Aircraft ice accretion measuring device

Abstract

The utility model is suitable for the technical field of airplane ice accretion measurement, and provides an airplane ice accretion measuring device, which comprises a shell; the vacuum chuck is fixedly arranged on the shell; the negative pressure pump is fixedly arranged on the inner wall of the shell; the negative pressure pipe is arranged at the air inlet end of the negative pressure pump and is communicated with the vacuum chuck; the one-way valve is arranged on the negative pressure pipe; the exhaust pipe is mounted at the exhaust end of the negative pressure pump and extends to the outside of the shell; the ultrasonic ice accumulation measuring mechanism is installed on the shell and measures the thickness of ice accumulated on the surface of the airplane by means of the propagation velocity difference of ultrasonic waves in different media. The airplane ice accumulation measuring device provided by the scheme is relatively convenient to mount and dismount, can measure the thickness of the ice accumulation through the propagation velocity difference of ultrasonic waves in different media, can determine the thickness of the ice accumulation through the change of the surface capacitance of the airplane, and is relatively high in measurement accuracy of the thickness of the ice accumulation on the surface of the airplane.

Description

TECHNICAL FIELD

[0001] The utility model belongs to aircraft icing measurement technical field especially relates to a kind of aircraft icing measurement device. BACKGROUND

[0002] Aircraft icing is one of the important factors affecting flight safety. Icing can change the aerodynamic shape of the aircraft, increase the weight of the aircraft, reduce the performance of the aircraft, and even cause the aircraft to lose control in severe cases. Aircraft icing measuring instrument can provide valuable real-time data, which can help forecasters better understand the influence of water vapor content, temperature, cloud structure and other factors in the atmosphere on aircraft icing, so as to improve the accuracy of weather forecast. These data also help researchers to deeply study the formation mechanism and prevention method of aircraft icing, and provide stronger support for aviation safety. Therefore, it is of great significance to develop an accurate and reliable aircraft icing measuring device for improving flight safety. However, there is no such measuring device on domestic civil aircraft and general aircraft at present. SUMMARY

[0003] The utility model provides a kind of aircraft icing measuring device, to solve the problem of measuring device for aircraft icing thickness in prior art proposed in the above background technique.

[0004] To solve the above problems, the utility model is realized as follows: a kind of aircraft icing measuring device, comprising: a shell;Vacuum chuck fixedly installed on the shell;Negative pressure pump fixedly installed on the inner wall of the shell;Negative pressure pipe is arranged on the suction end of the negative pressure pump and is communicated with the vacuum chuck;Check valve is arranged on the negative pressure pipe;Exhaust pipe is installed on the exhaust end of the negative pressure pump and extends to the outside of the shell;Ultrasonic icing measuring mechanism is installed on the shell, and the ultrasonic icing measuring mechanism measures the thickness of aircraft surface icing by using the difference in propagation speed of ultrasonic waves in different media;Capacitive icing measuring mechanism is installed on the shell, and the capacitive icing measuring mechanism determines the thickness of icing by measuring the change of aircraft surface capacitance.

[0005] Preferably, a pressure relief pipe is arranged on the vacuum chuck, one end of the pressure relief pipe extends to the outside of the shell, and an electromagnetic valve is arranged on the pressure relief pipe.

[0006] Preferably, the ultrasonic icing measuring mechanism comprises: a first cross plate fixedly installed on one side of the shell;Ultrasonic sensor transmitting end and ultrasonic sensor receiving end are installed on the first cross plate.

[0007] Preferably, the capacitive ice measuring mechanism comprises: a second horizontal plate fixedly installed on one side of the shell; a plurality of sliding rods slidably installed on the second horizontal plate; a plurality of springs respectively slidably sleeved on the plurality of sliding rods; a plurality of limiting blocks respectively fixedly installed at bottom ends of the plurality of sliding rods; a same mounting plate fixedly installed at top ends of the plurality of sliding rods; and a capacitive sensor arranged on the mounting plate.

[0008] Preferably, an inner wall of the shell is provided with a circuit board, the circuit board is electrically connected with the negative pressure pump, the electromagnetic valve, the ultrasonic sensor emitting end, the ultrasonic sensor receiving end and the capacitive sensor, the circuit board is provided with a single-chip microcomputer, a storage chip and a communication module, the shell is provided with an external antenna, and the external antenna is electrically connected with the communication module.

[0009] Preferably, an inner wall of the shell is provided with a lithium battery, a bottom of the shell is provided with a charging interface, and the lithium battery is electrically connected with the charging interface and the circuit board.

[0010] Preferably, the shell is provided with an operation panel, the operation panel is electrically connected with the circuit board, a handle is fixedly installed on the shell, a camera is arranged on the first horizontal plate, and the camera is electrically connected with the circuit board.

[0011] Compared with the related art, the aircraft ice accumulation measuring device has the following beneficial effects:

[0012] Compared with the prior art, the aircraft ice accumulation measuring device comprises a shell, a vacuum chuck is fixedly installed on the shell and used for adsorbing and fixing the device on a surface of an aircraft, a negative pressure pump is fixedly installed on an inner wall of the shell, an air inlet end of the negative pressure pump is communicated with the vacuum chuck through a negative pressure pipe, a one-way valve is arranged on the negative pressure pipe to prevent gas backflow, an air outlet end of the negative pressure pump extends to an outside of the shell through an air outlet pipe to discharge the gas, in addition, an ultrasonic ice accumulation measuring mechanism is further installed on the shell, the mechanism utilizes a difference in propagation speeds of ultrasonic waves in different media to accurately measure a thickness of ice accumulated on the surface of the aircraft, realizes non-contact and high-precision ice accumulation thickness detection, meanwhile, a capacitive ice accumulation measuring mechanism is further installed on the shell, the mechanism measures a change in capacitance of the surface of the aircraft to determine the thickness of the ice accumulated, and provides an ice accumulation measuring method based on physical properties, the comprehensive use of the ultrasonic and capacitive ice accumulation measuring mechanisms can complement each other, improve accuracy and reliability of ice accumulation measurement, and has important significance for guaranteeing flight safety. BRIEF DESCRIPTION OF DRAWINGS

[0013] Figure 1 is a front view structure schematic diagram of the aircraft ice accumulation measuring device provided by the utility model;

[0014] Figure 2 For Figure 1 Three-dimensional assembly structure schematic diagram of middle shell and vacuum chuck;

[0015] Figure 3 For Figure 1 Enlarged structure schematic diagram of A part shown in the figure.

[0016] Fig. 1, shell; 2, vacuum chuck; 3, negative pressure pump; 4, negative pressure pipe; 5, one-way valve; 6, exhaust pipe; 7, pressure relief pipe; 8, electromagnetic valve; 9, first cross plate; 10, ultrasonic sensor transmitting end; 11, ultrasonic sensor receiving end; 12, second cross plate; 13, sliding rod; 14, spring; 15, limit block; 16, mounting plate; 17, capacitive sensor; 18, circuit board; 19, single-chip microcomputer; 20, storage chip; 21, communication module; 22, external antenna; 23, lithium battery; 24, charging interface; 25, operation panel; 26, handle; 27, camera. DETAILED DESCRIPTION

[0017] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs; the terminology used in the description herein is for describing particular embodiments only and is not intended to be limiting of the application; the present application will be described with reference to the drawings in which is shown by way of illustration the application in accordance with embodiments described herein in which: the terminology includes the words specifically mentioned herein and all grammatical variations thereof; the terminology "include", "includes" and "including" is meant to be non-limiting; the terminology "first", "second" and the like does not denote any order, quantity, or importance, but rather is used to distinguish one element from another. The terminology "inner", "outer", "left", "right", "front", "back", "rear", "up", "down", "top", "bottom", "over", "under", and the like, terms are used herein for convenience and are not intended to denote or imply a specific orientation or configuration.

[0018] Reference herein to "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment can be included in at least one embodiment of the application. The appearances of the phrase "in an embodiment" in various places in the specification are not necessarily all referring to the same embodiment, nor are they necessarily all directed to the same embodiment, or to a single alternative embodiment. It is explicitly contemplated that embodiments described herein can be combined with each other.

[0019] The utility model embodiment provides a kind of aircraft icing measuring device, such as Figures 1-3As shown in the figure, the aircraft icing measuring device comprises a shell 1, a vacuum chuck 2 fixedly installed on the shell 1, a negative pressure pump 3 fixedly installed on the inner wall of the shell 1, a negative pressure pipe 4 arranged on the air inlet end of the negative pressure pump 3 and communicated with the vacuum chuck 2, a one-way valve 5 arranged on the negative pressure pipe 4, an exhaust pipe 6 installed on the air outlet end of the negative pressure pump 3 and extending to the outside of the shell 1, an ultrasonic icing measuring mechanism installed on the shell 1, the ultrasonic icing measuring mechanism uses the difference in the propagation speed of ultrasonic waves in different media to measure the thickness of the ice on the surface of the aircraft, and a capacitive icing measuring mechanism installed on the shell 1, the capacitive icing measuring mechanism determines the thickness of the ice by measuring the change of the capacitance of the surface of the aircraft.

[0020] In the embodiment, the shell 1 is provided, the vacuum chuck 2 is fixedly installed on the shell 1 to fix the device on the surface of the aircraft, the negative pressure pump 3 is fixedly installed on the inner wall of the shell 1, the air inlet end of the negative pressure pump 3 is communicated with the vacuum chuck 2 through the negative pressure pipe 4, the one-way valve 5 is arranged on the negative pressure pipe 4 to prevent the reverse flow of the gas, the air outlet end of the negative pressure pump 3 extends to the outside of the shell 1 through the exhaust pipe 6 to discharge the gas, in addition, the ultrasonic icing measuring mechanism is installed on the shell 1, the mechanism uses the difference in the propagation speed of ultrasonic waves in different media to accurately measure the thickness of the ice on the surface of the aircraft, realizes the non-contact and high-precision icing thickness detection, meanwhile, the capacitive icing measuring mechanism is installed on the shell 1, the mechanism determines the thickness of the ice by measuring the change of the capacitance of the surface of the aircraft, and provides an icing measuring method based on physical properties, the ultrasonic and capacitive icing measuring mechanisms are used in combination, the accuracy and reliability of the icing measurement are improved, and the method has important significance for ensuring the flight safety.

[0021] In the further preferred embodiment of the utility model, the vacuum chuck 2 is provided with a pressure relief pipe 7, one end of the pressure relief pipe 7 extends to the outside of the shell 1, and the pressure relief pipe 7 is provided with an electromagnetic valve 8.

[0022] In the embodiment, the external air can enter the vacuum chuck 2 through the pressure relief pipe 7 and the electromagnetic valve 8, so that the vacuum chuck 2 is released from the fixed state, and the device is convenient to disassemble.

[0023] In the further preferred embodiment of the utility model, the ultrasonic icing measuring mechanism comprises a first horizontal plate 9 fixedly installed on one side of the shell 1, an ultrasonic sensor transmitting end 10 and an ultrasonic sensor receiving end 11 installed on the first horizontal plate 9.

[0024] In the embodiment, the ultrasonic sensor transmitting end 10 and the ultrasonic sensor receiving end 11 cooperate to use the difference in the propagation speed of ultrasonic waves in different media to measure the thickness of the ice on the surface of the aircraft.

[0025] In a further preferred embodiment of the present invention, the capacitance ice accumulation measuring mechanism includes: a second horizontal plate 12 fixedly installed on one side of the housing 1; a plurality of sliding rods 13 slidably installed on the second horizontal plate 12; a plurality of springs 14 respectively slidably sleeved on the plurality of sliding rods 13; a plurality of limiting blocks 15 respectively fixedly installed at the bottom ends of the plurality of sliding rods 13; a same mounting plate 16 fixedly installed at the top ends of the plurality of sliding rods 13; and a capacitance sensor 17 disposed on the mounting plate 16.

[0026] In this embodiment, the return of multiple springs 14 can make the capacitive sensor 17 in close contact with the surface of the aircraft. The capacitive sensor 17 can monitor the change in the capacitance of the aircraft surface, thereby determining the thickness of the ice buildup.

[0027] In a further preferred embodiment of this utility model, a circuit board 18 is provided on the bottom inner wall of the housing 1. The circuit board 18 is electrically connected to the negative pressure pump 3, the solenoid valve 8, the ultrasonic sensor transmitter 10, the ultrasonic sensor receiver 11, and the capacitive sensor 17. A microcontroller 19, a storage chip 20, and a communication module 21 are provided on the circuit board 18. An external antenna 22 is provided on the housing 1, and the external antenna 22 is electrically connected to the communication module 21.

[0028] In this embodiment, the device can be controlled by a microcontroller 19, the measurement data can be stored by a storage chip 20, the measurement data can be sent to a cloud server by a communication module 21, and the signal strength of the communication module 21 can be enhanced by an external antenna 22.

[0029] In a further preferred embodiment of the present invention, a lithium battery 23 is provided on the inner wall of the housing 1, and a charging interface 24 is provided at the bottom of the housing 1. The lithium battery 23 is electrically connected to the charging interface 24 and the circuit board 18.

[0030] In this embodiment, the device can be powered by the lithium battery 23, and an external charging cable can be connected to the charging interface 24 to charge the lithium battery 23.

[0031] In a further preferred embodiment of the present invention, an operation panel 25 is provided on the housing 1, the operation panel 25 is electrically connected to the circuit board 18, a handle 26 is fixedly installed on the housing 1, and a camera 27 is provided on the first horizontal plate 9, the camera 27 is electrically connected to the circuit board.

[0032] In this embodiment, the handle 26 allows staff to easily hold the device for installation and disassembly, the control panel 25 allows for operation and control of the device, and the camera 27 allows for photographing and documenting ice buildup on the aircraft surface.

[0033] In summary, compared with related technologies, this device is not only easier to install and disassemble, but also able to measure the thickness of ice accumulation by measuring the difference in the propagation speed of ultrasonic waves in different media, and can determine the thickness of ice accumulation by measuring the change in the capacitance of the aircraft surface, thus achieving high accuracy in measuring the thickness of ice accumulation on the aircraft surface.

[0034] It should be understood, in the several embodiments provided in this application, that the disclosed apparatus may be implemented in other ways.

[0035] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit the scope of protection of this utility model. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on these embodiments, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model. Although this utility model has been described in detail with reference to the above embodiments, those skilled in the art can still combine, add, delete, or otherwise adjust the features of the various embodiments of this utility model according to the circumstances without conflict or creative effort, thereby obtaining different technical solutions that do not fundamentally depart from the concept of this utility model. These technical solutions are also within the scope of protection of this utility model.

Claims

1. An aircraft icing measuring device, characterized in that, include: case; A vacuum suction cup fixedly mounted on the housing; A negative pressure pump that is fixedly installed on the inner wall of the housing; A negative pressure pipe is installed at the air inlet end of the negative pressure pump and connected to the vacuum suction cup; A one-way valve is installed on the negative pressure pipe; An exhaust pipe installed at the exhaust end of the negative pressure pump and extending to the outside of the housing; An ultrasonic icing measurement mechanism is installed on the housing, which uses the difference in the propagation speed of ultrasonic waves in different media to measure the thickness of ice on the aircraft surface. A capacitance icing measurement mechanism is installed on the housing, which determines the thickness of the ice buildup by measuring changes in the capacitance of the aircraft surface.

2. The aircraft icing measuring device as described in claim 1, characterized in that, The vacuum suction cup is equipped with a pressure relief pipe, one end of which extends to the outside of the housing, and a solenoid valve is installed on the pressure relief pipe.

3. The aircraft icing measuring device as described in claim 2, characterized in that, The ultrasonic ice accumulation measuring mechanism includes: A first horizontal plate fixedly installed on one side of the housing; An ultrasonic sensor transmitter and an ultrasonic sensor receiver are mounted on the first horizontal plate.

4. The aircraft icing measuring device as described in claim 3, characterized in that, The capacitor ice accumulation measuring mechanism includes: A second horizontal plate is fixedly installed on one side of the housing; Multiple sliding rods are slidably mounted on the second horizontal plate; Multiple springs that are respectively slidably sleeved on multiple sliding rods; Multiple limiting blocks are respectively fixedly installed at the bottom ends of the multiple sliding rods; A mounting plate is fixedly installed on the top of the multiple sliding rods; Capacitive sensor mounted on the mounting plate.

5. The aircraft icing measuring device as described in claim 4, characterized in that, A circuit board is provided on the bottom inner wall of the housing. The circuit board is electrically connected to the negative pressure pump, solenoid valve, ultrasonic sensor transmitter, ultrasonic sensor receiver and capacitive sensor. A microcontroller, memory chip and communication module are provided on the circuit board. An external antenna is provided on the housing and is electrically connected to the communication module.

6. The aircraft icing measuring device as described in claim 5, characterized in that, A lithium battery is disposed on the inner wall of the housing, and a charging interface is disposed at the bottom of the housing. The lithium battery is electrically connected to the charging interface and the circuit board.

7. The aircraft icing measuring device as described in claim 5, characterized in that, An operation panel is provided on the housing and is electrically connected to the circuit board. A handle is fixedly installed on the housing. A camera is provided on the first horizontal plate and is electrically connected to the circuit board.

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