CN112857347A - Pointer type rotary platform for helicopter compass field calibration - Google Patents
Pointer type rotary platform for helicopter compass field calibration Download PDFInfo
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- CN112857347A CN112857347A CN202110084563.3A CN202110084563A CN112857347A CN 112857347 A CN112857347 A CN 112857347A CN 202110084563 A CN202110084563 A CN 202110084563A CN 112857347 A CN112857347 A CN 112857347A
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- rotary platform
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- 229910010293 ceramic material Inorganic materials 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 description 12
- 239000000463 material Substances 0.000 description 5
- 230000005484 gravity Effects 0.000 description 3
- 230000005389 magnetism Effects 0.000 description 3
- 229910000963 austenitic stainless steel Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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Classifications
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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 pointer type rotary platform for a helicopter compass field calibration, and relates to the technical field of compass calibration. The utility model provides a pointer-type rotary platform for helicopter school compass field, includes the fixing base and rotates the gyration dish of locating above-mentioned fixing base, and above-mentioned gyration dish is equipped with the pointer, and above-mentioned fixing base is equipped with the precision scale along above-mentioned gyration dish circumference. Calibrating an initial azimuth angle of a helicopter compass; moving a main machine wheel of the helicopter to a rotary disc, and placing a pointer at a zero scale position of the precise scale; the helicopter is pushed to rotate, the main engine wheel drives the rotary disc to rotate, the pointer is further driven to move, and the real-time magnetic azimuth angle of the helicopter is obtained according to the indication of the pointer on the precise scale; and comparing the real-time magnetic azimuth angle of the helicopter with a compass of the helicopter to obtain the deviation. The rotary platform can be moved and carried, so that the helicopter can rotate to perform calibration operation conveniently.
Description
Technical Field
The invention relates to the technical field of compass calibration, in particular to a pointer type rotary platform for a helicopter compass calibration field.
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 pointer type rotary platform for a helicopter compass field, which can be moved and carried and is convenient for the helicopter to rotate for calibration operation.
The embodiment of the invention is realized by the following steps:
the embodiment of the application provides a pointer type rotary platform for helicopter school compass field, locate the gyration dish of above-mentioned fixing base including fixing base and rotation, above-mentioned gyration dish is equipped with the pointer, and above-mentioned fixing base is equipped with the precision scale along above-mentioned gyration dish circumference.
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, further driving the pointer to move, and acquiring the real-time magnetic azimuth angle of the helicopter according to the indication of the pointer on the precise scale; 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.
Further, in some embodiments of the present invention, the upper sidewall of the rotating disc is provided with a locking groove.
Further, in some embodiments of the present invention, the cross-section of the clamping groove is an 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.
Further, in some embodiments of the present invention, the ball is made of a ceramic material.
Further, in some embodiments of the present invention, the bottom of the rotary plate is higher than the bottom of the fixed base.
Further, in some embodiments of the present invention, the thickness of the rotating platform is 2-4 cm.
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 pointer type rotary platform for a helicopter compass field, which comprises a fixed seat and a rotary disk rotatably arranged on the fixed seat, wherein a pointer is arranged on the rotary disk, and the fixed seat is circumferentially provided with precise scales along 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, further driving the pointer to move, and acquiring the real-time magnetic azimuth angle of the helicopter according to the indication of the pointer on the precise scale; 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 calibration method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter to a rotary disc, and placing a pointer at a zero scale position of the precise scale; the helicopter is pushed to rotate, the main engine wheel drives the rotary disc to rotate, the pointer is further driven to move, and the real-time magnetic azimuth angle of the helicopter is obtained according to the indication of the pointer on the precise scale; 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 rotating platform according to an embodiment of the present invention;
fig. 2 is a sectional view of a rotary platform 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-pointer.
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. 1-2, fig. 1 is a schematic structural diagram of a rotary platform according to an embodiment of the present invention; fig. 2 is a cross-sectional view of a rotating platform according to an embodiment of the present invention.
This embodiment provides a pointer-type rotary platform for helicopter school compass field, locate above-mentioned fixing base 2's gyration dish 1 including fixing base 2 and rotation, above-mentioned gyration dish 1 is equipped with pointer 7, and above-mentioned fixing base 2 is equipped with the precision scale along 1 circumference of above-mentioned gyration dish.
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. Based on this, the inventors have proposed the present invention.
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, further driving the pointer 7 to move, and acquiring the real-time magnetic azimuth angle of the helicopter according to the indication of the pointer 7 on the precise scale; 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.
Alternatively, the pointer 7 of the present embodiment may be movably disposed on the rotary disk 1 or may be fixedly disposed on the rotary disk 1, and when the pointer 7 is fixedly disposed on the rotary disk 1, the precision scale may be set as a floating scale.
Optionally, the pointer 7 of this embodiment may adopt a laser pen, and at this time, a flexible annular scale band with a radius of about 1 meter may be provided, and the precise scale is provided on the scale band, and the scale band material may be selected as a waterproof and wear-resistant fabric material. The scale band is wound around the periphery of the rotary platform, and the ray of the laser pen is aligned with the zero scale position of the precision scale.
As shown in fig. 1-2, 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 2, 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. 1-2, 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 2, 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. 1-2, 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. 1-2, 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. 1-2, 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. 1-2, 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. 1-2.
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 calibration method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter to the rotary disk 1, and placing the pointer 7 at a zero scale position of the precise scale; the helicopter is pushed to rotate, the main engine wheel drives the rotary disc 1 to rotate, the pointer 7 is further driven to move, and the real-time magnetic azimuth angle of the helicopter is obtained according to the indication of the pointer 7 on the precise scale; 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.
As shown in fig. 1-2, 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 pointer type rotary platform for helicopter compass field calibration, which includes a fixed base 2 and a rotary disc 1 rotatably disposed on the fixed base 2, wherein the rotary disc 1 is provided with a pointer 7, and the fixed base 2 is provided with precise scales along the circumferential direction of the rotary disc 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, further driving the pointer 7 to move, and acquiring the real-time magnetic azimuth angle of the helicopter according to the indication of the pointer 7 on the precise scale; 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 calibration method, which comprises the steps of calibrating the initial azimuth angle of the helicopter compass; moving a main machine wheel of the helicopter to the rotary disk 1, and placing the pointer 7 at a zero scale position of the precise scale; the helicopter is pushed to rotate, the main engine wheel drives the rotary disc 1 to rotate, the pointer 7 is further driven to move, and the real-time magnetic azimuth angle of the helicopter is obtained according to the indication of the pointer 7 on the precise scale; 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.
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. The utility model provides a pointer type revolving platform for helicopter school compass field which characterized in that: locate including fixing base and rotation the gyration dish of fixing base, the gyration dish is equipped with the pointer, the fixing base is followed gyration dish circumference is equipped with accurate scale.
2. The pointer-type 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.
3. The pointer-type rotary platform for a helicopter compass field according to claim 2, wherein: the section of the clamping groove is in an inverted trapezoid shape.
4. The pointer-type rotary platform for a helicopter compass field according to claim 2, wherein: and the upper side wall of the rotary disc, which is positioned in the clamping groove, is provided with anti-skid grains.
5. The pointer-type rotary platform for a helicopter compass field according to claim 2, 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.
6. The pointer-type 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.
7. The pointer-type rotary platform for a helicopter compass field according to claim 6, 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.
8. The pointer-type rotary platform for a helicopter compass field according to claim 7, wherein: the ball is made of ceramic materials.
9. The pointer-type rotary platform for a helicopter compass field according to claim 6, wherein: the bottom of the rotary disc is higher than the bottom of the fixed seat.
10. The pointer-type rotary platform for a helicopter compass field according to claim 1, wherein: the thickness of the rotary platform is 2-4 cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110084563.3A CN112857347A (en) | 2021-01-21 | 2021-01-21 | Pointer type rotary platform for helicopter compass field calibration |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110084563.3A CN112857347A (en) | 2021-01-21 | 2021-01-21 | Pointer type rotary platform for helicopter compass field calibration |
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| Publication Number | Publication Date |
|---|---|
| CN112857347A true CN112857347A (en) | 2021-05-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110084563.3A Pending CN112857347A (en) | 2021-01-21 | 2021-01-21 | Pointer type rotary platform for helicopter compass field calibration |
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| CN (1) | CN112857347A (en) |
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| CN201005253Y (en) * | 2007-03-08 | 2008-01-16 | 平杰铭 | Double-ring dining table rotary disk for advertising |
| CN102835822A (en) * | 2011-08-20 | 2012-12-26 | 南通突优科技创业有限公司 | Annular dining-table advertisement turnplate |
| CN203121495U (en) * | 2013-02-25 | 2013-08-14 | 吴壮慧 | Turning plate base of dinning table |
| CN104655114A (en) * | 2014-12-26 | 2015-05-27 | 国家电网公司 | Calibration device for magnetic compass of unmanned aerial vehicle |
| CN105091873A (en) * | 2014-05-16 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Compass field center turnplate |
| CN107228659A (en) * | 2016-03-25 | 2017-10-03 | 哈尔滨飞机工业集团有限责任公司 | A kind of rotating disk for being used to verify aircraft magnetic compasses |
| CN208688514U (en) * | 2018-09-30 | 2019-04-02 | 天津中航锦江航空维修工程有限责任公司 | A kind of slide-type helicopter swing a compass bracket |
| CN210664504U (en) * | 2019-06-19 | 2020-06-02 | 武汉光谷航天三江激光产业技术研究院有限公司 | Magnetic compass calibrating device |
-
2021
- 2021-01-21 CN CN202110084563.3A patent/CN112857347A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201005253Y (en) * | 2007-03-08 | 2008-01-16 | 平杰铭 | Double-ring dining table rotary disk for advertising |
| CN102835822A (en) * | 2011-08-20 | 2012-12-26 | 南通突优科技创业有限公司 | Annular dining-table advertisement turnplate |
| CN203121495U (en) * | 2013-02-25 | 2013-08-14 | 吴壮慧 | Turning plate base of dinning table |
| CN105091873A (en) * | 2014-05-16 | 2015-11-25 | 哈尔滨飞机工业集团有限责任公司 | Compass field center turnplate |
| CN104655114A (en) * | 2014-12-26 | 2015-05-27 | 国家电网公司 | Calibration device for magnetic compass of unmanned aerial vehicle |
| CN107228659A (en) * | 2016-03-25 | 2017-10-03 | 哈尔滨飞机工业集团有限责任公司 | A kind of rotating disk for being used to verify aircraft magnetic compasses |
| CN208688514U (en) * | 2018-09-30 | 2019-04-02 | 天津中航锦江航空维修工程有限责任公司 | A kind of slide-type helicopter swing a compass bracket |
| CN210664504U (en) * | 2019-06-19 | 2020-06-02 | 武汉光谷航天三江激光产业技术研究院有限公司 | Magnetic compass calibrating device |
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Application publication date: 20210528 |