阅读说明：本技术 一种固定翼扑翼复合式飞行器 (Fixed wing flapping wing combined type aircraft ) 是由 李道春 孙毅 邵浩原 李华东 张尧 于 2019-10-22 设计创作，主要内容包括：本发明公开一种固定翼扑翼复合式飞行器,整机蒙皮采用柔性材料,设计内、外翼结构机翼；在起飞过程中,内段机翼提供稳定的升力,外段机翼通过大幅度扑动和弦向扭转产生全部推力和部分升力。飞行过程中,以滑翔飞行为主,升力由内外段机翼提供,辅以较低扑频的外翼扑动,尾翼以提高飞行器的飞行稳定性。通过改变翼面下方悬挂物的重心,调整飞行器的飞行姿态。紧急状态下,外段扑翼可停止扑动并锁定在指定位置,与固定翼平行,形成固定翼布局,实现滑翔飞行。本发明具有更高的稳定性、安全性和舒适性,且可提升整个微型飞行器的升力特性。(The invention discloses a fixed wing flapping wing composite aircraft, wherein the whole aircraft skin is made of flexible materials, and wings with inner and outer wing structures are designed; in the take-off process, the inner section of wing provides stable lift force, and the outer section of wing generates all thrust force and partial lift force through large-amplitude flapping and chord direction twisting. In the flying process, the gliding flying behavior is mainly used, the lifting force is provided by the inner and outer wings, the outer wings with lower flapping frequency are used for flapping, and the tail wing is used for improving the flying stability of the aircraft. The flying attitude of the aircraft is adjusted by changing the gravity center of the suspension object below the airfoil. In an emergency state, the outer flapping wings can stop flapping and are locked at designated positions and are parallel to the fixed wings to form a fixed wing layout, and gliding flight is realized. The invention has higher stability, safety and comfort, and can improve the lift characteristic of the whole micro aircraft.)

1. The utility model provides a flapping wing fixed wing combined type aircraft which characterized in that: comprises a machine body, a wing lifting surface, a tail wing and a flapping wing driving system;

a connecting rod along the axial direction is arranged above the machine body main body, the front part of the connecting rod is provided with a wing lifting surface, and the rear end of the connecting rod is provided with an empennage;

the wing lifting surface comprises an inner wing and an outer wing; wherein, the inner wing is fixed with the connecting rod; the outer wings are positioned on two sides of the inner wing and connected with the inner wing through connecting pieces, so that the outer wings realize the up-and-down flapping and passive twisting motion; the inner wing generates part of stable lift force required by the flight of the aircraft; the outer wing is driven by the flapping wing driving system, thereby realizing large-amplitude flapping and chord direction torsion and generating all thrust and partial lift required by the flight of the aircraft.

2. The flapping-wing, fixed-wing, composite aircraft of claim 1, wherein: the top corner of the control tripod is fixed with the front end of the connecting rod, and the front end of the machine body main body is positioned in the control tripod; the bottom edge of the control triangular frame is provided with machine wheels near two bottom corners; and the inner wing framework is connected with the control tripod by installing a tension line so as to bear the pulling force from the inner wing of the aircraft in the flying process.

3. The flapping-wing, fixed-wing, composite aircraft of claim 1, wherein: the inner wing comprises an inner wing membrane and an inner wing framework; the inner wing framework comprises an obtuse triangular framework formed by two front side rods and one rear side rod and an inner wing rib for maintaining the aerodynamic shape of the inner wing membrane; the front side edge of the inner wing membrane is fixed with the front side edge of the inner wing framework, and is also fixed with the rear measuring rod and the inner wing rib; the back side of the inner wing membrane is parallel to the back side rod, the left width and the right width of the inner wing membrane are equal to the length of the back side rod, and the left side and the right side of the inner wing membrane are straight edges of length and are both parallel to the connecting rod.

4. The flapping-wing, fixed-wing, composite aircraft of claim 3, wherein: the front side rod, the rear side rod and the wing ribs are fixedly spliced through the plug connectors.

5. The flapping-wing, fixed-wing, composite aircraft of claim 3, wherein: the outer wing comprises an outer wing membrane, an outer wing framework and an outer wing rib; the front side edge of the outer wing membrane is a straight edge and is fixed on the outer wing framework and is also fixed with the outer wing ribs; the inner side edge of the outer wing membrane is a straight edge and is connected with the outer side edge of the inner wing membrane without connection; the rear side edge of the outer wing membrane is an arc-shaped edge.

Technical Field

The invention belongs to the field of aviation aircraft design, and particularly relates to a fixed-wing flapping-wing combined aircraft.

Background

A fixed wing flapping wing combined type aircraft is provided based on the lifting, pushing and control mechanism of large birds and bats, and the inner section of the aircraft wing is fixed and can provide a certain stable lifting force; the outer section of the wing generates lift force and thrust force through flapping and chord direction torsion.

The composite aircraft integrates the advantages of a fixed wing aircraft and a flapping wing aircraft, and has the characteristics of high pneumatic efficiency, capability of realizing horizontal take-off and landing and the like. The aircraft integrates the lifting thrust into a whole, the limitation of a take-off and landing site is less, and the micro-noise dynamic flight can be realized.

The existing fixed wing aircraft has high requirements on the field for taking off and landing, is easily influenced by crosswind during flying, and has relatively poor flying flexibility.

Disclosure of Invention

In order to solve the problems in the prior art, the invention provides a composite aircraft adopting fixed-wing flapping wings, which has higher stability, safety and comfort and can improve the lift characteristic of the whole flapping wing aircraft. The configuration aircraft platform provides a solution for large-scale flapping wings, and has certain application value on small and medium-sized flapping wing aircraft.

The utility model provides a flapping wing fixed wing combined type aircraft which characterized in that: comprises a body, a wing lifting surface, a tail wing and a flapping wing driving system.

The aircraft body top has along axial connecting rod, and wing lift face is installed to the connecting rod front portion, and the rear end installation displacement. The wing lifting surface comprises an inner wing and an outer wing. Wherein, the inner wing is fixed with the connecting rod; the outer wings are positioned on two sides of the inner wing and connected with the inner wing through connecting pieces, so that the outer wings can flap up and down and generate passive torsion. The inner wing generates part of stable lift force required by the flight of the aircraft; the outer wing is driven by the flapping wing driving system, thereby realizing large-amplitude flapping and chord direction torsion and generating all thrust and partial lift required by the flight of the aircraft.

The invention has the advantages that:

1. the fixed wing flapping wing combined type aircraft provided by the invention refers to the flight mechanism of large birds, adopts a sectional wing design, can provide relatively stable lift force through the inner wing, and has higher stability, safety and comfort compared with the flapping of the whole wing.

2. According to the fixed-wing flapping-wing combined type aircraft, the outer wing flapping can generate thrust to drive the aircraft to move forward, and can generate a certain lift force, and in the flapping process, the air in front can be driven to flow backwards, so that the wing tip airflow of the inner wing is improved, and the lift force characteristic of the whole micro aircraft can be improved to a certain extent.

3. The fixed wing flapping wing composite aircraft can realize the fixed-height/fixed-power flight of the aircraft with larger load under the condition of low altitude or ultra-low altitude. The net weight under the unpowered mode is 30KG, and the net weight after the motor is additionally arranged is 50KG, thereby completely meeting the requirement specification of No. 188 order of the civil aviation administration on the ultralight aircraft.

4. The fixed-wing flapping-wing composite aircraft has unique technical advantages in the aspects of high maneuvering flight and horizontal take-off and landing, can be applied to a bionic aviation sport project integrating sports, entertainment, appreciation and education, can provide flight experience superior to the existing navigation aircraft for users, expands social and economic benefits brought by the existing aviation sport, and can become one of individuals and special skills aircraft with the most potential in the market in the future.

Drawings

FIG. 1 is a schematic view of the overall structure of a fixed-wing flapping-wing composite aircraft according to the present invention;

FIG. 2 is a schematic view of a wing lifting surface structure of the fixed wing flapping wing composite aircraft according to the present invention;

FIG. 3 is a schematic view of the flapping wing drive system of the fixed wing flapping wing composite aircraft of the present invention;

FIG. 4 is a schematic view of the driving principle of the structure of the flapping wing driving system.

In the figure:

1-body 2-wing lifting surface 3-empennage

4-flapping wing driving system 101-punching bag 102-suspension beam

103-connecting rod 104-control tripod 105-wheel

106-lower tension line 201-inner wing 202 outer wing

201 a-inner wing membrane 201 b-front side rod 201 c-back side rod

201 d-inner wing rib 202 a-outer wing membrane 202 b-outer wing framework

202 c-outer wing rib 301-tail framework 302-tail membrane

401-pull rod 402-sleeve 403-gear

404 rocker 405 connecting piece 406 housing

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

The invention relates to a flapping-wing fixed wing composite aircraft, which comprises an aircraft body 1, a wing lifting surface 2, a tail wing 3 and a flapping wing driving system 4, as shown in figure 1.

The machine body 1 comprises a hanging bag 101, a hanging beam 102, a connecting rod 103, a control tripod 104 and a wheel 105. The punching bag 101 is mainly used for hanging people or objects, is in a pupa shape and is streamline, the front edge is blunt, and the rear edge is sharp. The upper part of the punching bag 101 is provided with a suspension beam 102 which is longitudinally arranged at the position apart from the 1/3 rear end of the punching bag 101 and the length of the punching bag 101 in the front-rear direction, the bottom end of the suspension beam 102 is fixed with the upper part of the punching bag 101, and the top part is provided with a connecting rod 103. The connecting rod 103 is horizontal in the front-rear direction; the middle part of the connecting rod 103 is fixed with the suspension beam 102. The front part of the connecting rod 103 is provided with a wing lifting surface 2, and the rear part is provided with a tail wing 3 for providing the stability of the aircraft during flying. The control tripod 104 is an isosceles triangle, the vertex angle is fixed with the front end of the connecting rod 103, and the front end of the punching bag 101 is positioned in the control tripod 104. Wheels 105 are mounted on the bottom edge of the control tripod 104 near two bottom corners for bearing the gravity of the aircraft during ground parking, taxiing, takeoff and landing, and braking during taxiing and taxiing. .

The wing lifting surface 2 is composed of an inner wing 201 and an outer wing 202, as shown in fig. 2, wherein the inner wing 201 is used for generating part of stable lifting force required by the flight of the aircraft; the outer wing 202 is driven by the flapping wing driving system 4 to realize large-amplitude flapping and chord direction torsion and generate all thrust and part lift required by the flight of the aircraft.

The inner wing 201 comprises an inner wing membrane 201a and an inner wing skeleton. The inner wing frame is composed of two front side rods 201b, one rear side rod 201c and an inner wing rib 201 d. The ends of the two front side rods 201b are connected and fixed to form an obtuse angle of 120-160 degrees. The rear ends of the two front side rods 201b are respectively spliced and fixed with the two ends of the rear side rod 201c through the plug connectors to form an isosceles obtuse triangle framework, and the vertical distance between the rear side rod 201c and the vertex angle is about 1 m. The top corner (obtuse angle position) of the inner wing framework is fixed with the front end part of the connecting rod 103, and the bottom edge center position is fixed with the connecting rod 103.

The front side edge of the inner wing membrane 201a is matched with an obtuse angle formed by the two front side rods 201b, a front side rod channel is designed along the front side edge of the inner wing membrane 201a, and the front side edge of the inner wing membrane 201a is sleeved on the two front side rods 201b of the wing membrane framework; meanwhile, a rear side rod penetrating channel is designed on the inner wing membrane corresponding to the rear side rod 201c, so that the rear side rod 201c penetrates through the channel and then is inserted into the front side rod 201 b. Inner wing rib channels parallel to the connecting rods 103 are designed on the inner wing membrane 201a at equal intervals in the span direction, after the inner wing ribs 201d are inserted into the inner wing rib channels, the inner wing ribs 201d are inserted and fixed with the plugs designed on the front side rods 201b through the plug connectors mounted at the end parts, and the inner wing membrane 201a is supported through the inner wing ribs 201d, so that the aerodynamic appearance of the inner wing membrane 201a is maintained. The rear side of the inner wing membrane 201a may be substantially parallel to the rear bar 201c, and the vertical distance from the rear bar 201c may be about 1.5 m. The left and right width of the inner wing membrane 201a is equal to the length of the rear rod 201c, and the left and right sides are straight edges with equal length and are both parallel to the connecting rod 103.

The outer wing 202 is mounted on the left and right sides of the inner wing 201, and includes an outer wing membrane 202a, an outer wing framework 202b, and an outer wing rib 202 c. The front side of the outer wing membrane 202a is a straight edge, and an outer wing framework channel is designed along the front side of the outer wing membrane 202a, so that the front side of the outer wing membrane 202a can be sleeved on the rod-shaped outer wing framework 202 b. Similarly, outer rib channels parallel to the tie bars 103 are formed in the outer wing membrane 202a at equal intervals in the span-wise direction, and after the outer ribs 202c are inserted into the outer rib channels, the outer ribs 202c are fixed to the plugs formed in the outer wing frame 202b by end-mounted connectors, and the outer wing membrane 202a is supported by the outer ribs 202c, thereby maintaining the outer shape of the outer wing membrane 202 a. An included angle of 150-160 degrees is formed between the outer wing frame 202b and the front side rod 201b of the inner wing frame, and meanwhile, the tail end of the outer wing frame 202b is hinged with the bottom angle of an obtuse triangle formed by the inner wing frame through a hinge piece. The axis of the hinge is parallel to the connecting rod 103; meanwhile, the hinge is installed at the end of the outer wing frame 202b through a rotating shaft, and the axis of the rotating shaft is perpendicular to the connecting rod 103. The outer wing 202 thus has a revolute pair rotatable about the hinge axis, and a revolute pair twisted in the chord direction of the outer wing. The inner side edge of the outer wing membrane 202a is a straight edge and is connected with the outer side edge of the inner wing membrane without connection. The rear side edge of the outer wing membrane 202a is an arcuate edge.

As shown in fig. 3 and 4, the flapping wing driving system 4 is suspended on the connecting rod 103 through a connecting rod, and the power is output by the motor, and is output to the gear transmission mechanism after the speed of the speed reducer is reduced, and finally, the power is output to the two pull rods 401 by the gear transmission mechanism. Sleeves 402 are sleeved at the tail ends of the two pull rods 401, the sleeves 402 are hinged with each other and with a support which is fixed relative to the motor, and connecting pieces 405 are fixedly arranged at the outer ends of the two pull rods 402 and are connected with the inner ends of the outer wing frameworks 202b through the connecting pieces 405. In the gear transmission mechanism, two gears 403 which are mutually kneaded and drive two pull rods 401 to move are hinged with a sleeve 402 on the tail end of the pull rod 401 through a rocker arm 404, and the rocker arm 404 is eccentrically connected with the gears 403. Therefore, when the two gears 403 rotate, the rocker arm 404 can drive the tail end of the pull rod 401 to perform circular motion, so that the pull rod 401 has vertical and horizontal displacement at the same time, and further the pull rod 401 can drive the outer wing 202 to flap up and down, and meanwhile, the outer wing 202 can generate driven torsion around the chord direction of the outer wing, so that the outer wing 202 generates partial lift force and full thrust, and in the flapping process of the outer wing 202, the air in the front can be driven to flow backwards, the wing tip airflow of the inner wing 201 is improved, and the lift force characteristic of the fixed wing can be improved. The preferred flapping amplitude of the outer wings 202 is within 60 and the twist amplitude is within 45.

The empennage 3 comprises a left empennage and a right empennage which are symmetrically arranged at the rear part of the connecting rod 103. The left empennage and the right empennage are both composed of empennage skeletons 301 and empennage wing membranes 302. The tail framework 301 has a front rod 301a and a rear rod 301 b; the inner ends of the front side rod 301a and the rear side rod 301b are fixedly connected with the connecting rod 103, and the rear ends are fixedly connected with each other to form an integral empennage framework. The tail framework 301 is fixedly provided with a tail wing film 302. The area of the wing membranes of the left empennage and the right empennage is 10 to 15 percent of the area of the inner wing membrane 201 a.

In the invention, a tension line 106 is additionally arranged between the control tripod 104 and the wing lifting surface 2, and as shown in figure 1, the tension lines are four in total and are made into a first tension line, a second tension line and a fourth tension line. The first lower opening line and the second lower opening line are arranged in bilateral symmetry, and one end of each lower opening line is connected with the top angle of the inner wing framework through a clamping hook; the other end is respectively connected with two bottom angles of the control tripod through the clamping hook. One end of the third and fourth lower tension lines is respectively connected with the two ends of the rear measuring rod 201c through the clamping hook; the other end is respectively connected with two bottom angles of the control tripod through the clamping hook. The inner wing frame is connected to the control tripod 104 by installing a tension wire 106 to withstand the pulling force of the aircraft from the inner wing 201 during flight.

The inner wing membrane 201a, the outer wing membrane 202a and the skin of the body are made of flexible materials, are made of paraglider cloth, are thickened at the front edge parts of the inner wing membrane and the outer wing membrane 202a, and are convenient to install inner wing membrane connecting rods and outer wing membrane connecting rods. The area of the outer wing membrane 202a is 35-45% of the area of the inner wing membrane 201a, and the wingspan of the whole wing is preferably 10-13 m.

When the flapping wing fixed wing composite aircraft takes off, a certain horizontal speed condition is required to be met, the inner wing 201 provides stable lift force, meanwhile, the flapping wing driving system 4 drives the outer wing 202 to flap at a flapping frequency of 1-2Hz to provide thrust and partial lift force, after a certain height is reached, the flapping frequency of the outer wing 202 is reduced, the aircraft can maintain a cruising state, and gliding can be realized.

In the flight process, the gliding flight is taken as the main action, the lift force is provided by the inner wing 201 and the outer wing 202, the outer wing 202 with lower flapping frequency is used for flapping, and the tail wing 3 is used for improving the flight stability of the aircraft. Under the condition that the aircraft carries people, the gravity center of the human body can be changed through adjustment, and the flying posture of the aircraft can be adjusted. In emergency, the outer wing 202 can stop flapping and is locked at a designated position, and is parallel to the inner wing 201 to form a fixed wing layout, so that gliding flight is realized.