A magnetometer probe mounting device for a helicopter

Abstract

The application discloses a hang-on device for a magnetometer probe of a helicopter, and relates to the technical field of helicopter magnetic surveying, which comprises a support frame I and a support frame II which are detachably connected to a sliding sledge main body, the support frame I is connected to the sliding sledge main body through a sliding assembly and a hydraulic rod control limiting column, one end of a probe is clamped and limited, and the other end is arranged on the support frame II through a fixing rod; the probe can deflect around the fixing rod, and when the helicopter turns, the probe deflects along with the situation instead of rigidly resisting inertial force, so that structural stress concentration and data jump are effectively reduced, low-frequency shaking is inhibited; a cylindrical bag is arranged in the middle of the fixing rod, expansion or contraction of the cylindrical bag is controlled through an air pressure valve, and the probe is locked or smoothly turned; in addition, the device is also provided with an angle sensor, a pressure sensor and an expansion bag and other components, impact is absorbed through pneumatic adjustment, and stability and safety are improved.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of helicopter airborne magnetic survey, and particularly relates to a device for mounting an airborne magnetic probe rod on a helicopter. BACKGROUND

[0002] In the field of helicopter airborne magnetic survey, a probe rod mounting device is used to carry airborne magnetic sensors for geological exploration. In the prior art, the probe rod is usually fixed on a helicopter skid in a rigid connection mode. When the helicopter turns or changes speed, the probe rod rigidly resists the inertial force, which causes stress concentration and excessively large peak stress of the structure, easily causing fatigue damage of components and shortening the service life. Meanwhile, the rigid conflict causes airborne magnetic data to jump, affects the measurement accuracy, and may cause low-frequency jitter due to inertial impact, which interferes with the stability of the sensor. SUMMARY

[0003] The application provides a device for mounting an airborne magnetic probe rod on a helicopter, which solves the technical problems of stress concentration, data jumping and low-frequency jitter of the probe rod in the prior art when the helicopter turns. The mounting structure with slidable deflection is adopted to deflect the probe rod, so that the technical effects of reducing stress peak, inhibiting data jumping, improving flight safety and measurement stability are achieved.

[0004] The application provides a device for mounting an airborne magnetic probe rod on a helicopter, which includes a support frame one and a support frame two which are detachably connected to a skid main body, and the middle parts of the support frame one and the support frame two are hollow structures; sliding assemblies are slidably connected to the upper end and the lower end of the support frame one, and a limiting column is fixed symmetrically between the two sliding assemblies; hydraulic rods are symmetrically installed at the two ends of the support frame one, and the output ends of the hydraulic rods are fixed to the limiting column; one end of the probe rod is clamped and limited by the limiting column and the sliding assemblies, and the other end of the probe rod is arranged on the support frame two through a fixing rod; the sliding assemblies are driven to move on the support frame one by controlling the extension and retraction of the hydraulic rods, so that the probe rod is deflected around the fixing rod.

[0005] The other end of the probe rod is provided with a rod hole, the middle part of the support frame two is provided with a through hole, and an internal thread is arranged in the through hole; external threads are arranged at the upper end and the lower end of the fixing rod, the fixing rod passes through the through hole and the rod hole of the probe rod in sequence, the fixing rod is connected with the internal thread of the through hole of the support frame two through the external threads arranged on the fixing rod, and a cylindrical capsule is arranged in the middle part of the fixing rod; the upper end and the lower end of the fixing rod are secondarily limited through the screw thread cooperation of the nuts; an air pressure valve one is further fixed on the support frame two, the air pressure valve one passes through the fixing rod through a connecting pipe and communicates with the cylindrical capsule; an angle sensor is arranged on the probe rod close to the end of the fixing rod.

[0006] The upper end and the lower end of the support frame one are symmetrically provided with a moving through slot and a pair of inner grooves, and the moving through slot is arranged between the pair of inner grooves.

[0007] The sliding assembly comprises a slide plate frame, side plates and pulleys, the side ends of the slide plate frame are symmetrically fixed with a pair of side plates, each pair of side plates is rotationally connected with a plurality of pulleys, and the plurality of pulleys slide in the inner grooves of the support frame one.

[0008] The opposite faces of the two slide plate frames are also symmetrically fixed with a pair of connecting columns and connecting blocks, the connecting blocks are between the pair of connecting columns, the connecting columns and the connecting blocks all pass through the moving through grooves, one end of the connecting column is fixed to the slide plate frame, and the other end is fixed to the corresponding top or bottom of the limiting column, and the opposite faces of the two limiting columns are shaped to be adapted to the outer section of the probe rod.

[0009] The opposite faces of the two connecting blocks are symmetrically fixed with limiting plates, and the opposite faces of the two limiting plates are shaped to be adapted to the outer section of the probe rod.

[0010] Further, the contact faces of the limiting plates and the connecting blocks are symmetrically fixed with a plurality of pairs of auxiliary capsules, the limiting plates are also symmetrically provided with inflation capsules one, the contact face of the inflation capsule one with the probe rod is also provided with an inflation face one, the connecting blocks are installed with air pressure valves two, the air pressure valves two control the inflation and contraction of the auxiliary capsules and the inflation capsules one through air pipes, and the inflation capsules one are provided with pressure sensors at corresponding positions.

[0011] Further, the opposite faces of the limiting columns are also symmetrically fixed with inflation capsules two, the contact face of the inflation capsule two with the probe rod is an inflation face two, the inflation face two is fixed with corrugated parts, the corrugated depth of the corrugated parts is 10 mm, the period interval is 15 mm, such a shape can be axially compressed or stretched when stressed, the surface area and volume are changed, large deformation energy absorption is realized, the inflation capsule two is divided into two layers of structures, the outer layer is wear-resistant nylon fabric with a Shore hardness of 80A, and the inner layer is a soft cavity of silicone rubber with a Shore hardness of 30A, the inflation capsule two is symmetrically provided with two in the limiting column, each inflation capsule two is provided with a pressure sensor at a corresponding position, and the connecting columns are installed with air pressure valves three, the air pressure valves three close to the upper part of the probe rod control the inflation and contraction of one inflation capsule two in the auxiliary capsule, and the air pressure valves three close to the lower part of the probe rod control the inflation and contraction of the other inflation capsule two.

[0012] One or more technical solutions provided in the application have at least the following technical effects or advantages:

[0013] When the probe rod turns with the helicopter, it deflects with the trend, rather than rigidly resisting the inertial force, reduces the structural stress peak value, and prolongs the service life of the component.

[0014] The probe rod deflects with the trend when turning, reduces the rigid conflict of the probe rod with the inertial force of the helicopter, thereby reducing stress concentration and data jump, and also helps to suppress low-frequency jitter caused by inertial impact.

[0015] When the probe rod turns, it can avoid the debris rolled up by the rotor airflow, reduce the probability of sudden collision, and improve flight safety.

[0016] The cylindrical capsule 122 is controlled to contract or expand by the air pressure valve one 123, to provide smooth movement for steering and to complete locking, reducing mechanical jamming. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a structure perspective view of the application, a kind of airborne magnetic probe rod mounting device suitable for helicopter;

[0018] Figure 2 It is a partial sectional structure view of the application, a kind of airborne magnetic probe rod mounting device suitable for helicopter;

[0019] Figure 3 It is a structure schematic view of the application, a kind of connecting block structure of airborne magnetic probe rod mounting device suitable for helicopter;

[0020] Figure 4 It is a structure schematic view of the application, a kind of limiting plate structure of airborne magnetic probe rod mounting device suitable for helicopter;

[0021] Figure 5 It is a position schematic view of the application, a kind of auxiliary capsule of embodiment two of airborne magnetic probe rod mounting device suitable for helicopter;

[0022] Figure 6 It is a position schematic view of the application, a kind of air pressure valve two of embodiment two of airborne magnetic probe rod mounting device suitable for helicopter;

[0023] Figure 7 It is a position schematic view of the application, a kind of corrugated part of embodiment three of airborne magnetic probe rod mounting device suitable for helicopter;

[0024] Figure 8 It is a structure schematic view of the application, a kind of inflatable capsule two of embodiment three of airborne magnetic probe rod mounting device suitable for helicopter;

[0025] Figure 9 It is a state schematic view of the application, a kind of inflatable capsule two of embodiment three of airborne magnetic probe rod mounting device suitable for helicopter when adjusting;

[0026] Figure 10 It is a state schematic view of the application, a kind of inflatable capsule two of embodiment three of airborne magnetic probe rod mounting device suitable for helicopter after adjusting.

[0027] In the drawings:

[0028] 100. Skid body; 101. Probe rod; 102. Rod hole; 110. Support frame one; 111. Moving through groove; 112. Inner groove; 120. Support frame two; 121. Fixing rod; 122. Cylindrical bladder; 123. Air pressure valve one; 130. Hydraulic rod; 140. Sliding assembly; 141. Slide frame; 142. Side plate; 143. Pulley; 200. Limiting post; 201. Connecting block; 202. Connecting post; 203. Limiting plate; 210. Auxiliary bladder; 211. Air pressure valve two; 212. Expansion bladder one; 213. Expansion surface one; 220. Expansion bladder two; 221. Expansion surface two; 222. Air pressure valve three; 223. Corrugated component. Detailed Implementation

[0029] To facilitate understanding of the present invention, a more complete description of this application will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the invention. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to enable a more thorough and complete understanding of the disclosure of the present invention.

[0030] It should be noted that the terms "vertical," "horizontal," "up," "down," "left," "right," and similar expressions used in this article are for illustrative purposes only and do not represent the only possible implementation.

[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains; the terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to limit the invention; the term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0032] Example 1: As Figures 1 to 4 As shown, this application discloses an aeromagnetic probe mounting device suitable for helicopters, comprising a skid body 100 with a support frame 110 and a support frame 120 detachably connected thereto. The support frame 110 and the support frame 120 have a hollow structure in the middle. The upper and lower ends of the support frame 110 are slidably connected to a sliding assembly 140, and a limit post 200 is symmetrically fixed between the two sliding assemblies 140. Hydraulic rods 130 are symmetrically installed at both ends of the support frame 110, and the output end of the hydraulic rod 130 is fixed to the limit post 200. One end of the probe 101 is clamped and limited by the limit post 200 and the sliding assembly 140, and the other end is set on the support frame 120 through a fixing rod 121. By controlling the extension and retraction of the hydraulic rod 130, the sliding assembly 140 is moved on the support frame 110, thereby causing the probe 101 to deflect around the fixing rod 121.

[0033] The other end of the probe rod 101 is provided with a rod hole 102, the middle part of the support frame two 120 is provided with a through hole, and the through hole is provided with an internal thread. The upper end and the lower end of the fixing rod 121 are provided with external threads. The fixing rod 121 passes through the through hole and the rod hole 102 of the probe rod 101 in sequence. The fixing rod 121 is connected with the internal thread of the through hole of the support frame two 120 through the external threads on the fixing rod 121. The middle part of the fixing rod 121 is provided with a cylindrical capsule 122. The upper end and the lower end of the fixing rod 121 are secondarily limited through the screw nuts matched with the threads. The support frame two 120 is further provided with an air pressure valve one 123. The air pressure valve one 123 passes through the fixing rod 121 through a connecting pipe and communicates with the cylindrical capsule 122. The probe rod 101 is provided with an angle sensor near the end of the fixing rod 121.

[0034] The upper end and the lower end of the support frame one 110 are symmetrically provided with a moving through slot 111 and a pair of inner inner grooves 112. The moving through slot 111 is arranged between the pair of inner inner grooves 112.

[0035] The sliding assembly 140 comprises a sliding plate frame 141, a side plate 142 and a plurality of pulleys 143. The side ends of the sliding plate frame 141 are symmetrically fixed with a pair of side plates 142. Each pair of side plates 142 is rotatably connected with a plurality of pulleys 143. The plurality of pulleys 143 slide in the inner grooves 112 of the support frame one 110.

[0036] The opposite faces of the two sliding plate frames 141 are further symmetrically fixed with a pair of connecting columns 202 and a connecting block 201. The connecting block 201 is between the pair of connecting columns 202. The connecting columns 202 and the connecting block 201 pass through the moving through slot 111. One end of the connecting column 202 is fixed to the sliding plate frame 141, and the other end is fixed to the corresponding top or bottom of the limiting column 200. The opposite faces of the two limiting columns 200 are shaped to match the outer cross section of the probe rod 101.

[0037] The opposite faces of the two connecting blocks 201 are symmetrically fixed with a pair of limiting plates 203. The opposite faces of the two limiting plates 203 are shaped to match the outer cross section of the probe rod 101.

[0038] Specific implementation: first, the support frame one 110 and the support frame two 120 are detachably installed on the sliding sledge main body 100 through bolts, ensuring that the flatness error of the connection surface is less than or equal to 0.1 mm. The probe rod 101 passes through the support frame one 110 and the support frame two 120 in sequence. One end is initially limited by the limiting plate 203 and the expansion capsule two 220, and the other end passes through the rod hole 102 through the fixing rod 121. The fixing rod 121 is connected with the through hole in the middle part of the support frame two 120 through threads, and is secondarily prevented from loosening through double nut back tightening, preventing vibration loosening.

[0039] When the probe rod 101 is working, the helicopter needs to adjust the heading, and the sliding assembly 140 and the limiting column 200 are controlled to move synchronously by the hydraulic rod 130; for example, the output force of the hydraulic rod 130 is set to 500N, and the stroke is ±50mm, which drives the sliding plate frame 141 to slide along the support frame 110, so that the probe rod 101 deflects around the fixed rod 121 (the maximum deflection angle is ±15°); this design makes the probe rod 101 deflect naturally when the helicopter turns, rather than rigidly resisting the inertial force, reducing the risk of stress concentration; during the deflection process, the probe rod 101 feeds back the position in real time through the angle sensor, maintains the stability of the magnetometer sensor pointing, and reduces the data jump rate; the natural deflection during turning reduces the rigid conflict between the probe rod 101 and the inertial force of the helicopter, thereby reducing stress concentration and data jump, which helps to suppress low-frequency jitter caused by inertial impact; at the same time, the probe rod 101 can avoid the debris rolled up by the rotor airflow during turning, reducing the collision risk; after turning, the cylindrical capsule 122 is inflated by controlling the pneumatic valve 123 (for example, the gas source pressure is 0.5MPa), and after expansion, it locks the probe rod 101; during turning, the cylindrical capsule 122 is first deflated to ensure smoothness.

[0040] Beneficial effects: The probe rod 101 deflects naturally when the helicopter turns, rather than rigidly resisting the inertial force, reducing the structural stress peak and prolonging the service life of the assembly.

[0041] The natural deflection of the probe rod 101 during turning reduces the rigid conflict between the probe rod 101 and the inertial force of the helicopter, thereby reducing stress concentration and data jump, and also helps to suppress low-frequency jitter caused by inertial impact.

[0042] The probe rod 101 can avoid the debris rolled up by the rotor airflow during turning, reducing the probability of sudden collision and improving flight safety.

[0043] The cylindrical capsule 122 is controlled to contract / expand by the pneumatic valve 123 to provide smooth movement for turning and complete locking, reducing mechanical jamming.

[0044] Embodiment two: In order to avoid the wind thrust during the natural process of the probe rod 101 moving more than the target movement, which is not conducive to reducing data jump and suppressing low-frequency jitter caused by inertial impact; the present application proposes the following technical solutions to solve the above technical problems, specifically:

[0045] As Figure 5 and Figure 6As shown, the contact surface of the limiting plate 203 and the connecting block 201 is symmetrically fixed with multiple pairs of auxiliary capsules 210; the limiting plate 203 is also symmetrically provided with an expansion capsule I 212, and the contact surface of the expansion capsule I 212 and the probe rod 101 is also provided with an expansion surface I 213; the connecting block 201 is installed with an air pressure valve II 211, which controls the expansion and contraction of the auxiliary capsule 210 and the expansion capsule I 212 through the air pipe; the expansion capsule I 212 is provided with a pressure sensor at the corresponding position, which is a prior art and not shown in the figure.

[0046] Specific implementation: for example, when the hydraulic rod 130 controls the probe rod 101 to turn, if the wind speed exceeds 15 m / s, the wind thrust may cause the probe rod 101 to move beyond the preset value; at this time, the auxiliary capsule 210 and the expansion capsule I 212 are controlled to act in coordination through the air pressure valve II 211, the air pressure valve II 211 receives the signal of the pressure sensor, for example, when it is detected that the lateral force of the probe rod 101 is greater than 100 N, the auxiliary capsule 210 in the turning direction is controlled to expand (for example, the inflation pressure is 0.3 MPa), so that it contacts the support frame I 110 to generate friction (for example, the friction damping coefficient μ is greater than or equal to 0.2), thereby reducing the influence of the wind thrust; at the same time, the air pressure valve II 211 controls the expansion capsule I 212 to expand, so that the expansion surface I 213 adheres to the outer cross section of the probe rod 101 (the adhesion gap is less than 0.5 mm), thereby providing a cushioning effect; when the helicopter turns, the system increases the expansion amount of the expansion capsule I 212 in the deflection direction (for example, the pressure increases to 0.4 MPa) according to the angle sensor data, and reduces the expansion amount in the opposite direction, so as to absorb the pitching oscillation and reduce the oscillation amplitude; the air source comes from the auxiliary system of the helicopter, and the air path tightness needs to be checked regularly.

[0047] The one or more technical solutions provided in the application have at least the following technical effects or advantages:

[0048] The auxiliary capsule 210 and the expansion capsule I 212 are controlled by the air pressure valve II 211 to offset the wind thrust and absorb the pitching oscillation.

[0049] After the auxiliary capsule 210 expands, friction damping is generated between the auxiliary capsule 210 and the support frame I 110, thereby reducing the problem of wind-induced movement exceeding the limit.

[0050] The expansion surface I 213 of the expansion capsule I 212 adheres to the probe rod 101, thereby providing a cushioning effect; the expansion amount is dynamically adjusted during turning, thereby reducing the pitching oscillation.

[0051] The pressure sensor feedback realizes closed-loop control, thereby ensuring accurate adjustment of the aerodynamic assembly during helicopter turning and improving the response speed of the system.

[0052] In the third embodiment, the two limiting columns 200 may have a gap between them when the probe rod 101 is turned, which may cause the probe rod 101 to shake laterally during turning, and a small free travel may be generated due to the gap, causing the components to repeatedly collide or swing within the gap range, thereby causing lateral shaking, which may change from low-frequency shaking to high-frequency shaking under the inertial force of the helicopter sharp turning. Under the action of the inertial force, the probe rod 101 may displace within the limited space provided by the limiting column 200 (i.e., within the gap range), and when it hits one side of the limiting column 200, it may be bounced back and hit the other side, forming continuous back-and-forth lateral swinging, which is not conducive to reducing data jumps and suppressing low-frequency shaking caused by inertial impact. The present application proposes the following technical solutions to solve the above technical problems, specifically:

[0053] As shown in Figures 7 to 10 The limiting column 200 is also symmetrically fixed with an expansion bag two 220 on the opposite surface. The contact surface of the expansion bag two 220 with the probe rod 101 is an expansion surface two 221, and the expansion surface two 221 is fixed with a corrugated part 223 on the surface. The corrugated part 223 has a corrugated depth of 10 mm and a periodic pitch of 15 mm. This shape can be axially compressed or stretched when stressed, changing the surface area and volume, and achieving large deformation energy absorption. The expansion bag two 220 is divided into two layers of structure, with the outer layer being a wear-resistant nylon fabric with a Shore hardness of 80A, and the inner layer being a soft silicone cavity with a Shore hardness of 30A.

[0054] The expansion bag two 220 is symmetrically provided with two in the limiting column 200, and each expansion bag two 220 is provided with a pressure sensor at the corresponding position. The pressure sensor is a prior art and is not shown in the figure.

[0055] The connecting column 202 is provided with an air pressure valve three 222, and the air pressure valve three 222 near the upper part of the probe rod 101 controls the expansion and contraction of one expansion bag two 220 in the auxiliary bag 210. The air pressure valve three 222 near the lower part of the probe rod 101 controls the expansion and contraction of the other expansion bag two 220.

[0056] Specific implementation: when the hydraulic rod 130 controls the probe rod 101 to turn, a gap may occur between the limiting column 200 and the probe rod 101 due to inertia, causing lateral shaking; through the intelligent adjustment of the air pressure valve three 222 controlling the expansion bag two 220, when turning, the system monitors the pressure sensor data, if a gap is detected (such as pressure <0.1 MPa), the air pressure valve three 222 controls the expansion bag two 220 at the corresponding position to expand (for example, the inflation pressure is 0.6 MPa), so that the expansion surface two 221 completely contacts the probe rod 101 through the corrugated part 223, for example, the lower part of the left limiting column 200 expands, and the upper part of the right limiting column 200 expands, to ensure 360° wrapping and reduce lateral shaking; facing a sharp turn or a change in speed, the inertial force compresses the expansion bag two 220, such as the depth of the corrugated part 223 being compressed from 10 mm to 5 mm (compression rate 50%), to absorb the impact through axial deformation; the inner layer of the silicone rubber cavity (Shore hardness 30A) shears to further dissipate energy; at the peak force, the system automatically adjusts the air pressure, such as when the force >500 N, the air pressure valve three 222 is released to 0.3 MPa, the inner layer becomes softer to enhance energy absorption; if the force is stable, the air pressure is maintained to provide a restoring force; after the inertial force weakens, the corrugated part 223 elastically rebounds, and the air pressure valve three 222 automatically inflates to restore the original state.

[0057] One or more technical solutions provided in the present application have at least the following technical effects or advantages:

[0058] The expansion bag two 220 fills the gap between the limiting column 200 and the probe rod 101 to prevent lateral shaking or shaking.

[0059] The corrugated part 223 is compressed and deformed when turning sharply, and the shear deformation of the inner layer of silicone rubber dissipates the peak inertial force to protect the structure of the probe rod 101.

[0060] The system automatically adjusts the air pressure according to the pressure sensor data, releases pressure to soften the working condition to absorb energy when the force is large, maintains the air pressure to provide a restoring force when the force is stable, and improves durability.

[0061] After the inertial force weakens, the corrugated part 223 elastically rebounds, the air pressure valve three 222 automatically inflates to restore the original state, and the maintenance requirement is reduced.

[0062] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Those skilled in the art can make various modifications and changes to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A magnetometer probe mounting device for a helicopter, characterized in that, The supporting frame one (110) and the supporting frame two (120) are hollow structures in the middle, the upper end and the lower end of the supporting frame one (110) are slidably connected with the sliding assembly (140), the two sliding assemblies (140) are symmetrically fixed with the limiting column (200), the two ends of the supporting frame one (110) are symmetrically provided with the hydraulic rod (130), the output end of the hydraulic rod (130) is fixed on the limiting column (200), one end of the probe rod (101) is clamped and limited by the limiting column (200) and the sliding assembly (140), the other end is arranged on the supporting frame two (120) through the fixing rod (121), the sliding assembly (140) is driven to move on the supporting frame one (110) by controlling the extension and contraction of the hydraulic rod (130), so that the probe rod (101) is deflected around the fixing rod (121).

2. A magnetometer probe mounting device for a helicopter as claimed in claim 1, wherein, The other end of the probe rod (101) is provided with a rod hole (102), the middle of the supporting frame two (120) is provided with a through hole, and the through hole is provided with an internal thread; the upper end and the lower end of the fixing rod (121) are provided with external threads; the fixing rod (121) passes through the through hole and the rod hole (102) of the probe rod (101) in sequence, and is connected with the internal thread of the through hole through the cooperation of the external threads; the middle of the fixing rod (121) is provided with a cylindrical capsule (122); the upper end and the lower end of the fixing rod (121) are secondarily limited through the screw thread cooperation of the nuts; the supporting frame two (120) is further provided with the air pressure valve one (123), the air pressure valve one (123) passes through the connecting pipe and communicates with the cylindrical capsule (122); the probe rod (101) is provided with an angle sensor near the end of the fixing rod (121).

3. The apparatus of claim 1 wherein, The upper end and the lower end of the supporting frame one (110) are symmetrically provided with a moving through slot (111) and a pair of inner grooves (112), and the moving through slot (111) is arranged between the pair of inner grooves (112).

4. A magnetometer probe mounting device for a helicopter as claimed in claim 3, wherein, The sliding assembly (140) comprises a slide plate frame (141), a side plate (142) and a pulley (143), and a pair of side plates (142) are symmetrically fixed on the side end of the slide plate frame (141), and a plurality of pulleys (143) are rotatably connected to each pair of side plates (142); a plurality of pulleys (143) slide in the inner grooves (112) of the supporting frame one (110).

5. A magnetometer probe mounting device for a helicopter as claimed in claim 4, wherein, A pair of connecting columns (202) and a connecting block (201) are symmetrically fixed on the opposite surfaces of the two slide plate frames (141), and the connecting block (201) is between the pair of connecting columns (202); the connecting column (202) and the connecting block (201) pass through the moving through slot (111); one end of the connecting column (202) is fixed on the slide plate frame (141), and the other end is fixed on the corresponding top or bottom of the limiting column (200); the shapes of the opposite surfaces of the two limiting columns (200) are matched with the outer cross section of the probe rod (101).

6. A magnetometer probe mounting device for a helicopter as claimed in claim 5, wherein, Two said connecting blocks (201) are symmetrically fixed with limit plates (203) on opposite faces, and the shapes of the opposite faces of the two limit plates (203) are adapted to the outer section of the probe rod (101).

7. A magnetometer probe mounting device for a helicopter as claimed in claim 6, wherein, The contact faces of the limit plate (203) and the connecting block (201) are symmetrically fixed with multiple pairs of auxiliary capsules (210); the limit plate (203) is also symmetrically provided with an inflation capsule (212) inside; the contact face of the inflation capsule (212) and the probe rod (101) is also provided with an inflation face (213); the connecting block (201) is installed with a gas pressure valve (211), which controls the inflation and contraction of the auxiliary capsule (210) and the inflation capsule (212) through a gas pipe; the inflation capsule (212) is provided with a pressure sensor at a corresponding position.

8. A magnetometer probe mounting device for a helicopter as claimed in claim 7, wherein, The opposite faces of the limit column (200) are also symmetrically fixed with inflation capsules (220); the contact face of the inflation capsule (220) and the probe rod (101) is an inflation face (221), and the surface of the inflation face (221) is fixed with a corrugated part (223); the inflation capsule (220) is divided into two layers, the outer layer is a wear-resistant nylon fabric with a Shore hardness of 80A, and the inner layer is a soft cavity of silicone rubber with a Shore hardness of 30A.

9. A magnetometer probe mounting device for a helicopter as claimed in claim 8, wherein, The inflation capsule (220) is symmetrically provided with two in the limit column (200), and each inflation capsule (220) is provided with a pressure sensor at a corresponding position.

10. A magnetometric probe mounting device for a helicopter as claimed in claim 9, characterized in that, The connecting column (202) is installed with a gas pressure valve (222), and the gas pressure valve (222) near the upper part of the probe rod (101) controls the inflation and contraction of one of the inflation capsules (220) in the auxiliary capsule (210), and the gas pressure valve (222) near the lower part of the probe rod (101) controls the inflation and contraction of the other inflation capsule (220).

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