阅读说明：本技术 提升、吊挂和移动载荷的防回转装置和方法 (Anti-slewing device and method for lifting, suspending and moving loads ) 是由 D·瓦永 S·莫罗 于 2018-06-18 设计创作，主要内容包括：在提升和移动载荷(12)的提升和移动机械(10)之下吊挂该载荷(12)的这个吊挂防转动装置(14),具有吊索系统(16A,16B,16C),吊索系统配有固定于提升和移动机械(10)的固定件(18)。吊挂防转动装置还具有分距梁(20),分距梁具有主纵向轴线(A<Sub>1</Sub>)和偏转转动横向轴线(A<Sub>2</Sub>),分距梁具有；固定于吊索系统(16A,16B,16C)的上部固定系统(22A,22B),设计为允许上部固定系统借助吊索系统(16A,16B,16C)在提升和移动机械(10)之下悬吊布置成其主纵向轴线(A<Sub>1</Sub>)基本水平和围绕其偏转转动横向轴线(A<Sub>2</Sub>)是自由的；固定于载荷(12)的下部固定系统(24A,24B,26A,26B),设计成允许通过分距梁(20)围绕其偏转转动横向轴线(A<Sub>2</Sub>)驱动载荷(12)。分距梁(20)具有推进装置(28),推进装置布置成当分距梁通过吊索系统(16A,16B,16C)悬挂于提升和移动机械(10)时,有选择地沿一个方向或者另一个方向,围绕分距梁的偏转转动横向轴线(A<Sub>2</Sub>)转动分距梁。(The suspension anti-rotation device (14) for suspending a load (12) under a lifting and moving machine (10) for lifting and moving the load (12) has a suspension cable system (16A, 16B, 16C) provided with a fixing element (18) for fixing to the lifting and moving machine (10). The suspension anti-rotation device also has a pitch beam (20) having a main longitudinal axis (A) 1 ) And deflecting the transverse axis of rotation (A) 2 ) The pitch beam is provided with; an upper fixing system (22A, 22B) fixed to the sling system (16A, 16B, 16C), designed to allow the upper fixing system to be suspended by means of the sling system (16A, 16B, 16C) below the lifting and moving machine (10) in an arrangement with its main longitudinal axis (A) 1 ) Substantially horizontal and surrounding itDeflecting the transverse axis of rotation (A) 2 ) Is free; a lower fixing system (24A, 24B, 26A, 26B) fixed to the load (12) and designed to allow the rotation of the transverse axis (A) about its deflection by the distancing beam (20) 2 ) A driving load (12). The pitch beam (20) has a propulsion device (28) arranged to rotate a transverse axis (A) about the pitch beam's deflection, selectively in one direction or the other, when the pitch beam is suspended from the lifting and moving machine (10) by a sling system (16A, 16B, 16C) 2 ) The pitch beam is rotated.)

1. Suspension anti-rotation device (14) for suspending a load (12) under a lifting and moving machine (10) for lifting and moving the load (12), the suspension anti-rotation device having a system of slings (16A, 16B, 16C) provided with a fixing (18) for fixing to the lifting and moving machine (10), characterized in that the suspension anti-rotation device also has a graduated beam (20) having a main longitudinal axis (A) ₁) And deflecting the transverse axis of rotation (A) ₂) The pitch beam has:

-an upper fixing system (22A, 22B) fixed to the sling system (16A, 16B, 16C), designed to allow the distancing beam to be suspended by means of the sling system (16A, 16B, 16C) below the lifting and moving machine (10) in arrangement with its main longitudinal axis (a) ₁) Substantially horizontal and about which the transverse axis of rotation (A) is deflected ₂) Is free to be used in the process of making,

-a lower fixing system (24A, 24B, 26A, 26B) fixed to the load (12) designed to allow rotation of the transverse axis (a) about its deflection by the distancing beam (20) ₂) A driving load (12);

and the pitch beam (20) having a propulsion device (28) arranged to rotate on command, selectively in one direction or the other, about a yaw rotation transversal axis (A) of the pitch beam, when the pitch beam is suspended from the lifting and moving machine (10) by means of a sling system (16A, 16B, 16C) ₂) The pitch beam is rotated.

2. Hanging anti-rotation device (14) according to claim 1, characterized in that the pitch beam (20) is designed in three parts (70, 72, 74) extending longitudinally:

-a central portion (70) having supply means (58) for supplying power to the propulsion means (28), and

-two side portions (72, 74) which can be retracted against the central portion (70), having an impelling member (32A, 52A, 54A, 32B, 52B, 54B) which impels by deflecting rotation, the impelling member being electrically connected to the supply means (58) of the central portion (70).

3. Hanging anti-rotation device (14) according to claim 1 or 2, characterized in that the propulsion device (28) has an electric screw system (32A, 52A, 32B, 52B) arranged at the longitudinal ends of the pitch beam (20).

4. The hanging anti-rotation device (14) of claim 3, wherein:

-a first auger (32A) of the propulsion device (28) is arranged at a first end of the pitch beam (20) and can be activated according to a first rotation comprised between 4000 and 6000 revolutions per minute, so as to enable a rotation of the pitch beam (20) in a first deflection rotation direction, and

-a second auger (32B) of the propulsion device (28), arranged at a second end of the pitch beam (20), able to be activated according to a second rotation comprised between 4000 and 6000 revolutions per minute, so as to enable the pitch beam (20) to be activated along a second deflection rotation direction opposite to the first deflection rotation direction.

5. Hanging anti-rotation device (14) according to claim 3 or 4, characterized in that each screw (32A, 32B) of the propulsion device (28) surrounds a main longitudinal axis (A) ₁) And a yaw rotation transverse axis (A) with the pitch beam (20) ₂) Are arranged in a substantially cylindrical streamlined conduit (34A, 34B).

6. The hanging anti-rotation device (14) of claim 5, wherein a protective grid is disposed at the inlet and outlet of each streamlined conduit (34A, 34B).

7. Hanging anti-rotation device (14) according to any of the claims 1 to 6, characterized in that the pitch beam (20) has a visual indicator (36) with at least three different visual states, indicating one operating state of the yaw angle control of the pitch beam (20) from at least three possible different operating states:

-a state in which the deflection angle control of the pitch beam (20) is not activated,

-a state in which the deflection angle control of the pitch beam (20) is activated, but awaiting the setting of the angle control, and

-state of set angle activated and received by the deflection angle control of the pitch beam (20).

8. Hanging anti-rotation device (14) according to any of claims 1 to 7, characterized in that the main sling (16C) of the sling system (16A, 16B, 16C) is intended to carry the yaw rotation transverse axis (A) of the spreader beam (20) ₂) The main sling has a swivel (18) at one of its ends, which is connected to the lifting and moving machine (10) or to the spreader beam (20).

9. Method for lifting and moving a load (12) by means of a hanging anti-rotation device (14) according to any of claims 1 to 8, characterized in that it comprises the following steps:

-a fixing step (102) of the sling system (16A, 16B, 16C) of the suspension anti-rotation device (14) to the lifting and moving machine (10),

-a fixing step (104) of the suspension anti-rotation device (14) to the load (12),

-a lifting and moving step (106) of lifting and moving the load (12) towards the placement area by means of the lifting and moving machine (10), and

-a control step (108) of controlling the thrust means (28) of the spreader beam (20) to maintain it in a set direction of rotation about the yaw transversal axis (a) with respect to a reference frame associated with the lifting and moving machine (10) or with the ground, during the lifting and moving step (106) of the load (12) ₂) And (4) limiting.

10. A method of lifting and moving a load (12) according to claim 9, characterised in that the load (12) is a pylon part of a cable transmission line and the lifting and moving machine (10) is a helicopter carrying a sling system (16A, 16B, 16C).

Technical Field

The present invention relates to a lifting and moving machine for lifting and moving a load, and to a swing preventing device for suspending the load. The invention also relates to a method for lifting and moving a load using such an anti-slewing device.

Background

The invention is particularly, but not exclusively, applicable to the field of high voltage line maintenance where buildings and cables are installed on continuous towers. Some jobs, for example, require the setting and installation of these towers. In view of the total weight of the pylon and the limited lifting capacity of the machines generally used for such operations, the pylon to be installed is designed as a plurality of individual parts to be installed, even to be fitted together, which are installed in succession in abutment with one another at the installation site. To this end, once the various components have been brought by road to the vicinity of the site, each section is assembled and then, typically using a crane such as a crane helicopter, a sling is suspended with its free end holding the section and lifting and moving each section. The first part of the pylon is positioned on the ground and each of the other parts is fitted to the previous one. One of the difficulties with this type of operation is controlling the orientation of each pylon portion when the first pylon portion is positioned above ground or one pylon portion is fitted to a previous pylon portion, which requires the provision of an anti-slewing device.

In general, the invention is applicable to any field where heavy loads must be lifted, moved and then placed with good directional control, whatever hoisting machine (helicopter, crane or other) is used.

A first solution, generally recommended, is the arrangement of the various parts of the tower, which involves lifting the load with a single electric sling, releasing it, providing a plurality of guide ropes fixed to the lower part of the load, for example four ropes fixed to the four corners of a rectangular part of the lower part, and the operator on the ground tightens the free ends of the ropes when the load is about to be placed. However, this solution requires the load and the presence of people in the vicinity of the lifting and moving machine, and is therefore difficult and time consuming to do. Furthermore, this is potentially dangerous, especially because, for safety reasons, in the case of a pylon section, if problems are encountered at a generally very restrictive stage of placement on the ground or on a previously arranged section, the load must be released by the helicopter at any time.

A second solution, particularly recommended in the arrangement of the pylon sections, involves providing a helicopter to accomplish this task, optionally with its own immovable device to rotate the hoisting load. In view of the safety constraints peculiar to helicopters, such helicopters, generally known as flying cranes, must be very specific and therefore very expensive. In addition, it is dedicated for lifting.

Another solution may involve the use of a sling system having a plurality of fixed points on the machine itself to limit the orientation of the load relative to the lifting and moving machine. For example, US6533220B2 recommends helicopters using such a sling system to lift and move loads. However, when it is possible to adapt to some not very heavy loads, such as a working basket, the operator takes with him the handling of the high voltage line section over a certain weight, such as the weight of a pylon section, which can be dangerous in view of the inertial stress of the load applied to the helicopter.

It would therefore be desirable to provide a load-suspending anti-slewing device that eliminates at least some of the problems and limitations described above.

Disclosure of Invention

Therefore, a hanging anti-rotation device is proposed for hanging a load under a lifting and moving machine for lifting and moving the load, having a sling system equipped with a fixing fixed to the lifting and moving machine, and also having a distancing beam having a main longitudinal axis and a yaw rotation transverse axis, the distancing beam having:

an upper fixing system fixed to the suspension cable system, designed to allow the distancing beam to be suspended by means of the suspension cable system under the lifting and moving machine with its main longitudinal axis substantially horizontal and with its transverse axis of rotation free about its deflection,

a lower fixing system fixed to the load, designed to allow driving the load by pivoting the transverse axis about its deflection by the distancing beam,

the spreader beam also has a propulsion device arranged to rotate the spreader beam on command, selectively in one direction or the other, about a yaw rotation transverse axis of the spreader beam when suspended from the lifting and moving machine by the hoist system.

The advantage of such an autonomously actuated anti-slewing device is that the operation, in particular the deployment of heavy loads using a helicopter, is safe and reliable without the need for an operator on the ground to come too close to the deployment site. In particular, the control of the yaw swivel of the load through the pitch beam, which itself is controllable in orientation, for example in accordance with remote control commands or in accordance with program control, ensures good control of the arrangement. Furthermore, the rotational freedom of the pitch beam about its yaw swivel transverse axis reduces the transmission of moments generated by the lifted and displaced loads to the lifting and displacing machine. Finally, it is simple to configure such anti-rotation devices, as long as the safety regulations of the helicopter are complied with, which are not specific to the mobile pylon segment.

Optionally, the pitch beam is designed as three sections extending longitudinally:

-a central portion having supply means for supplying power to the propulsion means, and

two side portions, which can be retracted against the central portion, have a propulsion member which propels by deflecting rotation, the propulsion member being electrically connected to the supply means of the central portion.

Also optionally, the propulsion device has an electric screw propulsion system arranged at a longitudinal end of the pitch beam.

It is also optional:

-a first auger of the propulsion device is arranged at a first end of the pitch beam, able to be activated according to a first rotation comprised between 4000 and 6000 revolutions per minute, rotating the pitch beam in a first deflection rotation direction, and

-a second auger of the propulsion device, arranged at a second end of the pitch beam, capable of being activated according to a second rotation comprised between 4000 and 6000 revolutions per minute, so that the pitch beam is activated in a second yaw rotation direction opposite to the first yaw rotation direction.

It is also optional that each auger of the propulsion device is arranged in a substantially cylindrical streamlined conduit about an axis orthogonal to both the main longitudinal axis and to the yaw rotation transverse axis of the distancing beam.

Optionally also, a guard grating is arranged at the inlet and outlet of each streamlined conduit.

Also optionally, the pitch beam has a visual indicator having at least three different visual states, indicating one operating state of the yaw angle control of the pitch beam from among at least three possible different operating states:

-a state in which the yaw angle control of the pitch beam is not activated,

-state of the yaw angle control of the spreader beam starting, but waiting for the angle control setting, and

-a state in which the deflection angle control of the pitch beam is activated according to the received set angle.

It is also optional that the main sling of the sling system is used to carry a deflecting swivel transverse axis of the pitch beam, the main sling having a swivel at one of its ends, the swivel being connected to the lifting and moving machine or to the pitch beam.

The invention also provides a method of lifting and moving a load using a hanging anti-rotation device, comprising the steps of:

-a fixing step of fixing the sling system of the suspension anti-rotation device to the lifting and moving machine,

-a fixing step of fixing the suspension anti-rotation device to the load,

-a lifting and moving step of lifting and moving the load towards the placement area by means of a lifting and moving machine, and

-a control step of controlling the thrust means of the spreader beam to maintain it in a set direction defined about the yaw rotation transverse axis with respect to a reference frame associated with the lifting and moving machine or with the ground during the lifting and moving steps of the load.

Alternatively, the load is a pylon portion of a cable transmission line and the lifting and moving machine is a helicopter carrying a sling system.

Drawings

The invention will be better understood from the following description, given purely by way of non-limiting example, with reference to the accompanying drawings, in which:

figure 1 schematically shows the general structure of an anti-rotation device for hanging loads according to one embodiment of the invention;

figure 2 schematically shows in detail the functional electromechanical components of the anti-rotation device shown in figure 1;

fig. 3 shows an exploded arrangement of the pitch beams of the anti-rotation device shown in fig. 1;

FIG. 4 shows successive steps of a method for lifting and moving a load using the anti-rotation device shown in FIG. 1;

figure 5 shows the successive steps of the operating method of the teleisolator of the anti-rotation device shown in figure 1; and

FIG. 6 shows the successive steps of the method of operation of the microcontroller of the anti-rotation device shown in FIG. 1.

Detailed Description

The apparatus shown schematically in figure 1 has a lifting and moving machine 10 such as a helicopter, a load 12 such as a pylon section of a high voltage cable transmission line, and an anti-rotation device 14 for suspending the load 12 beneath the lifting and moving machine 10.

The anti-rotation device 14 has a sling system 16A, 16B, 16C provided with a fixing element 18, for example a rotator 18, fixed to the helicopter 10. The sling system also has a spreader beam 20 having a main longitudinal axis A ₁And deflecting the transverse axis of rotation A ₂. Is divided intoThe distance beam 20 itself has a first upper fixing system 22A, 22B secured at the upper part to the sling system 16A, 16B, 16C and a first lower fixing system 24A, 24B secured at the lower part to the pylon portion 12.

More specifically, using the sling system 16A, 16B, 16C, a first upper fixing system 22A, 22B is used to suspend the spreader beam 20 at its main longitudinal axis A ₁And a vertical transverse axis a about which it is pivoted under the helicopter 10 ₂In the free state: thus, for example, this is a system with two fixed hooks 22A and 22B, the fixed hooks 22A and 22B being arranged in the upper part of the pitch beam 20, at the yaw rotation transverse axis a ₂Are equidistant from the yaw rotation transverse axis. The fixed hooks are fixed to the two ends of two slings 16A and 16B of the sling system, respectively, the two slings 16A and 16B being of the same length and being connected to one end of a third main sling 16C, the other end of which is fixed to a swivel 18 beneath the helicopter 10. Thus, the horizontal position of the spreader beam 20 is defined by the common length of the two slings 16A and 16B and the two hooks 22A and 22B to the axis A ₂Are ensured at equal distances. About an axis A ₂Is secured by the rotary body 18. For safety reasons, the slings 16A, 16B and 16C are preferably dimensioned to ensure a height of at least 20 metres, for example 30 metres +/-10%, between a fixed point fixed to the helicopter 10 and the spreader beam 20. However, in general, the size of the slings 16A, 16B and 16C will depend on the terrain and therefore on each individual case. It should be noted that the arrangement of the sling system and rotator 18 is suitable for many terrains. Thus, in other embodiments, the swivel 18 may be disposed at the junction of three slings 16A, 16B, 16C. Also, in other embodiments, only two slings 16A and 16B may be used, which are connected to the spinner 18 directly beneath the helicopter 10.

More precisely, the second lower fixing system 24A, 24B is designed for allowing the rotation of the transverse axis a by the deflection of the pitch beam 20 about it ₂The iron tower part 12 is manipulated to be fixed: thus, for example, this is a system with two remote control fixed hooks 24A and 24B, which open and close electrically operated,the load is released on command. For example, arranged in the lower part of the pitch beam 20, at the yaw rotation transverse axis a ₂The two sides are equidistant to ensure certain balance of the anti-rotation device. As shown in fig. 1, two parallel axes a are used ₂The vertically extending slings 26A and 26B may also be suspended at a height of, for example, more than 10 metres +/-10% to secure the pylon portion 12 when the environment does not allow the spreader beam 20 to be lowered fully to the ground. Here, however, the dimensions of the slings 26A and 26B depend on the terrain and therefore on each individual case. The cables may run along the slings 16C, 16A, 16B, 26A, 26B from the helicopter 10 to the two electric hooks 24A and 24B, ensuring that the pilot can manipulate the electric hooks 24A and 24B open and closed. It is often essential for safety. Also, for safety, these cables are installed into a sheath within the sling, as it is important to prevent damage thereto.

In accordance with the general principles of the present invention, the spreader beam 20 also has a propulsion device 28 arranged to deflect the transverse axis of rotation A about it, selectively in one direction or the other, using a remote-control device 30 or by program control, selectively in one direction or the other, as it is suspended from the helicopter 10 by the sling system 16A, 16B, 16C ₂And rotating according to the instruction. More precisely, the propulsion device has electric screw propellers arranged at both longitudinal ends of the pitch beam 20. Thus, at least one first auger 32A is arranged at a first end of pitch beam 20, relative to axis a ₂On the same side as the hooks 22A and 24A. More precisely, it is arranged in a first streamlined conduit 34A, which surrounds an axis a ₁And A ₂The orthogonal axis is substantially cylindrical. Which can be activated in response to a first rotation to rotate the pitch beam 20 counterclockwise in the first yaw rotation. At least one second auger 32B is also arranged at a second end of pitch beam 20, with respect to axis a ₂On the same side as the hooks 22B and 24B. More precisely, it is arranged in a second streamlined conduit 34B, which surrounds an axis A ₁And A ₂The orthogonal axis is substantially cylindrical. Which can be carried out according to a second rotationStarting to rotate the pitch beam 20 in the clockwise direction in the second yaw rotation. The streamlined conduits 34A, 34B perform a first guiding function, optimizing propulsion by increasing their energy efficiency. It also performs a protective function for the propellers 32A, 32B or the ground operator, wherein this second function is preferably enhanced by the arrangement of grilles at the inlet and outlet of these ducts.

Finally, the pitch beam 20 has a visual indicator having a plurality of different visual states, such as a plurality of different colors, indicating the operational state of one of the yaw angle controls of the pitch beam 20 from a plurality of possible different operational states. Optionally, but advantageously, at least three operating states are provided:

state in which the deflection angle controller of the pitch beam 20 is not activated: the visual indicator 36 may indicate this status in red,

state in which the yaw angle control of the spreader beam 20 is activated, but waits for the angle control setting: the visual indicator 36 may indicate this status with an orange color, an

The state in which the deflection angle controller of the pitch beam 20 starts up according to the received set angle: the visual indicator 36 may indicate this status in green.

Now, the propulsion device 28 and the remote control 30 of the pitch beam 20 will be described in detail with reference to fig. 2.

According to a first possible embodiment, the remote control 30 has:

-a switch 40 for switching the switching of the,

a power supply battery charge level indicator 42 (for example in the form of a bar graph),

a mode selector 44 selecting between a first mode of controlling the yaw orientation of the spar 20 relative to an angular reference frame associated with the helicopter 10 and a second mode of controlling the yaw orientation of the spar 20 relative to an angular reference frame associated with the ground,

display setting angle α _CThe screen (46) of the mobile terminal,

adjusting the set angle α displayed on the screen 46 _CAn adjustment wheel 48, and

-follow-up controlSwitch 50 which causes the deflection angle control of pitch beam 20 to be in accordance with the displayed set angle α _CStarting or stopping is performed.

Such a controller 30 is available to the pilot or copilot of the helicopter 10 and selects between the first and second control modes depending on whether the pylon segment 12, or even the null moment beam 20, is loaded, transported or positioned.

According to a simplified embodiment, the controller 30 may be operated according to the second control mode only without the mode selector 44. This simplified control may be performed by a surface operator.

The propulsion device 28 shown in operation in fig. 2 is mounted in the pitch beam 20. It has a first auger 32A mounted in its streamlined conduit 34A, a first motor 52A driving the first auger 32A, and a first inverter 54A controlling the power of the first motor 52A. It also has a second auger 32B mounted in its streamlined conduit 34B, a second motor 52B driving the second auger 32B, and a second inverter 54B controlling the power of the second motor 52B. Finally, it has an electronic control box 56 which is used to control the first and second inverters 54A, 54B. The electronic control box 56, the inverters 54A, 54B and the motors 52A, 52B are powered by one or more accumulators 58 also mounted in the spreader beam 20.

More specifically, the electronic control box 56 has a programmable microcontroller 60 that controls the first and second transducers 54A, 54B, and a receiver 62 that receives radio signals from the remote control 30, the receiver 62 being connected to the microcontroller 60 to provide a set angle α _CThe control signals, if necessary, provide control signals for yaw orientation of the longitudinal axis of the helicopter 10 relative to a reference frame of the ground the direction indicator is α _H. It also has an electronic compass 64, the longitudinal axis a of the spreader beam 20 being known at each instant ₁Yaw orientation relative to a reference frame of the ground, which is labeled α _P. It also has a charge level indicator 66 for the battery or batteries 58. Finally, it has a switch 68.

As shown in FIG. 3It is shown that the pitch beam 20 is preferably designed in three parts, which, when it is installed and operated, lie along the main axis a ₁Extending longitudinally. The central portion 70 has means for supplying power to the propulsion device 28, i.e. the accumulator or battery pack 58. Two accumulators 58 are shown in fig. 3, for example mounted on the rails, with a viewing hole and locking in place means in the central portion 70, simplifying the mounting or replacement operations. It is therefore also protected against impacts and environmental influences. The central portion 70 may also have an electronic control box 56 with the charge level indicator 66 visible on the surface. The first side portion 72 is secured to the central portion 70, such as by a pivotal connection using a hinge, and can be stowed on the central portion 70 in the storage configuration. For example, it has in its streamlined conduit 34A first inverter 54A, a first motor 52A and a first auger 32A. In other embodiments, the first side portion may be designed to be completely detachable from the central portion 70. A second side portion 74 is secured to the central portion 70, for example, also by a pivotal connection using a hinge, and can be stowed against the central portion 70 in the storage configuration. It has, for example, in its streamlined conduit 34B, a second inverter 54B, a second motor 52B and a second auger 32B. In other embodiments, the second side portion may be designed to be completely detachable from the central portion 70.

As is evident from fig. 3, this configuration of the spreader beam 20 enables it to be stored in a very compact volume V, such as the helicopter 10, before being installed on the ground and then used. This three-stowable-section configuration is indeed advantageous in view of the optimum length of such a distance beam 20 during use for installing a pylon carrying wires of the order of a few metres, for example of the order of 5 metres.

Fig. 4 shows the successive steps of a method of lifting and moving a load, such as a pylon portion 12, using the anti-rotation device 14 described above.

During a previous step 100, the spreader beam 20 is transported and mounted, for example, by the helicopter 10, at a lifting site of the pylon portion 12. Which is actuated by operation of switch 68 so that the battery charge level visible on indicator 66 can be checked. The sling systems 16A, 16B, 16C are secured to the spreader beam 20 by hooks 22A and 22B, forming the anti-rotation device 14.

During step 102, the sling systems 16A, 16B, 16C are secured to the helicopter 10, for example using the rotator 18.

During step 104, the anti-rotation device 14 is secured to the tower portion 12 by optional sling power hooks 24A and 24B.

Then, during a step 106 of lifting and moving the load, the helicopter 10 transports the pylon portion 12 to a placement area for placement on the ground, or another pylon portion of the area. During this step, propulsion devices 28 of pitch beam 20 may be controlled (step 108), using remote control 30 or by program control, to maintain pitch beam 20 in a set orientation defined about the yaw rotation transverse axis according to the reference frame of helicopter 10 or the ground. For example, during a lifting phase of the pylon portion, the propulsion means 28 may be controlled to maintain the spreader beam 20 in its orientation on the ground, preventing the pylon portion 12 from encircling the axis A ₂Self-rotation; during the transport phase of the pylon portion 12, or if necessary during the transport phase of the open pitch beam 20, the propulsion means 28 can be controlled to maintain the open pitch beam 20 along the longitudinal axis of the helicopter 10, thus shortening its lifting stroke; the propulsion means 28 may be controlled to orient the spreader beam 20 and pylon portion 12 in the correct direction of placement during the stage of placement of the pylon portion 12 on the ground or on another pylon portion.

Finally, during a final step 110, the pylon portion 12 is positioned according to the orientation required for release of the remote operated hooks 24A and 24B.

Steps 104 to 110 just described can be repeated to complete the installation of the pylon made up of a plurality of parts. Advantageously, it is part of a conventional installation procedure for installing a pylon from an installation platform in a placement area.

In view of the loads carried and the safety requirements of any lifting and movement performed by the helicopter in such a procedure, it is preferable to follow the following control conditions:

selecting carbon fiber composite material for the construction of the pitch beam 20 and its streamlined ducts 34A, 34B, optionally even also for the augers 32A, 32B, for anti-rotation devices not exceeding 5 meters long, 150 kg weight, capable of carrying up to 4.5 tons of static load and 19 tons of dynamic load,

selecting motors 52A, 52B with a power of approximately 15 kW or more, a weight of less than 2 kg each, and a thrust of more than 400N when connected to the propellers 32A, 32B,

selecting an auger 32A, 32B capable of rotating 4000 to 6000 revolutions per minute, in which case the direction of rotation of such an auger cannot be reversed: in the condition that the propellers are alternately actuated, but never actuated together, this does not cause any problem,

-selecting a battery having a battery life of at least 5 hours during the control, maintaining a total voltage of 48 volts and a charge capacity of 100 ampere-hours: two lithium-iron-polonium batteries, each at 24 volts and having a total weight of about 50 kg, mounted in series are suitable.

Now, the operation of the remote controller 30 in its embodiment having the mode selector 44 will be described in detail with reference to the flowchart of fig. 5.

During a first step 200, the telehorn 30 is manipulated by the pilot or co-pilot of the helicopter 10. It has a main indicator to indicate start and a control indicator to indicate angle control start or stop start. These indicators are now off.

The next step 202 is a waiting step for the remote controller 30 to be activated using the switch 40. The main indicator remains off as long as it remains off, and full power is cut off (step 204). Once the driver or co-driver manipulates the switch 40, the remote controller 30 is turned on, its primary indicator is activated, the charge level indicator 42 is activated, and the activated information signal is transmitted to the receiver 62 of the electronic control box (step 206).

After activation, the state of mode selector 44 is checked in step 208. If mode selector 44 is on a first yaw control mode of beam 20 with respect to the angular reference frame of helicopter 10, then a series of steps 210 through 220 are performed. If mode selector 44 is on the second mode of yaw control of the angular reference frame of beam 20 with respect to the ground, then a series of steps 222 through 232 are performed.

Step 210 is an instruction step for the remote controller 30 to wait for the setting of the angle control. This may be done using a predetermined message, such as "standby system" (STBY) on the display screen 46.

Step 212 is a step of acting on the control indicator to instruct the angular control to stop starting. Thus, the control indicator is, for example, red.

The next step 214 is to wait for the action on the follow-up control switch 50. As long as the driver or co-driver is not acting on the switch 50, steps 210 and 212 do not continue, once the angle control is activated by acting on the switch 50, step 216 is performed to act on the control indicator to indicate that the angle control is activated, so that the control indicator, for example, turns green, and the set angle α displayed on the screen 46 is changed to a set angle α _CAnd (4) returning to zero. Further, the start information signal of the angle controller is transmitted to the receiver 62 of the electronic control box 56.

The next step 218 is a step that may be applied to the wheel 48 to calibrate the set angle α _CIs-180 to +180 degrees, relative to the angle zero in step 216, the selected set angle value α is selected whenever the controller is activated (the control indicator is green) _CAngular orientation α of an angular reference frame of helicopter 10 relative to the ground _HTiming is transmitted to receiver 62 of the electronic control box this step uses an electronic compass on board helicopter 10 to know its orientation α _H。

Finally, step 220 is a step of waiting to act on the slave control switch 50. As long as the driver or co-driver is no longer acting on the switch 50, no further processing continues with step 218: for example during the entire deployment of the transport and deployment of one pylon segment. Once the angle controller is deactivated by acting on the switch 50, for example once the pylon portion 12 is positioned as desired, step 210 returns to: the display on screen 46 thus returns to indicating "spare system" (STBY) and the control indicator returns to red.

Steps 222 to 232 are identical to steps 210 to 220, respectively, except that step 230 does not include transmitting α the angular orientation of helicopter 10 with respect to the ground's angular reference frame _H。

Of course, operation of the remote control 30 is easily simplified if there is no mode selector for use by a ground operator, as described in detail above.

Now, the operation of the microcontroller 60 of the control box 56 of the anti-rotation device 14 will be described in detail with reference to the flowchart of fig. 6. This operation allows the use of multiple teleeffectors 30, with or without mode selectors.

During a first step 300, the electronic control box 56 is activated by acting on the switch 68. This action causes the visual indicator 36 to switch to red (step 302), indicating the charge level of the battery 58 on the indicator 66.

Then, during a test step 304, the microcontroller 60 performs a search to check whether at least one of the radios 30 is active. If this is not the case, step 302 is performed.

If at least one of the radios 30 is activated, another verification step 306 is performed during which the microcontroller 60 performs a search to check if at least two of the radios 30 are activated. If this is the case, then step 302 is performed and the microcontroller 60 does not accept the simultaneous use of two or more activated telemotors.

If only one of the remote radios 30 is activated, then step 308 is performed and the visual indicator 36 is switched to orange.

The next step 310 is a step of waiting for reception of the angle control setting. As long as the angular control of pitch beam 20 is not activated by switch 50 acting on one of the teleactuators 30, microcontroller 60 returns to steps 308 and 310.

When the receiver 62 receives the information signal indicating the activation of the angle controller, the visual indicator 36 is switched to green and a new checking step 312 is performed.

During this step 312, microcontroller 60 checks whether receiver 62 receives angular orientation α alone or accompanied by helicopter 10 _HSet angle value α _C。

If the receiver 62 receives two angular values α _CAnd α _HThat means then that at the remote control 30 that is activated aloneIn a first mode of control of the deflection of the beam 20 with respect to the angular reference frame of the helicopter 10, the microcontroller 60 executes a sequence of steps 314 to 320 if the receiver 62 receives only the set angular value α _CThis then means that a single activated remote control 30 is in the second mode of yaw control of the angular reference frame of the beam 20 relative to the ground, and the microcontroller 60 performs a series of steps 322 through 328.

During step 314, the microcontroller 60 is also in the first yaw control mode of the spar 20 relative to the angular reference frame of the helicopter 10.

It therefore performs the following calculations during step 316:

Δ＝α _P–(α _H–α _C) Wherein, α _PIs the angular value provided by the electronic compass 64.

The microcontroller 60 then compares its calculated result Δ to a predetermined threshold value for angular tolerance, such as 5 degrees, during a verification step 318. As long as Δ remains less than the threshold, return to step 316.

Once Δ exceeds the threshold, the microcontroller 60 proceeds to step 320 to drive one of the two augers 32A and 32B so that the pitch beam 20 is at α _PAs close as possible to α _H–α _CIn the orientation of (c).

During step 322, microcontroller 60 enters a second mode of yaw control of the angular reference frame of beam 20 with respect to the ground.

It therefore performs the following calculations during step 324:

Δ＝α _P–α _Cwherein, α _PIs the angular value provided by the electronic compass 64.

Thus, during a test step 326, the microcontroller 60 compares its calculated result Δ to a predetermined threshold value for angular tolerance. As long as Δ remains less than the threshold, return to step 324.

Once Δ exceeds the threshold, microcontroller 60 proceeds to step 328 to drive one of the two augers 32A and 32B to bring the pitch beam 20 at α _PAs close as possible to α _CIn the orientation of (c).

Steps 320 and 328 may be followed by returning to steps 316 and 324, respectively, further knowing that the pilot, copilot, or operator on the ground can change the set angle α using the wheel 48 at any time _C。

In addition, at any time between steps 312 to 320 or 328, any action on the switch 50 of the remote control 30 that is actuated causes the microcontroller 60 to return to step 308. Likewise, any actuation of the switch 40 of either remote control 30 between steps 308 and 320 or 328 causes the microcontroller 60 to return to step 302.

It is clear that an anti-rotation device as described above allows the load to perform its own yaw rotation from a single fixed point fixed to the machine that lifts and moves it, without transmitting the moment generated by the load. In addition, the device is simple to design, adjust, use and maintain. It can also be more safely automatically placed in emergency by means of the electric hooks 24A, 24B. It is also relatively lightweight, self-adjusting in terms of power consumption, and can be operated from a lift and move machine or remotely from the ground. Therefore, no person is required near the load. Finally, it is easy to design and does not interfere with the electrical equipment that carries the machinery, such as a helicopter.

Furthermore, it should be noted that the present invention is not limited to the specific devices and embodiments described above.

In particular, one embodiment has been described in which propulsion device 28 is operated using one or more teleeffectors 30, however, another embodiment may provide one or more set angles α directly in microcontroller 60 _CFor example in the form of GPS coordinates (global positioning system). In this case, the control of the propulsion device 28 may be at least partly by program control.

In general, it will be apparent to those skilled in the art that various changes can be made to the embodiments described above in accordance with the features described therein. In the following claims, the terms used should not be construed to be limited to the embodiments described in the specification, but should be construed to include all equivalent embodiments that the claims are intended to cover, within the scope of the description, those skilled in the art and having the benefit of the teachings of the present invention.