CN112857346A - Rotary platform for helicopter compass field calibration and measurement method - Google Patents
Rotary platform for helicopter compass field calibration and measurement method Download PDFInfo
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- CN112857346A CN112857346A CN202110084261.6A CN202110084261A CN112857346A CN 112857346 A CN112857346 A CN 112857346A CN 202110084261 A CN202110084261 A CN 202110084261A CN 112857346 A CN112857346 A CN 112857346A
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- 229910010293 ceramic material Inorganic materials 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 230000005389 magnetism Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 229910000963 austenitic stainless steel Inorganic materials 0.000 description 2
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- 229910000831 Steel Inorganic materials 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C17/00—Compasses; Devices for ascertaining true or magnetic north for navigation or surveying purposes
- G01C17/38—Testing, calibrating, or compensating of compasses
Abstract
The invention provides a rotary platform for a helicopter compass field calibration and a measuring method, and relates to the technical field of compass calibration. The utility model provides a revolving platform for helicopter school compass field, includes the fixing base and rotates the gyration dish of locating above-mentioned fixing base, and above-mentioned revolving platform is equipped with the count subassembly that is used for reading above-mentioned gyration dish turned angle. The rotary platform can be moved and carried, so that the helicopter can rotate to perform calibration operation conveniently. In addition, the invention also provides a measuring method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter onto a rotary disc to push the helicopter to rotate, driving the rotary disc to rotate by the main machine wheel, and reading the rotation angle of the rotary disc by a counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain the deviation. By adopting the method, the compass of the helicopter can be conveniently calibrated.
Description
Technical Field
The invention relates to the technical field of compass calibration, in particular to a rotary platform for a helicopter compass calibration field and a measuring method.
Background
Currently, the main navigation system of a helicopter is an inertial navigation and integrated navigation system, and a magnetic compass is used as a component of the integrated navigation system to play a role in backing up an instrument. The radio navigation system is mainly a navigation instrument used when a helicopter lands at an airport. The calibration of the magnetic compass and the radio compass is a basic work for the maintenance of the helicopter.
At present, the calibration operation of the magnetic compass and the radio compass is usually carried out by depending on a fixed compass field. The technical principle of compass calibration is as follows: the accurate azimuth angles of the helicopter in different directions are given by the technical means, the accurate azimuth angles are compared with azimuth angle data measured by the onboard compass, measuring errors of the onboard compass in different directions are obtained, and the compass errors are eliminated or adjusted to a reasonable interval by a standardized calibration method according to the error data. The nature of the compass field is technically that it provides an accurate azimuth angle for the helicopter.
Therefore, a fixed compass field is required to be relied on during calibration, calibration cannot be realized under the condition of no reliance, and particularly, the calibration device does not meet the actual application requirements in the field and needs highly motorized compass calibration equipment in the field.
Disclosure of Invention
The invention aims to provide a rotary platform for a helicopter compass field, which can be moved and carried, and is convenient for the helicopter to rotate for calibration operation.
Another object of the invention is to provide a measuring method with which the calibration of the compass of the helicopter is facilitated.
The embodiment of the invention is realized by the following steps:
in a first aspect, an embodiment of the present application provides a revolving platform for helicopter compass field, including the fixing base and the revolving disk of locating above-mentioned fixing base with rotating, above-mentioned revolving platform is equipped with the count subassembly that is used for reading above-mentioned revolving disk turned angle.
Further, in some embodiments of the present invention, the counting assembly employs a grating ruler, the grating ruler includes a scale grating and a grating reading head, the scale grating is circumferentially disposed along a sidewall of the rotating disc, and the grating reading head is disposed on the fixing base.
Furthermore, in some embodiments of the present invention, the counting assembly employs a photosensitive counter, the photosensitive counter is disposed on the rotating disc, and the fixing base is uniformly provided with a plurality of scale grooves matching with the photosensitive counter along the circumferential direction of the rotating disc.
Further, in some embodiments of the present invention, the upper sidewall of the rotating disc is provided with a locking groove, and the section of the locking groove is inverted trapezoid.
Further, in some embodiments of the present invention, the upper sidewall of the rotating disc located in the clamping groove is provided with an anti-slip pattern.
Further, in some embodiments of the present invention, a through hole penetrating through the rotary disk is formed in a side wall of the rotary disk, and the through hole is communicated with the clamping groove and is disposed below the clamping groove.
Further, in some embodiments of the present invention, the fixing base is provided with a rotation hole penetrating through the fixing base, and the rotation disc is disposed in the rotation hole and rotatably connected to the fixing base.
Further, in some embodiments of the present invention, a plurality of balls are disposed between the rotary disc and the fixed base; a first sliding groove is formed in the inner side wall of the fixed seat along the circumferential direction of the rotary hole, and a second sliding groove is formed in the outer side wall of the rotary disc in the circumferential direction; one end of any ball is embedded into the first sliding groove, and the other end of any ball is embedded into the second sliding groove.
In a second aspect, an embodiment of the present application provides a measurement method, including calibrating an initial azimuth angle of a helicopter compass; moving a main machine wheel of the helicopter onto a rotary disc to push the helicopter to rotate, driving the rotary disc to rotate by the main machine wheel, and reading the rotation angle of the rotary disc by a counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain the deviation.
Further, in some embodiments of the present invention, the calibrating the initial azimuth angle of the helicopter compass includes using a laser theodolite to direct a laser to the runway direction of the airport, then directing the laser to the ground perpendicular to the runway, and placing the center of the rotating platform on the laser spot;
after moving one main wheel of the helicopter to the rotary disk, the method also comprises the step of pushing the helicopter to enable the central point of the outer side of the hub of the other main wheel of the helicopter to be aligned with the laser spot in the vertical direction, and then the helicopter faces the airport runway direction.
Compared with the prior art, the embodiment of the invention at least has the following advantages or beneficial effects:
the embodiment of the invention provides a rotary platform for a helicopter compass field, which comprises a fixed seat and a rotary disk rotatably arranged on the fixed seat, wherein the rotary platform is provided with a counting assembly for reading the rotation angle of the rotary disk.
When the helicopter is actually used, after the initial magnetic azimuth angle of the helicopter is calibrated by using the laser theodolite compass, the rotary platform can be placed on the ground, and the fixed seat is in contact with the ground and supports the rotary disk; moving a main engine wheel of the helicopter to the central position of the rotary disc, then pushing the helicopter to rotate around the rotary platform, driving the rotary disc to rotate by the main engine wheel, and reading the rotation angle of the rotary disc by the counting assembly so as to obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain deviation, and calibrating the compass of the helicopter.
The rotary platform provided by the invention can be set to be a little larger than a main engine wheel of the helicopter, so that the rotary platform is convenient to move and carry in a motorized mode and convenient for the helicopter to rotate for calibration operation.
The embodiment of the invention also provides a measuring method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter onto a rotary disc to push the helicopter to rotate, driving the rotary disc to rotate by the main machine wheel, and reading the rotation angle of the rotary disc by a counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain the deviation. By adopting the method, the compass of the helicopter can be conveniently calibrated.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic structural diagram of a rotary platform provided with a scale grating and a grating reading head according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a rotary platform having a scale grating and a grating readhead according to an embodiment of this invention;
fig. 3 is a cross-sectional view of a rotary platform with a photosensitive counter according to an embodiment of the present invention.
Icon: 1-a rotary disc; 2-a fixed seat; 3-a clamping groove; 4-a through hole; 5-rotating the hole; 6-rolling balls; 7-scale grating; 8-grating reading head; 9-photosensitive counter.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without any inventive step, are within the scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that, if the terms "vertical", "horizontal", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings or the orientation or positional relationship which is usually placed when the product of the present invention is used, the description is only for convenience of describing the present invention and simplifying the description, but the indication or suggestion that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, cannot be understood as limiting the present invention.
Furthermore, the terms "horizontal", "vertical" and the like do not require that the components be absolutely horizontal or vertical, but may be slightly inclined. Such as "horizontal" simply means that its orientation is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the embodiments of the present invention, "a plurality" represents at least 2.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Examples
Referring to fig. 1 to 3, the present embodiment provides a rotary platform for helicopter compass field calibration, which includes a fixing base 2 and a rotary disk 1 rotatably disposed on the fixing base 2, wherein the rotary platform is provided with a counting assembly for reading a rotation angle of the rotary disk 1.
When the helicopter is actually used, after the initial magnetic azimuth angle of the helicopter is calibrated by using the laser theodolite compass, the rotary platform can be placed on the ground, and the fixed seat 2 is in contact with the ground and supports the rotary disk 1; moving a main engine wheel of the helicopter to the central position of the rotary disc 1, then pushing the helicopter to rotate around the rotary platform, driving the rotary disc 1 to rotate by the main engine wheel, and reading the rotation angle of the rotary disc 1 by the counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain deviation, and calibrating the compass of the helicopter.
The rotary platform provided by the invention can be set to be a little larger than a main engine wheel of the helicopter, so that the rotary platform is convenient to move and carry in a motorized mode and convenient for the helicopter to rotate for calibration operation.
Optionally, the revolving platform of the present embodiment is horizontally placed on the ground, and the revolving disc 1 rotates on the horizontal plane.
Because the compass needs to be calibrated so as to reduce the influence of an external magnetic conductive material on a magnetic field to improve the calibration precision, optionally, the rotating disc 1 and the fixing base 2 of the embodiment are made of a special austenitic stainless steel material, and the special austenitic stainless steel material is a high-strength corrosion-resistant magnetism-free special steel material which has high hardness, can support the helicopter, does not have magnetism, and improves the calibration precision.
As shown in fig. 1-3, in some embodiments of the present invention, the counting assembly is a grating scale, the grating scale includes a scale grating 7 and a grating reading head 8, the scale grating 7 is circumferentially disposed along a sidewall of the rotating disc 1, and the grating reading head 8 is disposed on the fixing base 2.
A grating scale, also called a grating scale displacement sensor (grating scale sensor), is a measurement feedback device that operates using the optical principle of a grating. The grating ruler can be used for detecting linear displacement or angular displacement. The signal output by the sensor is digital pulse, and the sensor has the characteristics of large detection range, high detection precision and high response speed. Therefore, the relative displacement of the scale grating 7 is read by the grating reading head 8 and converted into the rotation angle of the rotary disk 1.
As shown in fig. 1-3, in some embodiments of the present invention, the counting assembly employs a photosensitive counter 9, the photosensitive counter 9 is disposed on the rotary disk 1, and the fixing base 2 is uniformly provided with a plurality of scale grooves along the circumference of the rotary disk 1, the scale grooves cooperating with the photosensitive counter 9.
The working principle of the photosensitive counter 9 is as follows: when an object blocks the illumination of the photoresistor, the resistance value of the photoresistor is increased, the current in the circuit is reduced, the voltages at two ends of the photoresistor are reduced, the signal processing system obtains low voltage, and the number of the photoresistor is counted every time the photoresistor 9 is switched from high voltage to low voltage, so that the purpose of automatic counting is achieved, the number of the scale grooves through which the rotary disc 1 rotates can be calculated, and the rotation angle of the rotary disc 1 can be calculated according to the number of the scale grooves through which the rotary disc 1 passes.
As shown in fig. 1 to 3, in some embodiments of the present invention, the upper sidewall of the rotary disk 1 is provided with a catching groove 3.
According to the invention, the clamping groove 3 is formed in the upper side wall of the rotary disc 1, so that the main engine wheel of the helicopter can be moved into the clamping groove 3 to realize clamping and fixing, the main engine wheel of the helicopter is prevented from moving on the rotary disc 1 in the process of calibration operation by rotation of the helicopter, and the calibration precision is further improved.
In the current domestic heaviest helicopter, through pressure bearing analysis and multiple on-site measurements, under the condition that the tire pressure is normal and the inner and outer oil tanks are filled with oil, the length of the wheel contact surface is 45-50cm, so optionally, the opening length of the clamping groove 3 of the embodiment is more than 50cm, and through mechanical analysis, in order to meet the requirement of pressure bearing capacity, the outer diameter of the rotary platform is more than 65 cm.
As shown in fig. 1 to 3, in some embodiments of the present invention, the above-mentioned catching grooves 3 have an inverted trapezoidal section.
According to the invention, the section of the clamping groove 3 is in an inverted trapezoid shape, so that after the main engine wheel of the helicopter moves into the clamping groove 3, the inverted trapezoid shape is convenient for limiting the two sides of the main engine wheel of the helicopter, the main engine wheel of the helicopter is further prevented from moving on the rotary disc 1 in the process of calibration operation by rotation of the helicopter, and the calibration precision is improved.
And through the trapezoidal design of inversion, the main engine wheel that enables the helicopter is close to ground as far as possible, reduces the degree of inclination of helicopter, and is more steady when making the helicopter rotate.
As shown in fig. 1 to 3, in some embodiments of the present invention, the upper sidewall of the rotating disk 1 located in the clamping groove 3 is provided with anti-slip threads.
According to the invention, the anti-slip grains are arranged on the upper side wall of the rotary disk 1 positioned in the clamping groove 3, so that the friction force between the main wheel of the helicopter and the upper side wall of the rotary disk 1 is increased, the main wheel of the helicopter is prevented from sliding on the upper side wall of the rotary disk 1, and the calibration precision is further improved.
As shown in fig. 1 to 3, in some embodiments of the present invention, a through hole 4 is formed through the side wall of the rotary disk 1, and the through hole 4 is communicated with the catching groove 3 and is formed below the catching groove 3.
According to the invention, the through hole 4 penetrating through the rotary disc 1 is formed in the side wall of the rotary disc 1, and the through hole 4 is communicated with the clamping groove 3 and is arranged below the clamping groove 3, so that the mechanical processing technology is favorably developed, and the weight of the rotary platform is effectively reduced.
As shown in fig. 1-3, in some embodiments of the present invention, the fixing base 2 is provided with a rotation hole 5 penetrating through the fixing base 2, and the rotation disc 1 is disposed in the rotation hole 5 and rotatably connected to the fixing base 2.
According to the helicopter, the rotary hole 5 is arranged, and the rotary disc 1 is arranged in the rotary hole 5 and is in rotary connection with the fixed seat 2, so that the height of the rotary platform is conveniently reduced, a main engine wheel of the helicopter can be close to the ground as much as possible, the inclination degree of the helicopter is reduced, and the helicopter can rotate more stably.
But also the rotating disc 1 can rotate along the fixed seat 2 conveniently. Optionally, the fixing base 2 of this embodiment is in a circular ring shape, and the rotating disc 1 and the fixing base 2 are coaxially arranged in the vertical direction.
As shown in fig. 1 to 3, in some embodiments of the present invention, a plurality of balls 6 are disposed between the rotary disk 1 and the fixed seat 2; a first sliding groove is formed in the inner side wall of the fixed seat 2 along the circumferential direction of the rotary hole 5, and a second sliding groove is formed in the outer side wall of the rotary disc 1 along the circumferential direction; one end of any one of the balls 6 is fitted into the first slide groove, and the other end of any one of the balls 6 is fitted into the second slide groove.
The invention is provided with a plurality of balls 6; a first sliding groove is formed in the inner side wall of the fixed seat 2 along the circumferential direction of the rotary hole 5, and a second sliding groove is formed in the outer side wall of the rotary disc 1 along the circumferential direction; one end of any one of the balls 6 is fitted into the first slide groove, and the other end of any one of the balls 6 is fitted into the second slide groove. So form the structure of plane thrust ball bearing between gyration dish 1, fixing base 2 and a plurality of ball 6, the rotation between gyration dish 1 and the fixing base 2 of being convenient for.
As shown in fig. 1-3, in some embodiments of the present invention, the ball 6 is made of a ceramic material.
The ball 6 made of the ceramic material has high hardness and is free of magnetism, and the ball 6 is made of the ceramic material, so that on one hand, the hardness of the ball meets the requirement, the ball can bear the pressure of a helicopter, and the ball is free of magnetism, and the calibration precision is improved.
As shown in fig. 1 to 3, in some embodiments of the present invention, the bottom of the rotary plate 1 is higher than the bottom of the fixed base 2.
In the working process of the rotary platform, the rotary disk 1 directly bears the force, and the rotary disk 1 inevitably generates certain deformation due to the downward pressure, and the bottom of the rotary disk 1 is arranged to be higher than the bottom of the fixed seat 2, so that the rotary disk 1 is prevented from being stressed and deformed to further clamp on the ground.
Optionally, the bottom of the rotating disc 1 of the present embodiment is higher than the bottom of the fixed seat 2 by more than 3 mm.
In some embodiments of the invention, the thickness of the rotatable platform is 2-4cm, as shown in fig. 1-3.
According to the invention, the thickness of the rotary platform is 2-4cm, so that the gravity center deflection amount of the helicopter is reduced, the stable gravity center is ensured when the rotary platform is used, and particularly, the gravity center is kept stable before the airplane wheel passes through the fixed seat 2 and the rotary disc 1 and then reaches the clamping groove 3.
The embodiment also provides a measuring method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter onto the rotary disk 1 to push the helicopter to rotate, driving the rotary disk 1 to rotate by the main machine wheel, and reading the rotation angle of the rotary disk 1 by the counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; the real-time magnetic azimuth angle of the helicopter is compared with the compass of the helicopter to obtain the deviation, and the method is convenient for calibrating the compass of the helicopter.
As shown in fig. 1-3, in some embodiments of the present invention, calibrating the initial azimuth angle of the helicopter compass includes using a laser theodolite to direct a laser in the direction of the runway of the airport, then directing the laser on the ground in a direction perpendicular to the runway, and centering the rotating platform on the laser spot;
after moving one main wheel of the helicopter to the rotary disk 1, the method also comprises the step of pushing the helicopter to enable the central point of the outer side of the hub of the other main wheel of the helicopter to be aligned with the laser spot in the vertical direction, and then the helicopter faces the airport runway direction. This facilitates the determination of the orientation of the helicopter.
In summary, an embodiment of the present invention provides a rotary platform for helicopter compass field calibration, which includes a fixed base 2 and a rotary disk 1 rotatably disposed on the fixed base 2, wherein the rotary platform is provided with a counting assembly for reading a rotation angle of the rotary disk 1.
When the helicopter is actually used, after the initial magnetic azimuth angle of the helicopter is calibrated by using the laser theodolite compass, the rotary platform can be placed on the ground, and the fixed seat 2 is in contact with the ground and supports the rotary disk 1; moving a main engine wheel of the helicopter to the central position of the rotary disc 1, then pushing the helicopter to rotate around the rotary platform, driving the rotary disc 1 to rotate by the main engine wheel, and reading the rotation angle of the rotary disc 1 by the counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain deviation, and calibrating the compass of the helicopter. The rotary platform provided by the invention can be set to be a little larger than a main engine wheel of the helicopter, so that the rotary platform is convenient to move and carry in a motorized mode and convenient for the helicopter to rotate for calibration operation.
The embodiment also provides a measuring method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter onto the rotary disk 1 to push the helicopter to rotate, driving the rotary disk 1 to rotate by the main machine wheel, and reading the rotation angle of the rotary disk 1 by the counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter; the real-time magnetic azimuth angle of the helicopter is compared with the compass of the helicopter to obtain the deviation, and the method is convenient for calibrating the compass of the helicopter.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A rotary platform for helicopter compass field characterized in that: including fixing base and rotation locate the gyration dish of fixing base, rotary platform is equipped with and is used for reading gyration dish turned angle's count subassembly.
2. A rotary platform for a helicopter compass field according to claim 1, wherein: the counting assembly adopts a grating ruler, the grating ruler comprises a scale grating and a grating reading head, the scale grating is arranged along the circumferential direction of the side wall of the rotary disc, and the grating reading head is arranged on the fixed base.
3. A rotary platform for a helicopter compass field according to claim 1, wherein: the counting assembly adopts a photosensitive counter, the photosensitive counter is arranged on the rotary disc, and the fixed seat is uniformly provided with a plurality of scale grooves matched with the photosensitive counter along the circumferential direction of the rotary disc.
4. A rotary platform for a helicopter compass field according to claim 1, wherein: the upper side wall of the rotary disc is provided with a clamping groove, and the section of the clamping groove is in an inverted trapezoid shape.
5. A rotary platform for a helicopter compass field according to claim 4, wherein: and the upper side wall of the rotary disc, which is positioned in the clamping groove, is provided with anti-skid grains.
6. A rotary platform for a helicopter compass field according to claim 4, wherein: the lateral wall of gyration dish is equipped with the through-hole that runs through the gyration dish, the through-hole with joint groove intercommunication is located the below in joint groove.
7. A rotary platform for a helicopter compass field according to claim 1, wherein: the fixing base is provided with a rotary hole penetrating through the fixing base, and the rotary disc is arranged in the rotary hole and is rotatably connected with the fixing base.
8. A rotary platform for a helicopter compass field according to claim 7, wherein: a plurality of balls are arranged between the rotary disc and the fixed seat; a first sliding groove is formed in the inner side wall of the fixed seat along the circumferential direction of the rotary hole, and a second sliding groove is formed in the outer side wall of the rotary disc in the circumferential direction; one end of any ball is embedded into the first sliding groove, and the other end of any ball is embedded into the second sliding groove.
9. A method of measurement, characterized by: comprises that
Calibrating an initial azimuth angle of a helicopter compass;
moving a main machine wheel of the helicopter onto a rotary disc to push the helicopter to rotate, driving the rotary disc to rotate by the main machine wheel, and reading the rotation angle of the rotary disc by a counting assembly to further obtain the real-time magnetic azimuth angle of the helicopter;
and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain the deviation.
10. The measurement method according to claim 9, characterized in that: calibrating the initial azimuth angle of the helicopter compass comprises
Using a laser theodolite to point laser to the direction of an airport runway, then pointing the laser to the ground in the direction vertical to the runway, and placing the center of a rotary platform on the laser spot;
after a main wheel of the helicopter is moved to the rotary disk, the device also comprises
And pushing the helicopter to enable the central point of the outer side of the hub of the other main wheel of the helicopter to be aligned with the laser spot in the vertical direction, so that the helicopter faces the airport runway direction at the moment.
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| CN202110084261.6A CN112857346A (en) | 2021-01-21 | 2021-01-21 | Rotary platform for helicopter compass field calibration and measurement method |
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| CN202110084261.6A CN112857346A (en) | 2021-01-21 | 2021-01-21 | Rotary platform for helicopter compass field calibration and measurement method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114659510A (en) * | 2022-03-21 | 2022-06-24 | 贵州大学 | Portable geological compass suitable for occurrence measurement and use method |
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Application publication date: 20210528 |