408571 五、發明說明（1) 本發明係 是指一種兼具 巡航性能的全 按，目前 成二種，即： (一） 具有旋翼 以垂直昇 ，較不適 當。 (二） 具有固定翼的飛行器 佳，適合長 ’無法直接 關於一種旋 有旋翼機垂 新概念兩用 傳統的飛行 翼與固定翼兩 直、起降功能， 型飛行器。 器由其起降方 用型飛行器，特別 與固定翼飛機高速 式區分，可概略分 的飛行器， 降，不受場 合長距離飛 巡航性能 滑行昇降 制。 目前頗多 和，倘欲興建 摘的地區實屬 當時曰，誠屬 連空中也塞機 地區的機場 新的機場， 不易；況且 緩不濟急， 的情形發生 一般稱之為直 地限制，缺點 行，但在短距 ，即習知常見 距離飛行，缺 垂直昇降，故 隨著民航運量 需要相當面積 興建機場從評 所以為避免將 ，克服機場的 昇機，其優點是可 則是巡航性能不佳 離轉運上則頗為適 之飛機，其優點是 點則是必須有跑道 其昇降受到場地限 的增加皆已趨於飽 的土地，在地狹人 估到完工，需要相 來發生地面塞車， 限制實為當務之舉 為克服上述問題與瓶頸，頗多國家地區乃開放直昇機 ，載客業務’以期提供短程或交通擁塞地區的載人服務。 警如：由市區將旅客載運至設於郊區的機場，再轉搭飛機 至遠處。然如此仍沒有解決所有的間題’透過直昇機轉運 雖較地面運輸為快’但畢竟仍多一道步驟，且有上下機的408571 V. Description of the invention (1) The present invention refers to a full-press with both cruising performance and currently has two types, namely: (1) It has a rotor with a vertical lift, which is not appropriate. (2) Aircraft with fixed wing is good, suitable for long flight. It cannot be directly related to a rotary gyro. The new concept is dual-use. Traditional flying wing and fixed wing are straight and take off and land. The aircraft uses its take-off and landing aircraft type, which is specially distinguished from fixed-wing aircraft at high speeds. It can be roughly divided into aircraft and is not subject to long-distance flight. Cruise performance. At present, there are quite a lot. If the area to be picked is really a new airport at that time, it is not easy to be congested in the air, and it is not easy. The situation is generally called straight-line restriction. However, flying at short distances, which is a common distance, lacks vertical lift. Therefore, as the amount of civil shipping requires a considerable area to build an airport, so in order to avoid it and overcome the airport's lift, the advantage is that the cruise performance is not good. The Jiali transfer is quite suitable for the aircraft. The advantage is that there must be a runway, and the lift is limited by the increase of the site. The land is already full. People in the area are estimated to be completed, and there will be a traffic jam on the ground. Restriction is a top priority. To overcome the above problems and bottlenecks, many countries and regions are open for helicopters, and the passenger service is intended to provide short-distance or traffic congested areas with manned services. Police such as: Passengers are transported from the urban area to the airport in the suburbs, and then transferred to the distance. However, this still does not solve all the problems ‘Transport by helicopter is faster than ground transportation’, but after all, there is still one more step, and there are
第5頁 402571 五、發明說明（2) 麻煩存在，故仍 以本發明人 求而言，固定翼 飛機有南巡航性 可垂直起降，不 民航市場所需要 飛行器。於是， 能設計並研發一 直起降功能的全 題便可迎刃而解 與動機。 緣是，本發 直起降功能與固 飛行器。 有其不便 等之構思 飛機與旋 能，卻受 受場地限 的，就是 此分析結 款結合固 新概念飛 ，而這也 之處。 析’乃發覺就民航市場的需 翼機的功能是互補的，即固定翼 到起降機場的限制；而旋翼機雖 制，但巡航性能卻不佳。而目前 一軟能結合這兩者優點的兩用型 ，觸發了發明人一個構想：是否 ，翼飛機巡航性能以及旋翼機垂 行器，投入民航市場，則上述問 是發明人從事本發明創作的目的 明之主要目的在於提供一種兼具旋翼機垂 定翼飛機高速巡航性能的全新概念兩用型 盤，ίΪ: 在於機身上方裂置雙層圓 盤：片圓盤周圍各延伸出兩支旋葉片，而形成主旋翼， ，層圓盤連同旋葉片由主引擎驅動朝相反方向轉動，目的 在使兩層圓盤因旋轉而作用在機身上的轉動力矩能互相抵 消。機身尾部另裝一尾旋翼，由另一具引擎（副引擎）驅 動，主要在提供飛行器於固定翼模式飛行時的前向推力； 此兩用型飛行器於起飛時，圓盤旋轉，靠圓盤外圍的旋葉 片產生升力，採旋翼機的模式起飛，在 巡航速度與 度後，，靠由圓盤的翼剖面前進產生升力，採固定翼飛機模 式飛行。待飛至目的地時，飛行速度減緩，採旋翼機模式Page 5 402571 V. Description of the invention (2) Trouble exists, so in terms of the inventor's request, the fixed-wing aircraft has south cruising capability and can take off and land vertically, not the aircraft required by the civil aviation market. Therefore, the whole problem of designing and developing a straight landing function can be solved and motivated. The reason is that this hair straight-off and landing function and solid aircraft. There are inconveniences such as airplanes and spins, but they are limited by the site. This analysis and the combination of solid new concepts fly, and this is the point. Analysis' found that the functions of the wing aircraft in the civil aviation market are complementary, that is, the limitation of the fixed wing to the take-off and landing airport; while the rotorcraft is not good in cruise performance. At present, a dual-use type that combines the advantages of both software has triggered the inventor's idea: whether the wing aircraft cruise performance and the rotorcraft glider are put into the civil aviation market. The above question is the inventor's creation of the invention The main purpose of the purpose is to provide a new concept dual-purpose disc that has the high-speed cruising performance of the rotorcraft fixed-wing aircraft. Ϊ: It is a double-layer disc split above the fuselage: two rotor blades each extend around the disc. To form the main rotor, the layer discs and the rotor blades are driven by the main engine to rotate in opposite directions. The purpose is to make the two layers of discs' rotating moments acting on the fuselage due to rotation to offset each other. A tail rotor is installed at the rear of the fuselage, which is driven by another engine (sub-engine), which mainly provides forward thrust when the aircraft is flying in fixed-wing mode. This dual-purpose aircraft rotates the disk during take-off and relies on a circle. The rotor blades on the periphery of the disk generate lift, take off in the mode of the rotorcraft, and after cruising speed and degrees, they generate lift by advancing from the wing profile of the disk, and fly in the mode of fixed-wing aircraft. When flying to the destination, the flight speed is slowed down and the rotorcraft mode is adopted.
第6頁 403571 五、發明說明（3) 降落。 . 以下茲舉一較佳可行實、施例配合附圓詳述f發明的構 造組成及特徵所在，以利閱讀本說明書之人士得以全盤瞭 解。 圖式簡單說明如下： 第一圖所示係本發明實施例之外觀示意圖 第二圖所示係本發明實施例之側視示意圖 在本說明書及圖式中各元件編號對照如下： 1 — 飛 行 器 11 — 機身 12- -上圓盤 13 —— 下 圓 盤 121 —— 上曲 面 131- -下曲面 14 — 尾 旋 翼 22 —— 旋葉 片 23- -旋葉片 請 先 參 閱 第 _ 二圖 所 示， 本發明 實施 例整體係一飛 行 器 1 其 具 有 _ 機 身11 機身 11 的外 型可 類似一般傳統 的 直 昇 機 9 惟 其 内 部 空間 大 小則 不 受拘 限， 總以負載能力 足 夠 為 適 當 〇 在 該 機 身1 1 上 方裝 置 有雙 層圓 盤，分別為上 圓 盤12 及 下 圓 盤13 上 圓盤12 的上 曲 面1 21是- _球弧面，而 下 圓 盤13 的 下 曲 面1 31是一 -平面， 兩圓盤12， • 13間以微小 距 離 隔 開 不 互 相 碰 觸 ，每 片 圓盤12 、13 的周 圍各延伸出兩 支 旋 葉 片: 22 23 9 該 等上 > 下園 盤12、 13連 同旋葉片2 2、 23 皆 係 由 主 引 擎（未示於囷） 驅動 而 朝相 反方 向轉動，其之 所 以 設 計 成 朝 相 反 方 向轉 動 之最 大 目的 乃在 使兩層圓盤1 2 、 13 因 旋 轉 而 作 用 在 機身 11 上的 轉 動力 矩能 互相抵消。在 該 機 身 11 的 尾 部 另 設 有一 尾 旋翼: 14 ，由 另一 具副引擎（未 示 於 圖 ) 驅 動 y 主 要 在提 供 飛行 器 1處 於固 定翼模式飛行Page 6 403571 V. Description of the invention (3) Landing. The following is a detailed description of the composition and features of the invention, which is best practicable, with examples and the attached circle, so that those who read this specification will have a complete understanding. The drawings are briefly explained as follows: The first figure is a schematic diagram of the appearance of the embodiment of the present invention. The second figure is the side view of the embodiment of the present invention. The numbers of the components in this specification and the drawings are as follows: 1 — Aircraft 11 — Fuselage 12--Upper disk 13 —— Lower disk 121 —— Upper curved surface 131--Lower curved surface 14 — Tail rotor 22 — Rotary blade 23--Please refer to the first two figures for the rotary blade. The embodiment of the invention is an aircraft 1 as a whole. It has a fuselage 11 and the appearance of the fuselage 11 can be similar to that of a conventional helicopter 9 except that the internal space is not limited. The load capacity is always adequate. 1 The upper device has double-layer discs, which are the upper disc 12 and the lower disc 13, respectively. The upper curved surface of the upper disc 12 is 21-spherical arc surface, and the lower curved surface of the lower disc 13 is 31-plane. , Two discs 12, • 13 are separated by a small distance and do not touch each other. Each disc 12 and 13 each have two rotating blades: 22 23 9 The upper and lower discs 12, 13 and the rotor blades 2 2, 23 are driven by the main engine (not shown) to rotate in opposite directions. The reason why they are designed to rotate in the opposite direction is The turning moments of the two-layered discs 1 2 and 13 acting on the fuselage 11 due to rotation can cancel each other out. A tail rotor: 14 is set at the tail of the fuselage 11. It is driven by another auxiliary engine (not shown). It is mainly used to fly in fixed-wing mode when the aircraft 1 is provided.
402571 五、發明說明（4) 時間向前推力。 、13旋轉 此即採旋 可上昇； 、1 3可停 高速氣艘 上圓盤12 是平面， 此時係靠 改採固定 度減緩， 模式交替 器之目的 當飛行器1於起飛時，係驅動上、下圓盤12 ’靠圊盤12、13外圍的旋葉片22、23產生升力， 翼機的模式起飛而上昇，故不需有極長的跑道即 當其飛至適當巡航速度與高度後，上、下圓盤12 止轉動’故該等旋葉片22、23亦停止轉動，此時 流經該等上下圓盤12、13形成之固定機翼，而因 之上曲面121係球弧形，而下圓盤13的下曲面131 故即產生上下層氣流的壓力差，而形成升力，故 由上、下圓盤12、13的翼剖面前進產生升力，而 翼飛機模式飛行’待飛行至目的地後，令飛行速 再改採旋翼機模式降落，所、以本實施例可以兩種 昇降及飛行’完全達成本發明所預期兩用型飛行 本實施例所採用之各部功能配置雖非關本發明之 特徵’但仍予揭示說明如下，以利加強瞭解本發明： (一）動力系統 1. 配備兩具渦輪活塞引擎，一麁土 3丨坻 ^ 馮主W擎，一為副引整。 2. 主引擎傳動軸與齒輪箱遠桩，读.a ^ j jp %接透過齒輸箱内的歯銓撙 構將動力分給内轴與外料。内姑卞絲相内的齒輪機 内轴正轉，用以驅動上屉 圓盤12，外軸 ，用以驅動下層圓盤13〇 3. 副引擎負責驅動後方尾旋罝〗 . 疋翼14，產生向前或向後飛行 的推力。 二）「同轴雙層園盤加旋翼」機構402571 V. Description of the invention (4) Time forward thrust. 、 13 Rotation means that the rotation can be raised; ， 13 The disc 12 on the high-speed gas ship can be stopped. At this time, it is slowed down by changing the fixed degree. The purpose of the mode alternator is when the aircraft 1 is taking off. The lower disc 12 ′ is lifted by the rotor blades 22 and 23 around the stern discs 12 and 13 and the wing mode takes off and rises, so there is no need for a very long runway when it flies to an appropriate cruise speed and altitude. The upper and lower discs 12 do not rotate, so the rotor blades 22 and 23 also stop rotating. At this time, they flow through the fixed wing formed by the upper and lower discs 12, 13. Because the upper surface 121 is a spherical arc, and The lower curved surface 131 of the lower disc 13 thus generates a pressure difference between the upper and lower layers of air to form lift. Therefore, the wing sections of the upper and lower discs 12 and 13 move forward to generate lift, and the wing airplane mode flight is 'waiting to fly to the destination' After that, the flight speed was changed to use the rotorcraft mode to land. Therefore, in this embodiment, two types of lifting and flight can be achieved. The cost of the dual-purpose flight expected by the invention is fully achieved. Characteristics' but still revealed In order to facilitate better understanding of the present invention: (a) a power turbine system 1 is equipped with two piston engines, a Cu soil islet 3 Shu W ^ von main engine, as a whole the sub-lead. 2. The main engine drive shaft and the gearbox are far away from each other. Read .a ^ j jp% and then divide the power to the inner shaft and outer material through the structure in the gearbox. The inner shaft of the gear machine in the silk phase is rotating forward to drive the upper tray disc 12, and the outer shaft is used to drive the lower disc 1303. The auxiliary engine is responsible for driving the rear tail spinner. Thrust to fly forward or backward. B) "Coaxial double-layer disk plus rotor" mechanism
402571 五、發明說明（5) 1. 如圖二所示，上下兩層圓盤12、13各延伸出兩支旋葉 片22、23而構成主旋翼，兩盤以微小距離隔開不互相 碰觸，上盤12與内軸連接作正轉，下盤13與外軸連接 作反轉。上下兩盤轉速相同，如此，兩盤因旋轉而產 生的轉動力矩’恰可互相抵消。 2. 「雙層圓盤加旋翼」裝置，是透過環架（Gin]bal)機 構與機身連接，藉由控制連桿的驅動，可使圓盤具有 縱向及橫向傾斜的功能，用以改變飛行器飛行的方向 和姿態。 3. 主旋翼的旋葉片22、23'可係固定於圓盤12、13上，其 槳距（Pitch)為固定不可變，旋葉片22、23升力的 大小’由引擎轉速決定，轉速大則升力大，反之，轉 速小則升力大。 (三）尾旋翼機構 1_尾旋翼14的傾斜機構與圓盤12、13相同亦是透過環 架機構與機身連接，由控制連桿帶動尾旋翼面作二維 方向的傾斜。藉由旋翼方向的改變，便可達到改變推 動力方向的目的。 2·尾ί 3 Ϊ片的轉速為固定不變，但其槳距則為可變 r 控制’藉由控制樂距的變化，可以改變尾 疋翼14推力的大小，紫距變大 距變小則推力減小。 ^ (四）控制面機構 .俯仰（P 1 tch ).藉由縱向控制連桿，控制圓盤！ 2、 402571 五、發明說明（6) 1 3做前後方向傾斜’產生俯仰（p i tch )運動的變化 2. 滾轉（Rol 1 ):藉由橫向控制連桿，控制圓盤12、13 做左右方向傾斜，產生滚轉（R〇l丨）運動的變化。 3. 偏航（Yaw ):改變垂直尾舵的方向角，便可使飛行 器作出偏航（Yaw)動作。 (五）操控方式 1·垂直上升.增加主旋翼轉速到達起飛所需之轉速，使 升力克服機身重量而帶動機體垂直上升，此時尾旋翼 14的槳距（Pitch )設為零，即無向前或向後之推力f 〇 2.水平前進或後退：尾旋翼14正的槳距愈大，所產生的 向前推力愈大’前進速度愈快；反之，負槳距愈大， 所產生的向後推大愈大，後退的速度便愈快。 3，巡航：飛行到達巡航的高度與速度後，圓盤12、13翼 剖面所產生的升力已可負擔機體大部份的重量，此時 ，主旋翼的轉速要逐漸減慢，該圓盤翼剖面與主旋翼 兩者所產生的合升力維持在一定值，使飛行器能維持 在一固定高度巡航。 4，固定翼模式起降：此時圓盤不轉動，其功能如同一般 固定翼機的機翼，飛行器飛行時所需之動力，由尾旋 真提供’在此模式下’兩用型飛行器的飛行方式與一 般固定翼機相同。 由以上說明可知，本發明所創作之兩用型飛行器在實402571 V. Description of the invention (5) 1. As shown in Figure 2, the two upper and lower layers of disks 12, 13 each extend two rotor blades 22 and 23 to form the main rotor. The two disks are separated by a small distance and do not touch each other. The upper plate 12 is connected to the inner shaft for forward rotation, and the lower plate 13 is connected to the outer shaft for reverse rotation. The upper and lower discs rotate at the same speed. In this way, the rotating moments ′ caused by the rotation of the two discs can just cancel each other. 2. The "double-layer disc plus rotor" device is connected to the fuselage through a ring frame (Gin) bal mechanism. Driven by the control link, the disc can be tilted vertically and horizontally to change The direction and attitude of the aircraft. 3. The rotor blades 22 and 23 'of the main rotor can be fixed on the disks 12, 13. The pitch of the rotor blades is fixed. The lift of the rotor blades 22 and 23 is determined by the engine speed. The lift is large. Conversely, the smaller the speed is, the larger the lift is. (3) Tail rotor mechanism 1_ The tilt mechanism of the tail rotor 14 is the same as the disks 12 and 13 and is connected to the fuselage through the ring mechanism. The control link drives the tail rotor surface to tilt in two dimensions. By changing the rotor direction, the purpose of changing the thrust direction can be achieved. 2 · tail ί 3 The speed of the cymbals is fixed, but the pitch is variable. R Control 'By controlling the change of the music pitch, the thrust of the tail wing 14 can be changed. The purple distance becomes larger and the distance becomes smaller. The thrust is reduced. ^ (4) Control surface mechanism. Pitch (P 1 tch). Control the disc by controlling the link vertically! 2. 402571 V. Description of the invention (6) 1 3 Doing a tilt in the back and forth direction will generate changes in pitch (pi tch) motion. 2. Roll (Rol 1): With the lateral control link, control the discs 12, 13 to do left and right. The direction is tilted, resulting in a change in roll (Roll) motion. 3. Yaw: Changing the direction angle of the vertical tail rudder will enable the aircraft to make a yaw action. (V) Control method 1. Vertical rise. Increase the main rotor speed to the speed required for take-off, so that the lift overcomes the weight of the fuselage and the driven body rises vertically. At this time, the pitch of the tail rotor 14 (Pitch) is set to zero, that is, no Forward or backward thrust f 〇2. Horizontal forward or backward: the larger the positive pitch of the tail rotor 14 is, the greater the forward thrust generated is, the faster the forward speed is; on the contrary, the larger the negative pitch is, the greater the The bigger you push it back, the faster you go back. 3. Cruise: After the flight reaches the cruise altitude and speed, the lift generated by the profile of the disks 12 and 13 can already bear most of the weight of the body. At this time, the rotation speed of the main rotor must be gradually slowed down. The combined lift generated by the profile and the main rotor is maintained at a certain value, so that the aircraft can maintain a cruise at a fixed altitude. 4. Take-off and landing in fixed-wing mode: At this time, the disk does not rotate, and its function is similar to that of a fixed-wing wing. The power required by the aircraft during flight is provided by the tail spin really 'in this mode' dual-use aircraft. The flight mode is the same as that of general fixed-wing aircraft. From the above description, it can be seen that the dual-purpose aircraft created by the present invention is practical.
第1〇頁 403571 —--------- _ 五、發明說明（7) ---- 際飛行上可選擇採用旋翼機模式進行昇降或選擇採用固定 翼=機模式進行昇降皆可，其選擇端視機場跑道之適當性 =定；但巡航時則係採固定翼機模式飛行為宜，如此其續 航力較佳。簡而言之，即本發明之兩用型飛行器丄空或 低^飛行時，採旋葉片22、23旋轉模式，由旋葉片面22 : 23提供升力；當高速飛行時，則採旋葉片22、23不轉，而 由申央圓盤12、13提供升力的模式， 一=發明係經發明人等實際進行理論分析及試驗證實可 仃才提出申請’在試驗階段中曾作紀整理如 釣局審查時能一併詳閱。 #驳，以上說明可知，本發、明之最大特徵在於飛行器之主 _ : 穴上、下圓盤及周圍的旋葉片共同組成，所以 起飛時’可令該等中央圓盤帶動旋葉片轉動，以提 圓 上昇至適當高度及適當速度後’可改採由中央 見諸成之固定翼飛行。而經查本項構造特徵完全不曾 姑ω昔時’亦不曾公開在申請前，當具備高度創作性及新 顆性；而在佶田, ' 賴而 1之用性方面，可令飛行器擺脫對機場跑道的依 仍保有固定翼飛機的巡航能力，所以實用性及 皆已深鈥真供， ' .....’爰請依法准予發明專利，實感德便。 附件：發明人& & v对對本發明所作理論分析及試驗之紀錄。Page 10 403571 ----------- _ V. Description of the invention (7) ---- On the flight, you can choose to use the rotorcraft mode to lift or choose to use the fixed-wing = machine mode to lift. , Its choice depends on the appropriateness of the airport runway = fixed; but when cruising, it is advisable to fly in fixed-wing aircraft mode, so its endurance is better. In short, that is, when the dual-purpose aircraft of the present invention is flying at low or low altitudes, the rotary blades 22, 23 are used for rotation mode, and the rotary blade surfaces 22: 23 provide lift; when flying at high speed, the rotary blades 22 are used. And 23 do not turn, and the lift is provided by Shenyang discs 12, 13. First = the invention is based on theoretical analysis and tests by the inventor, and it is confirmed that the application can be submitted. It can be read together during the examination. # Regarding the above description, it can be known that the biggest feature of this hair and the Ming is the master of the aircraft:: The upper and lower disks and the surrounding rotor blades are combined, so when taking off, 'the central disks can be used to drive the rotor blades to rotate. After raising the circle to a proper height and speed, the fixed-wing flight from the center can be used instead. According to the investigation, this structural feature has never been ω in the past, nor was it disclosed before the application, when it has a high degree of creativity and newness; in Putian, '' the application of Lai 1 can make the aircraft free of The runway of the airport still retains the cruising capability of fixed-wing aircraft, so its practicality and depth have been deeply provided. '.....' Please grant an invention patent in accordance with the law, which is a good sense. Attachment: The inventors & & v's theoretical analysis and test records of the invention.