CN210618451U - Deformable wing of unmanned aerial vehicle - Google Patents
Deformable wing of unmanned aerial vehicle Download PDFInfo
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- CN210618451U CN210618451U CN201921456081.0U CN201921456081U CN210618451U CN 210618451 U CN210618451 U CN 210618451U CN 201921456081 U CN201921456081 U CN 201921456081U CN 210618451 U CN210618451 U CN 210618451U
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Abstract
A deformable wing of an unmanned aerial vehicle relates to the field of advanced intelligent materials and comprises a nickel-titanium memory alloy framework, a wing skin, an electric heating excitation device, a force sensor and a basalt fiber thermal insulation layer, wherein the electric heating excitation device and the force sensor are arranged in the nickel-titanium memory alloy framework, and the basalt fiber thermal insulation layer is coated on the outer surface of the nickel-titanium memory alloy framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form an upward deformation wing framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form a downward deformation wing framework; the upward deformation wing frameworks and the downward deformation wing frameworks are arranged in a staggered mode to form wing frameworks; the wing skin is covered on the outer surface of the wing framework. The utility model discloses a deformation method of four kinds of flexible wings. The utility model discloses an intelligent material carries out bionic structure design to effectively reduce flight resistance and noise, improve energy efficiency, improve the cruising and the sprint ability of aircraft, and flight mobility.
Description
Technical Field
The utility model relates to an advanced intelligent material field relates to an unmanned aerial vehicle flexible wing particularly for fixed wing unmanned aerial vehicle.
Background
The wings of the existing fixed wing unmanned aerial vehicle are all rigid members, the working states of the wings are controlled by the traditional mechanical transmission mode among all parts of the wings, the working mode of the wings has many defects, and larger vibration noise and larger flight resistance can be generated in the process of ultrahigh-speed flight, so that the service life of the aircraft is reduced. The wing members are more in number, the weight of the airplane is increased, the flight resistance of the airplane is increased, energy waste and environmental pollution are caused, and the manufacturing cost of the airplane is increased. On some small-size fixed wing uavs, in order to reduce the manufacturing degree of difficulty, usually the wing is designed as a fixing device, so although can reduce the degree of difficulty of manufacturing the aircraft, the aircraft performance is restricted. In order to ensure the flight safety, all parts of the wing must have high working reliability, the traditional mechanical transmission mode is adopted, and in order to ensure the working reliability of a complex mechanism, the maintenance frequency of a daily gauge must be increased, so that the utilization rate of the airplane is reduced, and a large amount of time and labor cost are wasted. And the mechanical transmission is greatly influenced by the environment, and the mechanism is easy to lose efficacy under the extreme environment.
Disclosure of Invention
The utility model provides a solve above-mentioned problem, and provide a flexible wing of unmanned aerial vehicle.
A deformable wing of an unmanned aerial vehicle comprises a nickel-titanium memory alloy framework, a wing skin, an electric heating excitation device, a force sensor and a basalt fiber heat-insulating layer, wherein the electric heating excitation device and the force sensor are arranged in the nickel-titanium memory alloy framework, and the basalt fiber heat-insulating layer is coated on the outer surface of the nickel-titanium memory alloy framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form an upward deformation wing framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form a downward deformation wing framework; the upward deformation wing frameworks and the downward deformation wing frameworks are arranged in a staggered mode to form wing frameworks; the wing skin is covered on the outer surface of the wing framework.
A deformable wing of an unmanned aerial vehicle comprises a nickel-titanium memory alloy framework, a wing skin, a basalt fiber heat-insulating layer and a biasing spring, wherein the basalt fiber heat-insulating layer is coated on the outer surface of the nickel-titanium memory alloy framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form an upward deformation wing framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form a downward deformation wing framework; the upward deformation wing frameworks and the downward deformation wing frameworks are arranged in a staggered mode to form wing frameworks; the wing skin is covered on the outer surface of the wing framework, one end of the upward deformation wing framework is connected with a bias spring, and the other end of the bias spring is connected to the root of the wing; one end of the downward deformation wing framework is connected with a bias spring, and the other end of the bias spring is connected to the root of the wing.
A deformable wing of an unmanned aerial vehicle comprises a nickel-titanium memory alloy framework, a wing skin, an electric heating excitation device, a force sensor and a basalt fiber heat-insulating layer, wherein the electric heating excitation device and the force sensor are arranged in the nickel-titanium memory alloy framework, and the basalt fiber heat-insulating layer is coated on the outer surface of the nickel-titanium memory alloy framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form an upward deformation wingtip framework; a plurality of nickel-titanium memory alloy frameworks are arranged at intervals to form a downward deformation wingtip framework; the upwards deformed wingtip framework and the downwards deformed wingtip framework are arranged in a staggered mode to form a wingtip framework; the wing skin is coated on the outer surface of the wing tip framework.
The deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin, a deformable memory alloy spring set and a biasing spring set, wherein the wing skin is wrapped on the outer surface of the wing framework, one ends of the deformable memory alloy spring set and the biasing spring set are connected with the wing framework, and the other ends of the deformable memory alloy spring set and the biasing spring set are connected to the root of the wing.
The deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin and a heating and temperature control system, wherein the wing skin is coated on the outer surface of the wing framework, the wing skin is made of deformable memory alloy, and the heating and temperature control system is arranged on the inner surface of the wing skin.
The wing skin is made of a flexible deformable polyether-ether-ketone fiber composite material.
The wing skin is adhered to the wing framework by using an adhesive.
The wing skin is adhered to the wing tip framework by using an adhesive.
The nickel-titanium alloy memory skeleton is forged into a bow shape at the temperature of the temperature, and then is processed into an original shape at normal temperature. The nickel-titanium alloy has a shape memory function, so that when the shape of the wing needs to be changed, the airplane control system controls the electrothermal exciting device and the electrothermal exciting device in the installation position of the force sensor to excite the wing framework needing to be changed, and when the temperature reaches the shape transition point of the memory alloy, the shape of the wing is changed. In conclusion, the flying state of the airplane can be regulated and controlled by regulating and controlling the shape of the wings.
When the wing needs to be restored to the original shape, the wing is restored to the original position through the three restoration modes. In order to ensure that the wing skin and the wing framework do not interfere with each other when the temperature changes, a thermal insulation layer is wrapped on the wing framework. The heat insulating layer is made of basalt fiber.
Go up the deformation wing skeleton and the differential drive of downward deformation wing skeleton, will go up deformation wing skeleton and the excitation of down deformation wing skeleton grouping, the utility model discloses can make the deformable wing take place to warp from top to bottom or warp from front to back, also can not take place deformation by wing itself, only the wing tip takes place to warp from top to bottom.
A method for deforming a deformable wing of an unmanned aerial vehicle comprises the following steps:
1. the deformation method of differential driving of the upward deformation wing framework and the downward deformation wing framework comprises the following steps: training the upward deformation wing framework and the downward deformation wing framework to have opposite deformation directions; the method comprises the following specific steps:
1.1, the unmanned aerial vehicle control system controls the temperature control system to heat an upward deformation wing framework or a downward deformation wing framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upward deformation wing framework or the downward deformation wing framework is transformed correspondingly, and a flexible deformable wing skin which is adhered with the upward deformation wing framework and the downward deformation wing framework is driven to deform.
1.2, when the wing deformation of the unmanned aerial vehicle needs to be recovered, the unmanned aerial vehicle control system controls the temperature control system to heat the unheated upward deformation wing framework or downward deformation wing framework, when the temperature reaches the shape transformation point of the memory alloy, the upward deformation wing framework and the downward deformation wing framework are subjected to opposite shape transformation, the deformation wing frameworks of the opposite side are pulled back to the original position, and therefore the flexible deformable wing skin glued with the wing framework frames is driven to return to the original position. Namely, the framework of the upward deformation wing is heated and deformed firstly, the framework of the downward deformation wing is heated and deformed later, and the framework of the upward deformation wing is pulled back to the original position; the downward deformation wing framework is heated and deformed firstly, and then is heated and deformed after being deformed upwards, so that the downward deformation wing framework is pulled back to the original position.
2. A deformation method that the shape memory alloy wing framework and the flexible wing skin are mutually driven; the method comprises the following specific steps:
and 2.1, heating the upward deformation wing framework or the downward deformation wing framework which needs to change the shape by the unmanned aerial vehicle control system control temperature control system, and when the temperature reaches the shape transformation point of the memory alloy, enabling the shape of the upward deformation wing framework or the downward deformation wing framework to be transformed correspondingly, and driving the flexible deformable wing skin which is adhered with the wing framework to be deformed.
And 2.2, when the shape of the wing needs to be recovered, controlling a temperature control system in the flexible deformable wing skin, and driving the upwards deformed wing framework or the downwards deformed wing framework to recover the original shape through the flexible deformable wing skin.
3. The deformation method of the wing framework matched with the spring comprises the following steps: the method can be divided into two modes, specifically as follows:
3.1 bias type deformation method of shape memory alloy wing skeleton matched with bias spring: the method comprises the following specific steps:
3.1.1 the unmanned aerial vehicle control system controls the temperature control system to heat the upwards deformed wing framework or the downwards deformed wing framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the wing framework of the unmanned aerial vehicle is transformed correspondingly, and the flexible deformable wing skin glued with the wing framework is driven to deform.
3.1.2 when the shape of the wing needs to be recovered, the wing framework is pulled back to the original position under the action of the bias spring, so that the flexible deformable wing skin bonded on the wing framework is driven to recover the original position.
3.1.3 the deformation method of the wing framework and the flexible deformable wing skin, wherein two groups of springs are arranged at the root of the wing, one group is a deformable memory alloy spring group, and the other group is a bias spring group; the method comprises the following steps:
3.2, the unmanned aerial vehicle control system controls the temperature control system to heat the memory alloy spring set which needs to change the shape, and when the temperature reaches the shape transformation point of the memory alloy, the memory alloy spring set drives the wing framework of the unmanned aerial vehicle to generate corresponding shape transformation, so that the flexible deformable wing skin glued with the wing framework is driven to deform.
3.2.1, when the shape of the wing needs to be recovered, the wing framework is pulled back to the original position under the action of the bias spring, so that the flexible deformable wing skin bonded on the memory alloy framework is driven to recover to the original position.
4. The method for deforming the wingtip part of the unmanned aerial vehicle wing comprises the following steps that a rigid framework of the unmanned aerial vehicle wing and a flexible deformable wing skin are integrally formed, only the wingtip part deforms, and the method for deforming the wingtip part is divided into two forms: grouping the upwards deformed wingtip frameworks and the downwards deformed wingtip frameworks into groups to form a differential deformation method for driving each other; and the deformation method is characterized in that the upward deformation wingtip framework and the downward deformation wingtip framework are mutually driven with the flexible deformable wing skin.
4.1, grouping an upward deformation wingtip framework and a downward deformation wingtip framework into groups to be mutually driven by a differential deformation method, wherein the upward deformation wingtip framework and the downward deformation wingtip framework are trained to have opposite deformation directions; the method comprises the following specific steps:
4.1.1, the unmanned aerial vehicle control system controls the temperature control system to heat the upwards-deformed wingtip framework or the downwards-deformed wingtip framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upwards-deformed wingtip framework or the downwards-deformed wingtip framework is transformed into a corresponding shape, and the flexible deformable wingtip skin glued with the wingtip framework is driven to deform.
4.1.2, when the deformation of the wing tip of the unmanned aerial vehicle needs to be recovered, the unmanned aerial vehicle control system controls the temperature control system to heat the downward deformation wing tip framework or the upward deformation wing tip framework, when the temperature reaches the shape transformation point of the memory alloy, the downward deformation wing tip framework or the upward deformation wing tip framework is subjected to opposite shape transformation, the memory alloy wing tip framework is pulled back to the original position, and therefore the flexible deformable wing tip skin glued with the wing tip framework is driven to return to the original position. Heating and deforming the wing tip framework deformed upwards, heating and deforming the wing tip framework deformed downwards, and pulling the wing tip framework deformed upwards back to the original position; the downward deformation wingtip framework is heated and deformed firstly, and then the downward deformation wingtip framework is heated and deformed after being deformed upwards, so that the downward deformation wingtip framework is pulled back to the original position.
And 4.2, a deformation method that the wingtip skeleton and the flexible deformable skin are mutually driven. The method comprises the following specific steps:
4.2.1, the unmanned aerial vehicle control system controls the temperature control system to heat the upwards-deformed wingtip framework or the downwards-deformed wingtip framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upwards-deformed wingtip framework or the downwards-deformed wingtip framework is transformed into a corresponding shape, and the flexible deformable wingtip skin glued with the wingtip framework is driven to deform.
And 4.2.2, when the shape of the wingtip of the wing needs to be recovered, controlling a heating and temperature control system in the wingtip skin of the flexible deformable wing, and driving the wingtip framework to recover the original shape through the wingtip skin of the flexible deformable wing.
The utility model discloses the theory of operation:
the wing deformable memory alloy framework and the wing flexible deformable skin are glued together, the nickel-titanium memory alloy wing framework has a one-way memory function, and can deform under the stimulation of a certain temperature through training, so that the wing flexible deformable skin is driven to deform.
When the airplane is in a flying state, the sensor collects the stress information of the wings and feeds the stress information back to the airplane control center, and the control center controls a temperature control system in the wing framework according to the collected information, so that the shape of the wing framework is controlled, the wings maintain or change the flying posture of the airplane in an optimal shape, and the problem caused by the traditional mechanical transmission of the wings is thoroughly solved. When the deformation needs to be recovered, three ways can be adopted:
the method comprises the following steps: the deformable wing frameworks which are excited in groups and a group of memory alloy wing frameworks which have the opposite deformation trend to the former memory alloy wing frameworks are subjected to deformation opposite to the initial deformation after being excited by temperature, so that the flexible deformable wing skin is driven to restore to the original position.
The second method comprises the following steps: an electric heating excitation system is arranged in the flexible deformable wing skin, and the flexible deformable wing skin is deformed through temperature change, so that the wing deformable memory alloy framework glued with the flexible deformable wing skin is driven to recover the original position.
The third method comprises the following steps: a spring device is arranged in the wing deformable memory alloy framework, and after the wings of the unmanned aerial vehicle deform, the wings are pulled back to the original positions by the spring device.
The utility model has the advantages that:
1. the material for manufacturing the wing is flexible deformation material, and the wing skin and the wing framework are integrally formed, so that the manufacturing period is greatly shortened.
2. The traditional mechanical action of the trailing edge of each discrete wing is eliminated, so that the resistance and the noise are reduced, the energy efficiency is improved, and the energy conservation is facilitated.
3. The wing has a simple structure, does not have a complex mechanical transmission structure, reduces the failure rate of the wing, and reduces the maintenance difficulty and cost of the airplane.
Drawings
FIG. 1 is a schematic view of a nickel titanium memory alloy skeleton formed at low temperature.
FIG. 2 is a schematic diagram of a Ni-Ti memory alloy skeleton after the temperature reaches the temperature change point of 40 ℃.
FIG. 3 is a schematic view of the mounting positions of the electrothermal excitation device and the force sensor in the Ni-Ti memory alloy skeleton.
FIG. 4 is a cross-sectional view of a combination of a nickel-titanium memory alloy skeleton, an electrothermal actuator and force sensor mounting, and a basalt fiber thermal insulation layer.
FIG. 5 is a schematic view of a differential drive for a memory alloy airfoil frame.
Fig. 6 is a schematic view of the deformation of the morphing wing of the drone.
Fig. 7 is a schematic diagram of front and back deformation of a deformed wing-shaped memory alloy framework of the unmanned aerial vehicle in cooperation with a spring device.
Fig. 8 is a schematic diagram of the deformation of the tip of the morphing wing of the unmanned aerial vehicle, wherein the solid line part is the shape of the tip of the wing after the shape transformation is completed, and the dotted line part is the shape before the shape transformation.
Detailed Description
As shown in fig. 1, 2, 3, 4, 5 and 6, the deformable wing of the unmanned aerial vehicle comprises a nickel-titanium memory alloy framework 1, a wing skin, an electrothermal exciting device and force sensor 3 and a basalt fiber heat-insulating layer 4, wherein the electrothermal exciting device and force sensor 3 are arranged in the nickel-titanium memory alloy framework 1, and the basalt fiber heat-insulating layer 4 is coated on the outer surface of the nickel-titanium memory alloy framework 1; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form an upward deformation wing framework 11; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form a downward deformation wing framework 12; the upward deformation wing frameworks 11 and the downward deformation wing frameworks 12 are arranged in a staggered mode to form wing frameworks; the wing skin is covered on the outer surface of the wing framework.
As shown in fig. 7, the deformable wing of the unmanned aerial vehicle comprises a nickel-titanium memory alloy framework 1, a wing skin, a basalt fiber thermal insulation layer 4 and a bias spring 2, wherein the basalt fiber thermal insulation layer 4 is coated on the outer surface of the nickel-titanium memory alloy framework 1; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form an upward deformation wing framework 11; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form a downward deformation wing framework 12; the upward deformation wing frameworks 11 and the downward deformation wing frameworks 12 are arranged in a staggered mode to form wing frameworks; the wing skin is covered on the outer surface of the wing framework, one end of the upward deformation wing framework 11 is connected with the bias spring 2, and the other end of the bias spring 2 is connected to the root of the wing; one end of the downward deformation wing framework 12 is connected with a bias spring 2, and the other end of the bias spring 2 is connected with the root of the wing.
As shown in fig. 4 and 8, the deformable wing of the unmanned aerial vehicle comprises a nickel-titanium memory alloy framework 1, a wing skin, an electrothermal excitation device and force sensor 3 and a basalt fiber thermal insulation layer 4, wherein the electrothermal excitation device and force sensor 3 are arranged in the nickel-titanium memory alloy framework 1, and the basalt fiber thermal insulation layer 4 is coated on the outer surface of the nickel-titanium memory alloy framework 1; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form an upward deformation wingtip framework; a plurality of nickel-titanium memory alloy frameworks 1 are arranged at intervals to form a downward deformation wingtip framework; the upwards deformed wingtip framework and the downwards deformed wingtip framework are arranged in a staggered mode to form a wingtip framework; the wing skin is coated on the outer surface of the wing tip framework.
The deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin, a deformable memory alloy spring set and a biasing spring set, wherein the wing skin is wrapped on the outer surface of the wing framework, one ends of the deformable memory alloy spring set and the biasing spring set are connected with the wing framework, and the other ends of the deformable memory alloy spring set and the biasing spring set are connected to the root of the wing.
The deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin and a heating and temperature control system, wherein the wing skin is coated on the outer surface of the wing framework, the wing skin is made of deformable memory alloy, and the heating and temperature control system is arranged on the inner surface of the wing skin.
The wing skin is made of a flexible deformable polyether-ether-ketone fiber composite material.
The wing skin is adhered to the wing framework by using an adhesive.
The wing skin is adhered to the wing tip framework by using an adhesive.
The nickel titanium alloy memory skeleton 1 is forged into a bow shape as shown in fig. 2 at 200 to 300 ℃, and then processed into an original shape as shown in fig. 1 at normal temperature. Since the nickel-titanium alloy has the shape memory function, when the shape of the wing needs to be changed, the airplane control system controls the electrothermal exciting device in the electrothermal exciting device and the force sensor 3 to excite the wing framework needing to be changed, the electrothermal exciting device and the force sensor 3 are arranged at the middle dotted line position shown in fig. 3, and when the temperature reaches the shape transition point of the memory alloy, the shape of the wing is changed. In conclusion, the flying state of the airplane can be regulated and controlled by regulating and controlling the shape of the wings.
When the wing needs to be restored to the original shape, the wing is restored to the original position through the three restoration modes. In order to ensure that the wing skin and the wing framework do not interfere with each other when the temperature changes, a thermal insulation layer is wrapped on the wing framework. Basalt fibers are selected as the material of the heat insulation layer, and are shown in figure 4.
Go up morphing wing skeleton 11 and the differential drive of down morphing wing skeleton 12, will go up morphing wing skeleton 11 and the excitation of down morphing wing skeleton 12 grouping, the grouping condition is as shown in fig. 5, the utility model discloses can make the morphing wing take place warp from top to bottom, as shown in fig. 6, warp around as shown in fig. 7, also can not take place deformation for wing itself, only the wingtip takes place warp from top to bottom, as shown in fig. 8.
A method for deforming a deformable wing of an unmanned aerial vehicle comprises the following steps:
1. the deformation method of the upper deformation wing framework 11 and the lower deformation wing framework 12 in a differential driving mode comprises the following steps: the upward morphing wing framework 11 and the downward morphing wing framework 12 are trained to have opposite morphing directions; the method comprises the following specific steps:
1.1, the unmanned aerial vehicle control system controls the temperature control system to heat an upward deformation wing framework 11 or a downward deformation wing framework 12 which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upward deformation wing framework 11 or the downward deformation wing framework 12 is transformed correspondingly, and a flexible deformable wing skin which is adhered with the upward deformation wing framework 11 and the downward deformation wing framework 12 is driven to deform.
1.2, when the wing deformation of the unmanned aerial vehicle needs to be recovered, the unmanned aerial vehicle control system controls the temperature control system to heat the upward deformation wing framework 11 or the downward deformation wing framework 12 which are not heated, when the temperature reaches the shape transformation point of the memory alloy, the upward deformation wing framework 11 and the downward deformation wing framework 12 are in opposite shape transformation, the deformation wing framework of the opposite side is pulled back to the original position, and therefore the flexible deformable wing skin glued with the wing framework is driven to return to the original position. Namely, the upward deformation wing framework 11 is heated and deformed firstly, the downward deformation wing framework 12 is heated and deformed later, and the upward deformation wing framework 11 is pulled back to the original position; the downward deformation wing framework 12 is heated and deformed firstly, and the downward deformation wing framework 12 is pulled back to the original position after the upward deformation wing framework 11 is heated and deformed.
2. A deformation method that the shape memory alloy wing framework and the flexible wing skin are mutually driven; the method comprises the following specific steps:
2.1, the unmanned aerial vehicle control system controls the temperature control system to heat the upward deformation wing framework 11 or the downward deformation wing framework 12 which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upward deformation wing framework 11 or the downward deformation wing framework 12 is transformed correspondingly, and the flexible deformable wing skin glued with the wing framework is driven to deform.
And 2.2, when the shape of the wing needs to be restored, controlling a temperature control system in the flexible deformable wing skin, and driving the upwards deformed wing framework 11 or the downwards deformed wing framework 12 to restore the original shape through the flexible deformable wing skin.
3. The deformation method of the wing framework matched with the spring comprises the following steps: the method can be divided into two modes, specifically as follows:
3.1 bias type deformation method of shape memory alloy wing skeleton matched with bias spring: the method comprises the following specific steps:
3.1.1 the unmanned aerial vehicle control system controls the temperature control system to heat the upwards deformed wing framework 11 or the downwards deformed wing framework 12 which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the wing framework of the unmanned aerial vehicle is transformed correspondingly, and the flexible deformable wing skin glued with the wing framework is driven to deform.
3.1.2 when the shape of the wing needs to be recovered, the biasing spring 2 acts to pull the wing framework back to the original position, so that the flexible deformable wing skin bonded on the wing framework is driven to recover to the original position.
3.1.3 the deformation method of the wing framework and the flexible deformable wing skin, wherein two groups of springs are arranged at the root of the wing, one group is a deformable memory alloy spring group, and the other group is a bias spring group; the method comprises the following steps:
3.2, the unmanned aerial vehicle control system controls the temperature control system to heat the memory alloy spring set which needs to change the shape, and when the temperature reaches the shape transformation point of the memory alloy, the memory alloy spring set drives the wing framework of the unmanned aerial vehicle to generate corresponding shape transformation, so that the flexible deformable wing skin glued with the wing framework is driven to deform.
3.2.1, when the shape of the wing needs to be recovered, the wing framework is pulled back to the original position under the action of the bias spring, so that the flexible deformable wing skin bonded on the memory alloy framework is driven to recover to the original position.
4. The method for deforming the wingtip part of the unmanned aerial vehicle wing comprises the following steps that a rigid framework of the unmanned aerial vehicle wing and a flexible deformable wing skin are integrally formed, only the wingtip part deforms, and the method for deforming the wingtip part is divided into two forms: grouping the upwards deformed wingtip frameworks and the downwards deformed wingtip frameworks into groups to form a differential deformation method for driving each other; and the deformation method is characterized in that the upward deformation wingtip framework and the downward deformation wingtip framework are mutually driven with the flexible deformable wing skin.
4.1, grouping an upward deformation wingtip framework and a downward deformation wingtip framework into groups to be mutually driven by a differential deformation method, wherein the upward deformation wingtip framework and the downward deformation wingtip framework are trained to have opposite deformation directions; the method comprises the following specific steps:
4.1.1, the unmanned aerial vehicle control system controls the temperature control system to heat the upwards-deformed wingtip framework or the downwards-deformed wingtip framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upwards-deformed wingtip framework or the downwards-deformed wingtip framework is transformed into a corresponding shape, and the flexible deformable wingtip skin glued with the wingtip framework is driven to deform.
4.1.2, when the deformation of the wing tip of the unmanned aerial vehicle needs to be recovered, the unmanned aerial vehicle control system controls the temperature control system to heat the downward deformation wing tip framework or the upward deformation wing tip framework, when the temperature reaches the shape transformation point of the memory alloy, the downward deformation wing tip framework or the upward deformation wing tip framework is subjected to opposite shape transformation, the memory alloy wing tip framework is pulled back to the original position, and therefore the flexible deformable wing tip skin glued with the wing tip framework is driven to return to the original position. Heating and deforming the wing tip framework deformed upwards, heating and deforming the wing tip framework deformed downwards, and pulling the wing tip framework deformed upwards back to the original position; the downward deformation wingtip framework is heated and deformed firstly, and then the downward deformation wingtip framework is heated and deformed after being deformed upwards, so that the downward deformation wingtip framework is pulled back to the original position.
And 4.2, a deformation method that the wingtip skeleton and the flexible deformable skin are mutually driven. The method comprises the following specific steps:
4.2.1, the unmanned aerial vehicle control system controls the temperature control system to heat the upwards-deformed wingtip framework or the downwards-deformed wingtip framework which needs to change the shape, when the temperature reaches the shape transformation point of the memory alloy, the shape of the upwards-deformed wingtip framework or the downwards-deformed wingtip framework is transformed into a corresponding shape, and the flexible deformable wingtip skin glued with the wingtip framework is driven to deform.
And 4.2.2, when the shape of the wingtip of the wing needs to be recovered, controlling a heating and temperature control system in the wingtip skin of the flexible deformable wing, and driving the wingtip framework to recover the original shape through the wingtip skin of the flexible deformable wing.
The utility model discloses the theory of operation:
the wing deformable memory alloy framework and the wing flexible deformable skin are glued together, the nickel-titanium memory alloy wing framework has a one-way memory function, and can deform under the stimulation of a certain temperature through training, so that the wing flexible deformable skin is driven to deform.
When the airplane is in a flying state, the sensor collects the stress information of the wings and feeds the stress information back to the airplane control center, and the control center controls a temperature control system in the wing framework according to the collected information, so that the shape of the wing framework is controlled, the wings maintain or change the flying posture of the airplane in an optimal shape, and the problem caused by the traditional mechanical transmission of the wings is thoroughly solved. When the deformation needs to be recovered, three ways can be adopted:
the method comprises the following steps: the deformable wing frameworks which are excited in groups and a group of memory alloy wing frameworks which have the opposite deformation trend to the former memory alloy wing frameworks are subjected to deformation opposite to the initial deformation after being excited by temperature, so that the flexible deformable wing skin is driven to restore to the original position.
The second method comprises the following steps: an electric heating excitation system is arranged in the flexible deformable wing skin, and the flexible deformable wing skin is deformed through temperature change, so that the wing deformable memory alloy framework glued with the flexible deformable wing skin is driven to recover the original position.
The third method comprises the following steps: a spring device is arranged in the wing deformable memory alloy framework, and after the wings of the unmanned aerial vehicle deform, the wings are pulled back to the original positions by the spring device.
Claims (7)
1. The utility model provides a but unmanned aerial vehicle deformation wing which characterized in that: the aircraft wing comprises a nickel-titanium memory alloy framework (1), a wing skin, an electrothermal excitation device and force sensor (3) and a basalt fiber thermal insulation layer (4), wherein the electrothermal excitation device and the force sensor (3) are arranged in the nickel-titanium memory alloy framework (1), and the basalt fiber thermal insulation layer (4) is coated on the outer surface of the nickel-titanium memory alloy framework (1); a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form an upward deformation wing framework (11); a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form a downward deformation wing framework (12); the upward deformation wing frameworks (11) and the downward deformation wing frameworks (12) are arranged in a staggered manner to form a wing framework; the wing skin is covered on the outer surface of the wing framework.
2. The utility model provides a but unmanned aerial vehicle deformation wing which characterized in that: a deformable wing of an unmanned aerial vehicle comprises a nickel-titanium memory alloy framework (1), a wing skin, a basalt fiber thermal insulation layer (4) and a bias spring (2), wherein the basalt fiber thermal insulation layer (4) is coated on the outer surface of the nickel-titanium memory alloy framework (1); a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form an upward deformation wing framework (11); a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form a downward deformation wing framework (12); the upward deformation wing frameworks (11) and the downward deformation wing frameworks (12) are arranged in a staggered manner to form a wing framework; the outer surface of the wing framework is coated with the wing skin, one end of the upward deformation wing framework (11) is connected with the bias spring (2), and the other end of the bias spring (2) is connected to the root of the wing; one end of the downward deformation wing framework (12) is connected with a bias spring (2), and the other end of the bias spring (2) is connected to the root of the wing.
3. The utility model provides a but unmanned aerial vehicle deformation wing which characterized in that: a deformable wing of an unmanned aerial vehicle comprises a nickel-titanium memory alloy framework (1), a wing skin, an electric heating excitation device, a force sensor (3) and a basalt fiber thermal insulation layer (4), wherein the electric heating excitation device and the force sensor (3) are arranged in the nickel-titanium memory alloy framework (1), and the basalt fiber thermal insulation layer (4) is coated on the outer surface of the nickel-titanium memory alloy framework (1); a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form an upward deformation wingtip framework; a plurality of nickel-titanium memory alloy frameworks (1) are arranged at intervals to form a downward deformation wingtip framework; the upwards deformed wingtip framework and the downwards deformed wingtip framework are arranged in a staggered mode to form a wingtip framework; the wing skin is coated on the outer surface of the wing tip framework.
4. The utility model provides a but unmanned aerial vehicle deformation wing which characterized in that: the deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin, a deformable memory alloy spring set and a biasing spring set, wherein the wing skin is wrapped on the outer surface of the wing framework, one ends of the deformable memory alloy spring set and the biasing spring set are connected with the wing framework, and the other ends of the deformable memory alloy spring set and the biasing spring set are connected to the root of the wing.
5. The utility model provides a but unmanned aerial vehicle deformation wing which characterized in that: the deformable wing of the unmanned aerial vehicle comprises a wing framework, a wing skin and a heating and temperature control system, wherein the wing skin is coated on the outer surface of the wing framework, the wing skin is made of deformable memory alloy, and the heating and temperature control system is arranged on the inner surface of the wing skin.
6. A transformable wing for unmanned aerial vehicles according to claim 1 or 2 or 3 or 4 or 5, characterized in that: the wing skin is made of a flexible deformable polyether-ether-ketone fiber composite material.
7. A transformable wing for unmanned aerial vehicles according to claim 1 or 2 or 3 or 4 or 5, characterized in that: the wing skin is adhered to the wing framework by using an adhesive.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201921456081.0U CN210618451U (en) | 2019-09-04 | 2019-09-04 | Deformable wing of unmanned aerial vehicle |
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| CN201921456081.0U CN210618451U (en) | 2019-09-04 | 2019-09-04 | Deformable wing of unmanned aerial vehicle |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110422316A (en) * | 2019-09-04 | 2019-11-08 | 吉林大学 | A kind of deformable wing of unmanned plane and its deformation method |
| CN115571324A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
-
2019
- 2019-09-04 CN CN201921456081.0U patent/CN210618451U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110422316A (en) * | 2019-09-04 | 2019-11-08 | 吉林大学 | A kind of deformable wing of unmanned plane and its deformation method |
| CN115571324A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
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