FR3092086A1 - Anchoring system for securing an aircraft - Google Patents

Anchoring system for securing an aircraft Download PDF

Info

Publication number
FR3092086A1
FR3092086A1 FR1900719A FR1900719A FR3092086A1 FR 3092086 A1 FR3092086 A1 FR 3092086A1 FR 1900719 A FR1900719 A FR 1900719A FR 1900719 A FR1900719 A FR 1900719A FR 3092086 A1 FR3092086 A1 FR 3092086A1
Authority
FR
France
Prior art keywords
anchor
anchoring
aircraft
ground
cord
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
FR1900719A
Other languages
French (fr)
Inventor
Reza ROSIER
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Musthane SARL
Original Assignee
Musthane SARL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Musthane SARL filed Critical Musthane SARL
Priority to FR1900719A priority Critical patent/FR3092086A1/en
Priority to FR1900719 priority
Publication of FR3092086A1 publication Critical patent/FR3092086A1/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00Ground or aircraft-carrier-deck installations
    • B64F1/12Anchoring
    • B64F1/16Pickets or ground anchors; Wheel chocks
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00Ground or aircraft-carrier-deck installations
    • B64F1/12Anchoring
    • B64F1/125Mooring or ground handling devices for helicopters

Abstract

Anchoring system for securing an aircraft Anchoring system (10) for securing an aircraft (A) to a ground (S), the anchoring system comprising at least a first anchor (12) configured to be driven into the ground , an anchoring point (14) arranged on the aircraft and a longilinear connecting device (16) connecting said first anchor and the anchoring point, said first anchor being mounted in an articulated manner to the connecting device so that the first anchor can pivot between an insertion position and an anchor position. Figure for the abstract: Fig. 1.

Description

Description Title of the invention: Anchoring system for securing an aircraft Technical field

The present invention relates to the field of anchoring systems for securing an aircraft on the ground.

[0002] On mission, aircraft, for example helicopters, are regularly kept on the ground between two flight sessions.

In the event of wind or gusts, it is necessary to secure the aircraft on the ground in order to prevent them from tipping and falling, which could cause serious damage.

Prior art

We thundered anchoring systems comprising an anchor consisting of a stake intended to be driven into the ground, as well as a cable connecting the stake to the aircraft, to keep the aircraft fixedly on the ground and prevent 'it does rock.

[0004] A drawback of this type of anchoring system is that the stake risks being extracted from the ground, in particular in certain regions where the soils are particularly loose, for example sandy soils.

It is therefore necessary to drive the stake very deeply, which is restrictive and sometimes still insufficient to hold the aircraft.

In addition, anchoring the aircraft using a stake remains unreliable despite everything and the aircraft tipping over may occur.

[0005] The most reliable stakes are configured to be driven very deep into the ground.

They are also excessively heavy and coupled to metal cables, which increases the weight and bulk of the anchoring system.

The payload capacity and therefore the operational performance of the aircraft are reduced.

[0006] In addition, the establishment of a stake leads the operator to make significant physical efforts and requires the use of high-performance tools such as construction hammers.

These tools are heavy, difficult to handle, move and carry on an aircraft

[0007] The known systems therefore have the drawbacks of being inefficient, heavy and bulky.

Disclosure of the invention 100081 An aim of the present invention is to provide an anchoring system which overcomes the aforementioned drawbacks.

100091 To do this, the invention relates to an anchoring system for securing an aircraft to the ground, the anchoring system comprising: at least one first anchor configured to be driven into the ground; - an anchor point placed on the aircraft; and 2 - an elongate connecting device connecting said first anchor and the anchoring point, said first anchor being mounted in an articulated manner to the connecting device so that the first anchor can pivot between an insertion position and a position of anchoring.

[0010] In a nonlimiting manner, the aircraft can be a helicopter or an airplane.

[0011] The first anchor preferably comprises a body and a head forming a point, facilitating its insertion into the ground.

In its insertion position, the first anchor can easily be inserted into the ground, for example by means of a rod making it possible to drive and guide the first anchor under the surface of the ground.

In its anchoring position, the first anchor is securely held in the ground, so as to fix the aircraft stably on the ground.

[0012] In comparison with the stakes of the prior art, the first anchor offers satisfactory anchoring, even when it is inserted into the ground at a shallow depth.

In particular, it is operational at a depth much less than the required driving depth with a stake.

Also, it is not necessary to use heavy tools such as a construction hammer to insert the first anchor in the ground, which reduces the efforts to be made, as well as the weight and size of the tools to be transported. to set up the anchoring system.

[0013] A tensile force applied to the connecting device advantageously enables the first anchor to pivot and therefore to pass from the insertion position to the anchoring position.

In a nonlimiting manner, the anchoring system may include a cord cooperating with the first anchor, so that traction on said cord allows the first anchor to pass from the insertion position to the anchoring position.

[0014] Preferably, the first anchor is brought from the insertion position to the anchoring position by pivoting through an angle approximately equal to 90 °.

[0015] The first anchor is preferably mounted at a first end of the connecting device.

Said first anchor advantageously extends in a longitudinal direction, the longitudinal direction preferably being substantially vertical when the first anchor is in the insertion position and substantially horizontal when the first anchor is in the anchoring position.

[0016] An example of such a first anchor is disclosed in WO2014170574.

[0017] The anchor point can be placed in any part of the aircraft capable of withstanding a tensile force.

It is preferably arranged on a side wall of the aircraft.

The anchor point may include a hook or a fixing ring, allowing easy attachment of the connecting device to said anchor point.

[0018] The connecting device is preferably flexible in order to facilitate its connection to the anchor point and the insertion of the first anchor in the ground.

Preferably, the anchor point cooperates with a second end of the connecting device, opposite to its first end.

To set up the anchoring system, in order to secure an aircraft on the ground, the aircraft is first placed on the ground, at the desired location.

The first anchor is then inserted, placed in the insertion position, in the ground, near the aircraft, preferably facing the anchor point.

The first anchor is then pivoted and brought into the anchoring position, in which it is held fixedly in the ground and withstands high tensile forces.

A portion of the connecting device then extends into the ground, between the first anchor and the surface of the ground.

[0020] The link device is then connected to the anchor point on the aircraft.

If necessary, the linkage device is then put under tension.

The installation of the anchoring system is particularly quick and easy.

[0021] The connection device then extends between a zone of the surface of the ground, situated substantially vertically with respect to the first anchor, and the anchor point on the aircraft.

Also, the anchoring system exerts a holding force on the aircraft, directed along the connecting device, towards said zone of the ground surface.

This force prevents the aircraft from tilting in said direction, in a direction opposite to said zone of the ground surface.

One advantage is to prevent the aircraft from being damaged in the event of strong winds or gusts.

In addition, the anchoring system makes it possible to reduce the roll or pitch of the aircraft placed on the ground.

[0023] The first anchor, in its anchoring position, offers a much higher resistance to tearing than that of a stake as used in the prior art.

The anchoring system according to the invention therefore makes it possible to maintain the aircraft all the more efficiently and in a stable manner on the ground, and in particular in the event of particularly violent wind.

[0024] In addition, the first anchor has a reduced weight and bulk compared to a metal stake as used in the prior art, which facilitates its transport, in particular within the aircraft.

[0025] In addition, it is not necessary to drive the anchor to a significant depth to obtain satisfactory anchoring.

The installation of the anchoring system is therefore facilitated, in particular in dry and / or rocky soils.

Without leaving the cover of the invention, several anchoring systems according to the invention can be used simultaneously, each of the connecting devices then being connected to a different anchoring point on the aircraft.

One advantage is to prevent the aircraft from tilting in different directions.

For example, anchoring systems can be placed on either side of the aircraft in order to prevent it from tilting sideways, to one side or the other.

[0027] Preferably, the connecting device comprises a first connecting element and a second connecting element connected to the first connecting element.

Advantageously, the first connecting element connects the anchor point and the second connecting element, and the second connecting element connects the first connecting element and the first anchor.

[0029] The second connecting element therefore extends partly into the ground when the first anchor is inserted into the ground.

Preferably, the first connecting element comprises a first end part and a second end part opposite the first end part, the first end part of the first connecting element being connected to the point of anchor, while the second end portion of the first link member is connected to the second link member.

[0031] Advantageously, the second connecting element comprises at least a first cord having a first junction portion and a second junction portion.

Such a rope has great strength, which reduces the risk of breakage, and has low elasticity, which limits the movements of the aircraft on the ground.

Such a rope is also particularly flexible, which facilitates the insertion of the first anchor in the ground, the connection of the connecting device to the anchoring point, as well as the storage of the anchoring system after use.

Furthermore, the cord has a reduced weight compared to a metal connecting element such as a chain used in the prior art.

[0032] Preferably, the first junction portion of said first cord is connected to the second end portion of the first connecting element.

In a non-limiting manner, the first cord can form a loop at the level of the first junction portion allowing connection with the first connecting element.

The first cord can also include a splice at the junction portion, making it possible to make a loop while avoiding knotting it, which would risk weakening it.

[0033] In a nonlimiting manner, the first junction portion of said first cord can be arranged at a first end of said first cord, so that the first cord and the first connecting element are connected end to end.

[0034] The first cord preferably has a length of between 50 and 150 centimeters.

[0035] According to a first advantageous variant, the second junction portion of the first cord is connected to the first anchor.

Also, in this first variant, the first cord advantageously extends between the first anchor and the first connecting element.

[0037] In a nonlimiting manner, the second junction portion of the first rope can be arranged at a second end of said first rope, so that the anchor is connected to said second end of the first rope.

According to a second advantageous variant, the anchoring system comprises at least a second anchor and the second connecting element comprises at least one second rope, the second rope connecting the first anchor and the second anchor, the second junction portion of the first string cooperating with the second string.

The use of two anchors greatly increases the resistance to tearing of the anchoring system.

This therefore makes it possible to improve the anchoring and the stability of the aircraft placed on the ground and to further reduce the risks of the aircraft tipping over.

[0039] The second anchor is preferably identical to the first anchor and is inserted into the ground in a similar manner, according to the steps detailed above.

[0040] In this second variant, the first cord extends between the first connecting element and the second cord.

The second junction portion of the first cord preferably cooperates with a connection part of the second cord.

Said connection part can be arranged at one end or at an intermediate part of the second cord.

The connection part can be movable along the second string.

[0042] The second cord defines a first strand extending between said connection part and the first anchor and a second strand extending between the connection part and the second anchor.

When the first and second anchors are driven into the ground, the first strand has a first segment, substantially vertical, extending between the first anchor and the surface of the ground, and a second segment extending between the surface of the ground, opposite the first anchor, and the connection part.

The second strand also has a first segment, substantially vertical, extending between the second anchor and the surface of the ground, and a second segment extending between the surface of the ground, opposite the second anchor, and the connection part .

The first and second anchors are preferably driven into the ground to a substantially identical depth so that the lengths of the first segments of the first and second strands of the second rope are substantially equal.

When the aircraft tends to tip, for example because of the wind, a traction force is exerted by the aircraft on the first connecting element.

This tensile force is transmitted by the first connecting element on the first cord, then by the first cord on the second cord, at the connection part of the second cord.

This force is then distributed between the first strand and the second strand of the second rope and therefore between the first and the second anchor.

The use of two cords cooperating with one another therefore makes it possible to reduce the tearing force exerted on each of the anchors so that the tearing resistance of the anchoring system is further improved.

Advantageously, the second junction portion of the first cord is provided with a connection ring and the second cord passes through said connection ring.

The connection ring is slidably mounted along the second cord, so that the connection ring cooperates with a connection part of the second cord, movable along said second cord.

The ring is advantageously fixed to the second junction portion.

When a tensile force is exerted by the aircraft on the first connecting element and transmitted to the first cord, the connection ring slides along the second cord, in the direction of said tensile force, towards the aircraft.

Such a traction force can be exerted, for example, when the connecting device is put under tension or when the aircraft tilts caused by the wind.

This displacement of the ring has the consequence of jointly tensioning the second segment of the first strand of the second string and the second segment of the second strand of the second string.

Here again, it is of interest to distribute the tensile forces exerted on the first strand and the second strand of the second rope and therefore on the first anchor and on the second anchor.

The resistance to tearing of the anchoring system, and therefore the anchoring and lashing of the aircraft on the ground, are further improved.

The ring advantageously has a diameter slightly greater than that of the second string.

Advantageously, the second cord has a first end portion fixed to the first anchor and a second end portion fixed to the second anchor.

The second rope then extends entirely between the two anchors.

One advantage is to reduce the length of the second cord and therefore the bulk of the anchoring system when not in use.

Preferably, said at least one first cord is made of high tenacity polyethylene fibers, thanks to which the first cord can withstand very high tensile forces without breaking.

In addition, such a rope has a low coefficient of friction, which improves the operation of the connecting device.

Moreover, this material is light.

Preferably, the second cord is also made of high tenacity polyethylene fibers.

Advantageously, the first connecting element comprises a strap.

Such a strap has the advantage of being flexible, light and easy to manufacture.

[0053] Preferably, the anchoring system further comprises a tensioning member configured to tension said connecting device.

One advantage is to allow an operator to easily tension the linkage device, with a minimum of effort, after having inserted the anchor (s) in the ground and after having connected the linkage device to the anchor point. of the aircraft.

[0054] The tensioning member can be a ratchet tensioner provided with an operable handle.

The tensioning member can be arranged on the first connecting element or on the second connecting element.

Advantageously, the tensioning member cooperates with the first connecting element, to tension said first connecting element, whereby said tensioning member is easily accessible for the operator.

In fact, the connecting element generally extends approximately 1 meter above the surface of the ground.

Preferably, the anchoring system further comprises a measuring device configured to measure the voltage applied to the connecting device, for example a dynamometer.

One advantage is being able to adjust the voltage applied to the tensioning device, for example during tensioning, in particular in order to minimize the roll or pitch of the aircraft placed on the ground.

Preferably, the anchoring point comprises a fastening member integral with the aircraft, for example a fastening hook.

The fixing member can consist of all types of fastener making it possible to connect the linkage device to the anchoring point.

According to a particularly advantageous aspect of the invention, the connection device is detachably connected to the anchoring point.

One advantage is that it is easy to fold up and store the connecting device after use.

Furthermore, this facilitates the installation of the anchoring system, as the first anchor can be easily driven into the ground before connecting the linkage device to the anchoring point.

The operator is not disturbed by the connecting device stretched between the first anchor and the anchor point.

In a nonlimiting manner, the connection device can be provided with a carabiner allowing the removable connection to the anchor point.

The invention also relates to a method for securing an aircraft to the ground comprising the steps according to which: an anchoring system is provided as described above; - An aircraft is provided comprising the anchoring point of the anchoring system; - the first anchor is driven into the ground; - Pulling on the connecting device so as to cause the first anchor to pass from the insertion position to the anchoring position; - The connecting device is connected to the anchor point; and - the connection device is energized

The invention further relates to an installation comprising an anchoring system as described above and an aircraft comprising the anchoring point.

Brief description of the drawings 8 100611 Ifig.11 Figure 1 illustrates a first embodiment of an installation comprising an anchoring system according to the invention;

[0062] [fig.2] Figure 2 illustrates the connection between the first connecting member and the anchor point of the anchoring system of Figure 1;

[0063] [fig.3] Figure 3 illustrates the connection between the second connecting element and the first anchor of the anchoring system of Figure 1;

[0064] [fig.4] Figure 4 illustrates the insertion of the first anchor of the anchoring system of Figure 1 in the ground;

[0065] [Fig.5] Figure 5 illustrates a second embodiment of an installation comprising an anchoring system according to the invention; and

[0066] [fig.6] Figure 6 illustrates the cooperation between the first rope and the second rope of the anchoring system of Figure 5.

Description of embodiments

Figure 1 illustrates a first embodiment of an installation 8 comprising an anchoring system 10 according to the present invention, as well as an aircraft A.

For reasons of readability, the aircraft is not shown to scale.

The anchoring system 10 comprises a first anchor 12, an anchoring point 14 arranged on the aircraft A and a connecting device 16 elongated.

In Figure 1, the anchoring system 10 is placed in a position of use so that the connecting device 16 connects the first anchor 12 and the anchoring point 14, the first anchor being driven into the ground S.

As illustrated in Figure 3, showing the connection between the connecting device and the first anchor, said first anchor 12 comprises a body 18 and an insertion head 20 forming a point.

It is also provided with a connector 22.

The connecting device 16 comprises a first connecting element 24 and a second connecting element 26 connected to the first connecting element 24.

In this non-limiting example, the aircraft A is a helicopter.

The anchoring point 14 comprises a fixing member 15 integral with the aircraft A having the shape of a hook or even of a half-ring.

The anchor point 14 is arranged on a side wall of the aircraft A.

The first connecting element 24 comprises a strap.

It comprises a first end part 24a and a second end part 24b, opposite to the first end part 24a.

The first end portion 24a is connected to the anchor point 14.

In this non-limiting example and as illustrated in Figure 2, the first end portion 24a of the first connecting member 24 is provided with a snap hook 25 removably connected to the fixing member 15 of the point of anchoring 14, so as to connect the first connecting element 24 to said anchoring point 14.

The first connecting element 24 is provided with a ratchet tensioner forming a tensioning member 28 configured to allow the tensioning of said connecting device 16.

The first link member 24 further comprises a dynamometer forming a measuring device 30 configured to measure the voltage applied to the link device 16.

In this first non-limiting embodiment, the second connecting element 26 comprises a single first cord 32 made of high tenacity polyethylene fibers.

The first cord 32 comprises a first junction portion 32a disposed at a first end of said first cord and connected to the second end portion 24b of the first connecting element 24.

More precisely, a loop is made on the first cord 32, so as to form said first junction portion.

The two pieces of first cord 32 protruding from said loop are braided so as to form a splice.

Said splice makes it possible to form the loop without tying the first cord, which would risk weakening it.

The second end portion 24b of the first connecting element 24 passes through the loop forming the first connecting portion 32a and is closed on itself in order to connect the first connecting element 24 to the second connecting element 26.

Without departing from the scope of the present invention, the first connecting element 24 could be connected to the first cord 32 by any other connection means.

The first anchor 12 is hingedly mounted to the connecting device so that the first anchor can pivot between an insertion position and an anchoring position.

In this non-limiting example, the first anchor is pivotally mounted at a first end of the connecting device 16.

The carabiner 25 is mounted at a second end of the connecting device, opposite the first end of said connecting device 16.

The first cord 32 also comprises a second junction portion 32b arranged at a second end of the first cord and connected to the connector 22 of the first anchor 12.

More precisely, the second end of the first cord 32 is also provided with a loop forming said second junction portion 32b, cooperating with the connector 22.

When the anchoring system 10 is not used, the carabiner 25 and therefore the connecting device 16 are disconnected from the anchoring point 14 of the aircraft A.

The connecting device and the first anchor 12 are advantageously kept connected and stored together.

To place the anchoring system 10 in the position of use illustrated in Figure 1, the operator places the first anchor 12 in the insertion position, as illustrated in Figure 4, in which it s' extends in a direction of substantially vertical insertion, transversely to the surface of the soil S.

The operator then inserts the first anchor 12 into the ground, for example by means of a rod 100 making it possible to drive and guide the first anchor 12 under the surface of the ground.

The first anchor 12 is inserted to the desired depth, so that part of the first rope 32 extends into the ground.

The first anchor 12 is then pivoted upwards by approximately 90 °, for example by pulling on the first rope 32, so as to place it in the anchoring position, as illustrated in FIG. 1.

In this anchoring position, the first anchor 12 extends transversely to the direction of insertion and substantially parallel to the surface of the ground S.

The first anchor 12 is then held securely in the ground.

The operator then connects the carabiner 25 disposed at the first end portion 24a of the first connecting element 24 to the fixing member 15 of the anchoring point 14, so as to connect the connecting device 16 to the aircraft A.

The operator can then tension the connecting device 16 by actuating the tensioning member 28.

More precisely, the operator actuates the handle of the ratchet tensioner, which has the consequence of reducing the length of the strap of the first connecting element 24 between the anchoring point 14 and the first junction portion 32a of the first rope 32.

The connecting device 16 is then tensioned between the first anchor 12 and the anchoring point 14.

In order to adjust the voltage applied to the connecting device 16, the user can use the measuring device 30.

The first cord 32 then has a first segment 34 extending substantially vertically between the first anchor 12 and the surface of the ground, opposite the first anchor.

The first cord 32 also has a second segment 36, forming an angle with the first segment 34 and extending between the surface of the ground, facing the first anchor 12, and the second end portion 24b of the first connecting element. 24.

The second segment 36 and the first connecting element extend in the extension of one another and are stretched between the surface of the ground and the anchor point 14.

Therefore, a traction force exerted by the aircraft A on the connecting device 16, 11 for example in the event of wind, is transmitted by the first connecting element 24 to the first cord 32, towards the aircraft AT.

This results in a tensile force exerted on the first anchor 12, directed along the first segment 34 of the first cord 32, substantially vertically, upwards.

Insofar as the first anchor 12 is held firmly in the ground, it resists this tensile force and raéroncf A is held fixedly on the ground.

Thanks to the invention, the aircraft does not run the risk of tipping over.

The aircraft is therefore effectively stowed on the ground and remains stable.

In addition, insofar as the connecting device 16 is stretched, the roll and pitch of the aircraft A placed on the ground, caused in particular by the wind, are reduced.

Several anchoring systems can be used simultaneously in order to hold the aircraft A more firmly on the ground and to improve its stability, whatever the direction of the forces to which it is subjected.

Each of the connecting devices of these anchoring systems is connected to an anchoring point 14 which is specific to it on the aircraft A.

These anchor points are then distributed over the aircraft.

FIG. 5 illustrates a second embodiment of an installation 8 'comprising an anchoring system 10' in accordance with the present invention and an aircraft A '.

In this second embodiment, the anchoring system 10 'comprises, as in the first embodiment, a first anchor 12', an anchoring point 14 'disposed on the aircraft A' and a device 16 'link.

The connecting device 16 'also comprises a first connecting element 24' and a second connecting element 26 '.

The first link member 24 'is substantially identical to the first link member 24 of the first embodiment.

In this non-limiting example, the anchoring system 10 'further comprises a second anchor 38', identical to the first anchor 12 ', and comprising a body 40', a head 42 'and a connector 44'.

As illustrated in Figure 6, the second connecting member 26 'comprises a first cord 32' having a first junction portion 32a 'and a second junction portion 32b'.

The second junction portion 32b 'is provided with a connection ring 38'.

The second connecting element 26 'further comprises a second cord 46' connecting the second anchor 38 'and the first anchor 12'.

More precisely, the second cord 46 'has a first end portion 46a' provided with a loop connected to the connector 22 'of the first anchor 12' and a second end portion 46b 'provided with a loop connected to the connector 44 'from the second anchor.

As seen in Figure 6, the second rope 46 'passes through the connection ring, so that said connection ring is slidably mounted along said second rope 46' and cooperates with said second rope in one part of 12 connection 48 '.

To place the anchoring system 10 'of this second embodiment in the position of use, the operator inserts the first and second anchors 12', 40 'in the ground, as detailed above.

These two anchors are inserted a few tens of centimeters from each other.

The operator then connects the carabiner 25 'of the first connecting element 24' with the anchoring point 14 ', then tensioning the connecting device 16' using the tensioning member 28 ', as detailed previously.

This tensioning has the consequence of sliding the connection ring 38 'along the second cord 46', substantially in the direction of the aircraft A '.

Also, the connection portion 48 'of the second string with the first string 32' moves along the second string 46 '.

One advantage is to distribute in a uniform manner the traction forces exerted by the aircraft A ′ on the second rope 46 ′ and on the first and second anchors.

[0100] When the connecting device 16 'is put under tension, the second cord defines a first strand 50' extending between said connection part 48 'and the first anchor 12' and a second strand 52 'extending between the connection part and the second anchor 38 '

When the first and second anchors 12 ', 38' are driven into the ground S, the first strand has a first segment 50a ', substantially vertical, extending between the first anchor 12' and the surface of the ground S, and a second segment 50b 'extending between the surface of the ground, opposite the first anchor 12', and the connection part 48 '.

The second strand also has a first segment 52a ', substantially vertical, extending between the second anchor and the surface of the ground, and a second segment 52b' extending between the surface of the ground, opposite the second anchor 38 ' , and the connection part.

[0102] The position of the connection ring along the second string 46 'is automatically adjusted so that the second segments 50b', 52b 'of the first and second strands 50', 52 'of the second string 46 'are stretched.

The tensile forces are then distributed over the two strands and therefore over the two anchors.

The anchoring and the pull-out resistance of the anchoring system are therefore improved. 13

FR1900719A 2019-01-28 2019-01-28 Anchoring system for securing an aircraft Pending FR3092086A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1900719A FR3092086A1 (en) 2019-01-28 2019-01-28 Anchoring system for securing an aircraft
FR1900719 2019-01-28

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1900719A FR3092086A1 (en) 2019-01-28 2019-01-28 Anchoring system for securing an aircraft

Publications (1)

Publication Number Publication Date
FR3092086A1 true FR3092086A1 (en) 2020-07-31

Family

ID=67587809

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1900719A Pending FR3092086A1 (en) 2019-01-28 2019-01-28 Anchoring system for securing an aircraft

Country Status (1)

Country Link
FR (1) FR3092086A1 (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU61210A1 (en) * 1939-04-22 1941-11-30 И.В. Яковлев Device for fastening aircraft to the ground
US3139163A (en) * 1960-12-27 1964-06-30 Augustine C Haller Ground anchor
WO1997033047A1 (en) * 1996-03-06 1997-09-12 Royal Anchor Systems, Inc. Ground anchor
US20070000183A1 (en) * 2005-06-30 2007-01-04 Logan Edward A Storm protection apparatus
WO2014170574A1 (en) 2013-04-19 2014-10-23 Musthane Anchoring assembly
EP2896568A1 (en) * 2014-01-08 2015-07-22 Honeywell International Inc. Rotorcraft tie-down detector system

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU61210A1 (en) * 1939-04-22 1941-11-30 И.В. Яковлев Device for fastening aircraft to the ground
US3139163A (en) * 1960-12-27 1964-06-30 Augustine C Haller Ground anchor
WO1997033047A1 (en) * 1996-03-06 1997-09-12 Royal Anchor Systems, Inc. Ground anchor
US20070000183A1 (en) * 2005-06-30 2007-01-04 Logan Edward A Storm protection apparatus
WO2014170574A1 (en) 2013-04-19 2014-10-23 Musthane Anchoring assembly
EP2896568A1 (en) * 2014-01-08 2015-07-22 Honeywell International Inc. Rotorcraft tie-down detector system

Similar Documents

Publication Publication Date Title
Visser et al. Expanding ground-based harvesting onto steep terrain: A review
US7908716B2 (en) Tensioning device
US4075913A (en) Remotely operable mechanism for disconnecting a pickup unit from a tilt-up concrete wall slab
US7871052B2 (en) Flexible cover hold down system
CN102064493B (en) Method for paying off overhead transmission line by unmanned helicopter
KR20100044842A (en) Aerodynamic wind propulsion device and method for controlling
US5243795A (en) Tie down stake
US10689823B2 (en) Anchoring assembly
US7076845B2 (en) Mechanical knot apparatus
US6540207B1 (en) Cable hanging system
US7611129B1 (en) Tension testing anchor lock
US9332748B2 (en) Aerial safety system
EP1224118B1 (en) Device for attaching a load to a helicopter
US9468283B2 (en) Hammock suspension device
US20080085669A1 (en) Portable game hanger
DE69936231T2 (en) Anchoring device
US7421967B1 (en) Mooring apparatus and method
US4934646A (en) Ski rope holder
US6375139B1 (en) Anchoring device for use in rock crevices and the like during rock climbing activities
US6345418B1 (en) Rope hook
JP2001515445A (en) Underwater self-aligning rigging latch device for mooring offshore structures
US20030116677A1 (en) Miniature aircraft catapult
US10189573B2 (en) Off-wing slide raft
DE10210540B4 (en) Cable-guided buoyant body, in particular for transferring loads
US20080010784A1 (en) Compression claw to connect wire meshes or wire netting, and a device to close the compression claws

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Search report ready

Effective date: 20200731