Aerial geophysical prospecting self-stabilization data acquisition system

Abstract

The utility model relates to an aviation geophysical prospecting self-stabilization data acquisition system which comprises a carrier aircraft, a data processing and measuring device and a detection device which are arranged in the carrier aircraft and are in signal connection with the data processing and measuring device, and an automatic steady state connecting device which is physically connected with the carrier aircraft and the detection device and comprises an upper hook, a lower hook and a lower hook, the upper end of the main body is hung on an aircraft landing gear; the lower end of the lower hook is used for hanging a detection device; the vertical stabilizing part and the circumferential stabilizing part are positioned between the upper hook and the lower hook; wherein the vertical stabilizing part comprises a telescopic spring, the upper end of the telescopic spring is connected to the upper hook, and the lower end of the telescopic spring is connected to the circumferential stabilizing part; the circumferential stabilizing part comprises a through semispherical shell and a hollow sphere which can be accommodated in the through semispherical shell in a relatively rotating manner, the upper end of the through semispherical shell is connected to the vertical stabilizing part, and the lower end of the hollow sphere is connected to the lower hook. The system improves the collection efficiency and collection quality of airborne geophysical prospecting data.

Description

Technical Field

[0001] The utility model relates to the field of aviation geophysical exploration, in particular to an aviation geophysical exploration self-stabilization data acquisition system. Background Art

[0002] Geophysical exploration refers to the science of using the basic principles and methods of geophysics to detect and study the earth's structure, physical properties, energy minerals, environment, etc. Among them, airborne geophysical exploration technology, as an efficient and advanced means, has a wide range of applications in the fields of geology and mineral resources. Airborne geophysical exploration has the advantages of fast speed, no restrictions on ground conditions (such as sea, river, lake, desert), relatively uniform accuracy over a large area, and the ability to work in areas with difficult terrain conditions. In particular, the development of automatic control and electronic computing technology has made airborne geophysical exploration comprehensive, thereby improving the speed of calculation and compilation of airborne geophysical observation data and the level of interpretation and inference, which has greatly promoted the development of airborne geophysical exploration.

[0003] The airborne geophysical data acquisition system detects changes in various geophysical fields during the flight of the aircraft through the special geophysical instrument probe carried on the aircraft. With the promotion, application and development of airborne geophysical technology, higher requirements have been placed on the quality and accuracy of airborne geophysical results and collected data. However, aircraft are often affected by unstable airflow and lose their attitude when operating in the air. In addition, most existing geophysical acquisition devices are mounted on carrier aircraft by fixed or rope connection, which makes the airborne geophysical data acquisition disturbed violently, making it difficult to collect high-precision and accurate data, and unable to further exert the advantages and characteristics of airborne geophysical exploration to provide scientific and technological means for the country's new round of high-quality mineral exploration operations. Therefore, a new airborne geophysical self-stabilizing data acquisition system is urgently needed to improve the technical level of airborne geophysical data acquisition. Utility Model Content

[0004] It is desired to provide an aerogeophysical self-stabilizing data acquisition system, which can minimize the impact of unstable flight of the carrier aircraft on the accuracy of the aerogeophysical data acquisition system through two-level self-stabilizing adjustment in vertical and circumferential directions.

[0005] According to one embodiment, there is provided an aerial geophysical self-stabilizing data acquisition system, comprising: a carrier aircraft, in which a data processing and measuring device is arranged, a detection device, which is signal-connected to the data processing and measuring device, and also comprising an automatic steady-state connection device that physically connects the carrier aircraft and the detection device, comprising: an upper hook, the upper end of which is mounted on the aircraft landing gear; a lower hook, the lower end of which is used to mount the detection device; a vertical stabilizing part and a circumferential stabilizing part located between the upper hook and the lower hook; wherein the vertical stabilizing part comprises a telescopic spring, the upper end of which is connected to the upper hook, and the lower end of which is connected to the circumferential stabilizing part; the circumferential stabilizing part comprises a hemispherical shell and an inner hollow sphere relatively rotatably accommodated in the hemispherical shell, the upper end of the hemispherical shell is connected to the vertical stabilizing part, and the lower end of the inner hollow sphere is connected to the lower hook.

[0006] As a preferred embodiment, the self-stabilizing data acquisition system is applicable to various types of aerial geophysical exploration methods. Specifically, the detection device can be any one of a magnetic probe for aeromagnetic measurement, a receiving coil for avionic measurement, and a crystal for aerobatic spectrum measurement. For different signal types of various detection devices, the data processing and measuring device can be compatible with receiving digital signals or analog signals transmitted by the detection device.

[0007] Preferably, the hemispherical shell is an aluminum alloy shell, and the inner hollow sphere is an aluminum alloy inner hollow sphere. The hollow structure of the inner control sphere ensures that the aircraft's payload is contributed as much as possible to the detection device as a substantial component of the aerogeophysical exploration. Furthermore, the aluminum alloy material has the advantages of both hardness and low density, which further reduces the occupation of the automatic steady-state connection device for the payload of the carrier aircraft.

[0008] The semi-spherical shell is made by horizontally cutting the half radius position below the center of the complete spherical shell. The semi-spherical shell structure provides a accommodating structure for the inner hollow sphere, and the cut circumferential portion provides a horizontal circumferential adjustment space for the lower hook connected to the lower end of the inner hollow sphere.

[0009] Preferably, the inner side of the hemispherical shell is provided with a plurality of ball grooves, each of which is provided with a ball of matching size, and the inner hollow sphere is accommodated in the hemispherical shell via the ball. The inner side of the hemispherical shell is provided with a ball groove at the center of the top of the hemispherical shell, and a plurality of ball grooves distributed along the horizontal circumference passing through the center of the circle. A lubricating medium is applied between the ball grooves and the ball.

[0010] Preferably, the vertical stabilizing portion further comprises an inner hollow cylindrical box, in which the telescopic spring is accommodated; the bottom of the telescopic spring and the bottom of the inner hollow cylindrical box are both connected to the central position of the upper end of the hemispherical shell.

[0011] The vertical stabilizing portion also includes a telescopic frame, which includes symmetrical left and right halves, wherein the left and right halves each include an upper half and a lower half connected by a rotating shaft; and the left upper half and the right upper half are connected to the upper hook 1 via a rotating shaft; the left lower half and the right lower half are respectively connected to the two sides of the upper part of the inner hollow cylindrical box via a rotating shaft.

[0012] Preferably, the upper hook and the lower hook both include connection reinforcement members for strengthening the connection with the carrier aircraft or the detection device.

[0013] Preferably, the carrier aircraft is a helicopter with a skid-type landing gear, and the detection device is a detection coil.

[0014] Beneficial effects of the utility model:

[0015] The self-stabilizing data acquisition system for aerial geophysical exploration provided by the utility model is applicable to various aerial geophysical exploration methods. For the vertical swing and horizontal swing instability problems of carrier aircraft, based on the vertical and circumferential automatic stabilizing adjustment of the automatic steady-state connection device, the geophysical detection device will automatically maintain the original stable posture to work, reducing the problem of irregular swing of the carrier probe caused by factors such as aircraft engine vibration and unpredictable airflow. The aerial geophysical exploration data acquisition is more stable and reliable, providing a basic guarantee for the quality of high-precision original data of aerial geophysical exploration.

[0016] The self-stabilizing data acquisition system for aerial geophysical exploration has changed the traditional aerial geophysical exploration method of using ropes to connect probes. While improving work efficiency, it has also improved the quality of aerial geophysical exploration data acquisition, giving full play to the technical advantages of aerial geophysical exploration and providing a reliable hardware foundation for the country's new round of mineral exploration. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The schematic diagram of the self-stabilizing data acquisition system for airborne geophysical exploration is shown;

[0018] Figure 2 The structure diagram of the automatic steady-state connection device is shown;

[0019] Figure 3 A top cross-sectional view of a circumferential stabilizer and a vertical stabilizer is shown;

[0020] Figure 4 The state diagram of the automatic steady-state connection device when the carrier aircraft swings horizontally to the maximum angle is shown;

[0021] Figure 5 The state diagram of the automatic steady-state connection device when the carrier aircraft swings vertically to the maximum distance is shown;

[0022] Markings in the figure: 1-hook, 2-screw, 3-telescopic spring, 4-inner hollow box body, 5-hemispherical shell, 6-ball, 7-inner hollow sphere, 8-telescopic frame.

[0023] The various aspects and features of various embodiments of the present invention are described with reference to the above drawings. The above drawings are merely illustrative and non-restrictive. Without departing from the subject matter of the present invention, the distribution, numbering, or appearance of the various units in the above drawings may be changed, and are not limited to those shown in the drawings of the specification. DETAILED DESCRIPTION

[0024] The utility model is described in detail below in conjunction with the accompanying drawings.

[0025] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the utility model and are not used to limit the utility model. The up, down, left and right in the embodiments refer to the positional relationship of the utility model in the use state, and the horizontal and vertical directions refer to the movement directions of the utility model in the use state.

[0026] Provide an airborne geophysical self-stabilizing data acquisition system, such as Figure 1-2 As shown, it includes: a carrier aircraft, in which a data processing and measuring device and a detection device are arranged, which are connected to the data processing and measuring device by signal. The detection device is a receiving coil for avionics measurement, and the data processing and measuring device receives the digital electrical signal transmitted by the detection device. The self-stabilizing data acquisition system also includes an automatic steady-state connection device that physically connects the carrier aircraft and the detection coil, which includes: an upper hook 1, whose upper end is mounted on the aircraft landing gear; a lower hook 1, whose lower end is used to mount the detection device; a vertical stabilizing part and a circumferential stabilizing part located between the upper hook 1 and the lower hook 1; wherein the vertical stabilizing part includes a telescopic spring 3, the upper end of which is connected to the upper hook 1, and the lower end of which is connected to the circumferential stabilizing part; the circumferential stabilizing part includes a hemispherical shell 5 and an inner hollow sphere 7 that can be relatively rotatably accommodated in the hemispherical shell 5, the upper end of the hemispherical shell 5 is connected to the vertical stabilizing part, and the lower end of the inner hollow sphere 7 is connected to the lower hook 1.

[0027] The self-stabilizing data acquisition system for airborne geophysical exploration achieves relative mechanical isolation between the airborne geophysical exploration detection device and the carrier aircraft through the vertical self-stabilizing function and horizontal self-stabilizing function of its automatic steady-state connection device, so as to realize high-precision acquisition of the geophysical response characteristics of the target ore body, and provide favorable support for high-precision original data acquisition and high-quality detection results of airborne geophysical exploration.

[0028] Specifically, the vertical stabilizing part includes a telescopic spring 3, the upper end of which is connected to the upper hook 1, and the lower end of which is connected to the circumferential stabilizing part; the circumferential stabilizing part includes a hemispherical shell 5 and an inner hollow sphere 7 which can be relatively rotatably accommodated in the hemispherical shell 5, the upper end of the hemispherical shell 5 is connected to the vertical stabilizing part, and the lower end of the inner hollow sphere 7 is connected to the lower hook 1.

[0029] Specifically, the difference between the upper hook 1 and the lower hook 1 is that the upper hook 1 is a reverse hook 1, which is used to mount the automatic steady-state connection device together with the detection device carried below it to the carrier aircraft; the lower hook 1 is a forward hook 1, which is used to carry the detection device. The reverse hook 1 and the forward hook 1 both include a connection reinforcement member, which is used to strengthen the connection with the aircraft or the probe. The connection reinforcement member can be specifically connected by bolts, with the forward hook 1 using an upward screw 2 and the reverse hook 1 using a downward screw 2 installed in the recessed parts of the two hooks 1, respectively used to reinforce the connection between the automatic steady-state connection device and the carrier aircraft and the probe device.

[0030] The hemispherical shell 5 and the inner hollow sphere 7 are both made of aluminum alloy. Aluminum alloy materials are both hard and low in density, which is very necessary for reducing the weight of the automatic stable connection device itself, so that the carrier aircraft can contribute as much load as possible to the probe device as a payload.

[0031] The semi-spherical shell 5 is made by horizontally cutting the half-radius position of the sphere center downward from the complete sphere shell. The specific size of the semi-spherical shell 5 is related to the allowable range of horizontal swing required by the design. The semi-spherical shell 5 formed by horizontally cutting the half-radius position, i.e., the 3 / 4 diameter position downward from the sphere center can achieve effective self-stabilizing adjustment within the range of 50° of horizontal unilateral deviation.

[0032] The inner side of the hemispherical shell 5 is provided with a plurality of ball grooves, each of which is provided with a ball 6 of matching size, and the hollow sphere 7 is accommodated in the hemispherical shell 5 via the ball 6. The inner side of the hemispherical shell 5 is provided with a ball groove at the top center of the hemispherical shell 5, and a plurality of ball grooves distributed along the horizontal circumference passing through the center of the circle, such as Figure 3 Specifically, 28 ball grooves are opened along the middle line of the spherical shell, one ball 6 is placed in the ball groove at the top center of the half spherical shell 5, and the other 28 balls 6 are placed in the ball grooves therein, and mechanical lubricating oil is added to enable the balls 6 to rotate freely.

[0033] The horizontal swing and vertical swing of the carrier aircraft may be relatively independent or may be compound movements. In order to more clearly illustrate the self-stabilizing adjustment of the automatic steady-state connection device in two directions, the following is divided into two independent movement modes for explanation.

[0034] refer to Figure 4, which shows the state diagram of the automatic steady-state connection device when the carrier aircraft swings horizontally at a maximum angle of 50°. The inner hollow sphere 7 can rotate relative to the hemispherical shell 5 to achieve the self-stabilizing state of the lower probe always in the horizontal direction. Since the horizontal disturbance introduced by the horizontal swing of the carrier aircraft is transmitted to the hemispherical shell 5 via the telescopic spring 3, the hemispherical shell 5 is the active party of relative rotation. The rotation of the hemispherical shell 5 relative to the inner hollow sphere 7 is achieved through the bearing action of the ball 6, that is, the inner hollow sphere 7 also rotates relative to the hemispherical shell 5, and the rotation state of the inner hollow sphere 7 itself is not limited, and the slight instantaneous self-rotation based on the gravity does not affect the horizontal self-stabilizing state of the probe at its lower end.

[0035] The vertical stabilizing portion further includes an inner hollow box body 4, in which the telescopic spring 3 is accommodated; the bottom of the telescopic spring 3 and the bottom of the inner hollow box body 4 are both connected to the central position of the upper end of the hemispherical shell 5. The inner hollow box body 4 is adapted to the shape of the telescopic spring 3 and can be in the form of an inner hollow cylindrical box.

[0036] The vertical stabilizing part also includes a telescopic frame 8, and the telescopic frame 8 includes symmetrical left and right halves, wherein the left and right halves each include an upper half and a lower half connected by a rotating shaft; and the left upper half and the right upper half are connected to the upper hook 1 via a rotating shaft; the left lower half and the right lower half are respectively connected to the upper sides of the inner hollow box body 4 via a rotating shaft. The left and right rotating shafts of the telescopic frame 8 are equivalent to two joints, which work together with the telescopic spring 3 to provide a vertical adjustment function for the self-stabilizing device. The telescopic frame 8 can prevent the telescopic spring 3 from breaking due to exceeding the load, and at the same time strengthen the connection stability between the vertical stabilizing part and the carrier aircraft. Reference Figure 5 , which shows the state diagram of the automatic steady-state connection device when the carrier aircraft swings vertically to the maximum distance: Figure 5 The middle figure shows the device state when the aircraft is flying steadily, and the telescopic spring 3 maintains the normal state when carrying objects; Figure 5 The left figure is a schematic diagram of the aircraft swinging upward to the position of 10 cm. The telescopic spring 3 is stretched upward, and at the same time, the telescopic frame 8 is transformed from a pentagonal outline to an approximately triangular outline by rotating the upper and lower halves based on the rotation axis therebetween, that is, the vertical distance is extended, and the semi-spherical shell 5 of the circumferential stabilizing part, the inner hollow sphere 7 and the probe carried by the bottom hook 1 are almost kept at the same height in the vertical direction; similarly, Figure 5 The right picture is a schematic diagram of the aircraft swinging downward to the 10 cm position. The telescopic spring 3 is compressed downward, and at the same time, the telescopic frame 8 is transformed from a pentagonal profile to an inverted trapezoidal profile by rotating the upper and lower halves on the axis of rotation therebetween, that is, the vertical distance is shortened, and the semi-spherical shell 5 of the circumferential stabilizing portion, the inner hollow sphere 7 and the probe carried by the bottom hook 1 are almost maintained at the same height in the vertical direction.

[0037] The carrier aircraft is a helicopter with a skid-type landing gear, and the detection device is a detection coil. The skid-type landing gear can provide a more reliable connection; as a common acquisition probe for airborne electromagnetic exploration, the detection coil is a widely used detection device. It is easy to understand that the airborne geophysical self-stabilizing data acquisition system can not only be used for various types of airborne geophysical carrier probes, but also for all aircraft carrying high-precision instruments and equipment in various industries, and has a wide range of promotion and application.

[0038] The method for using the aerial geophysical self-stabilizing data acquisition system provided in this embodiment generally includes: connecting the upper hook 1 of the automatic steady-state connection device to the carrier aircraft; connecting the lower hook 1 to the aerial geophysical probe that needs to work, such as a detection coil; and then rotating the screws 2 on the upper and lower hooks 1 to reinforce them. The existing machinery and materials are designed to meet the requirements of carrying probes with a total weight of up to 50kg.

[0039] After the carrier aircraft takes off, the automatic steady-state connection device continues to operate normally, allowing the aircraft to swing horizontally within a range of 50° and vertically within a range of 20cm. The carried detection coil will automatically maintain its original posture.

[0040] The device of the present invention is described above with reference to various embodiments, wherein the embodiments mentioned may include specific features, structures or characteristics, but not every embodiment necessarily includes the specific features, structures or characteristics. In addition, some embodiments may have some or all of the features described for other embodiments or none of the features described for other embodiments.

[0041] As used in the claims, unless otherwise indicated, the use of ordinal adjectives "first," "second," "third," etc. to describe common elements merely indicates that different instances of similar elements are mentioned, and is not intended to imply that the elements so described must be in a given order, whether in time, space, ranking, or any other manner.

[0042] The various features of different embodiments or examples can be combined in a variety of ways with some of the features included and other features excluded to adapt to a variety of different applications. The accompanying drawings and the foregoing description provide examples of embodiments. It will be appreciated by those skilled in the art that one or more of the elements described can be combined into a single functional element. Alternatively, some elements can be divided into multiple functional elements. Elements from one embodiment can be added to another embodiment. The scope of the embodiments is by no means limited by these specific examples. Whether or not clearly provided in the specification, many variations such as differences in product composition and structure are possible.

Claims

1. An aerogeophysical self-stabilizing data acquisition system, characterized in that: include: A carrier aircraft, in which data processing and measuring equipment is installed, a detection device, which is signal-connected to the data processing and measuring device, Also included is an automatic steady-state connection device for physically connecting the carrier aircraft and the detection device, which includes: An upper hook, the upper end of which is mounted on the aircraft landing gear; A lower hook, the lower end of which is used to mount the detection device; A vertical stabilizing portion and a circumferential stabilizing portion located between the upper hook and the lower hook; wherein, The vertical stabilizing portion includes a telescopic spring, the upper end of which is connected to the upper hook and the lower end of which is connected to the circumferential stabilizing portion; The circumferential stabilizing part comprises a semi-spherical shell and an inner hollow sphere relatively rotatably accommodated in the semi-spherical shell, the upper end of the semi-spherical shell is connected to the vertical stabilizing part, and the lower end of the inner hollow sphere is connected to the lower hook.

2. The system according to claim 1, characterized in that: The detection device is any one of a magnetic probe for aeromagnetic measurement, a receiving coil for avionics measurement, and a crystal for aeronautical energy spectrum measurement.

3. The system according to claim 2, characterized in that: The data processing and measuring device receives the digital signal or analog signal transmitted by the detection device.

4. The system according to any one of claims 1 to 3, characterized in that: The hemispherical shell is an aluminum alloy spherical shell, and the inner hollow sphere is an aluminum alloy inner hollow sphere.

5. The system according to claim 4, characterized in that: The semi-spherical shell is made by horizontally cutting the half-radius position below the center of the complete spherical shell.

6. The system according to claim 5, characterized in that: A plurality of ball grooves are arranged on the inner side of the hemispherical shell, each of which is provided with a ball with matching size, and the inner hollow sphere is accommodated in the hemispherical shell via the ball.

7. The system according to claim 6, characterized in that: The inner side of the hemispherical shell is provided with a ball groove at the center of the top of the hemispherical shell, and a plurality of ball grooves distributed along the horizontal circumference passing through the center of the circle; A lubricating medium is applied between the ball groove and the ball.

8. The system according to claim 4, characterized in that: The vertical stabilizing portion further comprises an inner hollow cylindrical box, in which the telescopic spring is accommodated; the bottom of the telescopic spring and the bottom of the inner hollow cylindrical box are both connected to the central position of the upper end of the hemispherical shell.

9. The system according to claim 8, characterized in that: The vertical stabilizing portion further comprises a telescopic frame, wherein the telescopic frame comprises symmetrical left and right halves, wherein the left and right halves each comprise an upper half and a lower half connected by a rotating shaft; and, The left upper half and the right upper half are connected to the upper hook via a rotating shaft; The left lower half and the right lower half are respectively connected to the two sides of the upper part of the inner hollow cylindrical box via rotating shafts.

10. The system according to claim 9, characterized in that: The upper hook and the lower hook both include connection reinforcement members for strengthening the connection with the carrier aircraft or the detection device.

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