CN204507270U - Novel high lift joined wing configuration aircraft - Google Patents
Novel high lift joined wing configuration aircraft Download PDFInfo
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Abstract
本实用新型公开了一种新型高升力联接翼布局飞行器，该飞行器包括：机身、设置在机身两侧的主翼、上翼、端翼、垂尾，所述设置在机身两侧的主翼的端部均设置端翼，所述两个端翼的上部分别通过设置在机身上方的上翼与设置在机身尾部的垂尾连接；所述机身的机头两侧设置有鸭翼；所述端翼的外侧均设置有外翼。本实用新型的外翼能够增加全机的有效升力面积，提高了飞行器的低速性能和横向安定性，增大了飞行器的升力系数及升阻比，降低了油耗，减少了飞行器的使用成本。
The utility model discloses a novel high-lift connected wing layout aircraft. The aircraft comprises: a fuselage, main wings arranged on both sides of the fuselage, an upper wing, an end wing, and a vertical tail; End wings are provided at the ends of the fuselage, and the upper parts of the two end wings are respectively connected with the vertical tail arranged at the tail of the fuselage through the upper wing arranged above the fuselage; the two sides of the nose of the fuselage are provided with canards ; The outer sides of the end wings are provided with outer wings. The outer wing of the utility model can increase the effective lift area of the whole aircraft, improve the low-speed performance and lateral stability of the aircraft, increase the lift coefficient and lift-to-drag ratio of the aircraft, reduce fuel consumption, and reduce the use cost of the aircraft.
Description
技术领域technical field
本实用新型属于飞行器设计领域，具体涉及一种新型高升力联接翼布局飞行器。The utility model belongs to the field of aircraft design, and in particular relates to a novel high-lift aircraft with a joint wing layout.
背景技术Background technique
随着电子科技、复合材料和机械加工等技术的进步，联接翼布局飞行器的研究得到了快速的发展，联接翼布局飞行器与常规布局飞行器相比具有明显的优势：强度大、重量轻、诱导阻力小、升阻比高、良好的稳定性和操纵性以及优良的机动性能，因此联接翼布局具有很高的应用价值和经济效益。With the advancement of electronic technology, composite materials and mechanical processing, the research on joint-wing layout aircraft has developed rapidly. Compared with conventional layout aircraft, joint-wing layout aircraft has obvious advantages: high strength, light weight, and induced resistance. Small size, high lift-to-drag ratio, good stability and maneuverability, and excellent maneuverability, so the joint wing layout has high application value and economic benefits.
联接翼布局飞行器在执行某些飞行任务时需要良好的低速性能，例如：农药播撒、航空测绘以及观光旅游等；一般的联接翼布局飞行器由于有效升力面大小的限制，导致其低速特性不能得到最佳的发挥。The joint-wing layout aircraft needs good low-speed performance when performing certain flight tasks, such as: pesticide spreading, aerial surveying and mapping, and sightseeing; the general joint-wing layout aircraft cannot obtain the best low-speed performance due to the limitation of the effective lift surface size. good play.
实用新型内容Utility model content
有鉴于此，本实用新型的主要目的在于提供一种新型高升力联接翼布局飞行器。In view of this, the main purpose of this utility model is to provide a novel high-lift aircraft with connected wing layout.
为达到上述目的，本实用新型的技术方案是这样实现的：In order to achieve the above object, the technical solution of the utility model is achieved in that:
本实用新型实施例提供一种新型高升力联接翼布局飞行器，该飞行器包括：机身、设置在机身两侧的主翼、上翼、端翼、垂尾，所述设置在机身两侧的主翼的端部均设置端翼，所述两个端翼的上部分别通过设置在机身上方的上翼与设置在机身尾部的垂尾连接；所述机身的机头两侧设置有鸭翼；所述端翼的外侧均设置有外翼。The embodiment of the utility model provides a new type of aircraft with high-lift joint wing layout, which includes: fuselage, main wings, upper wings, end wings and vertical tails arranged on both sides The ends of the main wings are all provided with end wings, and the upper parts of the two end wings are respectively connected with the vertical tail arranged at the tail of the fuselage through the upper wing arranged above the fuselage; both sides of the nose of the fuselage are provided with ducks Wings; the outer sides of the end wings are provided with outer wings.
上述方案中，所述两个端翼的尾部均设置有方向舵，所述两个上翼上均设置有升降舵。In the above solution, the tails of the two end wings are provided with rudders, and the two upper wings are provided with elevators.
上述方案中，所述两个主翼上均设置有副翼。In the above solution, the two main wings are provided with ailerons.
上述方案中，所述机头为扁平鸭嘴机头。In the above solution, the nose is a flat duckbill nose.
上述方案中，所述两个主翼上均设置有襟翼。In the above solution, flaps are provided on the two main wings.
上述方案中，其特征在于：所述外翼的设置方式采用前掠式、平直式或后掠式。In the above solution, it is characterized in that: the arrangement of the outer wings is forward-swept, straight or back-swept.
上述方案中，所述外翼上均设置有外副翼。In the above solution, the outer wings are provided with outer ailerons.
上述方案中，所述端翼垂直设置在主翼翼梢处的端翼安定面上，所述上翼设置在主翼的上方，并且两者之间设置有间距；所述鸭翼、主翼、上翼、端翼和外翼采用早期翼型、层流翼型、高升力翼型或超临界翼型。In the above scheme, the end wing is vertically arranged on the end wing stabilizer at the tip of the main wing, the upper wing is arranged above the main wing, and a distance is provided between the two; the canard, main wing, upper wing , The end wing and the outer wing adopt early airfoil, laminar flow airfoil, high lift airfoil or supercritical airfoil.
上述方案中，所述机身的尾部设置有动力装置，动力装置采用螺旋桨发动机或喷气式发动机。In the above solution, a power unit is provided at the tail of the fuselage, and the power unit adopts a propeller engine or a jet engine.
上述方案中，所述机身内部设置有可伸缩的旋翼轴，所述旋翼轴的顶部设置有两叶可折叠式旋翼，所述机身上还设置有旋翼舱盖。In the above solution, a retractable rotor shaft is arranged inside the fuselage, a two-leaf foldable rotor is arranged on the top of the rotor shaft, and a rotor hatch is also arranged on the fuselage.
与现有技术相比，本实用新型的有益效果：Compared with the prior art, the utility model has the beneficial effects:
本实用新型的外翼能够增加全机的有效升力面积，能够极大的提高飞行器的升力系数以及升阻比，提高了飞行器的低速性能，解决了现有联接翼布局飞行器低速性能不足的问题，同时有效的提高了飞行器的横向安定性，由于外翼靠近重心，在实现增大全机升力的过程中，所需的配平损失很小，利于飞行器的操稳控制；全机流线型的设计减少了气动阻力，通过主翼后掠，上翼采用前掠，飞行器的上反后掠机翼和下反前掠上翼连接在一起所形成的一前一后的机翼布局形式，使得飞行器的俯视图和主视图的外形都接近菱形，气动效率较高，上翼和主翼分别具有前掠翼和后掠翼的气动特性，两翼面间距足够，在较大迎角范围内，相互之间的不利干扰比小，充分发挥两组翼面的增升效应；大迎角飞行时，本实用新型具有良好的失速特性，在全机重量等同的情况下，相比一般联接翼布局飞行器，本实用新型能够用更小的速度实现巡航飞行，减少了油耗，降低了飞行器的使用成本。因此本实用新型不仅使联接翼布局低速性能得到极大提高，而且具有很高的经济效益。The outer wing of the utility model can increase the effective lift area of the whole aircraft, can greatly improve the lift coefficient and the lift-to-drag ratio of the aircraft, improve the low-speed performance of the aircraft, and solve the problem of insufficient low-speed performance of the existing connecting wing layout aircraft. At the same time, the lateral stability of the aircraft is effectively improved. Since the outer wings are close to the center of gravity, the required trim loss is very small in the process of increasing the lift of the entire aircraft, which is conducive to the stability and control of the aircraft; the streamlined design of the entire aircraft reduces aerodynamics. Resistance, through the sweep of the main wing, the upper wing adopts forward sweep, and the upper anti-sweep wing and the lower anti-sweep upper wing of the aircraft are connected together to form a front and one rear wing layout form, so that the top view of the aircraft and the main The shape of the view is close to a rhombus, and the aerodynamic efficiency is high. The upper wing and the main wing have the aerodynamic characteristics of the forward-swept wing and the swept-back wing respectively. , to give full play to the effect of increasing the lift of the two sets of wing surfaces; when flying at a high angle of attack, the utility model has good stall characteristics. The cruise flight is realized at a low speed, the fuel consumption is reduced, and the use cost of the aircraft is reduced. Therefore, the utility model not only greatly improves the low-speed performance of the connecting wing layout, but also has high economic benefits.
附图说明Description of drawings
图1为本实用新型实施例1提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 1 is the structural representation of a kind of novel high-lift connecting wing layout aircraft that the utility model embodiment 1 provides;
图2为本实用新型实施例2提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 2 is the structural representation of a kind of novel high-lift connecting wing layout aircraft that the utility model embodiment 2 provides;
图3为本实用新型实施例3提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 3 is the structural representation of a kind of novel high-lift connecting wing layout aircraft that the utility model embodiment 3 provides;
图4为本实用新型实施例5提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 4 is the structural representation of a kind of novel high-lift connecting wing layout aircraft that the utility model embodiment 5 provides;
图5为本实用新型实施例7提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 5 is a structural schematic diagram of a new type of high-lift coupled wing layout aircraft provided by Embodiment 7 of the present utility model;
图6为本实用新型实施例10提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 6 is a schematic structural view of a new type of high-lift connected-wing layout aircraft provided by Embodiment 10 of the present invention;
图7为本实用新型实施例11提供的一种新型高升力联接翼布局飞行器的结构示意图；Fig. 7 is a schematic structural view of a new type of high-lift aircraft with wing layout provided by Embodiment 11 of the present invention;
图8为本实用新型实施例11提供的一种新型高升力联接翼布局飞行器的展开结构示意图。Fig. 8 is a schematic diagram of the unfolded structure of a new type of high-lift coupled-wing layout aircraft provided by Embodiment 11 of the present invention.
图中，1-机身；2-鸭翼；3-主翼；4-上翼；5-端翼；6-外翼；7-副翼；8-升降舵；9-方向舵；10-垂尾；11-动力装置；12-机头；13-旋翼轴；14-两叶可折叠式旋翼；15-旋翼舱盖；16-外副翼；17-襟翼。In the figure, 1-fuselage; 2-canard; 3-main wing; 4-upper wing; 5-end wing; 6-outer wing; 7-aileron; 8-elevator; 9-rudder; 10-vertical tail; 11-power unit; 12-head; 13-rotor shaft; 14-two-blade foldable rotor; 15-rotor hatch; 16-outer aileron; 17-flap.
具体实施方式Detailed ways
下面结合附图和具体实施方式对本实用新型进行详细说明。The utility model will be described in detail below in conjunction with the accompanying drawings and specific embodiments.
实施例1：Example 1:
本实用新型实施例提供一种新型高升力联接翼布局飞行器，如图1所示，该飞行器包括：机身1、设置在机身1两侧的主翼3、上翼4、端翼5、垂尾10，所述设置在机身1两侧的主翼3的端部均设置端翼5，所述两个端翼5的上部分别通过设置在机身1上方的上翼4与设置在机身1尾部的垂尾10连接；所述机身1的机头12两侧设置有鸭翼2；所述端翼5的外侧均设置有外翼6。The embodiment of the utility model provides a new type of aircraft with high-lift joint wing layout. As shown in Figure 1, the aircraft includes: fuselage 1, main wing 3 arranged on both sides of Tail 10, the ends of the main wings 3 arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged above the fuselage 1 and the upper wing 4 arranged on the fuselage respectively. 1. The vertical tail 10 at the tail is connected; both sides of the nose 12 of the fuselage 1 are provided with canards 2; the outer sides of the end wings 5 are provided with outer wings 6.
所述外翼6能够增加全机的有效升力面积，能够极大的提高飞行器的升力系数以及升阻比，提高了飞行器的低速性能，解决了现有联接翼布局飞行器低速性能不足的问题，同时有效的提高了飞行器的横向安定性，由于外翼靠近重心，在实现增大全机升力的过程中，所需的配平损失很小，利于飞行器的操稳控制。The outer wing 6 can increase the effective lift area of the whole machine, can greatly improve the lift coefficient and the lift-to-drag ratio of the aircraft, improve the low-speed performance of the aircraft, and solve the problem of insufficient low-speed performance of the existing connecting wing layout aircraft. The lateral stability of the aircraft is effectively improved. Since the outer wings are close to the center of gravity, the required trim loss is small in the process of increasing the lift of the whole aircraft, which is beneficial to the stability control of the aircraft.
所述的鸭翼2的后掠或平直设计视机翼具体设计参数确定。The sweep or straight design of described canard 2 is determined according to the specific design parameters of the wing.
所述鸭翼2为上反或下反或平直设计视机翼具体设计参数确定，采用鸭翼2以增大全机的抬头力矩，并采用主动控制技术，解决了现有技术中全机的纵向静安定性不足的问题。The canard 2 is designed to be reversed up or down or straight depending on the specific design parameters of the wing. The canard 2 is used to increase the nose-up moment of the whole machine, and the active control technology is adopted to solve the problem of the whole machine in the prior art. The problem of insufficient longitudinal static stability.
本实用新型的全机流线型的设计减少了气动阻力，通过主翼后掠，上翼采用前掠，飞行器的上反后掠机翼和下反前掠上翼连接在一起所形成的一前一后的机翼布局形式，使得飞行器的俯视图和主视图的外形都接近菱形，气动效率较高，上翼和主翼分别具有前掠翼和后掠翼的气动特性，两翼面间距足够，在较大迎角飞行时，本实用新型具有良好的失速特性，在全机重量等同的情况下，相比一般联接翼布局飞行器，本实用新型能够用更小的速度实现巡航飞行，减少了油耗，降低了飞行器的使用成本。因此本实用新型不仅使联接翼布局低速性能得到极大提高，而且具有很高的经济效益。The streamlined design of the whole machine of the utility model reduces the aerodynamic resistance. The main wing is swept back and the upper wing is swept forward. The wing layout form of the aircraft makes the shape of the top view and the front view of the aircraft close to a rhombus, and the aerodynamic efficiency is high. When flying at an angle, the utility model has good stall characteristics. In the case of the same weight of the whole aircraft, compared with the general joint wing layout aircraft, the utility model can realize cruising flight at a lower speed, reduce fuel consumption, and reduce the cost of the aircraft. use cost. Therefore, the utility model not only greatly improves the low-speed performance of the connecting wing layout, but also has high economic benefits.
所述机身1和主翼3以及鸭翼2分别进行了翼身融和处理，从而在改善其气动效能的前提下，增加了机身机翼连接处的结构强度，所述主翼3的翼稍和端翼5的下翼面进行了融合，达到机翼和端翼结合的效果，所述垂尾9和机身1进行了融合连接，增加了强度。The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.
实施例2：Example 2:
本实用新型实施例提供一种新型高升力联接翼布局飞行器，如图2所示，该飞行器包括：机身1、设置在机身1两侧的主翼3、上翼4、端翼5、垂尾10，所述设置在机身1两侧的主翼3的端部均设置端翼5，所述两个端翼5的上部分别通过设置在机身1上方的上翼4与设置在机身1尾部的垂尾10连接；所述机身1的机头12两侧设置有鸭翼2；所述端翼5的外侧均设置有外翼6。The embodiment of the utility model provides a new type of aircraft with high-lift joint wing layout. As shown in Figure 2, the aircraft includes: fuselage 1, main wing 3 arranged on both sides of Tail 10, the ends of the main wings 3 arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged above the fuselage 1 and the upper wing 4 arranged on the fuselage respectively. 1. The vertical tail 10 at the tail is connected; both sides of the nose 12 of the fuselage 1 are provided with canards 2; the outer sides of the end wings 5 are provided with outer wings 6.
所述外翼6能够增加全机的有效升力面积，能够极大的提高飞行器的升力系数以及升阻比，提高了飞行器的低速性能，解决了现有联接翼布局飞行器低速性能不足的问题，同时有效的提高了飞行器的横向安定性，由于外翼靠近重心，在实现增大全机升力的过程中，所需的配平损失很小，利于飞行器的操稳控制。The outer wing 6 can increase the effective lift area of the whole machine, can greatly improve the lift coefficient and the lift-to-drag ratio of the aircraft, improve the low-speed performance of the aircraft, and solve the problem of insufficient low-speed performance of the existing connecting wing layout aircraft. The lateral stability of the aircraft is effectively improved. Since the outer wings are close to the center of gravity, the required trim loss is small in the process of increasing the lift of the whole aircraft, which is beneficial to the stability control of the aircraft.
所述两个端翼5的尾部均设置有方向舵9，所述两个上翼4上均设置有升降舵8，所述方向舵9能够增加飞行器的航向安定性与舵面操纵效率，改善了飞行器的抗侧风性能，降低联结处结构设计复杂度。The afterbody of described two end wings 5 is all provided with rudder 9, and described two upper wings 4 are all provided with elevator 8, and described rudder 9 can increase the heading stability of aircraft and the control efficiency of rudder surface, has improved the aircraft's Anti-crosswind performance, reducing the structural design complexity of the connection.
所述的鸭翼2的后掠或平直设计视机翼具体设计参数确定。The sweep or straight design of described canard 2 is determined according to the specific design parameters of the wing.
所述鸭翼2为上反或下反或平直设计视机翼具体设计参数确定，采用鸭翼2以增大全机的抬头力矩，并采用主动控制技术，解决了现有技术中全机的纵向静安定性不足的问题。The canard 2 is designed to be reversed up or down or straight depending on the specific design parameters of the wing. The canard 2 is used to increase the nose-up moment of the whole machine, and the active control technology is adopted to solve the problem of the whole machine in the prior art. The problem of insufficient longitudinal static stability.
本实用新型的全机流线型的设计减少了气动阻力，通过主翼后掠，上翼采用前掠，飞行器的上反后掠机翼和下反前掠上翼连接在一起所形成的一前一后的机翼布局形式，使得飞行器的俯视图和主视图的外形都接近菱形，气动效率较高，上翼和主翼分别具有前掠翼和后掠翼的气动特性，两翼面间距足够，在较大迎角飞行时，本实用新型具有良好的失速特性，在全机重量等同的情况下，相比一般联接翼布局飞行器，本实用新型能够用更小的速度实现巡航飞行，减少了油耗，降低了飞行器的使用成本。因此本实用新型不仅使联接翼布局低速性能得到极大提高，而且具有很高的经济效益。The streamlined design of the whole machine of the utility model reduces the aerodynamic resistance. The main wing is swept back and the upper wing is swept forward. The wing layout form of the aircraft makes the shape of the top view and the front view of the aircraft close to a rhombus, and the aerodynamic efficiency is high. When flying at an angle, the utility model has good stall characteristics. In the case of the same weight of the whole aircraft, compared with the general joint wing layout aircraft, the utility model can realize cruising flight at a lower speed, reduce fuel consumption, and reduce the cost of the aircraft. use cost. Therefore, the utility model not only greatly improves the low-speed performance of the connecting wing layout, but also has high economic benefits.
所述机身1和主翼3以及鸭翼2分别进行了翼身融和处理，从而在改善其动效能的前提下，增加了机身机翼连接处的结构强度，所述主翼3的翼稍和端翼5的下翼面进行了融合，达到机翼和端翼结合的效果，所述垂尾9和机身1进行了融合连接，增加了强度。The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its dynamic performance. The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.
实施例3：Example 3:
本实用新型实施例提供一种新型高升力联接翼布局飞行器，如图3所示，该飞行器包括：机身1、设置在机身1两侧的主翼3、上翼4、端翼5、垂尾10，所述设置在机身1两侧的主翼3的端部均设置端翼5，所述两个端翼5的上部分别通过设置在机身1上方的上翼4与设置在机身1尾部的垂尾10连接；所述机身1的机头12两侧设置有鸭翼2；所述端翼5的外侧均设置有外翼6；所述两个主翼3上均设置有副翼7。The embodiment of the utility model provides a new type of aircraft with high-lift joint wing layout, as shown in Figure 3, the aircraft includes: fuselage 1, main wing 3 arranged on both sides of Tail 10, the ends of the main wings 3 arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged above the fuselage 1 and the upper wing 4 arranged on the fuselage respectively. 1. The vertical tail 10 at the tail is connected; both sides of the nose 12 of the fuselage 1 are provided with canards 2; the outer sides of the end wings 5 are provided with outer wings 6; the two main wings 3 are provided with auxiliary Wing 7.
所述外翼6能够增加全机的有效升力面积，能够极大的提高飞行器的升力系数以及升阻比，提高了飞行器的低速性能，解决了现有联接翼布局飞行器低速性能不足的问题，同时有效的提高了飞行器的横向安定性，由于外翼靠近重心，在实现增大全机升力的过程中，所需的配平损失很小，利于飞行器的操稳控制。The outer wing 6 can increase the effective lift area of the whole machine, can greatly improve the lift coefficient and the lift-to-drag ratio of the aircraft, improve the low-speed performance of the aircraft, and solve the problem of insufficient low-speed performance of the existing connecting wing layout aircraft. The lateral stability of the aircraft is effectively improved. Since the outer wings are close to the center of gravity, the required trim loss is small in the process of increasing the lift of the whole aircraft, which is beneficial to the stability control of the aircraft.
实施例4：Example 4:
在实施例3的基础上，所述机头12为扁平鸭嘴机头，鸭嘴式扁平机头设计充分利用了生物仿真学，扁平的嘴唇是大雁等生物的共同特点，减少了空气阻力，利于生物的飞行。On the basis of embodiment 3, the nose 12 is a flat duckbill nose, and the design of the duckbill flat nose has made full use of bio-simulation, and the flat lips are a common feature of creatures such as wild geese, which reduces air resistance. Conducive to the flight of creatures.
实施例5：Example 5:
如图4所示，在实施例4的基础上，所述两个主翼2上均设置有襟翼17。As shown in FIG. 4 , on the basis of Embodiment 4, flaps 17 are provided on the two main wings 2 .
实施例6：Embodiment 6:
在实施例1～5任意一个实施例的基础上，所述外翼6的设置方式采用前掠式、平直式或后掠式。On the basis of any one of embodiments 1 to 5, the arrangement of the outer wings 6 is forward-swept, straight or back-swept.
实施例7：Embodiment 7:
如图5所示，在实施例6的基础上，所述外翼6上均设置有外副翼16。As shown in FIG. 5 , on the basis of Embodiment 6, the outer wings 6 are provided with outer ailerons 16 .
实施例8：Embodiment 8:
在实施例6的基础上，所述端翼5垂直设置在主翼3翼梢处的端翼安定面上，所述上翼4设置在主翼3的上方，并且两者之间设置有间距。On the basis of Embodiment 6, the end wing 5 is vertically arranged on the end wing stabilizer at the tip of the main wing 3, and the upper wing 4 is arranged above the main wing 3 with a space between them.
实施例9：Embodiment 9:
在实施例6的基础上，所述鸭翼2、主翼3、上翼4、端翼5和外翼6采用早期翼型、层流翼型、高升力翼型或超临界翼型。On the basis of embodiment 6, the canard 2, main wing 3, upper wing 4, end wing 5 and outer wing 6 adopt early airfoil, laminar flow airfoil, high-lift airfoil or supercritical airfoil.
实施例10：Example 10:
如图6所示，在实施例6的基础上，所述机身1的尾部设置有动力装置11，动力装置11采用螺旋桨发动机或喷气式发动机。As shown in Figure 6, on the basis of Embodiment 6, a power plant 11 is provided at the tail of the fuselage 1, and the power plant 11 adopts a propeller engine or a jet engine.
实施例11：Example 11:
如图7、8所示，在实施例6的基础上，所述机身1内部设置有可伸缩的旋翼轴13，所述旋翼轴13的顶部设置有两叶可折叠式旋翼14，所述机身1上还设置有旋翼舱盖15，使得飞行器具有短距起飞垂直着陆功能。As shown in Figures 7 and 8, on the basis of Embodiment 6, a retractable rotor shaft 13 is provided inside the fuselage 1, and a two-leaf foldable rotor 14 is provided on the top of the rotor shaft 13. The fuselage 1 is also provided with a rotor canopy 15, so that the aircraft has a short take-off and vertical landing function.
在准备着陆时，逐渐减小推进式发动机的工作状态，飞机开始减速，当飞行速度达到一定门限值，飞行控制系统控制打开旋翼舱盖15，驱动旋翼轴13升起，当旋翼轴13完全伸出并锁紧，并打开可折叠式旋翼14的锁紧装置，使可折叠式旋翼14在预紧力的作用下展开；同时推进动力装置11与发动机驱动轴的联结断开，采用动力转换装置，将发动机驱动轴与用于垂直着陆的旋翼轴13联结，驱动旋翼轴13工作，产生全机所需的着陆升力，使得飞行器垂直降落在预定地点，旋翼减速直到停止工作，可折叠式旋翼14折叠，所述旋翼轴13收入机身内，所述旋翼舱盖15关闭，飞行器完成垂直着陆。When preparing to land, the working state of the propulsion engine is gradually reduced, and the aircraft starts to decelerate. When the flight speed reaches a certain threshold, the flight control system controls to open the rotor hatch 15 to drive the rotor shaft 13 to rise. When the rotor shaft 13 is fully Stretch out and lock, and open the locking device of the foldable rotor 14, so that the foldable rotor 14 is unfolded under the effect of the pre-tightening force; at the same time, the connection between the propulsion power unit 11 and the engine drive shaft is disconnected, and the power conversion is adopted. The device connects the engine drive shaft with the rotor shaft 13 for vertical landing, drives the rotor shaft 13 to work, generates the landing lift required by the whole aircraft, makes the aircraft land vertically at the predetermined place, and the rotor decelerates until it stops working. The foldable rotor 14 is folded, the rotor shaft 13 is received in the fuselage, the rotor canopy 15 is closed, and the aircraft completes vertical landing.
以上所述，仅为本实用新型的较佳实施例而已，并非用于限定本实用新型的保护范围。The above descriptions are only preferred embodiments of the present utility model, and are not intended to limit the protection scope of the present utility model.
Claims (10)
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| CN201520170280.0U CN204507270U (en) | 2015-03-25 | 2015-03-25 | Novel high lift joined wing configuration aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN113044200A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | Novel solar unmanned aerial vehicle layout with connection wings close to space |
| CN113212737A (en) * | 2021-05-18 | 2021-08-06 | 浙江鸿鹄翼航空科技有限公司 | Aircraft with wing tip aileron |
-
2015
- 2015-03-25 CN CN201520170280.0U patent/CN204507270U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105416587A (en) * | 2015-12-02 | 2016-03-23 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Aerodynamic layout of aircraft with blended wing body |
| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN108045575B (en) * | 2017-12-18 | 2024-03-19 | 刘行伟 | Short-distance take-off vertical landing aircraft |
| CN113044200A (en) * | 2021-04-20 | 2021-06-29 | 西北工业大学 | Novel solar unmanned aerial vehicle layout with connection wings close to space |
| CN113044200B (en) * | 2021-04-20 | 2023-10-27 | 西北工业大学 | Solar unmanned aerial vehicle layout in adjacent space of connecting wing |
| CN113212737A (en) * | 2021-05-18 | 2021-08-06 | 浙江鸿鹄翼航空科技有限公司 | Aircraft with wing tip aileron |
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