CN212921971U - Aircraft - Google Patents

Abstract

The utility model provides an aircraft, including collapsible rotor device, collapsible rotor device includes: the device comprises a first rotor arm, a second rotor arm, a fixed chassis, a first rotating shaft, a steering engine, a first connecting rod group and a second connecting rod group; the first rotor arm and the second rotor arm are respectively connected with the fixed chassis in a sliding manner; the first rotating shaft is arranged on the fixed chassis; the steering engine is arranged on the first rotating shaft and can drive the first rotating shaft to rotate; one end of a first connecting rod group is connected with the first rotating shaft, the other end of the first connecting rod group is connected with the first rotating shaft, the first connecting rod group comprises a plurality of movable joints, and the first connecting rod group can be driven by the first rotating shaft to swing in a reciprocating mode; second connecting rod group one end with first pivot is connected, the other end with the second rotor arm is connected, second connecting rod group includes a plurality of freely movable joints, first connecting rod group can carry out reciprocating swing under the drive of first pivot.

Description

Aircraft

Technical Field

The utility model belongs to the aviation field, concretely relates to aircraft.

Background

The aircraft is operated at high altitude for artificial rainfall and the like, the aircraft adopts the conventional layout of straight wings and T-shaped empennage, the fixed-point vertical take-off and landing function under the condition of complex terrain is realized by additionally installing a rotor system for providing vertical lift force on an aircraft platform with fixed wings, moreover, the high-altitude operation is usually carried out under the condition of complex weather, correspondingly, under the condition of high humidity or low temperature, the surface of the aircraft is easy to freeze, the weight of the aircraft body is increased after the aircraft is frozen, the gravity center of the aircraft body is unstable, unpredictable influence is generated on the flight, action and performance of the aircraft, and even a flight accident is caused; at the same time, the aerodynamic profile of the aircraft is destroyed, increasing the drag and reducing the lift, leading to harmful vibrations.

The existing aircraft enters high altitude through the added rotor wing device and then stably and flatly flies at the moment and starts to operate, however, the added rotor wing device can interfere the flatly flying of the aircraft and brings resistance to the whole aircraft, so that the power consumption of the aircraft is increased, and the aircraft mostly adopts a series of deicing methods such as a hot air deicing system and the like to uniformly deice an ice layer on the aircraft.

Disclosure of Invention

Not enough to prior art exists, the utility model aims to provide an aircraft solves among the prior art rotor device and can disturb the aircraft and go flat to it is too big to bring resistance and deicing power consumption for the aircraft is whole, needs additionally to increase power generation system's problem.

In order to solve the technical problem, the utility model discloses a following technical scheme realizes, an aircraft, including collapsible rotor device, collapsible rotor device includes: the device comprises a first rotor arm, a second rotor arm, a fixed chassis, a first rotating shaft, a steering engine, a first connecting rod group and a second connecting rod group; the first rotor arm and the second rotor arm are respectively connected with the fixed chassis in a sliding manner; the first rotating shaft is arranged on the fixed chassis; the steering engine is arranged on the first rotating shaft and can drive the first rotating shaft to rotate; one end of a first connecting rod group is connected with the first rotating shaft, the other end of the first connecting rod group is connected with the first rotating shaft, the first connecting rod group comprises a plurality of movable joints, and the first connecting rod group can be driven by the first rotating shaft to swing in a reciprocating mode; second connecting rod group one end with first pivot is connected, the other end with the second rotor arm is connected, the second connecting rod group includes a plurality of freely movable joints, the second connecting rod group can carry out reciprocating swing under the drive of first pivot.

The aircraft still includes defroster, defroster includes detector and heater, the detector is established on the surface of aircraft wing covering, whether the detector is used for surveying on the surface of aircraft wing covering icing, the heater is located the detector with between the aircraft wing covering, with the detector electricity is connected, the heater includes the zone of heating, the heater is used for detaching the ice sheet on the aircraft wing covering.

The first connecting rod group comprises a first connecting rod, a second connecting rod and a first sleeve rod, one end of the first connecting rod is fixedly connected with the first rotor wing arm, a first movable joint is arranged at the other end of the first connecting rod and one end of the second connecting rod, a second movable joint is arranged at the other end of the second connecting rod and one end of the first sleeve rod, the other end of the first sleeve rod is arranged on the first rotating shaft, and when the steering engine drives the first rotating shaft to rotate in the positive direction, the first connecting rod group can drive the first rotor wing arm to rotate towards the first direction; when the steering engine drives the first rotary shaft to rotate reversely, the first connecting rod group can drive the first rotary wing arm to rotate towards a second direction, and the first direction is opposite to the second direction; the second connecting rod group comprises a third connecting rod, a fourth connecting rod, a fifth connecting rod and a second sleeve rod, one end of the third connecting rod is fixedly connected with the second rotor wing arm, a third movable joint is arranged at the other end of the third connecting rod and one end of the fourth connecting rod, a fourth movable joint is arranged at the other end of the fourth connecting rod and one end of the fifth connecting rod, a fifth movable joint is arranged at the other end of the fifth connecting rod and one end of the second sleeve rod, the other end of the second sleeve rod is arranged on the first rotating shaft, when the steering engine drives the first rotating shaft to rotate in the forward direction, the second connecting rod group can drive the second rotor wing arm to rotate in the second direction, and when the steering engine drives the first rotating shaft to rotate in the reverse direction, the second connecting rod group can drive the second rotor wing arm to rotate in the first direction.

When first pivot forward rotated, the contained angle scope of first rotor arm and second rotor arm opening angle was: 130 degrees to 180 degrees; when first rotor shaft antiport, the contained angle scope of first rotor arm and second rotor arm opening angle does: 0 to 30 degrees.

The fixed chassis comprises an upper chassis, a lower chassis, a first connecting lug, a second connecting lug and a second rotating shaft arranged between the upper chassis and the lower chassis, wherein the first connecting lug and the second connecting lug are respectively sleeved on the second rotating shaft.

And the first rotor arm and the second rotor arm are respectively provided with a rotor at one end far away from the fixed chassis.

The foldable rotor wing devices are arranged in two groups and are respectively arranged along the extending direction of the aircraft body, and when the two groups of foldable rotor wing devices are in a withdrawing state, the two groups of foldable rotor wing devices are staggered up and down in the aircraft body.

The heater also comprises an inner heat insulation layer, an outer insulation layer and an overheating protection layer which are respectively arranged on two sides of the heating layer, the inner heat insulation layer is arranged on one side close to the aircraft wing skin, the outer insulation layer is arranged on one side close to the detector, and the heating layer is a metal heating layer; the anti-abrasion protective layer wraps the inner heat insulation layer, the heating layer and the outer insulation layer; the overheating protection layer is arranged between the aircraft wing skin and the inner heat insulation layer.

The deicing devices are arranged on the outer surface of the aircraft wing skin at intervals.

The deicing device further comprises a camera, and the camera is arranged on the outer surface of the aircraft wing skin and close to the aircraft fuselage.

Compared with the prior art, the utility model, following technological effect has:

the aircraft of the utility model is provided with a foldable rotor wing device which is respectively arranged in the extending direction of the aircraft body, when the rotor wing arms are in a withdrawing state and need to be unfolded, the steering engine drives the first rotating shaft to rotate positively, the first connecting rod group drives the first rotor wing arms to be unfolded, and the second connecting rod group drives the second rotor wing arms to be unfolded; when the rotor wing needs to be retracted when in an unfolded state, the steering engine drives the first rotating shaft to rotate reversely, the first connecting rod group drives the first rotor wing arm to be retracted, and the second connecting rod group drives the second rotor wing arm to be retracted; the foldable retraction and the unfolding of the rotor wing can be realized, so that the rotor wing state required by the aircraft in different flight phases is met.

(II) the utility model discloses an aircraft is equipped with defroster, through set up the heater on the surface at aircraft wing covering and set up the detector on the heater, the heater includes the zone of heating, the zone of heating is connected with the detector electricity, the detector can obtain the signal of the freezing signal of aircraft surface, and transmit this signal of telecommunication for the zone of heating, the zone of heating can be based on this signal of telecommunication start work and to its place regional deicing, the fixed point deicing to the aircraft has been realized to the heat production through the zone of heating, the unified heating method in the traditional technique has been avoided, the reduction of very big degree the consumption of aircraft.

(III) the utility model discloses a collapsible rotor device is through setting up first connecting rod group and second connecting rod group, when realizing pivot forward rotation, when rotor device expandes promptly, the scope of the open angle of first rotor arm and second rotor arm does: 130-180 degrees, can adapt to different air flow speeds in the air.

(IV) the utility model discloses an aircraft simple structure, self weight are little, can the effectual load that reduces the aircraft to reduce the aircraft consumption.

(V) the utility model discloses a defroster sets up the camera through being close to the position of fuselage at the aircraft wing, and the camera can shoot the freezing position and the deicing effect of aircraft for the staff carries out real-time supervision to the deicing effect, and the staff can be according to the timely unusual heater of discovery deicing of the image information who shoots, and maintains or changes this heater, guarantees the normal clear of deicing work.

(VI) the utility model discloses an aircraft can be through defroster fixed point deicing on the one hand through defroster, reduces the aircraft and freezes the reduction of back aerodynamic characteristic to avoided the complete machine to lead to the focus unstability because freezing weight increases, this defroster consumption of on the other hand is less relatively, weight and the consumption that can effectual reduction aircraft.

Drawings

Fig. 1 is a schematic view of the overall structure of the aircraft of the present invention at the time of ascent;

fig. 2 is a schematic view of the overall structure of the aircraft of the present invention at the time of level flight;

fig. 3 is a schematic view of the overall structure of the foldable rotor device of the present invention;

fig. 4 is a schematic view of the overall structure of the deicing device of the present invention;

figure 5 is a schematic structural view of the collapsible rotor apparatus of the present invention in a retracted state;

figure 6 is a schematic structural view of the foldable rotor device of the present invention in an unfolded state;

fig. 7 is an exploded view of the stationary base plate of the present invention;

figure 8 is a top view of the collapsible rotor apparatus of the present invention within the fuselage in a retracted state;

figure 9 is a front view of the collapsible rotor apparatus of the present invention in a retracted state within the fuselage.

The meaning of the individual reference symbols in the figures is:

1-foldable rotor wing device, 2-deicer, 3-aircraft wing skin, 4-ice layer, 5-rotor wing, 6-aircraft fuselage, 7-camera;

101-a first rotor arm, 102-a second rotor arm, 103-a fixed chassis; 104-a first rotating shaft, 105-a steering engine, 106-a first connecting rod group, 107-a second connecting rod group;

1031-upper chassis, 1032-lower chassis, 1033-first connecting lug, 1034-second connecting lug and 1035-second rotating shaft;

1061-a first link, 1062-a second link, 1063-a first loop bar, 1064-a first movable joint, 1065-a second movable joint;

1071-third connecting rod, 1072-fourth connecting rod, 1073-fifth connecting rod, 1074-second loop bar, 1075-third movable joint, 1076-fourth movable joint, 1077-fifth movable joint;

201-detector, 202-heater;

2021-heating layer, 2022-inner insulating layer, 2023-outer insulating layer, 2024-anti-abrasion protective layer, 2025-overheating protective layer.

The following examples are provided to explain the present invention in further detail.

Detailed Description

The following embodiments of the present invention are given, and it should be noted that the present invention is not limited to the following embodiments, and all the equivalent transformations made on the basis of the technical solution of the present application all fall into the protection scope of the present invention.

Example (b):

the present embodiment presents an aircraft, as shown in fig. 1-9, comprising a foldable rotor apparatus 1 comprising: a first rotor arm 101, a second rotor arm 102, a fixed chassis 103, a first rotating shaft 104, a steering engine 105, a first connecting rod group 106 and a second connecting rod group 107; the first rotor arm 101 and the second rotor arm 102 are respectively connected with the fixed chassis 103 in a sliding manner; the first rotating shaft 104 is arranged on the fixed chassis 103; the steering engine 105 is arranged on the first rotating shaft 104 and can drive the first rotating shaft 104 to rotate; one end of a first connecting rod group 106 is connected with the first rotating shaft 104, the other end of the first connecting rod group 106 is connected with the first rotor arm 101, the first connecting rod group 106 comprises a plurality of movable joints, and the first connecting rod group 106 can be driven by the first rotating shaft 104 to swing in a reciprocating manner; one end of the second link group 107 is connected to the first rotating shaft 104, the other end of the second link group 107 is connected to the second rotor arm 102, the second link group 107 includes a plurality of movable joints, and the second link group 107 can swing back and forth under the driving of the first rotating shaft 104.

The foldable rotor wing devices of the aircraft are respectively arranged in the extending direction of the aircraft body, when the foldable rotor wing needs to be unfolded in a withdrawing state, the steering engine drives the first rotating shaft to rotate positively, the first connecting rod group drives the first rotor wing arm to be unfolded, and the second connecting rod group drives the second rotor wing arm to be unfolded; when the rotor wing needs to be retracted when in an unfolded state, the steering engine drives the first rotating shaft to rotate reversely, the first connecting rod group drives the first rotor wing arm to be retracted, and the second connecting rod group drives the second rotor wing arm to be retracted; the foldable retraction and the unfolding of the rotor wing can be realized, so that the rotor wing state required by the aircraft in different flight phases is met.

The first rotating shaft rotates clockwise in a forward direction, the first rotating shaft rotates anticlockwise in a reverse direction, the first rotating direction is clockwise rotation, and the second rotating direction is anticlockwise rotation.

As a preferable solution of this embodiment, the aircraft further includes a deicing device 2, the deicing device includes a detector 201 and a heater 202, the detector 201 is disposed on the outer surface of the aircraft wing skin 3, the detector 201 is used for detecting whether the ice is formed on the outer surface of the aircraft wing skin 3 and the thickness of the ice layer 4, the heater 202 is disposed between the detector 201 and the aircraft wing skin 3 and is electrically connected to the detector 201, the heater 202 includes a heating layer 2021, and the heater 202 is used for removing the ice layer 4 on the aircraft wing skin 3.

When the aircraft works aloft, the surface of the aircraft is frozen under any one of high humidity or low temperature, and the ice layer can cause the aircraft to be incapable of normal operation and even have potential safety hazards; the utility model discloses a set up the heater on the surface of aircraft wing covering and set up the detector on the heater, the heater includes the zone of heating, the zone of heating is connected with the detector electricity, the detector can obtain the freezing signal of electricity on aircraft surface, and transmit this signal of electricity for the zone of heating, the zone of heating can be based on this signal of electricity start work and to its place regional deicing, produce the heat through the zone of heating and realized the fixed point deicing to the aircraft, the unified heating method in the traditional technique has been avoided, the reduction of very big degree the consumption of aircraft.

The detector and the heater are responsible for deicing of a position area where the detector and the heater are located, the detector is a model 9732steel, the detector is an optical sensor consisting of a combined spectrometer and an optical switch, non-collimated light is used for monitoring the opacity and the optical refractive index of a substance on a probe, the change of the opacity and the refractive index is recorded as icing, the working principle of the detector is that signals of the change of the opacity and the refractive index are converted into four electrical signals capable of being directly detected through three signal lines with different colors, the output voltage of the detector is greater than 3V and is displayed as 1, and the output voltage of the detector is less than 0.5V and is displayed as 0. The detector outputs an electrical signal of 000 representing an icing-free state, 100 representing a small icing state, 110 representing a large icing state, and 111 representing an icing saturation state, and when the detector outputs electrical signals of 100, 110, and 111, the detector sends out an icing electrical signal. The heater is arranged on the outer surface of the aircraft wing skin, the detector is arranged on the heater, the heater comprises a heating layer, the heating layer is a conductive metal film, and the conductive metal film is electrically connected with the detector. The aircraft is provided with a power supply system, and the detector and the heater are respectively connected with the power supply system in parallel; when the skin of the aircraft is frozen, the detector can send an icing electric signal, at the moment, the heater receives the icing electric signal and then the power supply system provides electric energy for the heater, the heating layer starts to work after being electrified to generate heat to deice the area where the heating layer is located, and fixed-point deicing of the aircraft is realized.

The aircraft can seriously influence the normal operation of aircraft after ice sheet thickness exceedes 1mm at the flight in-process, when no more than 1mm, the influence to the aircraft production can be ignored, when the electricity signal of detector output is 110 and 111, it is greater than 1mm to show ice sheet thickness, consequently the detector in this embodiment sends the signal of icing electricity to the heater after ice sheet exceedes 1mm, power supply system provides the electric energy for the heater after the heater receives this signal of icing electricity, the zone of heating begins work after the circular telegram and produces the heat and carries out the deicing to its place region.

As a preferable scheme of this embodiment, the first link group 106 includes a first link 1061, a second link 1062, and a first link 1063, one end of the first link 1061 is fixedly connected to the first rotor arm 101, the other end of the first link 1061 and one end of the second link 1062 are provided with a first movable joint 1064, the other end of the second link 1062 and one end of the first link 1063 are provided with a second movable joint 1065, and the other end of the first link 1063 is disposed on the first rotating shaft 104, and when the steering engine 105 drives the first rotating shaft 104 to rotate in the forward direction, the first link group 106 can drive the first rotor arm 101 to rotate in the first direction; when the steering engine 105 drives the first rotating shaft 104 to rotate reversely, the first connecting rod group 106 can drive the first rotor arm 101 to rotate towards a second direction, and the first direction is opposite to the second direction; the second linkage 107 includes a third link 1071, a fourth link 1072, a fifth link 1073, and a second lever 1074, one end of the third link 1071 is fixedly connected to the second rotor arm 102, the other end of the third link 1071 and one end of the fourth link 1072 are provided with a third movable joint 1075, a fourth movable joint 1076 is provided at the other end of the fourth link 1072 and one end of the fifth link 1073, a fifth movable joint 1077 is provided at the other end of the fifth connecting rod 1073 and one end of the second sleeve rod 1074, the other end of the second sleeve rod 1074 is provided on the first rotating shaft 104, when the steering engine 105 drives the first rotating shaft 104 to rotate in the forward direction, the second connecting rod group 107 can drive the second rotor arm 102 to rotate in the second direction, when the steering engine 105 drives the first rotating shaft 104 to rotate reversely, the second connecting rod group 107 can drive the second rotor arm 102 to rotate towards the first direction.

The first rotor arm is changed from a retraction state to an expansion state in the process that the first rotating shaft rotates in the positive direction to drive the first sleeve rod to move clockwise, the second connecting rod drives the first connecting rod to rotate clockwise, and the first rotor arm is expanded by clockwise force; the first rotor arm is in a process of changing from the unfolding state to the folding state, the first rotating shaft rotates reversely to drive the first sleeve rod to rotate anticlockwise, the second connecting rod drives the first connecting rod to rotate anticlockwise, and the first rotor arm is folded by anticlockwise force;

the process that the second rotor arm is changed from the retraction state to the deployment state is that the first rotary shaft rotates positively, the second sleeve rod rotates anticlockwise, the fifth connecting rod drives the fourth connecting rod to rotate anticlockwise, the third connecting rod rotates anticlockwise, and the second rotor arm is deployed by anticlockwise force; the process that the second rotor arm changes from the unfolding state to the folding state is that the first rotating shaft rotates reversely, the second sleeve rod rotates clockwise, the fifth connecting rod drives the fourth connecting rod to rotate clockwise, the third connecting rod rotates clockwise, and the second connecting arm is folded by clockwise force.

As a preferable scheme of this embodiment, when the first rotating shaft 104 rotates in the forward direction, the angle range of the opening angle of the first rotor arm 101 and the second rotor arm 102 is: 130 degrees to 180 degrees; when the first rotating shaft 104 rotates reversely, the included angle range of the opening angles of the first rotor arm 101 and the second rotor arm 102 is as follows: 0 to 30 degrees.

Wherein, different opening angle ranges can provide the lift force required by the aircraft at different heights, and the opening angle is 180 degrees and 0 degree in the embodiment.

As a preferable solution of this embodiment, the fixing chassis 103 includes an upper chassis 1031, a lower chassis 1032, a first connecting lug 1033, a second connecting lug 1034, and a second rotating shaft 1035 disposed between the upper chassis 1031 and the lower chassis 1032, where the first connecting lug 1033 and the second connecting lug 1034 are respectively sleeved on the second rotating shaft 1035.

The first connecting lug and the second connecting lug can slide on the fixed chassis through the second rotating shaft.

As a preferable solution of this embodiment, the first rotor arm 101 and the second rotor arm 102 are respectively provided with a rotor 5 at an end away from the fixed chassis 103.

As an optimal solution of this embodiment, collapsible rotor device 1 is equipped with two sets ofly, sets up along the extending direction of aircraft fuselage 6 respectively, when two sets of collapsible rotor device 1 were in the state of withdrawing, staggered from top to bottom in aircraft fuselage 6 was placed, and the vertical lift of effectual improvement aircraft can be crossed to two sets of collapsible rotor device.

As a preferable solution of this embodiment, the heater 202 further includes an inner insulating layer 2022 and an outer insulating layer 2023 respectively disposed on two sides of the heating layer 2021, where the inner insulating layer 2022 is disposed on a side close to the skin 3 of the aircraft wing, the outer insulating layer 2023 is disposed on a side close to the detector 201, and the heating layer 2021 is a metal heating layer; an anti-abrasion protective layer 2024, wherein the inner heat insulation layer 2022, the heating layer 2021 and the outer heat insulation layer 2023 are wrapped by the anti-abrasion protective layer 2024; an overheating protection layer 2025, the overheating protection layer 2025 being provided between the aircraft wing skin 3 and the inner insulation layer 2022.

Wherein the inner insulating layer is used for preventing heat generated by the heating layer from diffusing to the inside of the skin of the aircraft wing; the heating layer is a conductive metal film and aims to generate heat for deicing; the outer insulating layer is used for preventing the heating layer from conducting electricity; the anti-abrasion protective layer can effectively protect the inner heat insulation layer, the heating layer and the outer insulation layer from being damaged by external factors such as air flow and the like in high altitude, and the service life can be prolonged; the metal heating layer is composed of mutually insulated electric heating sheets, the working voltage of the heater is 24V, the power is 24w, the highest heating temperature is 50 ℃, the metal heating layer is used for generating heat, when the temperature of the heating layer reaches 60 ℃, the generated heat is transmitted to an aircraft wing skin through the inner heat insulation layer and is transmitted to the ice layer through the outer heat insulation layer and the anti-abrasion protective layer, the anti-abrasion protective layer is made of glass fibers, the outer heat insulation layer is made of insulating heat-conducting silica gel, the inner heat insulation layer is made of Teflon high-temperature-resistant cloth, the material selected in the embodiment not only can play the effects of heat insulation, abrasion resistance and the like, and the load of the aircraft can be reduced due to the low self weight; the working principle of the overheating protection layer is as follows: the overheating protection layer comprises a temperature sensor and a heating switch, the heating switch is electrically connected with the heater, when the temperature sensor senses that the temperature of the surface of the aircraft wing skin is higher than 50 ℃, the heating switch is closed, and the metal heating layer stops working.

As a preferable scheme of this embodiment, the plurality of deicing devices 2 are arranged on the outer surface of the aircraft wing skin 3 at intervals, and are used for deicing the aircraft wing skin at different positions at fixed points.

As a preferable solution of this embodiment, the deicing device 2 further includes a camera 7, and the camera 7 is disposed on the outer surface of the aircraft wing skin 3 near the aircraft fuselage 6.

The camera can shoot the icing position and the deicing effect of the aircraft, so that a worker can monitor the deicing effect in real time, the worker can find the heater with abnormal deicing according to shot image information in time, the heater can be maintained or replaced, and normal operation of deicing operation is guaranteed.

The working principle of the aircraft of the embodiment is as follows:

foldable rotor use principle: when the aircraft enters the ascending process after taking off, the rotor wing needs to be unfolded to provide an upward lifting force, the steering engine drives the first rotating shaft to rotate positively, the first connecting rod group rotates clockwise to drive the first rotor wing arm to rotate clockwise, the first rotor wing arm is unfolded, the second connecting rod group rotates anticlockwise to drive the second rotor wing arm to rotate anticlockwise, and the second rotor wing arm is unfolded; when the aircraft enters a level flight state after reaching the operation height, the steering engine drives the first rotating shaft to rotate reversely, the first connecting rod group rotates anticlockwise to drive the first rotor arm to rotate anticlockwise, the first rotor arm is retracted, the second connecting rod group rotates clockwise to drive the second rotor arm to rotate clockwise, and the second rotor arm is retracted;

the principle of the deicing device is as follows: when the aircraft freezes at the high altitude construction surface, the utility model provides a pair of a defroster for aircraft, through at aircraft wing covering surface detector, the detector is through the signal conversion different electricity signals with the opacity of ice sheet and refractive index change, and then can draw the icing state on aircraft surface, and transmit this electric signal to the heater, the heater can carry out the deicing according to this electric signal to the region in place, produce the heat through the work of zone of heating, and transmit the heat to the ice sheet through outer insulation layer and abrasionproof damage protective layer, and then melt the ice sheet; in the process of deicing operation, the camera arranged on the outer surface of the aircraft wing skin can shoot the thickness of an icing area and an ice layer on the aircraft body, so that the deicing effect is effectively monitored; and when the temperature sensor senses that the temperature of the surface of the aircraft wing skin is higher than 50 ℃, the heating switch is closed, the heating layer stops working, and the deicing work is finished.

Claims (10)

1. An aircraft, characterized in that it comprises a foldable rotor device (1) comprising:

a first rotor arm (101) and a second rotor arm (102);

the first rotor arm (101) and the second rotor arm (102) are respectively connected with the fixed chassis (103) in a sliding manner;

the first rotating shaft (104) is arranged on the fixed chassis (103);

the steering engine (105) is arranged on the first rotating shaft (104) and can drive the first rotating shaft (104) to rotate;

one end of the first connecting rod group (106) is connected with the first rotating shaft (104), the other end of the first connecting rod group is connected with the first rotor arm (101), the first connecting rod group (106) comprises a plurality of movable joints, and the first connecting rod group (106) can be driven by the first rotating shaft (104) to swing in a reciprocating mode;

one end of the second connecting rod group (107) is connected with the first rotating shaft (104), the other end of the second connecting rod group is connected with the second rotor arm (102), the second connecting rod group (107) comprises a plurality of movable joints, and the second connecting rod group (107) can swing in a reciprocating mode under the driving of the first rotating shaft (104).

2. The aircraft of claim 1, wherein the aircraft further comprises:

deicing equipment (2), deicing equipment includes detector (201) and heater (202), detector (201) are established on the surface of aircraft wing skin (3), detector (201) are used for detecting whether icing on aircraft wing skin (3) surface, heater (202) are located detector (201) with between aircraft wing skin (3), with detector (201) electricity is connected, heater (202) include zone of heating (2021), heater (202) are used for detaching ice layer (4) on aircraft wing skin (3).

3. The aircraft of claim 1, wherein the first link group (106) comprises a first link (1061), a second link (1062) and a first loop bar (1063), one end of the first link (1061) is fixedly connected to the first rotor arm (101), the other end of the first link (1061) and one end of the second link (1062) are provided with a first movable joint (1064), the other end of the second link (1062) and one end of the first loop bar (1063) are provided with a second movable joint (1065), the other end of the first loop bar (1063) is arranged on the first rotating shaft (104), and when the steering engine (105) drives the first rotating shaft (104) to rotate in the forward direction, the first link group (106) can drive the first rotor arm (101) to rotate in the first direction; when the steering engine (105) drives the first rotating shaft (104) to rotate reversely, the first connecting rod group (106) can drive the first rotor arm (101) to rotate towards a second direction, and the first direction is opposite to the second direction;

the second connecting rod set (107) comprises a third connecting rod (1071), a fourth connecting rod (1072), a fifth connecting rod (1073) and a second loop bar (1074), one end of the third connecting rod (1071) is fixedly connected with the second rotor arm (102), the other end of the third connecting rod (1071) and one end of the fourth connecting rod (1072) are provided with a third movable joint (1075), the other end of the fourth connecting rod (1072) and one end of the fifth connecting rod (1073) are provided with a fourth movable joint (1076), the other end of the fifth connecting rod (1073) and one end of the second loop bar (1074) are provided with a fifth movable joint (1077), the other end of the second loop bar (1074) is arranged on the first rotating shaft (104), when the steering engine (105) drives the first rotating shaft (104) to rotate in the forward direction, the second connecting rod set (107) can drive the second rotor arm (102) to rotate towards the second direction, when the steering engine (105) drives the first rotating shaft (104) to rotate reversely, the second connecting rod group (107) can drive the second rotor arm (102) to rotate towards the first direction.

4. The aircraft according to claim 1, characterized in that the angle of the opening angle of the first and second rotor arms (101, 102) when the first rotation shaft (104) rotates in the forward direction is in the range: 130 degrees to 180 degrees;

when the first rotating shaft (104) rotates reversely, the included angle range of the opening angle of the first rotor arm (101) and the second rotor arm (102) is as follows: 0 to 30 degrees.

5. The aircraft of claim 1, wherein the fixed chassis (103) comprises an upper chassis (1031), a lower chassis (1032), a first connecting lug (1033), a second connecting lug (1034), and a second rotating shaft (1035) arranged between the upper chassis (1031) and the lower chassis (1032), and the first connecting lug (1033) and the second connecting lug (1034) are respectively sleeved on the second rotating shaft (1035).

6. The aircraft according to claim 1, characterized in that the ends of said first (101) and second (102) rotor arms remote from the fixed chassis (103) are provided with a rotor (5), respectively.

7. The aircraft according to claim 1, characterized in that said foldable rotor devices (1) are provided in two groups, each arranged along the extension direction of the aircraft fuselage (6), said two groups of foldable rotor devices (1) being staggered up and down inside the aircraft fuselage (6) when in the retracted state.

8. The aircraft of claim 2, wherein the heater (202) further comprises:

the heating layer (2021) is a metal heating layer, the inner heat insulation layer (2022) and the outer heat insulation layer (2023) are respectively arranged on two sides of the heating layer (2021), the inner heat insulation layer (2022) is arranged on one side close to an aircraft wing skin (3), the outer heat insulation layer (2023) is arranged on one side close to the detector (201);

an anti-abrasion protective layer (2024), wherein the anti-abrasion protective layer (2024) wraps the inner insulating layer (2022), the heating layer (2021) and the outer insulating layer (2023);

an overheating protection layer (2025), the overheating protection layer (2025) being provided between the aircraft wing skin (3) and the inner insulation layer (2022).

9. An aircraft according to claim 2, wherein said de-icing means (2) are provided in plurality, spaced apart on the outer surface of the aircraft wing skin (3).

10. The aircraft according to claim 2, wherein said de-icing device (2) further comprises:

the camera (7) is arranged at the position, close to the aircraft body (6), of the outer surface of the aircraft wing skin (3).

Images