CN113671211A - Airspeed measuring device and flight equipment - Google Patents
Airspeed measuring device and flight equipment Download PDFInfo
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- CN113671211A CN113671211A CN202010406158.4A CN202010406158A CN113671211A CN 113671211 A CN113671211 A CN 113671211A CN 202010406158 A CN202010406158 A CN 202010406158A CN 113671211 A CN113671211 A CN 113671211A
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- 230000003068 static effect Effects 0.000 claims abstract description 90
- 238000005259 measurement Methods 0.000 claims abstract description 62
- 238000000691 measurement method Methods 0.000 abstract description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 7
- 230000002706 hydrostatic effect Effects 0.000 description 6
- 230000004308 accommodation Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- ORQBXQOJMQIAOY-UHFFFAOYSA-N nobelium Chemical compound [No] ORQBXQOJMQIAOY-UHFFFAOYSA-N 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/02—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer
- G01P5/06—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer using rotation of vanes
- G01P5/07—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring forces exerted by the fluid on solid bodies, e.g. anemometer using rotation of vanes with electrical coupling to the indicating device
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
- G01P5/00—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft
- G01P5/14—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid
- G01P5/16—Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes, e.g. Machmeter
- G01P5/165—Arrangements or constructions of Pitot tubes
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- Measuring Fluid Pressure (AREA)
Abstract
本申请提供了一种空速测量装置及飞行设备。该空速测量装置应用于飞行设备。该空速测量装置采用皮托管测量装置和叶轮测量装置分别独立工作，其中，所述皮托管测量装置根据飞行设备飞行时的气流总压与气流静压之间的压力差来测量飞行设备的空速，所述叶轮测量装置根据叶轮测量装置的叶轮在飞行设备飞行时的转速来测量飞行设备的空速。该空速测量装置利用皮托管测量装置和叶轮测量装置两种不同的测量方式进行空速测量，增加了空速测量数据来源的多样性，以提高空速测量的准确性。
The application provides an airspeed measurement device and flight equipment. The airspeed measuring device is applied to flight equipment. The airspeed measurement device adopts a pitot tube measurement device and an impeller measurement device to work independently, wherein the pitot tube measurement device measures the air flow of the flight equipment according to the pressure difference between the total airflow pressure and the airflow static pressure during the flight of the flight equipment. The impeller measuring device measures the airspeed of the flying equipment according to the rotational speed of the impeller of the impeller measuring device when the flying equipment is flying. The airspeed measurement device utilizes two different measurement methods, a pitot tube measurement device and an impeller measurement device, to measure the airspeed, thereby increasing the diversity of airspeed measurement data sources and improving the accuracy of the airspeed measurement.
Description
Technical Field
The invention relates to the field of aerospace, in particular to an airspeed measuring device and flight equipment.
Background
With the progress of society, aircrafts are more and more popular. The aircraft obtains an accurate airspeed value in the flight process and directly influences the flight quality and the flight safety. Industrial unmanned aerial vehicle often faces extreme weather when the operation, like heavy fog, sleet weather, its airspeed measurement's accuracy often is difficult to guarantee, and then influences the response of flight control system to the aircraft state, and serious person can cause the explosive accident even.
The air speed tube used by the industrial unmanned aerial vehicle below 150kg is mostly a pitot tube measuring device with differential pressure due to factors such as cost and weight. This kind of differential pitot tube measuring device has better precision under general environment in the working range of 0-50 m/s's airspeed, nevertheless often can appear ponding, freeze and then lead to airspeed tube to block up and unable normal work in big fog, sleet weather, brings very big hidden danger to unmanned aerial vehicle's flight safety.
Disclosure of Invention
The application provides an airspeed measuring device and flight equipment to adopt single pitot tube measuring device can't accurately carry out airspeed measurement's problem among the solution prior art.
On the one hand, this application provides an airspeed measuring device, is applied to flight equipment, includes: the device comprises a pitot tube measuring device and an impeller measuring device fixedly connected with the pitot tube measuring device, wherein the pitot tube measuring device and the impeller measuring device respectively and independently work;
the pitot tube measuring device is used for measuring the airspeed of the flying equipment according to the pressure difference between the total airflow pressure and the static airflow pressure when the flying equipment flies;
the impeller measuring device measures the airspeed of the flying equipment according to the rotating speed of an impeller of the impeller measuring device when the flying equipment flies.
In some possible implementations, the pitot tube measurement device includes a total pressure component, a static pressure component, and a first measurer;
the total pressure assembly senses the total pressure of the airflow when the flying equipment flies;
the static pressure assembly senses the static airflow pressure when the flying equipment flies;
the first measurer is connected with the total pressure assembly and the static pressure assembly, measures the total airflow pressure and the static airflow pressure, and outputs the airspeed of the flight equipment according to the pressure difference between the total airflow pressure and the static airflow pressure.
In some possible implementations, the total pressure assembly includes a total pressure pipe sleeve and a total pressure pipe;
the total pressure pipe sleeve is provided with a total pressure cavity;
one end of the total pressure pipe is positioned in the total pressure pipe sleeve, and the other end of the total pressure pipe is connected with the first measurer;
one end of the total pressure pipe sleeve, which is far away from the total pressure pipe, is provided with a total pressure hole communicated with the total pressure cavity;
the total pressure hole and the total pressure cavity are communicated with the total pressure pipe and form the total pressure of the air flow.
In some possible implementations, the hydrostatic assembly includes a hydrostatic sleeve and a hydrostatic tube;
the static pressure pipe sleeve is provided with a static pressure cavity, and the side wall of the static pressure pipe sleeve is provided with a plurality of static pressure holes communicated with the static pressure cavity;
one end of the static pressure pipe is positioned in the static pressure pipe sleeve, and the other end of the static pressure pipe is connected with the first measurer; the static pressure hole and the static pressure cavity are communicated with the static pressure pipe and form the static pressure of the airflow.
In some possible implementations, the total pressure jacket includes a front cover and a front end plug connected to the front cover; the front cover and the front end plug are enclosed to form the total pressure cavity;
one end of the total pressure pipe penetrates through the front end plug and is fixed in the front cover.
In some possible implementations, the static pressure jacket includes a jacket connected to the front end plug, and a rear end plug connected to the jacket; the front end plug, the pipe sleeve and the rear end plug are enclosed to form the static pressure cavity;
one end of the static pressure pipe is positioned in the pipe sleeve, and the other end of the static pressure pipe is fixed on the rear end plug;
the other end of the total pressure pipe is fixed to the rear end plug.
In some possible implementations, the pitot tube measurement device further includes a first extension tube and a second extension tube connected to the back end plug; the first extension pipe is communicated with the total pressure pipe, and the second extension pipe is communicated with the static pressure pipe.
In some possible implementations, the pitot tube measurement device further includes a mounting support;
the mounting support comprises an upper shell and a lower shell which are fixedly connected, and an accommodating groove is formed between the upper shell and the lower shell; the rear end plug and a part of the pipe sleeve positioned at one side of the rear end plug are accommodated in the accommodating groove;
the first extension pipe and the second extension pipe extend to the outside of the mounting support through the receiving groove.
In some possible implementations, the impeller measuring device includes a housing fixedly connected to the pitot tube measuring device, a fixing portion fixedly connected to the housing, an impeller rotatably connected to the fixing portion, and a measuring assembly;
the measuring component measures the rotating speed of the impeller, and the airspeed of the flight equipment is calculated according to the rotating speed of the impeller.
In some possible implementations, the measurement component includes a measurement circuit, and a second measurer connected to the measurement circuit;
the measuring circuit is used for measuring the rotating speed of the impeller, converting the rotating speed of the impeller into a corresponding electric signal and transmitting the electric signal to a second measurer;
and the second measurer is used for calculating the airspeed of the flight equipment according to the electric signal.
In some possible implementations, the measurement circuit includes a diode and a photo-transistor disposed inside the housing and opposite to each other;
the diode and the phototriode are exposed out of the shell;
the diode is used for emitting light to irradiate the photoelectric triode;
when the impeller rotates, the light emitted by the diode is intermittently blocked;
the phototriode is used for measuring the rotating speed of the impeller and converting the rotating speed of the impeller into corresponding electric signals, wherein the phototriode outputs the high level of the electric signals when receiving the light rays emitted by the diode, and outputs the low level of the electric signals when not receiving the light rays emitted by the diode.
In some possible implementations, the measurement circuit further includes a measurement line connected to the phototransistor;
the measuring line is used for transmitting the electric signal to a second measurer.
In some possible implementations, the housing has a receiving hole; the fixed part and the impeller are both positioned in the accommodating hole.
In some possible implementations, the fixing portion includes a first bearing seat fixedly connected to the housing, a first bearing located in the first bearing seat, a second bearing seat fixedly connected to the housing and disposed parallel to the first bearing seat, a second bearing located in the second bearing seat, and a rotating shaft rotatably connected to both the first bearing and the second bearing;
the impeller is fixedly connected with the rotating shaft.
In another aspect, the present invention provides a flying apparatus comprising an airspeed measurement device as described above.
The application provides an airspeed measuring device and flight equipment adopt pitot tube measuring device and impeller measuring device independent work respectively, wherein, pitot tube measuring device measures the airspeed of flight equipment according to the pressure differential between the total pressure of air current and the air current static pressure when flight equipment flies, impeller measuring device measures the airspeed of flight equipment according to the rotational speed of impeller measuring device's impeller when flight equipment flies. This airspeed measuring device and flight equipment utilize pitot tube measuring device and two kinds of different measurement methods of impeller measuring device to carry out the airspeed measurement, have increased the variety of airspeed measurement data source to improve airspeed measurement's accuracy.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of an impeller measuring device provided in an embodiment of the present application;
FIG. 2 is a front view of an impeller measuring device provided by an embodiment of the present application;
FIG. 3 is a cross-sectional view at A-A of FIG. 2;
FIG. 4 is a left side view of an impeller measuring device provided by an embodiment of the present application;
FIG. 5 is a top view of an impeller measuring device provided in an embodiment of the present application;
fig. 6 is an exploded view of an impeller measuring device provided in an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In this application, the word "exemplary" is used to mean "serving as an example, instance, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the invention. In the following description, details are set forth for the purpose of explanation. It will be apparent to one of ordinary skill in the art that the present invention may be practiced without these specific details. In other instances, well-known structures and processes are not shown in detail to avoid obscuring the description of the invention with unnecessary detail. Thus, the present invention is not intended to be limited to the embodiments shown, but is to be accorded the widest scope consistent with the principles and features disclosed herein.
Referring to fig. 1 to 6, in an embodiment of the present application, an airspeed measuring device applied to a flight apparatus includes: the device comprises a pitot tube measuring device 10 and an impeller measuring device 20 fixedly connected with the pitot tube measuring device 10, wherein the pitot tube measuring device 10 and the impeller measuring device 20 respectively work independently;
the pitot tube measuring device 10 is used for measuring the airspeed of the flying equipment according to the pressure difference between the total airflow pressure and the static airflow pressure when the flying equipment flies;
the impeller measuring device 20 is used for measuring the airspeed of the flying equipment according to the rotating speed of the impeller measuring device 20 when the flying equipment flies.
It should be noted that the airspeed measuring device of the present invention employs a pitot tube measuring device 10 and an impeller measuring device 20 to respectively and independently operate, where the pitot tube measuring device 10 measures the airspeed of the flying equipment according to the pressure difference between the total pressure and the static pressure of the airflow when the flying equipment flies, and the impeller measuring device 20 measures the airspeed of the flying equipment according to the rotating speed of the impeller measuring device 20 when the flying equipment flies. This airspeed measuring device utilizes pitot tube measuring device 10 and two kinds of different measurement methods of impeller measuring device 20 to carry out the airspeed measurement, has increased the variety of airspeed measurement data source, through carrying out data fusion with two kinds of measurement data to improve airspeed measurement's accuracy. The impeller of the impeller measuring device 20 is insensitive to fog and rainwater, and is not easy to lose efficacy in extreme weather, so that the environmental adaptability of the airspeed measuring device is improved. In addition, when the pitot tube measuring device 10 fails, the judgment can be made through the airspeed measurement data of the impeller measuring device 20, so that the safety of the flight equipment is guaranteed, and the safety of the operation of the flight equipment is improved. In addition, the impeller measuring device 20 is generally smaller in size, lighter in weight, and simpler in structure than the pitot tube measuring device 10, and compared with the prior art in which a double pitot tube measuring device is adopted to prevent the airspeed measuring device from failing, the present invention has the characteristics of small size, light weight, and simple structure.
In some embodiments, referring to fig. 1-6, the pitot tube measurement device 10 includes a total pressure element 101, a static pressure element 102, and a first gauge (not shown);
the total pressure assembly 101 senses the total pressure of the airflow when the flight equipment flies;
the static pressure component 102 senses the static pressure of the airflow when the flight equipment flies;
the first measurer is connected with the total pressure assembly and the static pressure assembly, measures the total airflow pressure and the static airflow pressure, and outputs the airspeed of the flight equipment according to the pressure difference between the total airflow pressure and the static airflow pressure.
In some embodiments, referring to fig. 1 to 6, total pressure assembly 101 includes a total pressure pipe sleeve 1011 and a total pressure pipe 15;
the total pressure sleeve 1011 has a total pressure cavity (not shown); one end of the total pressure pipe 15 is positioned in the total pressure pipe sleeve 1011, and the other end is connected with the first measurer; a total pressure hole 111 communicated with the total pressure cavity is formed in one end, far away from the total pressure pipe 15, of the total pressure pipe sleeve 1011; the total pressure hole 111 and the total pressure cavity are communicated with the total pressure pipe 15 and form total pressure of the air flow.
In some embodiments, referring to fig. 1-6, the hydrostatic assembly 102 includes a hydrostatic sleeve 1021 and a hydrostatic tube 16;
the static pressure pipe sleeve 1021 is provided with a static pressure cavity (not shown), and the side wall of the static pressure pipe sleeve 1021 is provided with a plurality of static pressure holes 131 communicated with the static pressure cavity; one end of the static pressure pipe 16 is positioned in the static pressure pipe sleeve 1021, and the other end is connected with the first measurer; the static pressure hole 131 and the static pressure cavity are communicated with the static pressure pipe 16 and form airflow static pressure.
In some embodiments, referring to fig. 1 to 6, the total pressure sleeve 1011 includes a front cover 11 and a front end plug 12 connected to the front cover 11; the front cover 11 and the front end plug 12 enclose to form a total pressure cavity;
one end of the total pressure pipe 15 is fixed in the front cover 11 through the front end plug 12.
In some embodiments, referring to fig. 1-6, the static pressure jacket 1021 includes a jacket 13 connected to the front end plug 12, and a rear end plug 14 connected to the jacket 13; the front end plug 12, the pipe sleeve 13 and the rear end plug 14 are enclosed to form a static pressure cavity; the front end plug 12 has a sealing function, can enclose with the front cover 11 to form a total pressure cavity, can enclose with the pipe sleeve 13 to form a static pressure cavity, and can prevent accumulated water from entering the static pressure cavity, and the rear end plug 14 also has a sealing function, can enclose with the pipe sleeve 13 to form a static pressure cavity, and can prevent accumulated water from entering the static pressure cavity;
one end of the static pressure pipe 16 is positioned in the pipe sleeve 13, and the other end of the static pressure pipe is fixed to the rear end plug 14;
the other end of the total pressure pipe 15 is fixed to the rear end plug 14.
When the flying equipment flies, airflow enters the front cover 11 from the total pressure holes 111, the direction of the total pressure holes 111 is generally the same as the flying direction of the flying equipment, so the total pressure holes 111, the total pressure cavities and the total pressure pipe 15 are communicated with each other and form total airflow pressure, the total pressure pipe 15 can sense the total airflow pressure when the flying equipment flies, meanwhile, the airflow also enters the pipe sleeve 13 from a plurality of static pressure holes 131 on the side wall of the pipe sleeve 13, the airflow in the pipe sleeve 13 is static, and the static pressure holes 131, the static pressure cavities and the static pressure pipe 16 are communicated and form static airflow pressure, so the static pressure pipe 16 can sense the static airflow pressure when the flying equipment flies.
In some embodiments, one end of the total pressure pipe 15 extends into the front cover 11 through the first through hole 121 provided on the front end plug 12, and the other end of the total pressure pipe 15 is communicated with the second through hole 141 provided on the rear end plug 14; the other end of the static pressure pipe 16 is communicated with a third through hole 142 arranged on the rear end plug 14.
In some embodiments, referring to fig. 6, the front cover 11 includes a first portion 112 and a second portion 113 connected to each other, the second portion 113 is connected to the front end plug 12, in order to reduce wind resistance, the first portion 112 is shaped like a semi-ellipsoid sphere, the first portion 112 is hollow inside, the total pressure hole 111 is located at the top end of the semi-ellipsoid sphere, the second portion 113 is shaped like a cylinder, the connection between the second portion 113 and the first portion 112 is a plane with an air flow hole 1131, the air flow hole 1131 is located at the center of the plane, the air flow hole 1131 is communicated with the total pressure hole 111 and the total pressure pipe 15, and when there is a small amount of water accumulated inside the first portion 112, the accumulated water cannot flow into the second portion 113 through the air flow hole 1131 due to the height of the air flow hole 1131. To facilitate the air intake of the second portion 113, the air flow holes 1131 and the total pressure holes 111 may be located at the same level, that is, the height of the air flow holes 1131 relative to the bottom of the second portion 113 is the same as the height of the total pressure holes 111 relative to the bottom of the second portion 113. Furthermore, the first through hole 121 is located at the upper portion of the front end plug 12, and the height of the first through hole 121 relative to the bottom of the second portion 113 is greater than the height of the airflow hole 1131 relative to the bottom of the second portion 113, so that when a small amount of accumulated water exists in the second portion 113, the accumulated water does not flow into the total pressure pipe 15 through the first through hole 121, and by providing the second portion 113 and the position of the first through hole 121, the water resistance of the pitot tube measuring device 10 can be improved.
In some embodiments, referring to fig. 1, 3, 4 and 6, to facilitate the first measurer receiving data, the pitot tube measuring device 10 further includes a first extension tube 17 and a second extension tube 18 connected to the rear end plug 14; the first extension pipe 17 communicates with the total pressure pipe 15, and the second extension pipe 18 communicates with the static pressure pipe 16. The first measuring device is not directly connected to the total pressure pipe 15 and the static pressure pipe 16, but to the first extension pipe 17 and the second extension pipe 18.
In some embodiments, referring to fig. 1-6, the pitot tube measuring device 10 further includes a mounting support 30; the mounting support 30 can improve the structural stability of the airspeed measurement device and can also facilitate the installation of the airspeed measurement device on flight equipment;
the mounting support 30 comprises an upper shell 31 and a lower shell 32 which are fixedly connected, and a receiving groove 33 is formed between the upper shell 31 and the lower shell 32; the accommodating groove 33 is a through groove, that is, two ends of the accommodating groove 33 are not closed; the rear end plug 14, a part of the pipe sleeve 13 on one side of the rear end plug 14, and a part of the first extension pipe 17 and a part of the second extension pipe 18 on the other side of the rear end plug 14 are all accommodated in the accommodating groove 33;
the first and second extension pipes 17 and 18 extend to the outside of the mounting bracket 30 through the receiving groove 33, thereby facilitating the connection with the first measurer.
In some embodiments, the sleeve 13 is cylindrical in shape, the opening of the receiving groove 33 in contact with the sleeve 13 is circular in shape and has the same diameter as the sleeve 13 in order to improve the sealing property, and the shape and size of the inside of the receiving groove 33 correspond to those of the rear end plug 14 in order to improve the connection stability, respectively.
In some embodiments, the upper shell 31 and the lower shell 32 are fixedly connected by at least two bolts 34, and the upper shell 31 and the lower shell 32 have connecting holes corresponding to the positions of the bolts 34.
In some embodiments, referring to fig. 1, 3, 4 and 6, the impeller measuring device 20 includes a housing 21 fixedly connected to the pitot tube measuring device 10, a fixing portion 22 fixedly connected to the housing 21, an impeller 23 rotatably connected to the fixing portion 22, and a measuring assembly 40;
the measuring component 40 measures the rotating speed of the impeller 23, and calculates the airspeed of the flying equipment according to the rotating speed of the impeller 23.
In some embodiments, the measurement assembly 40 includes a measurement circuit 24, and a second measurer (not shown) connected to the measurement circuit 24;
the measuring circuit 24 is configured to measure a rotational speed of the impeller 23, convert the rotational speed of the impeller 23 into a corresponding electrical signal, and transmit the electrical signal to a second measurer;
and the second measurer is used for calculating the airspeed of the flight equipment according to the electric signal.
In some embodiments, the housing 21 is fixedly attached to the shroud 13. The housing 21 and the pipe sleeve 13 may be fixedly connected by a pin or by an adhesive.
In some embodiments, the sleeve 13 is cylindrical, and in order to facilitate the fixed connection between the housing 21 and the sleeve 13, the end of the housing 12 in contact with the sleeve 13 is arc-shaped, and the radius of the arc is the same as the radius of the sleeve 13.
In some embodiments, the measurement circuit 24 includes a diode 241 and a phototransistor 242 disposed inside the housing 21 and opposite to each other; of course, other circuits connecting the diode 241 and the phototransistor 242 are also included;
the housing 21 exposes the diode 241 and the phototransistor 242;
the diode 241 is used for emitting light to irradiate the phototriode 242;
when the impeller 23 rotates, the light emitted by the diode 241 is intermittently blocked;
the phototriode 242 is configured to measure a rotation speed of the impeller and convert the rotation speed of the impeller 23 into a corresponding electrical signal, wherein the phototriode 242 outputs a high level of the electrical signal when receiving the light emitted by the diode 241, and outputs a low level of the electrical signal when not receiving the light emitted by the diode 241.
The base of the phototriode 242 may serve as an optical window for receiving light emitted from the diode 241, when the impeller 23 rotates, the blade of the impeller 23 intermittently passes through between the diode 241 and the base of the phototriode 242 according to the rotation speed, when the blade of the impeller 23 is located between the diode 241 and the base of the phototriode 242, the light emitted from the diode 241 is blocked, the base of the phototriode 242 cannot receive the light, and thus a low level is output, when the rotation speed of the impeller 23 is faster, the frequency of the blade of the impeller 23 passing through between the diode 241 and the base of the phototriode 242 is faster, the frequency of the low level of the electrical signal is faster, that is, the frequency of the low level of the electrical signal corresponds to the rotation speed of the impeller 23, and the second measurer may calculate the airspeed of the flying device according to the frequency of the low level of the electrical signal.
In some embodiments, the measurement circuit 24 further includes a measurement line 25 connected to the phototransistor 242;
the measuring line 25 is used to transmit the electrical signal to a second measurer. The measuring line 25 can not only transmit electrical signals but also supply the measuring circuit 24.
In some embodiments, one end of the measurement line 25 is connected to the phototransistor 242 through a connection via (not shown) penetrating the tube sleeve 13 and the housing 21, and the other end extends to the outside of the rear plug 14 through a fourth via 143 disposed on the rear plug 14 to be connected to the second measuring device.
In some embodiments, referring to fig. 1 to 6, the housing 21 has a receiving hole 211; the accommodation hole 211 is a through hole, that is, both ends of the accommodation hole 211 are not closed; the fixing portion 22 and the impeller 23 are located in the accommodation hole 211. The housing 21 exposes the diode 241 and the phototransistor 242 at a side near the receiving hole 211.
In some embodiments, the fixing portion 22 includes a first bearing seat 221 fixedly connected to the housing 21, a first bearing 2211 located in the first bearing seat 221, a second bearing seat 222 fixedly connected to the housing 21 and disposed parallel to the first bearing seat 221, a second bearing 2221 located in the second bearing seat 222, and a rotating shaft 223 rotatably connected to both the first bearing 2211 and the second bearing 2221;
the impeller 23 is fixedly connected with the rotating shaft 223.
In some embodiments, the shape of the receiving hole 211 may be any shape as long as it does not affect the rotation of the impeller 23 and the photodiode 242 receives the light emitted from the diode 241. In the present invention, the shape of the accommodation hole 211 is preferably circular.
When the fixing portion 22 is located in the receiving hole 211, in order to improve connection stability, the first bearing seat 221 includes at least three first connection legs connected to the first bearing 2211, the first connection legs are fixedly connected to a hole wall of the receiving hole 211, orientations of the plurality of first connection legs are different, and when the number of the first connection legs is three, an included angle between every two adjacent first connection legs may be 120 °;
the second bearing seat 222 includes at least three second connection legs connected to the second bearing 2221, the second connection legs are fixedly connected to the hole wall of the receiving hole 211, the orientations of the plurality of second connection legs are different, and when the number of the second connection legs is three, an included angle between every two adjacent second connection legs may be 120 °.
In some embodiments, the second bearing seat 222 is identical in structure to the first bearing seat 221.
In some embodiments, the first measurer and the second measurer may be the same measurer.
Based on above-mentioned airspeed measurement device, still provide a flight equipment in this application's embodiment, include as above airspeed measurement device.
The airspeed measuring device and the flight equipment that this application embodiment provided adopt pitot tube measuring device 10 and impeller measuring device 20 independent work respectively, wherein, pitot tube measuring device 10 measures the airspeed of flight equipment according to the pressure differential between the total pressure of air current and the air current static pressure when flight equipment flies, impeller measuring device 20 measures the airspeed of flight equipment according to the rotational speed of impeller measuring device 20 when flight equipment flies. This airspeed measuring device and flight equipment utilize pitot tube measuring device 10 and two kinds of different measurement methods of impeller measuring device 20 to carry out the airspeed measurement, have increased the variety of airspeed measurement data source, through carrying out data fusion with two kinds of measured data to improve airspeed measurement's accuracy. The impeller of the impeller measuring device 20 is insensitive to fog and rainwater, and is not easy to lose efficacy in extreme weather, so that the environmental adaptability of the airspeed measuring device is improved. In addition, when the pitot tube measuring device 10 fails, the judgment can be made through the airspeed measurement data of the impeller measuring device 20, so that the safety of the flight equipment is guaranteed, and the safety of the operation of the flight equipment is improved. In addition, the impeller measuring device 20 is generally smaller in size, lighter in weight, and simpler in structure than the pitot tube measuring device 10, and compared with the prior art in which a double pitot tube measuring device is adopted to prevent the airspeed measuring device from failing, the present invention has the characteristics of small size, light weight, and simple structure.
In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and parts that are not described in detail in a certain embodiment may refer to the above detailed descriptions of other embodiments, and are not described herein again.
In a specific implementation, each unit or structure may be implemented as an independent entity, or may be combined arbitrarily to be implemented as one or several entities, and the specific implementation of each unit or structure may refer to the foregoing embodiments, which are not described herein again.
The airspeed measuring device and the flight equipment provided by the embodiment of the invention are described in detail, a specific example is applied in the text to explain the principle and the implementation mode of the invention, and the description of the embodiment is only used for helping to understand the method and the core idea of the invention; meanwhile, for those skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (15)
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| CN202010406158.4A CN113671211A (en) | 2020-05-14 | 2020-05-14 | Airspeed measuring device and flight equipment |
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| CN202010406158.4A CN113671211A (en) | 2020-05-14 | 2020-05-14 | Airspeed measuring device and flight equipment |
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