插入构件机械地脱离以启动脱离过程。键构件的反向旋转使得插入构件与捕获浮动螺母螺纹脱离，这使得检修面板被偏压到部分打开位置，其中检修面板可以手动完全打开。

9. 发明授权

US5699965A Infrared suppressor for a gas turbine engine 失效
标题翻译：燃气轮机的红外线抑制器
公开(公告)号：US5699965A
公开(公告)日：1997-12-23
申请号：US374025
申请日：1989-06-30
申请人： Armand F. Amelio
发明人： Armand F. Amelio
IPC分类号： F41H11/02 , B64D7/00 , B64D33/04 , F02C7/00 , F02K1/82 , F02K1/46
CPC分类号： F02K1/825 , B64D33/04 , B64D2033/045 , Y02T50/671
摘要： An IR suppressor produces a thin "ribbon" exhaust plume using a tapered exhaust manifold which has a plurality of discrete exhaust nozzles that are longitudinally aligned with the exhaust manifold. Optionally, the nozzles extend within but are spaced apart from mixing ducts which are open to the ambient air at both ends. The mixing ducts mix ambient air with the exhaust plume. In another aspect of this invention, a single nozzle (which is longitudinally aligned with the manifold) is substituted for the plurality of discrete exhaust nozzles. In this aspect, the nozzle extends within but is spaced apart from a mixing duct which is open at both ends and has a curve sufficient to block a line of sight to the nozzle. A helicopter that has a rotatable IR suppressor so that the exhaust can be directed substantially parallel to the helicopter blades when the blades are not turning to protect them from exhaust heat is also disclosed.
摘要翻译： IR抑制器使用具有与排气歧管纵向对准的多个离散排气喷嘴的锥形排气歧管产生薄的“带状”排气羽流。可选地，喷嘴在内部延伸，但是与在两端的环境空气开放的混合管道间隔开。混合管道将环境空气与排气羽流混合。在本发明的另一方面，单个喷嘴（其与歧管纵向对齐）被代替多个离散的排气喷嘴。在这方面，喷嘴在其两端敞开的混合管道内延伸而间隔开，并具有足以阻挡喷嘴的视线的曲线。一种具有可旋转的IR抑制器的直升机，其特征在于还公开了当叶片不转动以保护它们免于排热时，排气可以直接指向直升机叶片。

10. 发明授权

US5072898A Engine cowling roller attachment 失效
标题翻译：发动机整流罩附件
公开(公告)号：US5072898A
公开(公告)日：1991-12-17
申请号：US576571
申请日：1990-08-31
申请人： Armand F. Amelio
发明人： Armand F. Amelio
IPC分类号： B64C1/14 , B64D29/04
CPC分类号： B64D29/06
摘要： An aircraft cowling (20) is comprised of a cowling body (22), forward and aft bearings (24,25) disposed on the cowling body (22), corresponding sets of guides (29,30) disposed on and conforming with the shape of the aircraft (26), a screw fastener assembly (74), latches (82), and complementary interaction between the cowling edges (68,70) and aircraft edges (69,71) to provide lateral support for the cowling (20). The aft bearing (25) is comprised of two rollers (44) and two roller supports (46) which are disposed on the cowling body (22) in a manner permitting lateral motion and coupled by a shaft (50) with right-hand threads (56) on one end and left-hand threads (58) on the other end. The shaft (50), due to the opposing threads (56,58), restricts the roller supports (46) to convergent and divergent movements and prevents movement in a common direction, thereby providing lateral support to the cowling (20) during opening and closing.
摘要翻译：飞机整流罩（20）由整流罩体（22），布置在整流罩主体（22）上的前后轴承（24,25））组成，相应的一组导向件（29,30）设置在该形状飞行器（26）的螺旋紧固件组件（74），闩锁（82）以及整流罩边缘（68,70）和飞行器边缘（69,71）之间的互补相互作用，以提供整流罩（20）的侧向支撑，。后轴承（25）由两个辊（44）和两个辊支撑件（46）组成，其以允许侧向运动的方式设置在整流罩主体（22）上，并且由轴（50）与右螺纹（56）和另一端的左侧螺纹（58）。由于相对的螺纹（56,58），轴（50）限制了辊支撑件（46）的会聚和发散运动，并防止在共同的方向运动，从而在打开和关闭的过程中向整流罩（20）提供横向支撑关闭。

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