TRACTION VEHICLE FOR AIRCRAFT AND ENGAGEMENT AND HOISTING DEVICE THEREFOR

Abstract: A traction vehicle (2) for moving an aircraft (1) comprises a wheel-mounted chassis (7) and an engagement and hoisting device (12) that can be raised and lowered and comprises a U-shaped stand (17); journalling members (15), flexibly connecting the stand to the chassis; actuators (13), arranged between the stand and the chassis to raise and lower the engagement and hoisting device relative to the chassis; and a nose-wheel holder (18), mounted on the stand to carry and hold the nose wheel (4) of the aircraft. In accordance with the invention, the nose-wheel holder and stand are designed as two units and have co-operating journalling members (70, 71), arranged in a circular arc and defining a vertical axis of rotation for said units, the nose-wheel holder being U-shaped to form a space for receiving the nose wheel. The invention also relates to such an engagement and hoisting device.

Description: Traction vehicle for aircraft and engagement and hoisting device therefor The present invention relates to a traction vehicle for ground movement of an aircraft, having at least one nose wheel, which traction vehicle comprises - a wheel-mounted chassis and - an engagement and hoisting device that can be raised and lowered relative to the chassis and is of a type that is brought into freely carrying engagement with the nose wheel and which comprises - a stand, being substantially U-shaped with its opening turned towards the aircraft, - journalling members, flexibly connecting the stand to the chassis, - actuators, arranged between the stand and the chassis to raise and lower the engagement and hoisting device relative t.o the chassis, and - a nose-wheel holder, having - an inner space that can be opened in the direction of the nose wheel for receiving the same, - carrying members for carrying the nose wheel in said space, and - forward and rear wheel supports for holding the nose wheel in the longitudinal direction of the traction vehicle. The invention also relates to such an engagement and hoisting device. Once the maximum steering angle of an aircraft has been attained, whilst moving the aircraft on the ground with the aid of a traction vehicle coupled to the nose wheel of the aircraft, when the direction of travel of the traction vehicle is changed, torque is transferred to the nose-wheel stand via the nose wheels and its upwardly-directed steering or rotary axle. This torque must not exceed prescribed values laid down by the various aircraft manufacturers in question. In the following, this maximum permitted torque is referred to as the maximum torque or maximum value . A traction vehicle in accordance with the preamble to claim 1 is known through SE-500 744. The engagement and hoisting device supported by the chassis of the traction vehicle is arranged to be brought into a starting position close to, but not touching, the nose wheels of the aircraft, both in front of and behind the contact point between the nose wheels and the ground, when the traction vehicle is moved relative to the nose wheels, and to be raised from said starting position in order, when in free surface contact with the nose-wheel tread on both sides of said contact point with the ground, to be brought into releasable engagement with the nose wheels so that the same are lifted from the ground when the engagement and hoisting device is raised. The engagement and hoisting device forms a rigid connection between the nose wheels and the chassis. Thus, to enable a change of angle between the traction vehicle and the aircraft, the steering hydraulics of the aircraft must be disconnected and the rotary movement of the nose wheels limited by mechanical terminal stops on the aircraft. At these terminal stops, the aircraft has attained its maximum steering angle and torque will be transmitted to the nose-wheel unit, via the rotary axle of the nose wheels, wherein, as mentioned above, the torque value must not exceed a maximum value determined by the manufacturers of the aircraft . Exceeding the maximum torque without forewarning presents a very great risk of the nose-wheel unit being damaged. 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The platform can be provided with a rotary plate on which the nose wheel rests. However, the WO specification does not show any device for retaining the nose wheel on the rotary plate and platform. The platform is arranged such that it can perform a swinging or pendulum movement relative to the chassis in the longitudinal direction of the tractor from a resting position. When the aircraft is moved on the ground, the deviation of the swinging or pendulum movement from the resting position is a measure of the load on the nose wheel in the horizontal and vertical direction. By measuring the swinging or pendulum movement with a linear-movement or angle transducer, the load can be kept within prescribed values by limiting the acceleration or retardation of the tractor when too great a deviation from the resting position is measured. The known traction vehicles in accordance with US-4,576,245 and the WO specification 98/25822 are of a type completely different from the one to which the invention refers. Unlike the traction vehicle in accordance with the invention, they cannot be used for aircraft of varying sizes and they are not intended to be docked to the aircraft. They lack, and cannot be provided with, an engagement and hoisting device that can be raised and lowered relative to a chassis and has a U-shaped stand to enable said docking to a stationary aircraft and provide freely supporting engagement with the nose wheel with the aid of a special nose-wheel holder, the engagement and hoisting device being raised to lift the nose wheel from the ground. The object of the present invention is to provide a traction vehicle with an improved engagement and hoisting device that enables security demands from aviation • authorities or operative or functional demands from users to be met so that an improved control of and security during the ground movement of the aircraft is obtained, as compared with known traction vehicles. The traction vehicle, as well as the engagement and hoisting device, is characterised in - that the nose-wheel holder and the stand are shaped as two separate units and comprise co-operating journalling members, arranged in a circular arc and defining a vertical axis of rotation for said units and - that the nose-wheel holder is substantially U-shaped with its opening turned towards the aircraft as viewed in a starting position, when the nose-wheel holder is situated to be moved into a position to receive the nose wheel . The invention will be further described in the following with reference to the drawings . Figure 1 shows a traction vehicle with an engagement and hoisting device in accordance with the invention carrying an aircraft by its nose wheel. Figure 2 shows the engagement and hoisting device in accordance with Figure 1 with its nose-wheel holder rotated in one direction relative to its stand. Figure 3 shows the engagement and hoisting device in accordance with Figure 2, but with the nose-wheel holder rotated in the other direction relative to its stand. Figure 4 shows the journalling of the nose-wheel holder to the stand. Figure 5 shows an engagement and hoisting device similar to the one in Figure 2, but additionally provided with a break-device between the nose-wheel holder and the stand, the engagement and hoisting device being open and ready to receive the nose wheels. Figure 6 shows the engagement and hoisting device in accordance with Figure 5 engaged with the nose wheels. Figure 7 shows an engagement and hoisting device similar to the one in Figure 2, but additionally provided with a braking mechanism between the nose-wheel holder and the stand. Figure 8 shows the braking mechanism in Figure 7. Figure 9 shows an engagement and hoisting device similar to the one in Figure 2, but additionally provided with a torque indicator between the nose-wheel holder and the stand. Figure 10 shows the torque indicator in Figure 9 Figure 1 shows an aircraft 1 and a traction vehicle 2, provided with wheels, for moving the aircraft 1 relatively short distances on the ground. The aircraft 1 has a nose-wheel unit 3, comprising two nose wheels 4 and an upwardly-directed steering or rotary axle 5 that carries the nose wheels 4 and is rotatably journalled to the nose-wheel unit 3 and lockable in the same with a hydraulic locking mechanism (not shown) to lock the single wheel axle 6 of the nose wheels 4 in a position at right angles to the longitudinal direction of the aircraft 1. The traction vehicle 2 comprises a chassis 7, carrying, at one of its end portions, a driver's cabin 8 and including two longitudinal, horizontal beams 9, 10, spaced a pre-determined distance from each other to define between them a space 11, which is open at the end that faces away from the driver's cabin 8 to be positioned in accordance with the aircraft 1, when the ω ω CO to h-> μ> LΠ o LΠ o LΠ o LΠ CQ H a SD Φ ; CQ SD l_l. 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The journalling member 70 of the stand 17 comprises a plurality of rolling elements, equidistantly mounted on the topside of said bottom plates 22 with the aid of angle profiles 25 along a circular arc of a pre-determined radius. As further illustrated in Figure 4, each angle profile 25 carries a first roller 26, journalled on a vertical shaft journal 27 on the horizontal part of the angle profile 25, and a second roller 28, journalled on a horizontal shaft 29 on the vertical part of the angle profile 25. Adjacent to the outside 37 of the nose-wheel holder 18, that is radially inside the same, the outer edge portion 36 of the nose-wheel holder 18 is provided with a horizontal carrying and rolling surface 38 for co-operation with the second rollers 28 of the rolling elements and with two vertical, inner and outer, concentric, supporting and rolling surfaces 39, 40 for co-operating with the first rollers 26 of the rolling elements. Thus, said carrying and rolling surface 38 and supporting and rolling surfaces 39, 40 together form the journalling members 71 of the nose-wheel holder 18. The nose-wheel holder 18 is thus carried by said second rollers 28 via its horizontal carrying and rolling surface 38, which extends in a continuous circular arc along the entire outside 37, the carrying and rolling surface 38 being located such, relative to the horizontal underside 41 of the nose-wheel holder 18, that a small clearance gap 42 is created between said underside 41 and the horizontal parts of the angle profiles 25, thereby preventing friction between them. The two concentric supporting and rolling surfaces 39, 40 and the second rollers 28 are arranged at a radial distance from each other that is equal to or only somewhat greater than the diameter of the second rollers 28. The two supporting and rolling surfaces 39, 40 and the second rollers 28 LO ω CO CO μ> H Ln o LΠ o LΠ O LΠ TI CQ TJ φ. Ω S S tr rr H CQ 0 ϋ SD rt 3 rr rr 3 3 rt Q Ω 3 tr rr 3 Ω trj ii H, Hi H Ω 0 0 £ VD SD 0 tr ti tr 00 a ri 0 tr 0 O J a tr 0 O tr 0 0 Φ tr tr SD a Ω Ω 0 ω Ω Ω ri TI SD ri t Φ μ- φ T 3 Φ CD TI Φ CD 0 a a rr Φ Φ Hi Hj rr rt I SD rr TJ rr ϋ φ Φ 3 μ- TJ ω 3 0 φ CQ Φ Φ φ rt ■ a a * S Φ Hi rr SD SD μ- Ω rr μ- 0 Φ ■ : O LQ ri rr 0 3 •> ϋ μ- CQ 1 tr 3 ^ Φ rr Φ Ω "< tr rr μ- rt CD TJ Φ 0 H o μ- <! CQ $. ϋ μ- SD Φ r • > P. CQ s. Φ Ω φ Φ SD μ- φ μ- 3 μ- Φ ϋ 3 rr Φ- Ω 3 φ rr TJ 0 rt LQ ii ii SD tr φ 0 tr rr Pi 3 H CO 3 Hi 0 LQ 0 Hi Hi 00 SD LQ ϋ φ. tr μ- tr Si 3 Φ Hi 0 Φ Si μ- ri a LQ 3 3 μ- SD μ- Ul Φ> rr - Φ D TI Φ- rt μ- φ rr Hi Φ μ- CQ Ω rr rr ^ Tl CQ SD X rr 3 o Φ> SD Φ TJ rr 0 Φ. ■ <; tr 3 tr SD 3 0 3 tr tr μ- TJ Tl rr a H-" Φ φ •« • 3 Si rr 0 •> "< o LQ CQ SD μ- rr φ φ φ 3 0 tr Hi Si ϋ SD tr tr 3 φ μ- CQ ri CQ rt ri tr tr 3 rr Tl H LQ ii SD Φ Hi TJ : > Φ ■ s H3 SD rt φ Φ H CQ tr μ- - Φ- Ω φ 0 CQ tr μ- Φ <! rt rr SD 0 μ- μ- <! tr tr TJ Φ Φ ii φ Ω tsi μ- ϋ μ- SD φ 0 φ TJ Φ 3 Ω CQ 3 rr φ μ- Φ ii TJ 3 * 0 Ω TJ μ- TI 0 0 SD CQ SD <! Pi O rr Ω 3 ri φ. 0 Φ μ- tr Ω Φ ri φ. 0 i ^ μ- 0 μ- 3 ri 3 Hi SD φ 3 Φ rr SD Φ> > CQ CQ rr rr tr Ω Hi Φ 00 en CQ CD < 3 rr Pi Ω rr ii ii μ- rr μ- rr - CO φ μ- tr φ SD Φ 1 φ a - μ- 0 LQ SD a ii • μ- 0 rr to Ω Ω Φ ^ 1 CO Ω Φ SD μ- tr ii ri Si SD 1 TJ 3 rt rt a Ω a O μ> Hi CQ μ> SD 3 <£> 3 Ω rr SD ri SD Φ 3 3 TJ rr ϋ SD tr 0. μ- SD i H a 00 •< tr φ. 0 CO tr •- Hi tr i CQ * ! tr rr ϋ tr 0 0 Φ tr Φ a Φ Hi 3 Φ tr CQ rr TJ Φ CO Ω φ Φ SD μ- M Φ Φ ii H M ri ϋ 0 φ Ω tr 0 $ • SD φ Φ Φ> α 0 rt SD 3 •<; ii SD Φ rr rr CQ •<; a Hi LQ ϋ tr ■ <; ϋ SD Φ CQ μ- Pi φ rt O Ω μ- rt tr LQ 3 3 tr a SD Φ 3 Φ Ω μ- 3 μ- rr μ- LQ Φ •fl 3 SD tr Φ ϋ μ- Φ- Φ Φ- 3 Pi Ω SD SD 3 3 rr tr Q tr ϋ μ- tr i CQ Φ 0 Tl φ 3 o tr Φ- σi o Φ Φ TJ 3 Si ϋ φ o μ- TJ c Φ LQ 0 Φ φ Hj Φ 3 <! Φ a 0 φ a ii O SD SD ϋ a ■ s CQ O rr SD SD a μ- 1 Hi Λ Si Si 3 SD φ & rr rr 3 tr a CQ SD H Ω Si TJ > CQ H- Φ 3 tr SD μ- 1 Ω H{ Si μ- a μ- Q LQ 3 rr Φ ϋ O Si φ rr μ- 3 rr a Φ rt μ- μ- rr φ Ω SD TJ φ φ 3 Φ Hi 0 φ SD φ Si ri Φ CQ μ- Φ Pi i μ- Φ 3 o tr " > Ω Φ CQ ri ri Hi Φ a Φ ri $ μ- ri tr 3 (i Φ O <! μ- fi LQ 3 tr SD SD Si ri Φ LΠ rr Ω rr TJ Si Φ. μ- CQ tr φ o LQ μ- 3 φ 3 CQ tr Φ 3 μ- co 1 μ> rr rr tr o co rr rr 0 μ> SD Hi o O CQ Pi rt Tl Φ Φ Si ri co μ- Si O tr * ; μ- SD * ; tr SD HJ 00 Ii Hi a Hi Φ- CQ 0 Tl ra tr φ 3 Φ SD Φ Ω rr rr tr 3 μ- rr μ- 1 cπ φ SD ri rr . Φ 0 LQ rt 3 Ω 3 μ- CQ SD rr Ω N Ω SD tr Φ rr rr 0 - μ] Ω rr rr Φ Hi SD CO Φ Si Ω <! rr rr 0 CQ tr Φ 0 0 LQ Φ X tr tr Ω tr rr tr Φ CD Hi m SD rr φ. TJ ri 3 φ tr μ- tr 3 0 φ 3 3 SD μ- Φ φ SD s; φ μ- φ Φ μ- tr ϋ TJ μ- 3 SD Tl ri Φ Hj φ TS SD SD rr TI μ- £ tr rr tr 0 φ- a rr Φ l_l. o <! SD SD μ- a Hi rr Hj Φ- μ- μ- tr SD ri 3 tr 3 CQ Φ μ- Ω 3 ϋ co rt ~ ri a ■ c φ 3 rt 3 μ- μ- rt φ 3 LΠ 3 tr 3 o μ- CQ Φ •<! 0 rr ϋ Ω SD CQ SD Φ Φ CQ φ Si Φ φ μ- CQ Ω s- CD 0 LQ 0 3 <! CQ rt Φ CQ SD tr ri "> Si tr P. CD tr rr ii rr ϋ 3 Φ SD Ω TJ CQ 0 ii Φ Φ - > Φ Ω φ a μ- ii μ- SD Φ Φ Ω SD φ. ^ a CQ μ- 1 φ φ Hi CQ μ- ri tr CQ rr 0 1 ϋ 3 tr • ; SD μ- CQ tr Ω i Ω ri CO Si φ CQ Ω 1 a N rr Φ tr CQ 3 •> SD μ- CQ •<: a * ; rr Φ μ- ii SD SD a rr rt ri 0 3 tr Φ SD Φ £ 3 tr " CQ 3 0 S ii rr SD tr φ CQ 3 X Tl μ- tr tr Hi 3 tr Φ 3 TJ φ Φ μ_ Φ LQ CQ r-h P. Φ tr a μ- φ 3 X rt μ- Tl < Φ φ SD rr Φ 3 TJ Ω Φ tr <; SD tr Ω μ- Φ ϋ 3 0 rt SD tr μ- CQ o φ Φ Ω SD Φ Ω CQ o 0 o rr Φ Φ TJ o ϋ o Hi a Si <! Φ a 0 3 H μ- Φ SD a a CD Hj Φ ≤ μ- 3 Hi o SD φ SD 3 Ω 3 Ω rr 0 3 ii TJ rt φ rr Pi tr SD 3 Hi Ω φ CQ ϋ ri tr Pi Φ μ- Φ Hi μ- Hi 3" 3 SD Φ ii TJ Φ - 0 tr $. rr Hi ^ K Φ SD CQ CQ N Hi 3 0 φ 3 i • ; o H Φ> Φ μ- Φ μ- φ < φ Tl ^ SD 0 LQ μ- ri Si LQ μ- fi Φ. < P. Φ rr 3 ϋ Φ a rr . — . tr a rr Si Φ 3 rr μ- φ tr tr φ rt Φ 3 0 rr SD CQ φ μ- LQ rr SD ii SD 3 Si 0 SD 3 H Q 0 CQ rr rr Φ ϋ co co to CO μ> μ> σi o LΠ o LΠ o cπ SD Hi Hi SD <! SD rr 3 Ω Hi Ω φ TJ tr LQ φ Ω tr Tl φ φ 0 μ- Hj Φ Φ Hj Ω Ω rr HJ ^ Si H- 1 (D Hj Ω CQ SD φ Ω SD Hi Hi 3 tr Ω o Ω Ω to rr rr 00 rr φ N μ- tr $D μ- Φ Ω φ Ω rr 3 CQ Hi 3 Hi μ- μ- Ω rr Ω rr Ω <! Hi rr 3 tr tr Φ SD SD a tr SD 3 tr Ω φ >τl 3 μ- rr μ- LQ Φ Ω μ- Hi - ! LQ φ CQ H-" 0 Ω a P. CQ Φ 3 CQ Hi a φ tr rr to <J μ- CQ Q SD tr φ 3 TJ Ω Φ CQ tr LQ φ μ 1 ? Ω μ- a I i Ω φ ϋ CO μ- rt " Φ H Hi tr Φ Φ ϋ 3 Φ SD 3 rt Ω rr CO φ Ω tr rr rr a a φ tr μ- μ- ri rr Φ Ω rr Φ . rr 3 3 tr Ω Φ ϋ SD μ] Φ CQ 3 Ω Ω rr tr Φ t Hi Φ μ- μ- CQ 1 Ω CQ <! Q rr : > Si rt Φ SD tr μ- tr 3 3 3 Φ 3 Φ Ω rr φ Si Φ Φ rr Ω SD 3 rt 3 μ> rr Hi Si rr CQ tr SD μ- tr 0 μ- Ω 3 Φ rr < 3 rr μ- tr μ- i μ- 3 3 SD SD φ Ω μ- 0 rr Hj 3 CQ CQ rr tr Φ rr tr μ- tr φ CQ SD Φ a wheels 4 can vary without any significant torque being transferred to the nose wheels 4. In this embodiment, the nose wheels 4 can be locked, but they can also be disengaged. It should thus be understood that, when the nose wheels 4 are disengaged, the turning radius of the traction vehicle 2 relative to the aircraft 1 can be further increased by making use of the full rotation angle of the nose-wheel holder 18 as well as the full rotation angle of the disengaged nose wheels 4. Although the shown journalling members 70, 71 are currently preferred, they can obviously be designed in many other ways, for instance in the shape of a ball-bearing segment or girdle in one of the units and co-operating rolling surfaces for the balls in the other unit . Figures 5 and 6 show an engagement and hoisting device 12, similar to the one in Figures 1-3, but additionally provided with a rotation-inhibiting device in the shape of a break-device 60, arranged on the stand 17 and the nose-wheel holder 18 in proximity to its central stop 57, seen in the starting position of the nose-wheel holder 18, when the axle 6 of the nose wheels 4 is at right angles to the longitudinal direction of the traction vehicle 2. The break-device 60 comprises a breakpin 61 that fixes the nose-wheel holder 18 against rotation in said starting position. The breakpin 61 is constructed such that it breaks when the nose-wheel holder 18 is subjected to a certain, permitted torque relative to the stand 17. In this embodiment, the nose wheels 4 of the aircraft 1 are disengaged, whereby the rotary axle 5 of the nose-wheel unit 3 is not permitted to transmit a prescribed, maximum torque to a fixed construction element of the nose-wheel unit. Thus, said permitted torque has a value that is less than the value of said prescribed, maximum torque. LO CO to t μ 1 cπ o cπ o o cπ H- SD μ- m 0 SD rr μ- Ω S SD 00 Ω CQ 3 μ- μ- H H τι oo H tr 3 3 tr TJ H- 1 Ω Q tr tr rt o tr rr φ 3 a Ω HJ o 3 Φ Si < Φ φ SD Hj SD Ω rr SD SD Ω H- 1 Si rt φ Φ H Hi £1 3 3 SD TJ 3 3 tr a μ- rr SD 1 TJ rt Hj rr 3 Φ SD 3 a Ω LQ rr μ- Φ LQ Si SD CQ Ω tr rt CQ Φ tr μ- tr rr 3 rr Φ rr μ- tr 3 ri φ 3 rt £U φ Φ Φ Hj φ CQ Φ μ- LQ μ- SD 3 Φ φ CQ μ> μ- Hi rr rt ? Ω SD Ω 3 μ- ϋ LQ 3 P. Ω -j CQ SD Ω φ Ω φ SD 3 LQ 3 Si Q Ω Φ μ- 3 rr Hi g- Φ 3 0 μ- Φ 3 rr tr 3 3 SD φ SD 3 " Hi Hj Φ 3 SD SD Φ tr SD rr rt 3 P. 0 Ω rr Ω Ω 3 Φ a rt φ CQ tr » rr Si > ] i a Si tr ii SD 3 rr rt SD Φ tr tr - μ- Φ Ω μ- a SD tr rt Ω SD 3 Si rr Hi φ rr Tl ^ 3 Hi 3 3 Hi μ< 3 μ- Si μ- tr μ- Ω tr μ- rr φ μ- φ SD rr Φ SD SD 3 Hi Φ 3 Hi rr φ Q >τ| tr 3 Q 3 3 Q 3 rr Φ Ω Φ Pi Ω rr μ- φ rr φ rr rr ϋ μ- Pi Ω Ω μ- μ- Hi 3 Ω LQ φ CQ Φ Ω rr Ω Ω rr Tl Ω 3 Λ O 3 a Ω μ- X CQ μ- Hi tr tr SD CQ μ- TJ SD CQ a CD Hi Ω 3 Ω 3 Hi tr φ Ω H-" SD φ Ω Ω rr rr Φ φ Ω φ 3 Φ Ω Ω Φ μ- H- 1 3 Hj Ω SD 1 •<; CQ SD Φ Hi SD Hj SD CQ > ; CQ rr rr Hi a μ- s μ- 1 μ> rr Ω Si Ω 3 3 rt μ- Ω Ω a Ω 3 tr μ- o Hi Ω φ CQ Ω Φ LQ μ- CQ LQ Hi a en φ Φ 3 • ^ a Ω Pi SD Ω rr SD 3 a 3 μ> μ- ι - rr Φ i Ω Hi μ- Hj tr CQ φ LQ CQ SD o rr rr tr φ μ- rr Si Pi Si SD a TS μ- 1 o 3" ^ Φ Ω Φ Hj CQ μ- SD rr SD rr Hj tr Si Φ Φ 3 Hi tr Ω 3 tr 3 3 Φ Φ Φ 3 μ- TJ 0 μ- 3 0 σi a a Ω Φ SD Ω μ- P. rr < Si CQ φ rr Hi rr Ω 00 ω Φ X Φ CQ 3 μ- CD ϋ Hj Q tr CQ Si φ Ω 3 μ- 3 Φ Ω Φ SD Hj Φ Φ Φ Hi Pi Hi $ Ω 3 5 > rr μ- Φ Φ rr 3 Ω Ω Φ SD I ri b-~ μ- CQ a μ- tr rr 3 tr μ- Φ rr ϋ 3 Φ μ- 3 Φ 3 rt Φ 3" μ- φ rr 3 μ- a CQ SD tr μ> X 3 tr tr 1 tr Ω rr 3 rt rr Ω Ω μ- X Φ 00 μ- CQ μ- 3 rr ϋ a tr SD φ 3 μ- LQ μ- Φ tr rt Ω •rl tr Ω <τi SD rr Φ SD μ- ϋ Ω 3 3 3 SD Φ tr μ- Φ Hj μ- a Ω H Hi <1 LQ SD a 3 • : SD LQ Φ Λ LQ Q Pi rr Ω Ω rr Φ H- 1 3 tr Si Pi μ- a a a Φ μ- Hj Ω Hi tr rr tr rr Ω Ω CQ Hj Φ Hi Hj Hi SD Hj SD SD tr μ- tr rt rr H- 1 Hj Ω Ω φ tr . Φ φ Ω i Hi rr φ Ω Φ O Ω ϋ Φ 3 Hi Hi 0 Ω Ω rt SD rr H- 1 Hi φ SD 3 a vo H 1 Hi rt μ- 3 1 Φ 3 φ rr rt Λ Hi Ω Φ SD H - P. Hh - o Ω 3 3 SD . o tr a rr Ω rr Φ rr Ω a Φ o CQ X Hi φ μ> CQ rr tr tr SD Hj rr SD tr Ω <! SD μ- H Λ 00 CQ Hi Φ tr Φ a <l S Φ LQ 3 Hi a Si μ- • rr SD ii rr μ> μ- tr rt φ μ- 3 Φ a Φ Hi CQ Ω rr ? Ω 00 CQ Hj Si SD tr rr Φ CD 3 rt μ- ■ ≥l tr μ- Hi SD Hi Ω μ- tr 3 tr tr < tr Φ 3 Λ ^ ? μ- rr Ω rt SD μ- ^ φ Φ LQ a μ- μ- < . rr 3 Q Hj 3 Φ H- 1 3 φ φ tr - LQ Hi Φ or some other person assembling equipment of the type described in SE-501 788, for instance, incorrectly is eliminated. The traction vehicle in accordance with the invention enables simple and quick docking and coupling with the nose wheel or nose wheels without the aircraft being disturbed from its parked position and without using a screw joint or the like. The nose wheel has to be lifted only a short distance, for instance about 50-100 mm, to clear any unevenness in the transport path. The height of the construction is sufficiently modest to allow it to clear the flaps hanging down on the sides of the nose-wheel stand. The engagement and hoisting device in accordance with the invention with its said rotation girdle, formed by said journalling members 70, 71, is unique, in that it allows rotation and generation of torque, respectively, during the application of tractive forces, as well as braking forces, and in that the engagement elements acting against the nose wheel do not impede such a function in any way.

Claims: C L A I M S 1. A traction vehicle (2) for ground movement of an aircraft (1) , having at least one nose wheel (4) , which traction vehicle (2) comprises - a wheel-mounted chassis (7) and - an engagement and hoisting device (12) that can be raised and lowered relative to the chassis (7) and is of a type that is brought into freely carrying engagement with the nose wheel (4) and which comprises - a stand (17) , being substantially U-shaped with its opening turned towards the aircraft (1) , - journalling members (15) , flexibly connecting the stand (17) to the chassis (7) , - actuators (13) , arranged between the stand (17) and the chassis (7) to raise and lower the engagement and hoisting device (12) relative to the chassis (7) , and - a nose-wheel holder (18) , having - an inner space (35) that can be opened in the direction of the nose wheel (4) for receiving the same, - carrying members (43, 48) for carrying the nose wheel (4) in said space (35) , and - forward and rear wheel supports (44, 49) for holding the nose wheel (4) in the longitudinal direction of the traction vehicle, characterized in - that the nose-wheel holder (18) and the stand (17) are shaped as two separate units and comprise co-operating journalling members (70, 71) , arranged in a circular arc and defining a vertical axis of rotation for said units (17, 18) , and - that the nose-wheel holder (18) is substantially U-shaped with its opening turned towards the aircraft (1) as viewed in a starting position, when the nose-wheel holder (18) is situated to be moved into a position to receive the nose wheel (4) . 2. A traction vehicle as claimed in claim 1, characterized in that the journalling members (70) of the stand (17) comprise a plurality of rolling elements that are mounted along a circular arc on a bottom plate (22) of the stand (17) by means of angle profiles (25) , which rolling elements comprise first and second rollers (26; 28), rotatably journalled to the horizontal and vertical parts of each angle profile (25) , respectively, to co-operate with the journalling members (71) of the nose-wheel holder in the form of vertical, opposing, concentric supporting and rolling surfaces (39, 40) and a horizontal carrying and rolling surface (38) , which supporting and rolling surfaces (39, 40) together with said first rollers (26) define the vertical axis of rotation of the nose-wheel holder (18) . 3. A traction vehicle as claimed in claim 2, characterized in that the nose-wheel holder (18) has outer edge portions (36) that are arc-shaped so that it acquires a vertical outside (37) with a pre-determined radius that is somewhat greater than the radius of an arc-shaped inside (24) of the bottom plate (22) of the stand (17) . 4. A traction vehicle as claimed in any one of claims 1-3, characterized in that the stand (17) and the nose-wheel holder (18) are provided with co-operating stops (55, 56, 57) that are arranged to limit the rotation of the nose-wheel holder (18) in both directions from a central starting position. 5. A traction vehicle as claimed in claim 4, characterized in that the stand (17) is provided with two terminal position transducers (58, 59) arranged in front of the two stops (55, 56) on the stand (17) for sensing the stop (57) of the nose-wheel holder (18) to indicate the angle of rotation of the nose-wheel holder (18) relative to the stand (17) and the traction vehicle (2) . 6. A traction vehicle as claimed in any one of claims 1-5, characterized in that the nose-wheel holder (18) is arranged to be able to rotate freely when the direction of travel of the traction vehicle (2) changes relative to the aircraft (1) . 7. A traction vehicle as claimed in any one of claims 1-5, characterized in that the engagement and hoisting device (12) comprises a rotation-inhibiting device acting between the stand (17) and the nose-wheel holder (18) for generating a moment of torque between the stand (17) and the nose-wheel holder (18) when the direction of travel of the traction vehicle (2) changes relative to the aircraft (1) . 8. A traction vehicle as claimed in claim 7, characterized in that the rotation-inhibiting device consists of a break-device (60) , arranged on the stand (17) and the nose-wheel holder (18) to secure the nose-wheel holder (18) against free rotation in a starting position, the break-device (60) being arranged to break when the nose-wheel holder (18) is subjected to a pre-determined, permitted torque relative to the stand (17) . 9. A traction vehicle as claimed in claim 7, characterized in that the rotation-inhibiting device consists of a braking mechanism (62) , arranged to act with a pre-determined braking power between the stand (17) and the nose-wheel holder (18) , which braking power is arranged to be overcome when a pre-determined, permitted torque acts on the nose-wheel holder (18) . 10. A traction vehicle as claimed in claim 7, characterized in that the rotation-inhibiting device consists of a torque indicator (67) , attached to the stand (17) and the nose-wheel holder (18) and arranged to sense and react to changes in the torque in the nose-wheel holder (18) . 11. A device for a traction vehicle (2) for ground movement of an aircraft (1) , having at least one nose wheel (4) , which traction vehicle has a wheel-mounted chassis (7) , which device is designed to be brought into freely carrying engagement with and raise the nose wheel (4) relative to the chassis and which comprises - a stand (17) , being substantially U-shaped with its opening turned towards the aircraft (1) , - journalling members (15) , flexibly connecting the stand (17) to the chassis (7) , - actuators (13) , arranged between the stand (17) and the chassis (7) to raise and lower the engagement and hoisting device (12) relative to the chassis (7) , and - a nose-wheel holder (18) , having - an inner space (35) that can be opened in the direction of the nose wheel (4) for receiving the same, - carrying members (43, 48) for carrying the nose wheel (4) in said space (35) , and - forward and rear wheel supports (44, 49) for holding the nose wheel (4) in the .longitudinal direction of the traction vehicle, characterized in - that the nose-wheel holder (18) and the stand (17) are shaped as two separate units and comprise co-operating journalling members (70, 71) , arranged in a circular arc and defining a vertical axis of rotation for said units (17, 18) , and - that the nose-wheel holder (18) is substantially U-shaped with its opening turned towards the aircraft (1) as viewed in a starting position, when the nose-wheel holder (18) is situated to be moved into a position to receive the nose wheel (4) . 12. A device as claimed in claim 11, characterized in that the journalling members (70) of the stand (17) comprise a plurality of rolling elements that are mounted along a circular arc on a bottom plate (22) of the stand (17) by means of angle profiles (25) , which rolling elements comprise first and second rollers (26; 28), rotatably journalled to the horizontal and vertical parts of each angle profile (25) , respectively, to co-operate with the journalling members (71) of the nose-wheel holder in the form of vertical, opposing, concentric supporting and rolling surfaces (39, 40) and a horizontal carrying and rolling surface (38) , which supporting and rolling surfaces (39, 40) together with said first rollers (26) define the vertical axis of rotation of the nose-wheel holder (18) . 13. A device as claimed in claim 12, characterized in that the nose-wheel holder (18) has outer edge portions (36) that are arc-shaped so that it acquires a vertical outside (37) with a pre-determined radius that is somewhat greater than the radius of an arc-shaped inside (24) of the bottom plate (22) of the stand (17) . 14. A device as claimed in any one of claims 11-13, characterized in that the stand (17) and the nose-wheel holder (18) are provided with co-operating stops (55, 56, 57) that are arranged to limit the rotation of the nose-wheel holder (18) in both directions from a central starting position. 15. A device as claimed in claim 14, characterized in that the stand (17) is provided with two terminal position transducers (58, 59) arranged in front of the two stops (55, 56) on the stand (17) to sense the stop (57) of the nose-wheel holder (18) to indicate the angle of rotation of the nose-wheel holder (18) relative to the stand (17) and the traction vehicle (2) . 16. A device as claimed in any one of claims 12-15, characterized in that the nose-wheel holder (18) is arranged to be able to rotate freely when the direction of travel of the traction vehicle (2) changes relative to the aircraft (1) . 17. A device as claimed in any one of claims 12-15, characterized in that the engagement and hoisting device (12) comprises a rotation-inhibiting device acting between the stand (17) and the nose-wheel holder (18) for generating a moment of torque between the stand (17) and the nose-wheel holder (18) when the direction of travel of the traction vehicle (2) changes relative to the aircraft (1) . 18. A device as claimed in claim 17, characterized in that the rotation-inhibiting device consists of a break-device (60) , arranged on the stand (17) and the nose-wheel holder (18) to secure the nose-wheel holder (18) against free rotation in a starting position, the break-device (60) being arranged to break when the nose-wheel holder (18) is subjected to a pre-determined, permitted torque relative to the stand (17) . 19. A device as claimed in claim 17, characterized in that the rotation-inhibiting device consists of a braking mechanism (62) , arranged to act with a pre-determined braking power between the stand (17) and the nose-wheel holder (18) , which braking power is arranged to be overcome when a pre-determined, permitted torque acts on the nose-wheel holder. 20. A device as claimed in claim 17, characterized in that the rotation-inhibiting device consists of a torque indicator (67) , attached to the stand (17) and the nose-wheel holder (18) and arranged to sense and react to changes in the torque in the nose-wheel holder (18) .

Inventors: JOHANSSON MAGNUS, JOHANSSON, MAGNUS
Applicants: JOHANSSON MAGNUS, KALMAR MOTOR AB, JOHANSSON, MAGNUS
Application year: 2001
Main classification: B64F1
IPC codes: B60P3, B64F1