WO2014032295A1 - 一种舰载机斜坡下滑起飞平台及应用航母和实现方法 - Google Patents

一种舰载机斜坡下滑起飞平台及应用航母和实现方法 Download PDF

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Publication number
WO2014032295A1
WO2014032295A1 PCT/CN2012/080891 CN2012080891W WO2014032295A1 WO 2014032295 A1 WO2014032295 A1 WO 2014032295A1 CN 2012080891 W CN2012080891 W CN 2012080891W WO 2014032295 A1 WO2014032295 A1 WO 2014032295A1
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Prior art keywords
carrier
aircraft
slope
bracket
tail
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PCT/CN2012/080891
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English (en)
French (fr)
Inventor
赵天烁
赵军
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Zhao Tianshuo
Zhao Jun
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Application filed by Zhao Tianshuo, Zhao Jun filed Critical Zhao Tianshuo
Priority to PCT/CN2012/080891 priority Critical patent/WO2014032295A1/zh
Publication of WO2014032295A1 publication Critical patent/WO2014032295A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G11/00—Aircraft carriers

Definitions

  • the invention relates to the field of naval weapons, in particular to an aircraft carrier accelerated take-off platform for an aircraft carrier.
  • the aircraft carrier adopting the skid-type take-off method and device has low requirements on the hull structure and equipment and the front landing gear strength of the carrier, it has a low barrier to entry, but the disadvantages are: 1
  • the carrier aircraft is required to have a higher thrust-to-weight ratio (the ratio of the engine's engine thrust to its own weight). 2
  • the aircraft carrier deck limits the length of the take-off runway, it limits the payload of the carrier aircraft, limits the range and ammunition of the carrier aircraft, and has weak combat capability.
  • the fixed-wing early warning aircraft with lower take-off weight becomes more difficult.
  • the object of the present invention is mainly to solve the technical shortcomings of the carrier-based aircraft adopting the skid-type take-off, and proposes a carrier-based ramp-down take-off platform and an application carrier and an implementation method thereof.
  • a carrier-based ramp-down takeoff platform which is characterized in that: a slope curved track is included, and the top end of the slope curved track is connected by a bracket carrier connection shaft.
  • a bracket carrier plate There is a bracket carrier plate, and a flip drive mechanism for the jacking carrier carrier plate to rotate with the bracket carrier plate connecting shaft as a fulcrum at the bottom of the bracket carrier plate, so that the bracket carrier plate is turned up and smoothly connected with the slope curved track;
  • a folded structure tail flame deflector that exerts a reaction thrust on the carrier aircraft; a lifting platform is provided at a rear end of the carrier carrier.
  • the slope top end of the slope-curved runway has a drop of 20 ⁇ 3 m at the bottom end of the slope.
  • the bracket carrier plate is embedded in a slot corresponding thereto when the water carrier is in a water state;
  • the flip drive mechanism is a carrier hydraulic ram group connected between the slot and the carrier carrier.
  • the front end of the tail flame deflector is provided with a suspension bracket, and the suspension bracket is provided with an elliptical shaft;
  • the bracket carrier has a guiding groove on both sides of the bottom, and the tail end of the guiding slot is connected with a circular slot, the suspension bracket
  • the upper elliptical shaft is placed in the guiding groove, and a driving tail flame deflector is pushed to the tail between the front end of the tail flame deflector and the bracket carrier plate, and the tail flame diversion is performed after the elliptical axis moves into the circular groove.
  • a set of flap hydraulic rods that are turned upside down at the end of the plate.
  • An aircraft carrier applying the take-off platform is characterized in that: a deck and a ship island disposed on the deck are included, and the bottom end of the slope curved runway smoothly transitions with the deck, and the slope top of the slope curved track is connected at the top On the island of the ship.
  • An aircraft carrier using the take-off platform is characterized in that: a deck and a front ship island body and a rear ship island body disposed on the deck are included, and the bottom end of the slope curved runway smoothly transitions with the deck, and the slope surface The top of the slope of the runway is connected to the front ship island; the front ship island includes driving, command and weather cabins; the rear ship island is provided with a radar antenna and a chimney for the conventional power engine of the aircraft carrier.
  • a method for realizing accelerated takeoff of a carrier aircraft using the takeoff platform characterized in that the method comprises the following steps:
  • the flip drive mechanism drives the support carrier plate to be flipped so as to smoothly mate with the slope curved track;
  • the tail flame deflector exits backwards and flips upwards to block the tail gas flow of the carrier aircraft after the carrier aircraft is turned on, and applies a reaction thrust to the carrier aircraft;
  • the tail-hook of the carrier-type aircraft is released by the firing type carrier-end hook fixing device, and the carrier-based aircraft takes off along the slope curved surface runway in a ramping manner.
  • the takeoff platform of the present invention is equally applicable to amphibious assault ships or helicopter carriers of straight-through decks.
  • the beneficial effects of the invention are: 1 Using the carrier's own gravity and the gradient of the slope surface, the carrier aircraft increases the acceleration of gravity on the basis of the acceleration of its own engine thrust during the take-off process, achieving fuel saving, shortening the takeoff distance, increasing the load, and increasing the combat radius. And the purpose of combat power is superior to the existing take-off mode in the cost-effectiveness ratio of daily operations; 2 Indirectly increases the length of the runway on the aircraft carrier and the internal space under the deck of the aircraft carrier.
  • the space on the top and the front of the ship island can be effectively utilized, and the runway of the plane is extended to the space, thereby eliminating the limitation of the length of the runway body on the runway length, and the slope surface
  • the underside of the runway becomes a closed space that can be utilized, reducing the volume of the island and the radar reflection area; 3.
  • the catapult take-off aircraft carrier it saves about 500 cubic meters under the deck of a catapult and other devices.
  • the huge space reduces the weight of the aircraft carrier and increases the payload, avoiding the huge overload of the carrier aircraft pilot during the ejection process.
  • the invention is an auxiliary method, so that the carrier aircraft can have multiple take-off modes for flexible selection at the same time, which is beneficial to improving the wartime resistance to war damage.
  • Existing carrier aircraft application The invention does not need to be modified, which reduces the difficulty of technical implementation. 6 Overcoming the problem of overlap between the take-off runway and the landing runway of the original port side, that is, when the take-off runway with the ship-borne aircraft landing on the port side is closed, the runway of the device can still be used normally, which solves the bottleneck of the aircraft carrier's take-off and landing overlap. The problem has increased the efficiency of shipboard aircraft take-off and landing. 7.
  • the device has a simple structure, and the existing aircraft carrier can be implemented by modification.
  • Figure 1 is a reference diagram A of the use state of the take-off platform of the invention.
  • Figure 2 is a reference diagram B of the use state of the takeoff platform of the invention.
  • FIG. 3 is a reference diagram C of the use state of the takeoff platform of the invention.
  • Figure 4 is a reference diagram D of the use state of the take-off platform of the invention.
  • Figure 5 is a schematic perspective view of the take-off platform of the invention.
  • Figure 6 is a schematic left side view of the takeoff platform of the invention.
  • FIG. 8 is a working principle diagram of the invention.
  • Figure 9 is a view showing the working state of the tail flame deflector of the present invention.
  • Figure 10 is a working state diagram of the tail flame deflector of the present invention b;
  • Figure 11 is a working state diagram of the tail flame deflector of the present invention c;
  • Figure 12 is a perspective view showing the three-dimensional structure of the single-ship tower aircraft carrier
  • Figure 13 is a front view of Figure 12;
  • Figure 14 is a schematic perspective view showing the structure of the double-ship tower aircraft carrier
  • Figure 15 is a comparison table of theoretical data of the present invention.
  • Figure 16 is a schematic view showing the structure of the amphibious assault ship or helicopter carrier of the take-off platform of the present invention applied to a straight-through deck. .
  • the overall structure of a carrier-based ramp-down take-off platform proposed by the present invention includes a sloped curved runway 18, a bracket carrier plate 3 is connected to the top of the slope of the slope surface runway 18, and the bottom of the bracket carrier plate 3 is provided with a flip drive mechanism 9 on which the tail carrier fixing device of the launching type carrier is provided.
  • the bracket carrier plate 3 is also connected with a folded structure tail flame deflector 10 for blocking the tail gas flow of the carrier aircraft 1 and exerting a reaction thrust on the carrier aircraft 1; and a lifting platform at the rear end of the carrier carrier plate 3 2 .
  • the carrier aircraft 1 is glided to a predetermined position on the lifting platform 2, and the lifting platform 2 is a carrier carrier 1 As shown in FIG. 2, the carrier platform 1 is lifted by the lifting platform 2 to a uniform height of the carrier carrier 3 in a horizontal state; as shown in FIG. 3, the carrier aircraft 1 to the carrier are further moved.
  • the carrier aircraft 1 puts down the carrier tail hook 5 for the original landing, and the carrier tail hook 5 hooks the bracket carrier 3 to raise the tail-type tail hook fixing device 6 to make the carrier aircraft 1
  • the flip drive mechanism at the bottom of the starter carrier 3 the flip drive mechanism 9 drive the carrier carrier 3 end up, so that the carrier carrier 3 and the sloped runway
  • the top slope of 18 is the same, that is, the bracket carrier 3 and the slope curved track 18 are smooth and overslept.
  • the horizontal angle of the bracket carrier 3 can be about 36 degrees, and thereafter, from the bracket carrier 3
  • the bottom surface of the tail flame deflector 10 is lifted upward and parallel to the predetermined position, and the tail end of the tail flame deflector 10 is lifted upward, forming a 75-85 with the carrier carrier 3
  • the firing tail hook fixing device 6 releases the carrier tail hook 5, and the carrier aircraft 1 is out of steady state, the carrier aircraft 1 Under the action of the gravity generated by its own weight and the engine thrust, the carriage carrier 3 starts to slid toward the slope surface runway 18, and accelerates, and at the same time, the carrier tail hook 5 is taken up, when the carrier aircraft 1 Fly off the ship when it reaches the takeoff speed.
  • the slope top end and the bottom end of the slope curved track 18 have a drop of 20 ⁇ 3 m.
  • Bracket carrier 3 Connect the shaft through the bracket carrier 4 Active connection, bracket carrier connection shaft 4 As the support carrier 3
  • the step of moving to the support carrier 3 does not form a step to facilitate the movement of the carrier 1; the reverse drive mechanism 9 is connected to the slot 31 and the carrier carrier 3
  • the inter-board hydraulic ram group is also composed of a plurality of hydraulic rods side by side.
  • the specific structure of the tail flame deflector 10 and the support carrier 3 is: the surface of the tail flame deflector 10 is made of high temperature resistant material, and the tail flame deflector 10
  • the front side is provided with a suspension bracket 101, and the suspension bracket 101 is provided with an elliptical shaft 102;
  • the bracket carrier plate 3 has guide grooves 14 at both sides of the bottom, and the rear end of the guide groove 14 is connected with a circular groove.
  • the elliptical shaft 102 on the suspension bracket 101 is placed in the guiding groove 14 , and the tail flame deflector 10 is provided between the front end of the tail flame baffle 10 and the bracket carrier 3 10 to the tail and the bracket carrier 3
  • a set of flap hydraulic rods 12 propelled in parallel the flap hydraulic rod 12 is connected to the front end of the tail flame deflector 10 by connecting the guide shaft 11 , the flap hydraulic rod 12 is lifted, and the tail flame deflector 10 Exiting backward (to the right in Figure 10), and during the exit process, the tail flame deflector 10 remains parallel to the carriage carrier 3, and the exiting process ellipse shaft 102 moves synchronously backwards in the guide slot 14 as the elliptical axis 102 After moving into the circular slot 16, the elliptical axis 102 can be flipped.
  • the flap hydraulic rod 12 continues to rise, the elliptical axis 102 Restricted, stop and retreat, the tail flame deflector 10 is flipped with the elliptical axis 102 as the fulcrum, and the tail end of the tail flame deflector 10 is turned upside down to block the rear side of the tailgate of the carrier engine.
  • the bottom of the carrier carrier plate 3 is also provided with a sliding groove 103 matching the connecting guide shaft 11 and the sliding groove 103
  • the tail end is also provided with a slot notch 17 for the connecting guide shaft 11 to slide out when the tail flame deflector 10 is turned over.
  • the aircraft carrier using the above-described carrier-slope ramp-down take-off platform includes a deck 7 and is located on the deck 7
  • the upper part of the ship's island 8 and the sloped surface runway 18 have a smooth transition from the bottom of the deck to the deck.
  • the direction is aligned with the starboard runway on the aircraft carrier and aligned with the midline and connected to the starboard runway to form a complete runway.
  • the engine thrust continues to accelerate along with the aircraft carrier's runway, reaching the takeoff speed and then flying away from the ship.
  • the aircraft carrier ship can be upturned and slippery.
  • the aircraft carrier ship can also be horizontal;
  • the top of the slope of 18 is connected to the island 8 and the above-mentioned carrier-slope slope-off landing platform is integrated with the ship island 8 as a whole island.
  • Ship Island 8 retains the function of the island, such as the island 8 It consists of multiple compartments for driving, commanding, landing, etc., and various antenna bases and chimneys that protrude upward from the right side.
  • nuclear power can be used to omit the chimney to reduce volume, ship island 8 and slope.
  • Curved runway 18 The upper cross-shaped connection, the left and right are suspended, the width of the right side is larger than the left side, and the width of the antenna frame, the chimney and the like from the slope surface runway 18 depends on the span of the carrier aircraft.
  • the carrier aircraft referred to in the present invention 1 It can be a carrier-based fighter or a ship-borne early warning aircraft 1', or a ship-borne fixed-wing aircraft such as a carrier-based tanker.
  • the above-mentioned ramp-down takeoff platform is installed at the appropriate position on the starboard side of deck 7, with the front end being 110 meters from the bow and the sloped curved runway 18 being 20 meters high. It can also retain the original skid take-off runway and installation.
  • the carrier aircraft 1 does not affect the island when taking off.
  • the antenna works on the present embodiment.
  • the present embodiment can also divide the ship island body of the existing aircraft carrier into two for the former ship island 8 and the rear ship island 8'.
  • the former ship island 8 is placed on the aircraft carrier deck 7
  • the starboard side is mainly integrated with the aforementioned flight platform, double or multi-layer driving, command and weather cabins and some equipment antennas; It is placed behind the starboard side of the aircraft carrier. It is mainly composed of the control room where the carrier aircraft landed, various radar antennas and the chimney required for the aircraft carrier's conventional power engine. (If nuclear power is used, the device can be omitted to reduce the volume) It is the highest part of the aircraft carrier and the need for the field of view of electronic detection equipment such as radar.
  • the takeoff platform of the present invention can also be applied to an amphibious assault ship or helicopter carrier of a straight-through deck.
  • the carrier aircraft 1 can also be based on the carrier aircraft 1
  • the thrust determines when the force is applied (the engine is running at full capacity), ie in this process it can be based on the carrier aircraft 1
  • the ratio of thrust-to-weight ratio ie, the ratio of thrust to its own weight plus its own load determines when to apply full force, and there are multiple power configuration options. In this example, three options are listed: Figure 8 and Figure 15 The segmentation diagram and table in the figure are shown.
  • the first is that when the carrier aircraft 1 begins to disengage from the firing-type carrier tail hook fixture 6, the first segment shown in Figure 8 is fully energized; the second is in the middle section of the slope-curved runway 18 The second section shown in Figure 8 is fully energized; the third is at the end of the sloped surface runway 18, and the third section shown in Figure 8 is fully energized.
  • the above power configuration scheme can make the carrier of the corresponding thrust smoothly off the ship. take off.
  • the acceleration effect achieved by the present invention such as the theoretical data comparison chart 15
  • the load-carrying ratio of the carrier-based machine 1 with different thrust-to-weight ratios increases by about 25/km/h
  • the acceleration effect is inversely proportional to the thrust-to-weight ratio of the carrier-based engine. by In several cases, from 1.15 to 0.6, it is equivalent to extending the runway by 35-55 meters.
  • the carrier aircraft When the load of the carrier aircraft engine is relatively high, the carrier aircraft can be glided to the slope surface runway 18 At the bottom end, that is, before the connection with the deck, the minimum power can be achieved, and 23m / s, that is, about 83km / h can be achieved. Speed, then re-energize until the ship takes off to save fuel, which will save a lot of cost in daily high-density carrier-based aircraft take-off and landing training.

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Abstract

一种舰载机斜坡下滑起飞平台及应用航母和实现方法，涉及海军武器领域，解决舰载机釆用滑跃式起飞存在技术不足，包括有一条斜坡曲面跑道，在斜坡曲面跑道的坡顶端连接有支架载板，在支架载板的底部设有翻转驱动机构；在支架载板上设有在舰载机起跑前用于与舰载机的尾钩配合钩挂的击发式舰载机尾钩固定装置；所述的支架载板还连接有升降平台。利用舰载机自身重力和斜坡曲面跑道落差，使舰载机在起飞过程中在自身发动机推力的加速基础上又增加了重力加速，达到了节省燃料、缩短起飞距离、增加载荷、提高作战半径和作战力的目的，在日常运营的效费比上，优于已有起飞方式。

Description

一种舰载机斜坡下滑起飞平台及应用航母和实现方法
技术领域
本发明涉及海军武器领域，尤其是涉及一种航空母舰的舰载机加速起飞平台。
背景技术
目前，公知的航空母舰上，固定翼舰载机起飞方式主要有两种：一种是采用蒸汽弹射装置使固定翼舰载机从甲板上起飞的弹射起飞方式，对舰载机自身的推重比要求不高且具有很高的效率。缺点是： 1 、效费比高， 2 、制造难度大， 3 、体积巨大占用甲板下有限的空间， 4 、对舰载机结构尤其是前起落架强度要求高；另一种是采用滑跃式起飞方式，即通过加强舰载机自身动力实现起飞阶段的加速度，这种方式需要在航母甲板前部舰艏位置设置 10 ～ 15 度 向上翘起的滑翘来增加升力，同时，在舰载机起飞过程中，需要航母以约 50km/h 的速度迎风航行，来达到增速的目的。虽然采用滑跃式起飞方式和装置的航母对舰体结构和设备及舰载机前起落架强度要求不高，具有较低的准入门槛，但缺点是： 1 、要求舰载机要有较高的推重比（舰载机发动机推力和自身重量之比）。 2 、由于航母甲板限制了起飞跑道的长度，制约了舰载机的有效载荷，限制了舰载机的航程和弹药数量，作战力弱，起飞推重比较低的固定翼预警机变得更加困难。
发明内容
本发明的目的主要在于解决舰载机采用滑跃式起飞存在技术不足，而提出一种舰载机斜坡下滑起飞平台及应用航母和实现方法。
为解决本发明提出的技术问题，采用的技术方案为：一种舰载机斜坡下滑起飞平台，其特征在于：包括有一条斜坡曲面跑道，在斜坡曲面跑道的坡顶端通过支架载板连接轴连接有支架载板，在支架载板的底部设有用于顶升支架载板以支架载板连接轴为支点旋转，使支架载板翻起与斜坡曲面跑道平滑对接的翻转驱动机构；在支架载板上设有在舰载机起跑前用于与舰载机的尾钩配合钩挂的击发式舰载机尾钩固定装置；所述的支架载板还连接有用于阻挡舰载机尾焰气流，对舰载机施加反作用推力的折叠结构尾焰导流板；在支架载板后端位置设有升降平台。
所述的斜坡曲面跑道的坡顶端与坡底端落差为 20 ± 3m 。
所述的支架载板处于水状态时嵌入在一个与其吻合的板槽内；所述的翻转驱动机构为连接在板槽与支架载板间的载板液压顶杆组。
所述的尾焰导流板正面上设有悬挂支架，悬挂支架上设有椭圆轴；所述的支架载板底部两侧设有导向槽，导向槽的尾端连接有圆形槽，悬挂支架上的椭圆轴置于导向槽中，在尾焰导流板的前端与支架载板之间设有驱动尾焰导流板向尾部推进，当椭圆轴移入圆形槽中之后，尾焰导流板尾端向上翻转的一组翻板液压杆。
一种应用所述起飞平台的航空母舰，其特征在于：包括有甲板和设于甲板上的舰岛体，所述的斜坡曲面跑道的坡底端与甲板平滑过渡，斜坡曲面跑道的坡顶端连接在舰岛体上。
一种应用所述起飞平台的航空母舰，其特征在于：包括有甲板和设于甲板上的前舰岛体和后舰岛体，所述的斜坡曲面跑道的坡底端与甲板平滑过渡，斜坡曲面跑道的坡顶端连接在前舰岛体上；所述的前舰岛体上包含有驾驶、指挥及气象舱室；所述的后舰岛体设有雷达天线及航母常规动力发动机所需的烟筒。
一种应用所述起飞平台的实现舰载机加速起飞的方法，其特征在于所述方法包括有如下步骤：
1 ）、通过升降平台将舰载机升起后移动到支架载板上；
2 ）、在舰载机的尾钩与击发式舰载机尾钩固定装置钩挂后，翻转驱动机构驱动支架载板翻转，使之与斜坡曲面跑道平滑对接；
3 ）、尾焰导流板向后退出，并向上翻转，在舰载机开机后阻挡舰载机尾焰气流，对舰载机施加反作用推力；
4 ）、在舰载机发动机推力满足起飞条件后，击发式舰载机尾钩固定装置释放舰载机的尾钩，舰载机沿斜坡曲面跑道以斜坡下滑方式起飞。
本发明的起飞平台同样适用于直通式甲板的两栖攻击舰或直升机航母。
本发明的有益效果是： 1 、利用舰载机自身重力和斜坡曲面跑道落差，使舰载机在起飞过程中在自身发动机推力的加速基础上又增加了重力加速，达到了节省燃料、缩短起飞距离、增加载荷、提高作战半径和作战力的目的，在日常运营的效费比上，优于已有起飞方式； 2 、间接增加了航空母舰上的跑道的长度和航空母舰甲板下的内部空间。将本发明提出的起飞平台和航空母舰舰岛集成为一体，可有效地利用舰岛体顶部及前部的空间，把平面的跑道向空间延展，消除了舰岛体对跑道长度的限制，斜坡曲面跑道下方变成了一个可以利用的封闭空间，减小了舰岛体的体积和雷达反射面积； 3 、和弹射起飞航空母舰相比，省出了一条弹射器等装置所占甲板下约 500 立方米 的巨大空间，减轻了航空母舰自身重量，提高了有效载荷，避免了舰载机飞行员在弹射过程中所承受巨大的过载。 4 、本发明型作为一种辅助方式，使舰载机可同时拥有多种起飞方式供灵活选择，利于提高战时抗战损能力。 5 、现有舰载机应用本发明不用做任何改装，降低了技术实现难度。 6 、克服了原有左舷的起飞跑道和降落跑道重叠的问题，即在有舰载机降落左舷的起飞跑道封闭时，所述装置的跑道仍可正常使用，解决了舰载机起降重叠的瓶颈问题，增加了舰载机起降效率。 7 、所述装置结构简单，现有航空母舰可通过改装即可实施。
附图说明
图 1 为发明的起飞平台使用状态参考图Ａ；
图 2 为发明的起飞平台使用状态参考图Ｂ；
图 3 为发明的起飞平台使用状态参考图Ｃ；
图 4 为发明的起飞平台使用状态参考图Ｄ；
图 5 为发明的起飞平台的立体结构示意图；
图６为发明的起飞平台的左视结构示意图；
图 7 为发明的起飞平台的俯视结构示意图；
图 8 为发明的工作原理图；
图９为本发明的尾焰导流板工作状态图 a ；
图 10 为本发明的尾焰导流板工作状态图 b ；
图 11 为本发明的尾焰导流板工作状态图 c ；
图 12 为本发明为单舰塔航空母舰时的立体结构示意图；
图 13 为图 12 的主视图；
图 14 为本发明为双舰塔航空母舰时的立体结构示意图；
图 15 为本发明的理论数据对比表；
图 16 为本发明的起飞平台应用于直通式甲板的两栖攻击舰或直升机航母时的结构示意图。。
具体实施方式
以下结合附图和本发明优选的具体实施例，对本发明的结构作进一步地说明。
参照图 1 ～ 11 中所示，本发明提出的一种舰载机斜坡下滑起飞平台的整体结构包括有一条斜坡曲面跑道 18 ，在斜坡曲面跑道 18 的坡顶端连接有支架载板 3 ，支架载板 3 的底部设有翻转驱动机构 9 ，在支架载板 3 上设有在击发式舰载机尾钩固定装置 6 ，支架载板 3 还连接有用于阻挡舰载机 1 尾焰气流，对舰载机 1 施加反作用推力的折叠结构尾焰导流板 10 ；在支架载板 3 后端位置设有升降平台 2 。
本发明的舰载机斜坡下滑起飞平台的工作过程如下：
如图１中所示，舰载机 1 滑行至升降平台 2 上的规定位置，升降平台 2 是一个运载舰载机 1 的升降电梯；如图２中所示，由升降平台 2 将舰载机 1 提升至处于水平状态的支架载板 3 一致的高度；如图３中所示，再移动舰载机 1 至支架载板 3 上的规定位置，舰载机 1 放下原降落用的舰载机尾钩 5 ，舰载机尾钩 5 钩住支架载板 3 上面处于升起状态的击发式尾钩固定装置 6 使舰载机 1 处于稳定状态；如图 4 中所示，启动支架载板 3 底部的翻转驱动机构 9 ，翻转驱动机构 9 驱动支架载板 3 尾端向上跷起，使得支架载板 3 与斜坡曲面跑道 18 的顶端斜度一致，也即是支架载板 3 与斜坡曲面跑道 18 平滑过滑，在具体实施过程中，支架载板 3 的水平夹角可为 36 左右度，此后，从支架载板 3 的底面平行向后移出尾焰导流板 10 至规定位置，尾焰导流板 10 尾端向上跷起，与支架载板 3 形成 75 ～ 85 度的夹角，遮挡住舰载机发动机尾喷口，舰载机 1 开机，尾焰导流板 10 阻挡舰载机 1 尾焰气流，起到导流的作用，同时还可以对舰载机 1 施加反作用推力。当满足起飞条件时，击发式尾钩固定装置 6 释放舰载机尾钩 5 ，舰载机 1 脱离稳定状态，舰载机 1 在自身重量所产生的重力和发动机推力的作用下，由支架载板 3 向斜坡曲面跑道 18 方向开始滑跑，并实现加速，同时收起舰载机尾钩 5 ，当舰载机 1 达到起飞速度时离舰飞行。
本发明提出的舰载机斜坡下滑起飞平台的各部件具体结构如下：
图 1 及图９至图 13 中所示，斜坡曲面跑道 18 的坡顶端与坡底端落差为 20 ± 3m 。支架载板 3 通过支架载板连接轴 4 活动连接，支架载板连接轴 4 作为支架载板 3 尾端上向翻转时的支点，保证支架载板 3 能翻起与斜坡曲面跑道 18 平滑对接，支架载板 3 处于水状态时嵌入在一个与其吻合的板槽 31 内，支架载板 3 置于板槽 31 内时，支架载板 3 处于水平状态，舰载机 1 从升降平台 2 移动至支架载板 3 的行程中不会形成台阶，方便舰载机 1 的移动；所述的翻转驱动机构 9 为连接在板槽 31 与支架载板 3 间的载板液压顶杆组，也即是由多根液压杆并排构成。
而尾焰导流板 10 与支架载板 3 的具体结构为：尾焰导流板 10 表面由耐高温材料制成，尾焰导流板 10 正面上设有悬挂支架 101 ，悬挂支架 101 上设有椭圆轴 102 ；所述的支架载板 3 底部两侧设有导向槽 14 ，导向槽 14 的尾端连接有圆形槽 16 ，悬挂支架 101 上的椭圆轴 102 置于导向槽 14 中，在尾焰导流板 10 的前端与支架载板 3 之间设有驱动尾焰导流板 10 向尾部与支架载板 3 平行推进的一组翻板液压杆 12 ，翻板液压杆 12 通过连接导向轴 11 与尾焰导流板 10 的前端活动连接，翻板液压杆 12 顶升，尾焰导流板 10 向后（图 10 中的右侧）退出，且退出过程中，尾焰导流板 10 保持与支架载板 3 相平行，退出过程椭圆轴 102 在导向槽 14 中同步向后移动，当椭圆轴 102 移至圆形槽 16 中之后，椭圆轴 102 可作翻转活动，在椭圆轴 102 移至圆形槽 16 中之后，翻板液压杆 12 继续顶升，椭圆轴 102 受限，停止后退，尾焰导流板 10 则以椭圆轴 102 为支点翻转，则尾焰导流板 10 尾端向上翻转跷起，遮挡在舰载机发动机尾喷口后侧位置。为了提升尾焰导流板 10 向后退出稳定性，能稳定保护与支架载板 3 相平行状态退出，支架载板 3 底部两侧还设有与连接导向轴 11 配合的滑槽 103 ，滑槽 103 的尾端还设有在尾焰导流板 10 翻转时供连接导向轴 11 滑出的滑槽缺口 17 。
参照图 12 和图 13 中所示，应用有上述舰载机斜坡下滑起飞平台的航空母舰，括有甲板 7 和设于甲板 7 上的舰岛体 8 ，斜坡曲面跑道 18 的坡底端与甲板 7 平滑过渡，方向和航空母舰上的右舷跑道一致，并与中线对齐，并和右舷跑道连接成一个完整的跑道，舰载机 1 实现由支架载板 3 到斜坡曲面跑道 18 底端的加速，到达斜坡曲面跑道 18 底端与甲板 7 衔接处后，再由发动机推力沿着与航空母舰舰艏跑道继续加速，达到起飞速度后离舰飞起。航空母舰舰艏可以是上翘的滑翘，如果航母上有弹射起飞装置，航空母舰舰艏也可以是水平的；斜坡曲面跑道 18 的坡顶端连接在舰岛体 8 上，上述舰载机斜坡下滑起飞平台与舰岛体 8 集成为一个整体的舰岛。舰岛体 8 保留已有舰岛功能，如舰岛体 8 包括多层的驾驶、指挥、降落等各种舱室和右侧向上突起的各种天线机座和烟筒等组成，如采用核动力可省略烟筒这一装置以减小体积，舰岛体 8 和斜坡曲面跑道 18 上部十字交叉状连接，左右是悬空的，右侧伸出的宽度大于左侧，天线机座、烟筒等距离斜坡曲面跑道 18 的宽度因舰载机的翼展而定。本发明所称的舰载机 1 可以是舰载战斗机，也可以是舰载预警机 1' ，或舰载空中加油机等舰载固定翼飞机。
以排水量约为 6 万吨的常规动力滑跃式起飞的航空母舰为例，吃水深度约为 10 米 ，甲板 7 的长度约为 305 米 ，宽约为 78 米 。上述斜坡下滑起飞平台安装在甲板 7 的右舷适当的位置上，最前端距舰艏 110 米 ，斜坡曲面跑道 18 高度为 20 米 ，还可保留原有滑跃起飞跑道及装置。
参照图 14 中所示，为了舰载机 1 在起飞时不影响舰岛体 8 上的天线工作，本实施方案：还可以将现有航空母舰的舰岛体一分为二为前舰岛体 8 和后舰岛体 8' 。其中前舰岛体 8 置于航空母舰甲板 7 的右舷中部，主要集成有前述的飞行平台、双层或多层的驾驶、指挥及气象舱室和部分设备天线等；后舰岛体 8' 置于航空母舰的右舷后方，主要是由舰载机降落的控制室、多种雷达天线及航母常规动力发动机所需的烟筒等组成（如采用核动力可省略烟筒这一装置以减小体积），是航空母舰的最高部分，也是雷达等电子侦测设备视野的需要。
参照图 16 中所示，本发明的起飞平台还可以应用于直通式甲板的两栖攻击舰或直升机航母。
如图 8 和图 15 所示，在舰载机 1 滑跑起飞初期，也可以根据舰载机 1 推力决定何时开加力（发动机满负荷运行），即在此过程可根据舰载机 1 的推重比（即推力和自身重量加自身载荷之比）大小决定何时开全加力，可以有多种动力配置方案，本例列举三种方案：如图 8 和图 15 中的分段图和表格所示。第一种是在舰载机 1 开始脱离击发式舰载机尾钩固定装置 6 的同时，图 8 所示的第一段开全加力；第二种是在斜坡曲面跑道 18 中段，图 8 所示的第二段开全加力；第三种是在斜坡曲面跑道 18 末端，图 8 中所示的第三段开全加力，上述动力配置方案均可使相应推力的舰载机实现顺利离舰起飞。
根据牛顿第二定律原理和相关数学公式计算，本发明所达到的加速效果，如理论数据对比表图 15 所示，在跑道水平长度相同的情况下，不同推重比的舰载机 1 全程开加力，速度平均增加约 25/km/h ，加速效果和舰载机 1 发动机推重比成反比，推重比由 1.15 到 0.6 等几种情况下，相当于把跑道延长了 35-55米。舰载机发动机推重比较高时，舰载机可以在滑行至 斜坡曲面跑道 18 底端即和甲板连接处前，保持最低功率的着车状态，就可实现 23m /s 即约 83km/h 速度，然后再开全加力直至离舰起飞，以达到节省燃料的目的，这一点在日常高密度的舰载机起降训练时会节省大量的成本。

Claims (7)

  1. 一种舰载机斜坡下滑起飞平台，其特征在于：包括有一条斜坡曲面跑道（18），在斜坡曲面跑道（18）的坡顶端通过支架载板连接轴（4）连接有支架载板（3），在支架载板（3）的底部设有用于顶升支架载板（3）以支架载板连接轴（4）为支点旋转，使支架载板（3）翻起与斜坡曲面跑道（18）平滑对接的翻转驱动机构（9）；在支架载板（3）上设有在舰载机（1）起跑前用于与舰载机尾钩（5）配合钩挂的击发式舰载机尾钩固定装置（6）；所述的支架载板（3）还连接有用于阻挡舰载机（1）尾焰气流，对舰载机（1）施加反作用推力的折叠结构尾焰导流板（10）；在支架载板（3）后端位置设有供舰载机升降的升降平台（2）。
  2. 根据权利要求１所述的一种舰载机斜坡下滑起飞平台，其特征在于：所述的斜坡曲面跑道（18）的坡顶端与坡底端落差为20±3m。
  3. 根据权利要求１所述的一种舰载机斜坡下滑起飞平台，其特征在于：所述的支架载板（3）处于水状态时嵌入在一个与其吻合的板槽（31）内；所述的翻转驱动机构（9）为连接在板槽（31）与支架载板（3）间的载板液压顶杆组。
  4. 根据权利要求１所述的一种舰载机斜坡下滑起飞平台，其特征在于：所述的尾焰导流板（10）正面上设有悬挂支架（101），悬挂支架（101）上设有椭圆轴（102）；所述的支架载板（3）底部两侧设有导向槽（14），导向槽（14）的尾端连接有圆形槽（16），悬挂支架（101）上的椭圆轴（102）置于导向槽（14）中，在尾焰导流板（10）的前端与支架载板（3）之间设有驱动尾焰导流板（10）向尾部推进，当椭圆轴（102）移入圆形槽（16）中之后，尾焰导流板（10）尾端向上翻转的一组翻板液压杆（12）。
  5. 一种应用权利要求１～４任一项所述起飞平台的航空母舰，其特征在于：包括有甲板（7）和设于甲板（7）上的舰岛体（8），所述的斜坡曲面跑道（18）的坡底端与甲板（7）平滑过渡，斜坡曲面跑道（18）的坡顶端连接在舰岛体（8）上。
  6. 一种应用权利要求１～４任一项所述起飞平台的航空母舰，其特征在于：包括有甲板（7）和设于甲板（7）上的前舰岛体（8）和后舰岛体（8’），所述的斜坡曲面跑道（18）的坡底端与甲板（7）平滑过渡，斜坡曲面跑道（18）的坡顶端连接在前舰岛体（8）上；所述的前舰岛体（8）上包含有驾驶、指挥及气象舱室；所述的后舰岛体（8’）设有雷达天线及航母常规动力发动机所需的烟筒。
  7. 一种应用权利要求１～４任一项所述起飞平台的实现舰载机加速起飞的方法，其特征在于所述方法包括有如下步骤：
    1）、通过升降平台（2）将舰载机（1）升起后移动到支架载板（3）上；
    2）、在舰载机（1）的尾钩（5）与击发式舰载机尾钩固定装置（6）钩挂后，翻转驱动机构（9）驱动支架载板（3）翻转，使之与斜坡曲面跑道（18）平滑对接；
    3）、尾焰导流板（10）向后退出，并向上翻转，在舰载机（1）开机后阻挡舰载机（1）尾焰气流，对舰载机（1）施加反作用推力；
    4）、在舰载机（1）发动机推力满足起飞条件后，击发式舰载机尾钩固定装置（6）释放舰载机（1）的尾钩（5），舰载机（1）沿斜坡曲面跑道（18）以斜坡下滑方式起飞。
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CN110616610A (zh) * 2019-09-12 2019-12-27 青岛度丘新能源技术有限公司 一种陆地飞行平台
CN112158357A (zh) * 2020-08-28 2021-01-01 成都飞机工业（集团）有限责任公司 一种无人机助推火箭推力线与重心偏差测量装置及方法
CN112158357B (zh) * 2020-08-28 2021-08-03 成都飞机工业（集团）有限责任公司 一种无人机助推火箭推力线与重心偏差测量装置及方法
CN113386969A (zh) * 2021-07-13 2021-09-14 大连大学 一种航母舰载机起飞复合式跑道
CN114087069A (zh) * 2021-11-19 2022-02-25 中国航发沈阳发动机研究所 一种规避发动机进口温度畸变的导流装置
CN114087069B (zh) * 2021-11-19 2023-02-28 中国航发沈阳发动机研究所 一种规避发动机进口温度畸变的导流装置

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