阅读说明：本技术 飞行器稳定尾翼装置 (Aircraft rear-fin stabilizer device ) 是由 赵兴隆 张赢 郝波 许萍 刘本慧 黄书平 丁云鹏 惠轶 居闽 颜雯清 刘康 张 于 2019-08-06 设计创作，主要内容包括：本发明提供了一种飞行器稳定尾翼,包括中心筒,栅格翼,外环翼,栅格翼分布在中心筒外侧,外环翼环绕栅格翼的外缘从而组成整体式尾翼。栅格翼分为多个纵横交错的横向翼面和纵向翼面,位于中心位置的横向翼面分为左翼面和右翼面,位于中心位置的纵向翼面分为上翼面和下翼面,左翼面的内缘、右翼面的内缘分别与中心筒外壁的左侧、右侧连接,上翼面的内缘、下翼面的内缘分别与中心筒外壁的上侧、下侧连接。本发明能在发射筒等空间限制条件下为飞行器的稳定飞行提高足够大的稳定力矩和气动力；无运动机构,提高了工作可靠性,并降低了成本采用整体式结构,结构的强度和刚度好,结构效率高；尾翼一体化结构,加工以及飞行器现场安装得到简化。(The present invention provides a kind of aircraft rear-fin stabilizer, including central tube, lattice fin, the outer ring wing, lattice fin is centrally located on the outside of cylinder, and the outer ring wing forms monoblock type empennage around the outer rim of lattice fin.Lattice fin is divided into multiple criss-cross lateral aerofoils and longitudinal aerofoil, lateral aerofoil positioned at center is divided into left wing face and right flank face, longitudinal aerofoil positioned at center is divided into top airfoil and lower aerofoil, the inner edge in left wing face, the inner edge in right flank face are connect with the left side of center drum outer wall, right side respectively, and the inner edge of top airfoil, the inner edge of lower aerofoil are connect with the upside of center drum outer wall, downside respectively.The present invention can improve sufficiently large stabilizing moment and aerodynamic force under the restrictive condition of the spaces such as launching tube for the stabilized flight of aircraft；Without motion mechanism improves functional reliability, and reduces costs using monolithic construction, and the strength and stiffness of structure are good, and structure efficiency is high；Empennage integral structure, processing and aircraft in-site installation are simplified.)

1. a kind of aircraft rear-fin stabilizer, which is characterized in that including central tube, lattice fin, the outer ring wing, the lattice fin is distributed in On the outside of central tube, the outer ring wing forms monoblock type empennage around the outer rim of lattice fin.

2. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the lattice fin is divided into multiple criss-cross Lateral aerofoil and longitudinal aerofoil, in the transverse direction aerofoil, the lateral aerofoil positioned at center is divided into left wing face and right flank face, Longitudinal aerofoil positioned at center is divided into top airfoil and lower aerofoil, connects on the left of the inner edge in the left wing face and center drum outer wall It connects, the inner edge in the right flank face is connect with the right side of center drum outer wall, the inner edge of the top airfoil and the upside of center drum outer wall Connection, the inner edge of the lower aerofoil is connect with the downside of center drum outer wall.

3. aircraft rear-fin stabilizer according to claim 2, which is characterized in that the spacing dimension of the transverse direction aerofoil and vertical The spacing dimension of airfoil will guarantee the number of plies of lattice fin not less than 2 layers.

4. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the leading edge sweep of the lattice fin is 45°。

5. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the outer ring wing is hollow cylinder knot Structure.

6. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the central tube, lattice fin, the outer ring wing one It is body formed.

7. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the central tube and aircraft engine tail Nozzle section socket.

8. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the internal diameter and aircraft of the central tube are received The outer diameter of contracting shape jet pipe matches.

9. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the central tube, lattice fin, the outer ring wing are adopted With PVC or aluminium alloy or steel.

10. aircraft rear-fin stabilizer according to claim 1, which is characterized in that the diameter size and flight of the outer ring wing The matching of device main structure size.

Technical field

The present invention relates to aircraft devices technical fields, and in particular, to a kind of aircraft rear-fin stabilizer device.

Background technique

Rear-fin stabilizer is Aircraft Conceptual Design and the indispensable part of composition, the parameters pair such as area, length of empennage In the stability for guaranteeing aircraft and to provide enough mobility most important.But the size of another aspect empennage is again It is limited by structure and (or transmitting) environment that takes off, for aircraft such as guided missile, rocket projectile and cartridge type transmitting unmanned planes, is stablized The design of empennage is just limited by the space of emitter.Currently, the aircraft such as guided missile, rocket projectile and cartridge type transmitting unmanned plane Aerofoil generallys use fold design.After aircraft leaves emitter or launching tube, drive empennage fast by unfolding mechanism Speed expansion, requires after expanding in place and reliably securely locks.The expansion of empennage is usually relatively complex with locking, will lead to The unfavorable factors such as aircraft weight increases, the rear heart moves back, and there are reliabilities and cost constraint.In order to guarantee the work of fold mechanism Make Performance And Reliability, the functional reliability after especially long-term storage will usually pay relatively high cost price.Especially For low-cost design aircraft, complicated folding fin influences the totle drilling cost of aircraft can be bigger.In addition, slightly one The technical difficulty of the folding fin of reliable design is also very big on type aircraft.

Therefore, the aircraft such as a part of guided missile, rocket projectile and unmanned plane need a kind of novel tail gear, can be with Simple limited mode is interior in a limited space to provide sufficiently large pneumatic face area and air force, and simplifies design and peace Dress to improve aircraft stabilization and mobility, and improves reliability, reduces cost.

By the retrieval to the prior art, application No. is 201510043929.7 patents of invention to disclose a kind of fixed-wing The tail structure of unmanned vehicle, including fuselage and positioned at the empennage mechanism of fuselage afterbody, the empennage mechanism includes that empennage connects Socket part and a pair of of the empennage being fixedly connected with empennage interconnecting piece, vertical plane of a pair of empennage along empennage interconnecting piece center line Be symmetrical arranged, wherein be equipped with connecting cavity connect with fuselage afterbody in the middle part of the empennage interconnecting piece, the connecting cavity with after fuselage Portion is detachable is fixedly connected.The tail structure interior in a limited space can not provide sufficiently large pneumatic face area and air Power can not improve aircraft stabilization and mobility.

Summary of the invention

For the defects in the prior art, the object of the present invention is to provide a kind of aircraft rear-fin stabilizer devices.

A kind of aircraft rear-fin stabilizer provided according to the present invention, including central tube, lattice fin, the outer ring wing, the grid The wing is centrally located on the outside of cylinder, and the outer ring wing forms monoblock type empennage around the outer rim of lattice fin.

Further, the lattice fin is divided into multiple criss-cross lateral aerofoils and longitudinal aerofoil, the transverse direction aerofoil In, the lateral aerofoil positioned at center is divided into left wing face and right flank face, and longitudinal aerofoil positioned at center is divided into top airfoil And lower aerofoil, the inner edge in the left wing face are connect with the left side of center drum outer wall, the inner edge in the right flank face and center drum outer wall Right side connection, the inner edge of the top airfoil is connect with the upside of center drum outer wall, outside the inner edge of the lower aerofoil and central tube The downside of wall connects.

Further, the spacing dimension of the lateral aerofoil and the spacing dimension of longitudinal aerofoil will guarantee the number of plies of lattice fin Not less than 2 layers.

Further, the leading edge sweep of the lattice fin is 45 °.

Further, the outer ring wing is hollow cylindrical structure.

Further, the central tube, lattice fin, the outer ring wing are integrally formed.

Further, the central tube and aircraft engine jet pipe section are socketed.

Further, the internal diameter of the central tube is matched with the outer diameter that aircraft shrinks shape jet pipe.

Further, the central tube, lattice fin, the outer ring wing is using PVC or aluminium alloy or steel.

Further, the diameter size of the outer ring wing is matched with aircraft body structure size.

Compared with prior art, the present invention have it is following the utility model has the advantages that

1, in aircraft rear-fin stabilizer of the invention, lattice fin is combined into a monoblock type empennage by central tube, the outer ring wing, And connect by central tube with body part, the outer ring wing makes grid be closed as a monolithic construction, and further increases pneumatic The area in face, lattice fin and the outer ring wing are pneumatic force generating mechanism, and leading-edge sweep, aerofoil profile can be carried out according to cruising speed Optimization design, the leading edge sweep of lattice fin can reduce flight resistance and improve flight stability, and flying speed is bigger, angle of sweep It is bigger, generally take 45 degree or so.

2, in aircraft rear-fin stabilizer of the invention, multi-disc aerofoil is staggeredly combined, to expand in a limited space effective Pneumatic face area.

3, in aircraft rear-fin stabilizer of the invention, grid connects into an integrally closed structure, reinforces the strong of lattice fin Degree improves protection for lattice fin, and outer ring wing itself can also expand the aerodynamic area of empennage.

4, in aircraft rear-fin stabilizer of the invention, in the effective space such as launching tube, fold mechanism is not used Improve the aerofoil of enough large area.

5, in aircraft rear-fin stabilizer of the invention, can fly under the restrictive condition of the spaces such as launching tube for the stabilization of aircraft Row improves sufficiently large stabilizing moment and aerodynamic force；Without motion mechanism improves functional reliability, and reduces costs using whole The strength and stiffness of body formula structure, structure are good, and structure efficiency is high；Empennage integral structure, processing and aircraft in-site installation It is simplified.

Detailed description of the invention

Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention, Objects and advantages will become more apparent upon:

Fig. 1 is a kind of aircraft rear-fin stabilizer frontal view in the present invention；

Fig. 2 is a kind of aircraft rear-fin stabilizer side view in the present invention；

Fig. 3 is a kind of perspective view of aircraft rear-fin stabilizer in the present invention；

Fig. 4 is the aircraft schematic diagram of this use tail gear of the present invention.

Specific embodiment

The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention Protection scope.

As shown in Figure 1 to Figure 3, a kind of aircraft rear-fin stabilizer 4, including central tube 1, lattice fin 2, the outer ring wing 3, lattice fin 2 are centrally located 1 outside of cylinder, and the outer ring wing 3 forms monoblock type empennage, central tube 1, lattice fin around the outer rim of lattice fin 2 2, the outer ring wing 3 is integrally formed, and the outer ring wing 3 is hollow cylindrical structure.

Lattice fin 2 divides for multiple criss-cross lateral aerofoils 21 and longitudinal aerofoil 22, in lateral aerofoil 21, is located at center The lateral aerofoil 21 of position divides for left wing face 211 and right flank face 212, and longitudinal aerofoil 22 positioned at center divides for top airfoil 221 and lower aerofoil 222, the inner edge in left wing face 211 connect with the left side of 1 outer wall of central tube, the inner edge in right flank face 212 and central tube The right side of 1 outer wall connects, and the inner edge of top airfoil 221 is connect with the upside of 1 outer wall of central tube, the inner edge and center of lower aerofoil 222 The downside connection of 1 outer wall of cylinder.

The spacing dimension of the spacing dimension of lateral aerofoil 21 and longitudinal aerofoil 22 will guarantee the number of plies of lattice fin 2 not less than 2 Layer.

The leading edge sweep of lattice fin 2 is 45 °.

The internal diameter of central tube 1 is matched with the outer diameter that aircraft shrinks shape jet pipe, the diameter size of the outer ring wing 3 and aircraft master The matching of body structure size.

Central tube 1, lattice fin 2, the outer ring wing 3 is using PVC or aluminium alloy or steel.

As shown in figure 4, a kind of aircraft 5, has and folds front wing 6 and aircraft rear-fin stabilizer 4 of the present invention, in tail gear Center be aircraft 5 engine nozzle 7.

In conclusion lattice fin is combined integral by central tube, the outer ring wing in aircraft rear-fin stabilizer of the invention Formula empennage, and connect by central tube with body part, the outer ring wing makes grid be closed as a monolithic construction, and further increases The area in pneumatic face, lattice fin and the outer ring wing are pneumatic force generating mechanism, can carry out leading-edge sweep, aerofoil profile according to cruising speed The optimization design of section；In aircraft rear-fin stabilizer of the invention, multi-disc aerofoil is staggeredly combined, to expand in a limited space Effectively pneumatic face area；In aircraft rear-fin stabilizer of the invention, grid connects into an integrally closed structure, reinforces lattice fin Intensity, improve protection for lattice fin, outer ring wing itself can also expand the aerodynamic area of empennage；Aircraft of the invention is stablized Empennage, can the stabilized flight under the restrictive condition of the spaces such as launching tube for aircraft improve sufficiently large stabilizing moment and pneumatic Power；Without motion mechanism improves functional reliability, and reduces costs using monolithic construction, and the strength and stiffness of structure are good, Structure efficiency is high；Empennage integral structure, processing and aircraft in-site installation are simplified.

In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower" Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.

Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase Mutually combination.