CA2176914A1 - Process and apparatus for maneuvering especially a landed helicopter - Google Patents
Process and apparatus for maneuvering especially a landed helicopterInfo
- Publication number
- CA2176914A1 CA2176914A1 CA002176914A CA2176914A CA2176914A1 CA 2176914 A1 CA2176914 A1 CA 2176914A1 CA 002176914 A CA002176914 A CA 002176914A CA 2176914 A CA2176914 A CA 2176914A CA 2176914 A1 CA2176914 A1 CA 2176914A1
- Authority
- CA
- Canada
- Prior art keywords
- helicopter
- transverse
- wheels
- manipulators
- running gears
- 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.)
- Abandoned
Links
- 238000000034 method Methods 0.000 title claims description 6
- 238000010168 coupling process Methods 0.000 claims description 13
- 230000008878 coupling Effects 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 238000006073 displacement reaction Methods 0.000 description 2
- 206010016334 Feeling hot Diseases 0.000 description 1
- 240000004752 Laburnum anagyroides Species 0.000 description 1
- 101100338513 Mus musculus Hdac9 gene Proteins 0.000 description 1
- 101150084935 PTER gene Proteins 0.000 description 1
- XDXHAEQXIBQUEZ-UHFFFAOYSA-N Ropinirole hydrochloride Chemical compound Cl.CCCN(CCC)CCC1=CC=CC2=C1CC(=O)N2 XDXHAEQXIBQUEZ-UHFFFAOYSA-N 0.000 description 1
- 240000004543 Vicia ervilia Species 0.000 description 1
- 101100338514 Xenopus laevis hdac9 gene Proteins 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000007775 late Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND 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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/12—Ground or aircraft-carrier-deck installations for anchoring aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Manipulator (AREA)
Abstract
For maneuvering a helicopter (1) which has landed on a platform (2) it is well known to use an apparatus which is provided with two transverse guides (11) which each have two transverse running gears (10). The transverse guides (11) are provided with gripping means (13) which are mechanically coupled to the transverse running gears (10) such that the helicopter (1) is grippable on its two longitudinal sides. Such an apparatus is relatively complicated. An apparatus which is simplified according to the invention is provided with only one transverse guide (11) having two transverse running gears (10). Each transverse running gear is assigned a manipulator (12). The transverse running gears (10) are provided with supporting surfaces (16) onto which the wheels (5) of the main landing gear of the helicopter (1) are movable by means of the manipulators (12).
The apparatus according to the invention is particularly suitable for ships on which helicopters (1) that have landed on a platform (2) shall be accommodated in hangars (3).
The apparatus according to the invention is particularly suitable for ships on which helicopters (1) that have landed on a platform (2) shall be accommodated in hangars (3).
Description
2 1 76~ 1 4 -Process and apparatus for maneuvering especially a landed helicopter .
D e s c r i D t i O n ;
The invention relates to a process for m~neuvering especi~ a landed helicopter according to the generic part of claim 1.
Furthermore, the invention r~lates to d ~orresponding apparatus according to the generic part of claim 2.
s An apparatus for maneuvering a helicopter ~hicll has landed on a platform is kno~n from European Patent No. O 518 405 Al. This apparatus is provided wlth four transverse running gears and t~o transverse gu~des spaced apart from one another. The ~wo o respective transverse running gears located at the same side are connected to one another by a longitudinal crosspiece. On each longitudinal crosspiece there are arr~nged gripping means which grip the landed helicopter at predetermined places of both of its sides. The two longitudinal crosspieces are connected to ~he transverse running gedrs in an articulated 2 1 76~ 1 4 manner and are extendible in a teles~opic manner. As a r~sult, it i5 possible to align the longitudinal crosspiece obliquely relative to the longitudinal di rçct i on to be ab 1 e to gri p an obliquely landed hel;copter. The longitudinal crosspieces and' the gripping means are liftable for lifting thç wheels of the main landing gear of the helicopter. As a result, it is ensured that the no~-steerable wheels of the main landing gear do not scrub on the platform during the traverse.
The known apparatus hds the disadvantage that it requires two transverse guides and four in~ependently controllable trans~erse runnlng gears with separate drives. Since the four transverse running gears have to operate in coordination, d great expenditure in terms of technical oontrol is requi~ed.
,~ Moreover, the longitudinal crosspieces must be provided with lift;ng means which are suitable for lifting the entire helicopter.
Therefore, the invention is based on the object to create a, 20 simple method for maneuvering preferably helicopters, and an apparat~s of the generiç type ~h;ch has a simple and cost-effective configuration and is easy to handle.
A process for attaining this object has the features of cla;m 2s 1 . As a result of the helIcopters ~eing p~shed onto runnlng gears, the manipulators need not be configured for lifting the helicopter. Furthermore, additional securing means which hold the hel icopter on the running gea~s during the traverse become unnecessary because the manipulators also take over this task ,0 and, consequently, fulfill m41tiple funet;ons An apparatus for attaining the object of the inven~ion has the features of claim 1, accordlng to which the apparatus only needs to be provided wlth t~o transverse runnlng gears with one 3~ transverse guide. This simple configuration of the apparatus allo~s a cost-effective production thereof. Apart from that, the traverse of ~nly two transverse running gears is easier to coordinate.
~,r~c 2176ql4 Each transvers~ running gear is provided with a manipulator ~hich may be conf;gured in the kno~n manner and especially operates accord;ng to the telescope principle or the articulated-arm principle.
~he manipulators are only required to operate at low penformance because they only need to displace and secure the respective helicapter. Lifting the helicopter, on the other hand, is not required ~ecause supporting surfaces are arranged on the running gears onto which the wheels of the m~in landing gear of the helicopter are pushed by the man;pulators, and on which the wheels rest during the traverse of the helicopter by the transvers~ ~unning gëars, the wheels being secured against displacement by the manipulators.
~g ~xpedjent embod1ments of the invention result fro~ subclaims 3 to 12.
Preferred embodiments of the invention will be explained in more detail hereinbelow with refenence to the drawings. In these:
Fig. 1 sho~s a perspective view of an apparatus for maneuvering a helicopter ~hich has landed on a pl atform, Figs 2 to 7 show a plan view of individ~al successive steps during the maneuvering of the helicopter, Fig. 8 shows a front vlew and partial sectional vie~ of a gripping means of a manipulator engaged with a wheel hub of the helicopter, Fig. 9 shows a plan view of a longitudinal running gear, and Fig. 10 shows a perspective vie~ of a sec~nd embodiment of a transverse guide.
D e s c r i D t i O n ;
The invention relates to a process for m~neuvering especi~ a landed helicopter according to the generic part of claim 1.
Furthermore, the invention r~lates to d ~orresponding apparatus according to the generic part of claim 2.
s An apparatus for maneuvering a helicopter ~hicll has landed on a platform is kno~n from European Patent No. O 518 405 Al. This apparatus is provided wlth four transverse running gears and t~o transverse gu~des spaced apart from one another. The ~wo o respective transverse running gears located at the same side are connected to one another by a longitudinal crosspiece. On each longitudinal crosspiece there are arr~nged gripping means which grip the landed helicopter at predetermined places of both of its sides. The two longitudinal crosspieces are connected to ~he transverse running gedrs in an articulated 2 1 76~ 1 4 manner and are extendible in a teles~opic manner. As a r~sult, it i5 possible to align the longitudinal crosspiece obliquely relative to the longitudinal di rçct i on to be ab 1 e to gri p an obliquely landed hel;copter. The longitudinal crosspieces and' the gripping means are liftable for lifting thç wheels of the main landing gear of the helicopter. As a result, it is ensured that the no~-steerable wheels of the main landing gear do not scrub on the platform during the traverse.
The known apparatus hds the disadvantage that it requires two transverse guides and four in~ependently controllable trans~erse runnlng gears with separate drives. Since the four transverse running gears have to operate in coordination, d great expenditure in terms of technical oontrol is requi~ed.
,~ Moreover, the longitudinal crosspieces must be provided with lift;ng means which are suitable for lifting the entire helicopter.
Therefore, the invention is based on the object to create a, 20 simple method for maneuvering preferably helicopters, and an apparat~s of the generiç type ~h;ch has a simple and cost-effective configuration and is easy to handle.
A process for attaining this object has the features of cla;m 2s 1 . As a result of the helIcopters ~eing p~shed onto runnlng gears, the manipulators need not be configured for lifting the helicopter. Furthermore, additional securing means which hold the hel icopter on the running gea~s during the traverse become unnecessary because the manipulators also take over this task ,0 and, consequently, fulfill m41tiple funet;ons An apparatus for attaining the object of the inven~ion has the features of claim 1, accordlng to which the apparatus only needs to be provided wlth t~o transverse runnlng gears with one 3~ transverse guide. This simple configuration of the apparatus allo~s a cost-effective production thereof. Apart from that, the traverse of ~nly two transverse running gears is easier to coordinate.
~,r~c 2176ql4 Each transvers~ running gear is provided with a manipulator ~hich may be conf;gured in the kno~n manner and especially operates accord;ng to the telescope principle or the articulated-arm principle.
~he manipulators are only required to operate at low penformance because they only need to displace and secure the respective helicapter. Lifting the helicopter, on the other hand, is not required ~ecause supporting surfaces are arranged on the running gears onto which the wheels of the m~in landing gear of the helicopter are pushed by the man;pulators, and on which the wheels rest during the traverse of the helicopter by the transvers~ ~unning gëars, the wheels being secured against displacement by the manipulators.
~g ~xpedjent embod1ments of the invention result fro~ subclaims 3 to 12.
Preferred embodiments of the invention will be explained in more detail hereinbelow with refenence to the drawings. In these:
Fig. 1 sho~s a perspective view of an apparatus for maneuvering a helicopter ~hich has landed on a pl atform, Figs 2 to 7 show a plan view of individ~al successive steps during the maneuvering of the helicopter, Fig. 8 shows a front vlew and partial sectional vie~ of a gripping means of a manipulator engaged with a wheel hub of the helicopter, Fig. 9 shows a plan view of a longitudinal running gear, and Fig. 10 shows a perspective vie~ of a sec~nd embodiment of a transverse guide.
rhe apparatus shown here is situated on board of a ship which is only partly shown in Fig. 1. A part of the deck of the shlp ~erves as a platfor~ 2 for the landi~g of the helicopter 1.
Furthermore, two hangars 3 for accommodating helicopters 1 are prov;ded in the shown embodiment. Uow~ver, the apparatus may also ser~e for accommodating helicopters in only one hangar 3 or ;n more than two hangars 3.
The shown apparatus serves for maneuvering a helicopter ~o landed on a platfo~m 2. The object, in particular, is to move a respective landed helicopter 1 into a corresponding hangdr 3 and, if required, back out of said hang~r.
The apparatus shown hene ls provided with two longitudinal " guides 21 which extend in the longitudinal diroction of the ship and each 1ead into a d;fferent hangar 3. The ends of the two longitud~na~ guides 21 pointing out of the hangar 3 are assigned a common transverse guide 11 whioh e~tends transversely to the longitudinal direction of the ship. One zo single transverse guide thus serves both longitudinal guides 21. The transver5e guide 11 i5 provided with two transverse r~nn;ng gears 10. A displaçeable longitudinal running gear ~0 is arranged alang each longitudinal gujde Zl. However, the Figures only show the longitudinal running gear 20 of a 25 longit~dinal guide ~1.
One manipulator 12 is arranged, specifically stationarily, on each transverse running gear 10. Each man;puldtor lZ i5 provided with a movable gripping means 13 by means of which d 30 helicopter can be grasped on its two longitudinal sides. Since a helicopter cannot land precisely on a predeterlnined spot the gripping mean~ 13 are horizontally and longitudinally displaceable on each manipulator 12 about a cert~in l~ngth.
This length corresponds to at least twice the radius of the 3~ wheels 5 of the ~ain landing gear of the helicopter 1. On each transverse landing gear 10 are arranged s~pporting surfaees 16 onto which the wheels 5 of the main landing gear of the helicopter l can be mo~ed, preferably pushed, by the man;pulator 12.
2176ql4 -Fig. 1 shows an apparatus in which the transverse guide 11 i5 stationarily arranged on the platform 2. Alternatively, the trans~erse guide ~1 of the transverse running gear 10 may also be a~ranged on the platform Z so as to be longitudinally s displaceable, as shown in fig. 10. The longitudinal guides 21 may also be used for this purpose. Oue to the longitudinal displaceability of the transverse guide 11 and a simultaneo~s use of manipulators lZ with a great telescopic or lifting range it is also possible to use the apparatus for maneuv~rin3 ~o helieopters 1 for other purposes, e.g. for transport;ng loads.
Fig. 8 sho~s that the gripping ~eans 13 arranged on each manipulator 12 is provited with a coupling bushing 14 which can be engaged with a coupling head 26 arranged on a wheel hub of the main landing gear of the helicopter 1. A cylinder 17 which can be subjected to a pressure ~edium serves for lo~king the coupling head 26 with the coupling bushing 14. A s~nsor 15 is arranged on each coupling bushing 14 which controls the coupling process, especially determines the end of the coupling 20 proçess As a result, it is possible to ;ndependently stop the lateral advance Or the transverse running gears 10 towards the helicopter 1 with a corresp~nding control. Furthermore, the locking of the coupling bushing 14 with the coupling head 26 can be auto~ated by means of the cyl; nder.
~7~
The respective longitudinal running gear 20 is provided with support~ng surfaces 23 for the wheels 5 and with supporting surfaces 22 for the wheels ~ of the nose landing gear of the he1icopter 1. Furthermore, the longit~dinal running gear 20 is 30 provided with a grid 24 with hotes. ~elicopters 1 which are usually equipped ~ith gripping devices (so-called harpoons) can be arrested on the longitudinal runn;ng gear 20 by means ~f this grid 24, specifically at different positions.
9~ Fig. 9 shows the longitudinal running gear 20. this longitudinal ~unning gear is designed in such a ~anner that the supporttng surfaces 2~ of the ~heels 4 of the nose landing gear are longitudinally displaceable relative to the supporting surfaces ~3 of the wheels 5 of the main landing gear (Fig. 1~.
-As a result, the longitudinal running gear can be quickly and edsily adapted to the dif~erent wheelbases of the different t~pes of helicupters.
From a constructive point of view the solution provides that the supporting surfaces 23 for the ~heels 5 of the main landing gear are fixedly attached to a travers;ng cable extending in a longitudina~ guide, whereas the s~pporting surface 22 for ~he ~heels of the nose landing gear is clampable to any place of the traversing cable extending in the long;tud;nal guide Z1 if required, specific~l1y when a corresponding distance between the supporting su~faces 22 and the supporting surfaces 23 i 5 formed Instead of a traversing cable other pulling members may be used, e.g. chains o~ rods.
1~
figs 2 to 7 show individual steps during the maneuvering of the helicopter 1. f~rthermore, the broad arrows lndicate the ~ovement of the helicopter 1, whereas the narrow arrows clarify the adjustment of the trans~erse running gears lO.
~o The maneuvering of a helicopter 1 with the apparatus takes place in the following manner-Fig. 2 shows a hellcopter immediately after landing. ~or2~ secùring the helic~pter 1, it is anchored with its harpoon on a grid (not shown in the Figure) arranged on the p~atform 2. Due to the movement of the shlp and the influence of the wind, the heli~opter 1 according to the representat;on does normally not land exactly in the direction of the longitudinal running ~ears ~o Z1 (Fig. 1) extending in the direction of the longitudinal dXi5 of the ship~ In case of a great angular deviation, the helicopter 1 is rotated with its tail rotor about its an~hored hdrp~on until it is roughly aligned in the longitudinal direction. Afterwards, the harpoon o~ the hellcopter 1 is 3- released because the helicopter is now secured by the manipulators 12 or the gripping means 13 of the transverse running gears 10.
~'E E D~
As shown in fig. 3, the helicopter l ;s now rctated such that its longitudinal direction is parallel to the direction of the longitudinal guide 21 (Fig. 1). To this ~nd the gripping ~eans 13 of the adiusted uppçr transverse running gear 10 is extended, whereas the gripp;ng means 13 of the lower transverse runn;ng gear 10 is retracted. During the rotation of the helicopter 1, the wheels 4 of the nos~ landing gear are situated in a trans~erse position.
According to F;g. 4, the helicopter 1 is displaced in the longitudinal direc~ion such that the wheels 5 of the main landing gear o~ the helicopter 1 st~nd on the supporting surfaces 16 o~ the transverse running gears 10 (Fig. 1).
According to the invention, the wheels 5 of the main landing gear of the helicopter 1 are pushed onto the supporting surfaces 16 of the transverse running gears 10 for this purpose. The manipulators lZ serve for this purpose by correspondingly displacing, esp~cially retract;ng, the gripping ~eans 13 of the manipulators 12. The position assumed in this 20 manner is shown in Fig. 5. When the wheels 5 of the main landing gear of the helicopter 1 are pushed onto the supporting surfaces 16 of the trans~erse running gears 10, the wheels 4 of the nose landing gear are al;yned in the longitudinal direttion.
2~
After the wheels 4 of the nose landing gear have again been transversely aligned, the helicopter 1 is displaced in the transv~rse direction until its longitudinal axis is aligned with the longitudinal axis of one of the two longitudinal 30 guides ~1 (Fig. 1). This transverse displacement of the helicopter is carried out by traversing both transverse running gears 10 on the transverse guide 11. The helicopter 1 is secured on the transverse running gears 10, especially on the suppo~ting surfaces 16 thereof by the manipulators 12 and their 95 gripping means 13.
After the displace~ent of the helicopter 1 in the transverse direction, the helicopter 1 is pushed onto the previously cor~espondingly posit;oned longitudin~l running gear 20 after ~ 8 -the ~heels ~ of the n~se landing gear have been adjuste~ in the straight direction by means of the two manipulators 12 or gripping means 13 of the transverse running gears 1~. This position is shown in Fig. 6.
A~ter the helicopter 1 has been pushed onto the longitudinal runn;ng gear 20, the wheels 4 of the nose landiny gear stand on the supporting surface 22 of the longitudinal runn;ng gear 20, and the wheels 5 of the main landing gear stand on the supporting surfaces ~3 of the longitudinal running gear 20 (Fig. l) After~ards, the harpoon i5 anchored in the grid 24 to secure the helicopt~r I on the longitudinal runn;ng gear 20.
Finally, as shown in Fig. 7, the gripping means 13 ~re released from the helicopter 1 and the transverse running gears 10 are moved ;nto their starting position. furthermore, the tail p~rt of the helicopter 1 is folded to enable the accommodation of the helicopter in the hangar 3. Afterwards, the longitudinal running gear 20 moves the helicopter 1 which stands on the 2c supporting surfaces 22 and 23 of said longitudinal running ~ea~
20 a~ong said longitudinal guide Z1 into th~ hangar into which the corresponding longitud;nal guide 21 leads.
For starting t~e helicopte~, it is moved out of the hangar 3 zs back onto the platform 2 by the longitudinal running gear 20.
rl r~q
Furthermore, two hangars 3 for accommodating helicopters 1 are prov;ded in the shown embodiment. Uow~ver, the apparatus may also ser~e for accommodating helicopters in only one hangar 3 or ;n more than two hangars 3.
The shown apparatus serves for maneuvering a helicopter ~o landed on a platfo~m 2. The object, in particular, is to move a respective landed helicopter 1 into a corresponding hangdr 3 and, if required, back out of said hang~r.
The apparatus shown hene ls provided with two longitudinal " guides 21 which extend in the longitudinal diroction of the ship and each 1ead into a d;fferent hangar 3. The ends of the two longitud~na~ guides 21 pointing out of the hangar 3 are assigned a common transverse guide 11 whioh e~tends transversely to the longitudinal direction of the ship. One zo single transverse guide thus serves both longitudinal guides 21. The transver5e guide 11 i5 provided with two transverse r~nn;ng gears 10. A displaçeable longitudinal running gear ~0 is arranged alang each longitudinal gujde Zl. However, the Figures only show the longitudinal running gear 20 of a 25 longit~dinal guide ~1.
One manipulator 12 is arranged, specifically stationarily, on each transverse running gear 10. Each man;puldtor lZ i5 provided with a movable gripping means 13 by means of which d 30 helicopter can be grasped on its two longitudinal sides. Since a helicopter cannot land precisely on a predeterlnined spot the gripping mean~ 13 are horizontally and longitudinally displaceable on each manipulator 12 about a cert~in l~ngth.
This length corresponds to at least twice the radius of the 3~ wheels 5 of the ~ain landing gear of the helicopter 1. On each transverse landing gear 10 are arranged s~pporting surfaees 16 onto which the wheels 5 of the main landing gear of the helicopter l can be mo~ed, preferably pushed, by the man;pulator 12.
2176ql4 -Fig. 1 shows an apparatus in which the transverse guide 11 i5 stationarily arranged on the platform 2. Alternatively, the trans~erse guide ~1 of the transverse running gear 10 may also be a~ranged on the platform Z so as to be longitudinally s displaceable, as shown in fig. 10. The longitudinal guides 21 may also be used for this purpose. Oue to the longitudinal displaceability of the transverse guide 11 and a simultaneo~s use of manipulators lZ with a great telescopic or lifting range it is also possible to use the apparatus for maneuv~rin3 ~o helieopters 1 for other purposes, e.g. for transport;ng loads.
Fig. 8 sho~s that the gripping ~eans 13 arranged on each manipulator 12 is provited with a coupling bushing 14 which can be engaged with a coupling head 26 arranged on a wheel hub of the main landing gear of the helicopter 1. A cylinder 17 which can be subjected to a pressure ~edium serves for lo~king the coupling head 26 with the coupling bushing 14. A s~nsor 15 is arranged on each coupling bushing 14 which controls the coupling process, especially determines the end of the coupling 20 proçess As a result, it is possible to ;ndependently stop the lateral advance Or the transverse running gears 10 towards the helicopter 1 with a corresp~nding control. Furthermore, the locking of the coupling bushing 14 with the coupling head 26 can be auto~ated by means of the cyl; nder.
~7~
The respective longitudinal running gear 20 is provided with support~ng surfaces 23 for the wheels 5 and with supporting surfaces 22 for the wheels ~ of the nose landing gear of the he1icopter 1. Furthermore, the longit~dinal running gear 20 is 30 provided with a grid 24 with hotes. ~elicopters 1 which are usually equipped ~ith gripping devices (so-called harpoons) can be arrested on the longitudinal runn;ng gear 20 by means ~f this grid 24, specifically at different positions.
9~ Fig. 9 shows the longitudinal running gear 20. this longitudinal ~unning gear is designed in such a ~anner that the supporttng surfaces 2~ of the ~heels 4 of the nose landing gear are longitudinally displaceable relative to the supporting surfaces ~3 of the wheels 5 of the main landing gear (Fig. 1~.
-As a result, the longitudinal running gear can be quickly and edsily adapted to the dif~erent wheelbases of the different t~pes of helicupters.
From a constructive point of view the solution provides that the supporting surfaces 23 for the ~heels 5 of the main landing gear are fixedly attached to a travers;ng cable extending in a longitudina~ guide, whereas the s~pporting surface 22 for ~he ~heels of the nose landing gear is clampable to any place of the traversing cable extending in the long;tud;nal guide Z1 if required, specific~l1y when a corresponding distance between the supporting su~faces 22 and the supporting surfaces 23 i 5 formed Instead of a traversing cable other pulling members may be used, e.g. chains o~ rods.
1~
figs 2 to 7 show individual steps during the maneuvering of the helicopter 1. f~rthermore, the broad arrows lndicate the ~ovement of the helicopter 1, whereas the narrow arrows clarify the adjustment of the trans~erse running gears lO.
~o The maneuvering of a helicopter 1 with the apparatus takes place in the following manner-Fig. 2 shows a hellcopter immediately after landing. ~or2~ secùring the helic~pter 1, it is anchored with its harpoon on a grid (not shown in the Figure) arranged on the p~atform 2. Due to the movement of the shlp and the influence of the wind, the heli~opter 1 according to the representat;on does normally not land exactly in the direction of the longitudinal running ~ears ~o Z1 (Fig. 1) extending in the direction of the longitudinal dXi5 of the ship~ In case of a great angular deviation, the helicopter 1 is rotated with its tail rotor about its an~hored hdrp~on until it is roughly aligned in the longitudinal direction. Afterwards, the harpoon o~ the hellcopter 1 is 3- released because the helicopter is now secured by the manipulators 12 or the gripping means 13 of the transverse running gears 10.
~'E E D~
As shown in fig. 3, the helicopter l ;s now rctated such that its longitudinal direction is parallel to the direction of the longitudinal guide 21 (Fig. 1). To this ~nd the gripping ~eans 13 of the adiusted uppçr transverse running gear 10 is extended, whereas the gripp;ng means 13 of the lower transverse runn;ng gear 10 is retracted. During the rotation of the helicopter 1, the wheels 4 of the nos~ landing gear are situated in a trans~erse position.
According to F;g. 4, the helicopter 1 is displaced in the longitudinal direc~ion such that the wheels 5 of the main landing gear o~ the helicopter 1 st~nd on the supporting surfaces 16 o~ the transverse running gears 10 (Fig. 1).
According to the invention, the wheels 5 of the main landing gear of the helicopter 1 are pushed onto the supporting surfaces 16 of the transverse running gears 10 for this purpose. The manipulators lZ serve for this purpose by correspondingly displacing, esp~cially retract;ng, the gripping ~eans 13 of the manipulators 12. The position assumed in this 20 manner is shown in Fig. 5. When the wheels 5 of the main landing gear of the helicopter 1 are pushed onto the supporting surfaces 16 of the trans~erse running gears 10, the wheels 4 of the nose landing gear are al;yned in the longitudinal direttion.
2~
After the wheels 4 of the nose landing gear have again been transversely aligned, the helicopter 1 is displaced in the transv~rse direction until its longitudinal axis is aligned with the longitudinal axis of one of the two longitudinal 30 guides ~1 (Fig. 1). This transverse displacement of the helicopter is carried out by traversing both transverse running gears 10 on the transverse guide 11. The helicopter 1 is secured on the transverse running gears 10, especially on the suppo~ting surfaces 16 thereof by the manipulators 12 and their 95 gripping means 13.
After the displace~ent of the helicopter 1 in the transverse direction, the helicopter 1 is pushed onto the previously cor~espondingly posit;oned longitudin~l running gear 20 after ~ 8 -the ~heels ~ of the n~se landing gear have been adjuste~ in the straight direction by means of the two manipulators 12 or gripping means 13 of the transverse running gears 1~. This position is shown in Fig. 6.
A~ter the helicopter 1 has been pushed onto the longitudinal runn;ng gear 20, the wheels 4 of the nose landiny gear stand on the supporting surface 22 of the longitudinal runn;ng gear 20, and the wheels 5 of the main landing gear stand on the supporting surfaces ~3 of the longitudinal running gear 20 (Fig. l) After~ards, the harpoon i5 anchored in the grid 24 to secure the helicopt~r I on the longitudinal runn;ng gear 20.
Finally, as shown in Fig. 7, the gripping means 13 ~re released from the helicopter 1 and the transverse running gears 10 are moved ;nto their starting position. furthermore, the tail p~rt of the helicopter 1 is folded to enable the accommodation of the helicopter in the hangar 3. Afterwards, the longitudinal running gear 20 moves the helicopter 1 which stands on the 2c supporting surfaces 22 and 23 of said longitudinal running ~ea~
20 a~ong said longitudinal guide Z1 into th~ hangar into which the corresponding longitud;nal guide 21 leads.
For starting t~e helicopte~, it is moved out of the hangar 3 zs back onto the platform 2 by the longitudinal running gear 20.
rl r~q
Claims (11)
1. Process for maneuvering especially a helicopter (1) which has landed on a platform (2) by means of running gears which are traversable on the platform (2), wherein the helicopter (1) is being gripped at suitable places by manipulators (12) and held there by the manipulators during the subsequent traverse on the running gears.
2, Apparatus for maneuvering especially a helicopter (1) which has landed on a platform (2) or the like, with transverse running gears (10) which are traversable along at least one transverse guide (11), and with manipulators (12) assigned to said transverse running gears (10), characterized in that the transverse running gears (10) have supporting surfaces (16) onto which the wheels (4, 5) of the helicopter (1) or the like can be moved by the manipulators (12).
3. The apparatus as claimed in Claim 2, wherein the manipulators (12) are fixedly attached to the running gears, especially transverse running gears (10).
4. The apparatus as claimed in Claim 2 or 3, wherein the manipulators (12) are provided with gripping means (13), and the gripping means (13) are movable especially on the manipulators (12).
5. The apparatus as claimed in claim 4, wherein the gripping means (13) arranged on each manipulator (12) is displaceable horizontally and/or in the longitudinal direction by at least one length which corresponds to at least twice the radius of the wheels (4, 5) of the landing gear of the helicopter (1) to be gripped, especially of the main landing gear,
6. The apparatus as claimed in Claim 2, wherein the gripping means (13) arranged on each manipulator (12) are provided with a coupling bushing (14) which is engageable with a coupling head arranged on the helicopter (1).
7. The apparatus as claimed in Claim 6, wherein a sensor (15) is arranged on each coupling bushing (14) which determines or signals the end of the coupling process.
8. The apparatus as claimed in Claim 2, wherein the transverse guide (11) is stationarily arranged on the platform (2).
9. The apparatus as claimed in Claim 2, wherein the transverse guide is arranged on the platform (2) so as to be longitudinally displaceable.
10. The apparatus as claimed in Claim 2, characterized by a longitudinal running gear (10) which is provided with supporting surfaces (23) for the wheels (5) of the main landing gear and with supporting surfaces (22) for the wheels (4) of the nose landing gear of the helicopter (1).
11. The apparatus as claimed in Claim 10, wherein the supporting surfaces (22) for the wheels (4) of the nose landing gear are longitudinally displaceable relative to the supporting surfaces (23) for the wheels of the main landing gear.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19518454A DE19518454C2 (en) | 1995-05-19 | 1995-05-19 | Device for maneuvering a landed helicopter |
| DE19518454.8 | 1995-05-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2176914A1 true CA2176914A1 (en) | 1996-11-20 |
Family
ID=7762376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002176914A Abandoned CA2176914A1 (en) | 1995-05-19 | 1996-05-17 | Process and apparatus for maneuvering especially a landed helicopter |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP0743248B1 (en) |
| CA (1) | CA2176914A1 (en) |
| DE (2) | DE19518454C2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106608359A (en) * | 2016-08-31 | 2017-05-03 | 马宏 | Application of electric land vehicle |
| CN106608363A (en) * | 2016-08-31 | 2017-05-03 | 马宏 | Application of electrical source traction equipment |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19644857A1 (en) * | 1996-10-29 | 1998-04-30 | Mbb Foerder & Hebesysteme | Method and device for coupling in particular a landed helicopter to a moving device |
| CN102351043B (en) * | 2011-07-27 | 2014-02-19 | 南京航空航天大学 | Sliding and controlled motion landing area |
| CN104828257B (en) * | 2014-02-09 | 2019-03-29 | 王意 | A kind of placement scheme of aircraft carrier-based aircraft hangar |
| CN106986043B (en) * | 2014-11-19 | 2020-03-06 | 深圳市大疆创新科技有限公司 | Positioning mechanism and UAV base station adopting same |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| LU69808A1 (en) * | 1974-04-08 | 1976-03-17 | ||
| GB2059889B (en) * | 1979-07-25 | 1983-06-02 | Westland Aircraft Ltd | Apparatus for moving a helicopter along a deck |
| AU550608B2 (en) * | 1981-06-04 | 1986-03-27 | British Aerospace Public Limited Company | Retrieving and launching vtol planes by crane |
| US5123615A (en) * | 1988-02-03 | 1992-06-23 | Indal Technologies Inc. | System and components useful in landing airborne craft |
| IT1248041B (en) * | 1991-06-12 | 1995-01-05 | Riva Calzoni Spa | TAKING AND HANDLING EQUIPMENT OF HELICOPTERS PARTICULARLY FOR SHIPS, PLATFORMS AND SIMILAR. |
| GB9205120D0 (en) * | 1992-03-10 | 1992-04-22 | Mactaggart Scott | Improvements in or relating to apparatus for aligning and traversing an aircraft on the deck of a ship or the like |
-
1995
- 1995-05-19 DE DE19518454A patent/DE19518454C2/en not_active Expired - Fee Related
-
1996
- 1996-05-14 DE DE59609673T patent/DE59609673D1/en not_active Expired - Fee Related
- 1996-05-14 EP EP96107632A patent/EP0743248B1/en not_active Expired - Lifetime
- 1996-05-17 CA CA002176914A patent/CA2176914A1/en not_active Abandoned
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106608359A (en) * | 2016-08-31 | 2017-05-03 | 马宏 | Application of electric land vehicle |
| CN106608363A (en) * | 2016-08-31 | 2017-05-03 | 马宏 | Application of electrical source traction equipment |
| CN106608363B (en) * | 2016-08-31 | 2018-10-19 | 马宏 | The application of electrical source pulling equipment |
| CN106608359B (en) * | 2016-08-31 | 2019-01-04 | 马宏 | The application of electric floor vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| DE19518454A1 (en) | 1996-11-21 |
| EP0743248A3 (en) | 1998-01-07 |
| EP0743248A2 (en) | 1996-11-20 |
| DE19518454C2 (en) | 1998-01-29 |
| EP0743248B1 (en) | 2002-09-18 |
| DE59609673D1 (en) | 2002-10-24 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FZDE | Dead |