CN220357097U - Device integrating attack angle and sideslip angle measurement - Google Patents
Device integrating attack angle and sideslip angle measurement Download PDFInfo
- Publication number
- CN220357097U CN220357097U CN202320968035.9U CN202320968035U CN220357097U CN 220357097 U CN220357097 U CN 220357097U CN 202320968035 U CN202320968035 U CN 202320968035U CN 220357097 U CN220357097 U CN 220357097U
- Authority
- CN
- China
- Prior art keywords
- angle
- carrier
- attack
- sideslip
- integrating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 16
- 238000009434 installation Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Landscapes
- Length Measuring Devices With Unspecified Measuring Means (AREA)
Abstract
The utility model discloses a device for measuring an integrated attack angle and a sideslip angle, which belongs to the technical field of flight parameter measurement and comprises a carrier, wherein two angle encoders with mutually perpendicular axes are fixedly arranged on the carrier, rotary tables are coaxially and fixedly arranged at the end parts of rotating shafts of the angle encoders, and vane wings are fixedly arranged on the rotary tables; wherein, still be provided with the balancing weight that is used for the balancing on the carousel. The utility model has simple structure and reasonable design, can effectively reduce the overall structure size, and is further suitable for the installation and use of the microminiature fixed wing unmanned aerial vehicle.
Description
Technical Field
The utility model relates to the technical field of flight parameter detection, in particular to a device for integrating angle of attack and sideslip angle measurement.
Background
The attack angle data and the sideslip angle data have significance for sensing the attitude of the aircraft, and related data are generally collected by adopting an attack angle sideslip angle sensor. However, the conventional angle of attack sideslip angle sensor is designed mainly for general aviation aircrafts and large unmanned aerial vehicles, and has large volume, complex installation structure and high installation requirement, so that the sensor is difficult to be suitable for miniature unmanned aerial vehicles.
In order to solve the problem, chinese patent publication No. CN216206641U discloses a miniature unmanned aerial vehicle air flow measuring device, which comprises a airspeed tube assembly, wherein the front end of the airspeed tube assembly is provided with a total pressure air inlet, the front end of the airspeed tube assembly is also provided with a static pressure air inlet, and the middle section of the airspeed tube assembly is fixedly provided with an angle-of-attack flag and a sideslip angle flag; the airspeed tube assembly is also provided with an installation connecting pipe and a connector near the tail end, and the airspeed tube assembly is connected with an atmosphere computer through a connector signal.
Although the utility model can realize the measurement of the attack angle and the sideslip angle, the main rod for supporting the attack angle mark flag and the sideslip angle mark flag is directly exposed, and the length of the movable rod is larger, so that the two mark flags need to keep a larger distance to avoid collision, the measuring device needs to have a larger length, and the flying gesture of the microminiature unmanned aerial vehicle is easily influenced when the measuring device is applied to the microminiature unmanned aerial vehicle.
Disclosure of Invention
The utility model aims to provide a device for integrating angle of attack and sideslip angle measurement, which aims to solve the problems in the prior art that the dimensional structure of the angle of attack and sideslip angle measurement device is large.
In order to achieve the above purpose, the technical scheme of the utility model is as follows:
the device for measuring the integrated attack angle and sideslip angle comprises a carrier, wherein two angle encoders with mutually perpendicular axes are fixedly arranged on the carrier, rotary tables are coaxially and fixedly arranged at the end parts of rotating shafts of the angle encoders, and wind vane wings are fixedly arranged on the rotary tables; and the turntable is also provided with a balancing weight for balancing.
Preferably, the carrier is in a cylindrical structure, and the head end is subjected to conical treatment.
Preferably, the angle encoders are all arranged in the carrier, two shaft holes respectively used for enabling the rotating shafts of the two angle encoders to penetrate out are formed in the surface of the carrier, and the rotary disc is arranged outside the carrier.
Preferably, two filling holes for respectively disassembling and assembling the two angle encoders are further formed in the surface of the carrier.
Preferably, the angle encoder is detachably and fixedly connected with the carrier through a screw or a bolt.
Preferably, a wire slot for wiring is formed on the surface of the carrier, and the wire slot is connected with the two filling holes in series.
Preferably, the tail end of the carrier is coaxially provided with a connecting pipe for being connected with an aircraft, the connecting pipe is communicated with the inner space of the carrier, and the tail end surface of the carrier is also provided with a through hole communicated with the wire slot.
Preferably, a clamping groove for installing the wind vane is formed in the surface of the turntable.
Preferably, the carrier is also fixedly provided with a level meter.
By adopting the technical scheme, the utility model has the beneficial effects that: in the unmanned aerial vehicle flight process, the two vane wings correspondingly rotate under the influence of wind direction change and drive the angle encoder to rotate through the turntable, and rotation information of the angle encoder is transmitted to an onboard computer carried in the fuselage through a cable, so that the onboard computer obtains an attack angle and a sideslip angle of the unmanned aerial vehicle. In the utility model, the vane is directly connected with the rotating shaft of the angle encoder through the turntable, so that a long rod piece is not required to be configured, the whole structure is more compact, and the wind vane is more suitable for the microminiature fixed-wing unmanned aerial vehicle.
Drawings
FIG. 1 is a front view of the present utility model;
FIG. 2 is a rear view of the present utility model;
FIG. 3 is a schematic diagram of the structure of the present utility model;
FIG. 4 is a schematic view of another embodiment of the present utility model;
FIG. 5 is a schematic view of a turntable separated from an angle encoder according to the present utility model;
FIG. 6 is a schematic diagram of the connection of the vane and counterweight to the turntable according to the utility model.
In the figure, 1-carrier, 11-filling hole, 12-shaft hole, 13-sinking groove, 14-wire slot, 15-through hole, 2-angle encoder, 3-turntable, 31-clamping groove, 4-vane, 5-balancing weight, 6-cable, 7-connecting pipe and 8-level.
Detailed Description
The following describes the embodiments of the present utility model further with reference to the drawings. The description of these embodiments is provided to assist understanding of the present utility model, but is not intended to limit the present utility model. In addition, the technical features of the embodiments of the present utility model described below may be combined with each other as long as they do not collide with each other.
It should be noted that, in the description of the present utility model, the positional or positional relation indicated by the terms such as "upper", "lower", "left", "right", "front", "rear", etc. are merely for convenience of describing the present utility model based on the description of the structure of the present utility model shown in the drawings, and are not intended to indicate or imply that the apparatus or element to be referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present utility model.
The terms "first" and "second" in this technical solution are merely references to the same or similar structures, or corresponding structures that perform similar functions, and are not an arrangement of the importance of these structures, nor are they ordered, or are they of a comparative size, or other meaning.
In addition, unless explicitly stated and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two structures. It will be apparent to those skilled in the art that the specific meaning of the terms described above in this application may be understood in the light of the general inventive concept in connection with the present application.
An integrated attack angle and sideslip angle measuring device is shown in fig. 1-6, and comprises a carrier 1, an angle encoder 2, a rotary disc 3, a vane 4 and a balancing weight 5.
The carrier 1 is configured in a cylindrical configuration, and its head end is tapered to be closed.
The angle encoders 2 are two, and the axes of the two are perpendicular to each other, and the two angle encoders 2 are arranged inside the carrier 1. Wherein, two filling holes 11 for respectively disassembling and assembling the two angle encoders 2 are arranged on the surface of the carrier 1. And at the position of the surface of the carrier 1 opposite to the loading hole 11, two shaft holes 12 for respectively penetrating out the rotation shafts of the two angle encoders 2 are further formed, so that the rotation shafts of the angle encoders 2 can penetrate out from the inside of the carrier 1. In this embodiment, after the angle encoder 2 is installed into the carrier 1 from the loading hole 11 and its rotation shaft passes through the shaft hole 12, the housing of the angle encoder 2 is detachably and fixedly connected to the carrier 1 by a screw, for example, a certain range of the surface of the carrier 1 is cut and flattened with the shaft hole 12 as the center, so as to obtain a sinking groove 13 suitable for connecting the screw.
The rotary shaft end of each angle encoder 2 is fixedly mounted coaxially with a turntable 3, i.e. the turntable 3 is arranged outside the carrier 1 and preferably at a sink recess, so as to conceal at least a part of the turntable 3 and thereby minimize wind resistance.
The vane 4 is configured as a substantially trapezoidal flat wing structure, wherein a protruding clamping block (not shown in the figure) is arranged on one wing edge, and a clamping groove 31 suitable for matching is correspondingly formed on the surface of the turntable 3, so that the vane 4 is connected to the surface of the turntable 3 in an embedded manner. Wherein the wing surface of the vane 4 coincides with the axis of the turntable 3.
It will be appreciated that, after the vane 4 is mounted on the turntable 3, its geometric centre is generally no longer in line with the axis of the turntable 3, which makes the vane 4 eccentric and the turntable 3 rotates unbalanced, so that the measurement of the wind direction is not accurate. To solve this problem, the present embodiment is further provided with a balancing weight 5 for balancing on the turntable 3 so that the turntable 3 mounted with the vane 4 and the balancing weight 5 resumes dynamic balance again.
Setting the weight 5 on the turntable 3 includes two ways: one is to open holes at the corresponding positions of the turntable 3 and fill the holes with a balancing weight made of a material having a higher density; another is to directly fix a weight made of the same material at a lighter position of the turntable 3 (opposite to the position where the center of gravity of the vane 4 is located), and generally, when the turntable 3 is manufactured, the weight is integrally formed on the turntable 3, that is, the position where the weight is required for the turntable 3 has a greater thickness, or conversely, a part of the material is removed at a heavier side of the turntable 3 (i.e., the side where the center of gravity of the vane 4 is located). In this embodiment, the two modes are adopted simultaneously.
In this embodiment, the cable 6 (including the power supply cable and the communication cable, or the cable having both the communication function and the power supply function) for connecting the angle encoders 2 is routed from the loading hole 11, and accordingly, the wire slot 14 for routing is formed on the surface of the carrier 1, and the wire slot 14 is simultaneously connected in series with the two loading holes 11, so that the cables connected to the two angle encoders 2 are routed through the same wire slot 14.
In this embodiment, the rear end of the carrier 1 is coaxially provided with a connection tube 7 for connection with an aircraft, for example, the connection tube 7 is screwed with the carrier 1 while the connection tube 7 communicates with the inner space of the carrier 1, and the rear end surface of the carrier 1 is also provided with a through hole 15 communicating with a wire slot 14. So configured, the cable can be connected to the onboard computer and power supply carried by the fuselage via the connection tube 7, thereby powering the angle encoder 2 and collecting and processing its yaw angle.
In this embodiment, a level 8 is also fixedly mounted on the carrier 1, so that when the connection pipe 7 is fixed to the aircraft, the attitude of the carrier 1 is guided by the level 8 to ensure that the axes of the two angle encoders 2 are respectively in a horizontal and vertical state. In the specific installation, the level 8 is located at the top surface side of the carrier 1, the weathervaning wing 4 for measuring sideslip angle is located at the top surface side of the carrier 1, and the weathervaning wing 4 for measuring attack angle is located at the side surface of the carrier 1.
The working process of the utility model is as follows:
in use, the connection tube 7 is fixedly mounted to the microminiature fixed wing unmanned aerial vehicle, typically horizontally mounted in front of the fuselage, and the mounting posture of the carrier 1 is guided by the level 8. In the flight process of the unmanned aerial vehicle, the two vane wings 4 correspondingly rotate under the influence of wind direction change, the rotary table 3 drives the angle encoder 2 to rotate, and rotation information of the angle encoder 2 is transmitted to an onboard computer carried in the unmanned aerial vehicle body through the cable 6, so that the onboard computer obtains the attack angle and the sideslip angle of the unmanned aerial vehicle. In the utility model, the vane 4 is directly connected with the rotating shaft of the angle encoder 2 through the turntable 3, so that long rod pieces do not need to be configured, the whole structure is more compact, and the utility model is more suitable for microminiature fixed wing unmanned aerial vehicles.
The embodiments of the present utility model have been described in detail above with reference to the accompanying drawings, but the present utility model is not limited to the described embodiments. It will be apparent to those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the utility model, and yet fall within the scope of the utility model.
Claims (9)
1. An integrated angle of attack and sideslip angle measuring device which characterized in that: comprises a carrier, wherein two angle encoders with mutually perpendicular axes are fixedly arranged on the carrier, the rotating shaft ends of the angle encoders are coaxially and fixedly provided with rotating discs, and the rotating discs are fixedly provided with vane wings; and the turntable is also provided with a balancing weight for balancing.
2. The apparatus for integrating angle of attack and sideslip angle measurement of claim 1, wherein: the carrier is in a cylindrical structure, and the head end of the carrier is subjected to conical treatment.
3. The apparatus for integrating angle of attack and sideslip angle measurement of claim 2, wherein: the angle encoders are respectively arranged in the carrier, two shaft holes respectively used for enabling the rotating shafts of the two angle encoders to penetrate out are formed in the surface of the carrier, and the rotary disc is arranged outside the carrier.
4. The apparatus for integrating angle of attack and sideslip angle measurement of claim 3, wherein: the surface of the carrier is also provided with two filling holes for disassembling and assembling the two angle encoders respectively.
5. The apparatus for integrating angle of attack and sideslip angle measurement of claim 4, wherein: the angle encoder is detachably and fixedly connected with the carrier through a screw or a bolt.
6. The apparatus for integrating angle of attack and sideslip angle measurement of claim 4, wherein: the surface of the carrier is provided with a wire slot for wiring, and the wire slot is connected with two filling holes in series.
7. The apparatus for integrating angle of attack and sideslip angle measurement of claim 6, wherein: the tail end of the carrier is coaxially provided with a connecting pipe used for being connected with an aircraft, the connecting pipe is communicated with the inner space of the carrier, and the surface of the tail end of the carrier is also provided with a through hole communicated with the wire slot.
8. The apparatus for integrating angle of attack and sideslip angle measurement of claim 1, wherein: the surface of the turntable is provided with a clamping groove for installing the vane.
9. The apparatus for integrating angle of attack and sideslip angle measurement of claim 1, wherein: and the carrier is also fixedly provided with a level meter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320968035.9U CN220357097U (en) | 2023-04-25 | 2023-04-25 | Device integrating attack angle and sideslip angle measurement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320968035.9U CN220357097U (en) | 2023-04-25 | 2023-04-25 | Device integrating attack angle and sideslip angle measurement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220357097U true CN220357097U (en) | 2024-01-16 |
Family
ID=89476360
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320968035.9U Active CN220357097U (en) | 2023-04-25 | 2023-04-25 | Device integrating attack angle and sideslip angle measurement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220357097U (en) |
-
2023
- 2023-04-25 CN CN202320968035.9U patent/CN220357097U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102944375B (en) | Compound pneumatic data sensor applicable to micro aerial vehicle | |
| CN104034301B (en) | Microminiature angle of attack sensor | |
| EP3444186B1 (en) | Flight vehicle, tilt driving mechanism and control method therefor | |
| CN212386689U (en) | Three-rotor tilt rotor aircraft capable of tilting | |
| CN104787327A (en) | Axle distance-variable multi-rotor aircraft | |
| CN204007586U (en) | Microminiature angle of attack sensor | |
| CN208313197U (en) | Aircraft rudder surface deflection angle measurement device | |
| CN108583867A (en) | A kind of three ducted fan bionic Aircraft of torque self-balancing | |
| CN220357097U (en) | Device integrating attack angle and sideslip angle measurement | |
| CN114132512B (en) | Optical fiber icing sensor probe and adjusting method | |
| CN209351591U (en) | A kind of VTOL fixed-wing unmanned plane rotor inclining rotary mechanism | |
| CN115140323A (en) | Pneumatic characteristic testing device of tension torque decoupling type single rotor system | |
| CN205300888U (en) | A test model for measuring rudder face hinge moment | |
| CN210912933U (en) | Control surface measuring device of fixed wing unmanned aerial vehicle | |
| CN114001906A (en) | Automatic rudder deflection angle changing device for hypersonic wind tunnel hinge moment measurement test and use method thereof | |
| CN207917149U (en) | A kind of inclining rotary mechanism for unmanned plane | |
| CN208887551U (en) | A kind of oar propeller carpenters square measuring unmanned helicopter blade pitch angle | |
| CN212709964U (en) | But VTOL aircraft based on rotor and fan wing | |
| CN115230958A (en) | Bionic investigation type unmanned aerial vehicle | |
| CN215155629U (en) | Vertical take-off and landing type mooring unmanned aerial vehicle system | |
| CN215984348U (en) | Fixed wing unmanned aerial vehicle rudder angle calibration device | |
| CN214084750U (en) | Unmanned plane | |
| CN213768962U (en) | Exploration unmanned aerial vehicle that exploration precision is high | |
| CN205209734U (en) | Balance installation base | |
| CN211001888U (en) | Four rotor unmanned aerial vehicle camera linkage |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |