阅读说明：本技术 一种自适应弹翼结构 (Self-adaptive missile wing structure ) 是由 郑艳军 王海峰 于 2020-12-06 设计创作，主要内容包括：本发明提供了一种自适应弹翼结构,包含记忆合金杆、连杆机构和弹翼,所述的弹翼铰接在飞行器上,所述的记忆合金杆一端固连在飞行器上,另一端通过连杆机构连接弹翼,且连杆机构与弹翼铰接,连杆机构和弹翼的铰接轴与飞行器和弹翼的铰接轴不同轴；所述的记忆合金受控伸缩,带动弹翼转动；所述的弹翼外壳包括若干变形区和固定区,变形区和固定区交替设置,变形区采用记忆合金制成,受控变形。本发明在减轻重量、降低临界载荷、改善雷达散射界面以及尽可能增大升阻比等方面存在很大的优势和潜力。(The invention provides a self-adaptive missile wing structure, which comprises a memory alloy rod, a link mechanism and a missile wing, wherein the missile wing is hinged on an aircraft, one end of the memory alloy rod is fixedly connected on the aircraft, the other end of the memory alloy rod is connected with the missile wing through the link mechanism, the link mechanism is hinged with the missile wing, and a hinged shaft of the link mechanism and the missile wing is not coaxial with a hinged shaft of the aircraft and the missile wing; the memory alloy is controlled to stretch and retract to drive the missile wing to rotate; the missile wing shell comprises a plurality of deformation areas and fixing areas, wherein the deformation areas and the fixing areas are alternately arranged, and the deformation areas are made of memory alloy and controlled to deform. The invention has great advantages and potentials in the aspects of reducing weight, reducing critical load, improving radar scattering interface, increasing lift-drag ratio as much as possible and the like.)

1. A self-adaptive missile wing structure comprises a memory alloy rod, a link mechanism and a missile wing, and is characterized in that the missile wing is hinged on an aircraft, one end of the memory alloy rod is fixedly connected on the aircraft, the other end of the memory alloy rod is connected with the missile wing through the link mechanism, the link mechanism is hinged with the missile wing, and a hinged shaft of the link mechanism and the missile wing is not coaxial with a hinged shaft of the aircraft and the missile wing; the memory alloy is controlled to stretch and retract to drive the missile wing to rotate; the missile wing shell comprises a plurality of deformation areas and fixing areas, wherein the deformation areas and the fixing areas are alternately arranged, and the deformation areas are made of memory alloy and controlled to deform.

2. The adaptive missile wing structure of claim 1, wherein the memory alloy is TiNi shape memory alloy, and the temperature shape of the memory alloy is changed by applying current.

3. The adaptive missile wing structure of claim 1 further comprises a base, wherein the base is provided with a fixed end, one end of the memory alloy rod is welded on the fixed end, the other end of the memory alloy rod is fixedly connected to the middle of the connecting rod, and two ends of the connecting rod are connected with the missile wing through the missile wing rotating frame.

4. The adaptive missile wing structure of claim 1, wherein the missile wing deforms up and down when the same current is applied to the front edge and the rear edge of the missile wing; when different currents are applied to the front edge and the rear edge of the missile wing, the missile wing twists.

5. The adaptive missile wing structure of claim 1, wherein the deformation zone comprises upper and lower wall surfaces and memory alloy blocks fixedly supported on both sides, and each memory alloy block is independently powered for bending and torsional deformation of the missile wing.

Technical Field

The invention belongs to the field of deformation wings, and particularly relates to a missile wing structure.

Background

The traditional driving modes of missile wing folding, unfolding and deformation mainly comprise a fire control type driving mode, a hydraulic driving mode, a motor type driving mode and a torsion spring type driving mode. The fire control type driving mode is to drive the mechanism to move by using instantaneous high-temperature and high-pressure airflow generated when explosives explode. The mode has larger shock impact during explosion, influences the stability of the aircraft and is easy to generate pollution. The hydraulic drive can output larger thrust or torque, and low-speed and large-tonnage operation is realized. However, the hydraulic source is large in volume and sensitive to environmental temperature change, and is not suitable for working at high temperature or low temperature. The motor type driving precision is high, and the precise control is realized according to the setting of parameters. However, the motor type drive occupies a large volume, and the motor generates electromagnetic waves during operation, so that the flight control of the aircraft is influenced to a certain extent. The torsion spring type driving mode has a simple structure and can not generate electromagnetic interference, but the phenomenon of torsion and non-return frequently occurs. Therefore, the research on a new unfolding deformation driving mechanism of the missile wing is of great significance. The novel idea is to use intelligent materials as drivers or to combine the intelligent materials with structural materials, so that the structure is miniaturized and has a deformation function, or the intelligent materials have double functions of driving materials and structural materials, so that the structure is most compact and light.

At present, the piezoelectric actuator and the shape memory alloy actuator are mainly widely applied. From the performance of the actuator, the piezoelectric actuator is accurate in control and high in response speed, but the existing piezoelectric actuator is limited in performance, can generate small control force, and is difficult to generate enough wing deformation when applied to the wing surface deformation control technology. The shape memory alloy actuator has simple structure, can generate larger control force and is easy to realize the integrated design with the wing.

After the traditional missile wing is unfolded, the geometrical shape of the missile wing is basically determined and unchanged, the system model is basically fixed, and only some specific flights can be carried out and some special tasks can be completed in the same atmospheric environment, so that the flight state of the missile wing can not be flexibly changed in different environments. The aircraft has good maneuverability, and the penetration capacity can be obviously improved, the geometrical shape of the missile wing of the traditional aircraft is almost unchanged, and certain maneuverability, such as sudden change of flight path, attack angle, flight speed and the like, is difficult to implement at the task end.

Therefore, in view of the need for increasing survival and defense capacity, it is urgently required to develop a missile wing capable of changing a corresponding shape according to a specific task and having a better survival in continuous change. Under the background of the demand, the traditional structural materials in structural design cannot meet the development demand, and the core technology of future development is to develop an intelligent self-adaptive missile wing structure which can be controlled according to instructions and can generate preset deformation.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention provides a self-adaptive missile wing structure which is driven by a memory alloy and can deform according to a command.

The technical scheme adopted by the invention for solving the technical problems is as follows: a self-adaptive missile wing structure comprises a memory alloy rod, a connecting rod mechanism and a missile wing.

The missile wing is hinged on the aircraft, one end of the memory alloy rod is fixedly connected on the aircraft, the other end of the memory alloy rod is connected with the missile wing through a link mechanism, the link mechanism is hinged with the missile wing, and a hinged shaft of the link mechanism and the missile wing is not coaxial with a hinged shaft of the aircraft and the missile wing; the memory alloy is controlled to stretch and retract to drive the missile wing to rotate; the missile wing shell comprises a plurality of deformation areas and fixing areas, wherein the deformation areas and the fixing areas are alternately arranged, and the deformation areas are made of memory alloy and controlled to deform.

The memory alloy adopts TiNi shape memory alloy, and the temperature shape of the memory alloy is changed by applying current.

The invention also comprises a base, wherein a fixed end is arranged on the base, one end of the memory alloy rod is welded on the fixed end, the other end of the memory alloy rod is fixedly connected to the middle part of the connecting rod, and two ends of the connecting rod are connected with the missile wing through the missile wing rotating frame.

The missile wing is provided with a pin hole, the aircraft is provided with a hole, a spring and a limiting pin are arranged in the hole, the spring is in a compression state when the missile wing is folded, and the spring pushes the limiting pin into the pin hole on the missile wing after the missile wing is unfolded in place to lock the missile wing.

The front edge and the rear edge of the missile wing are applied with the same current, so that the missile wing deforms up and down; when different currents are applied to the front edge and the rear edge of the missile wing, the missile wing twists.

The deformation zone comprises memory alloy blocks which are fixedly supported by the upper wall surface, the lower wall surface and two sides, and each memory alloy block is independently powered and used for bending and twisting deformation of the missile wing.

The invention has the beneficial effects that:

the self-adaptive missile wing capable of being actively deformed adopts the shape memory alloy as a driver, and the TiNi shape memory alloy is electrified with currents with different intensities to change the wing shape according to the flight condition, so that the optimal aerodynamic characteristics are obtained. Compared with the conventional control surface, the self-adaptive missile wing has great advantages and potentials in the aspects of reducing weight, reducing critical load, improving radar scattering interface, increasing lift-drag ratio as much as possible and the like.

Drawings

FIG. 1 is a schematic view of a missile wing deployment configuration;

FIG. 2 is a schematic view of the deformation of the end face of the missile wing;

FIG. 3 is a schematic structural diagram of a TiNi memory alloy block.

Detailed Description

The present invention will be further described with reference to the following drawings and examples, which include, but are not limited to, the following examples.

The invention provides a self-adaptive missile wing structure which comprises a base 1, a fixed end 2, a TiNi shape memory alloy rod 3, a rotating shaft sleeve 4, a spring limiting pin 5, a connecting rod mechanism 6 and a wing 7, wherein the wing 7 comprises a TiNi shape memory alloy block 8 and a wing thin shell 9.

The base 1 on have stiff end 2, 3 one end welding of TiNi shape memory alloy pole are on stiff end 2, the other end welding is in the middle part of connecting rod 6, 6 both ends of connecting rod are through pin joint missile wing 7 rotating turret, do not take place the dislocation. The missile wing 7 is rotatably connected with the base 1 through a rotating shaft, a pin hole is formed in the missile wing 7, a hole is formed in the base 1, a spring and a limiting pin are arranged in the hole, the spring is in a compression state when the missile wing is folded, and the limiting pin 5 is pushed into the pin hole in the missile wing 7 by the spring on the base 1 after the missile wing 7 is unfolded in place, so that the missile wing is locked. The missile wing 7 comprises a deformation area and a fixing area, the deformation area and the fixing area are alternately connected, the deformation area is composed of an upper wall surface thin plate 9, a lower wall surface thin plate 9 and TiNi memory alloy blocks 8 which are fixedly supported on two sides, the TiNi memory alloy blocks 8 are arranged at intervals, the memory alloys on the two sides of the deformation area are independently supplied with power and are used for bending and torsional deformation of the missile wing 7, the TiNi memory alloy blocks 8 which are fixedly supported on the two sides are provided with current with the same strength, the bending deformation effect is achieved, and the torsional deformation effect is achieved when the current with different strengths is applied to the two sides.

The self-adaptive missile wing structure provided by the invention adopts shape memory alloy as a driver to unfold and deform the missile wing, and the specific implementation steps are as follows:

need carry out the ohmic heating to TiNi shape memory alloy pole 3 when playing wing 7 and expanding, TiNi shape memory alloy pole 3 can realize the heating shrinkage, the effect of cooling extension, the dependent variable is big, can remember the reconversion completely under 5 ~ 8% dependent variable, drive 6 linear motion of connecting rod to preset position, make play wing 7 expand to playing the rear end through pivot 4 by playing the front end fold condition, play wing 7 rotates to expand behind the maximum position, by 5 auto-locks of spring spacer pin.

When the missile wing 7 generates a bending deformation effect, the TiNi memory alloy blocks 8 at the same positions at the two sides of a deformation region need to be electrified with the same intensity current, and the TiNi memory alloy blocks 8 arranged at the same side at intervals are electrified with different intensity currents, so that the upper wall surface thin plate 9 and the lower wall surface thin plate 9 generate bending deformation, and the whole missile wing generates a bending deformation effect; the missile wing 7 generates a torsional deformation effect, currents with different intensities need to be conducted on the TiNi memory alloy blocks 8 at the same positions on the two sides of the deformation region, wherein the current intensities are different only by enabling the two sides of the front edge and the rear edge to generate a current intensity difference, and the current intensity of the front edge is higher than that of the rear edge. The other side is opposite.

According to the change of the flying speed of the missile, the TiNi shape memory alloy at different positions is controlled by instructions to be supplied with currents with different strengths so as to control the folding, unfolding and deformation of the missile wing, and the optimal flying state is achieved.