AU5407099A

AU5407099A - Device and method for the targeted placement or reception of goods carried by aircraft

Info

Publication number: AU5407099A
Application number: AU54070/99A
Authority: AU
Inventors: Bernhard Kampf; Ingolf Schafer
Original assignee: INGOLF SCHAFER INGOLF
Current assignee: Cargolifter AG
Priority date: 1998-06-22
Filing date: 1999-06-22
Publication date: 2000-01-10
Also published as: CA2336046A1; DE19827664C1; JP2002518254A; EP1087887A1; WO1999067131A1

Description

WO 99/67131 PCT/DE99/01817 Device and method for the targeted putting down or picking up of goods from aircraft The invention relates to a method for the targeted 5 putting down or picking up of goods from aircraft according to the preamble of claim 1. It is known to load or unload goods or persons from aircraft. In this context, the problem arises that the 10 aircraft has to land for this purpose. It is also known to let down or pick up persons or goods from unlanded aircraft by means of a roping-down winch. There is the problem here, that it is not 15 possible or it is possible only with difficulty for them to be put down accurately, especially under difficult weather conditions. This method is therefore ruled out in many applications. 20 The patent specification FR 2 364 851 A of April 1978 describes a device which makes it possible for the load to be put down via a rope framework extended in space. The problem in this case is the need for the rope framework to be permanently pre-tensioned by means of 25 the aircraft. In this case, the permissible radius of movement of the aircraft is limited by the geometry of the rope framework and by the requirement that all the ropes must remain pre-tensioned. Generating the vertical pre-tension by means of the aircraft is 30 associated, here, with a considerable outlay in terms of energy and construction. The patent application P 196 25 297.0 of June 1996 describes a method which demonstrates and solves 35 essential aspects which are not mentioned in the patent specified above. Fundamentally, however, there is still AMENDED SHEET (RULE 91)

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WO 99/67131 - 2 - PCT/DE99/01817 the problem of pre-tensioning a three-dimensional rope framework by means of the aircraft. Patent specification US 3,393,769 A (June, 1968) 5 likewise illustrates a device which resorts to a pre tensioned rope system, three-dimensional positioning of the load to be put down not being possible because of the geometry illustrated. 10 Utility model DE 295 09 940 (November, 1995) likewise illustrates a device for letting down goods or persons, which braces safety ropes relative to the ground in order to secure the persons more effectively. There is no mention here of proper three-dimensional securing 15 and of the geometric conditions necessary for this purpose. Patent specification GB 2 055 728 A (March, 1981) describes a device which makes it possible to let down 20 loads from airships, without indicating solutions for putting down with pinpoint accuracy or avoiding by design the interception of disturbances which act on the aircraft and have an effect on the putting-down operation. 25 Furthermore, it is known as prior art to place an intermediate platform above the putting-down point, the load then being let down from this intermediate platform. In this case, however, this intermediate 30 platform is likewise held in its position via a pre-tensioned three-dimensional framework. It is therefore still necessary to pre-tension the system by means of the airship, the geometry of the rope framework defining the space of movement of the 35 aircraft. AMENDED SHEET (RULE 91)

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WO 99/67131 - 3 - PCT/DE99/01817 The object on which the invention is based is, therefore, to specify a device and a method, by means of which a targeted putdown becomes possible to the 5 extent of a load being put down or picked up with pinpoint accuracy, even when the ambient conditions do not allow the aircraft to be held steady and vertical pre-tension relative to the ground is for any reason not possible or is undesirable or cannot be ensured for 10 the duration of the method. This object is achieved, here, by means of a device having the defining features of claim 1. 15 By virtue of the three-dimensional framework with pressure-loadable supports, the position of the intermediate platform is already essentially fixed in space, without the need for the aircraft to be in a steady state. Inaccuracies in the position of the 20 intermediate platform may occur while the intermediate platform is being let down and before securing by means of the pressure supports. In this case, the aircraft itself is at an appropriately selected distance above the load. The pre-tension between the aircraft and 25 intermediate platform is, in this case, obtained from the aircraft lift which is to be kept essentially constant during the putting-down operation. In an expedient development of the invention, the load 30 is let down from the intermediate platform via a rope system which allows a further increase in positioning accuracy. This rope system may consist, for example, of vertically running ropes which allow the load to be moved manually, even in the case of large masses to be 35 moved, or of a system which, in turn, is connected to AMENDED SHEET (RULE 91)

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WO 99/67131 - 4 - PCT/DE99/01817 the ground and makes it possible for the load to be led to the putdown point (such as for example, guide rails, docking devices, etc.). 5 It is advantageous to integrate into the pressure absorbing elements of the mounting of the intermediate platform, components which, during the erection of the mounting of the intermediate platform, allow a movement which is damped according to the requirements. These 10 damping elements may, for example, be spring elements, hydraulic dampers or the like. Alternatively, each individual pressure support also per se constitutes a damping element. 15 It is an expedient further development when the pressure-absorbing elements can absorb successively rising pressure forces only after connection to the ground and approximate adjustment of the intermediate platform, so that the impact load on the overall system 20 is kept low. This may be achieved, for example, by means of kinematic chains or mechanisms which are restricted step by step in degrees of freedom at a plurality of joints to be appropriately selected and thus lead to an increasing stiffening of the three 25 dimensional supporting framework. As a further variant, use is to be mentioned here of a support which is to be stabilized by internal pressure and which is stiffened only by the application of an 30 internal pressure and thus constructs the three dimensional supporting framework. In addition to this, it may also be expedient to construct the three-dimensional supporting framework 35 from a composite structure of pressure-absorbent AMENDED SHEET (RULE 91)

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wO 99/67131 - 5 - PCT/DE99/01817 supports and of braces serving for securing these pressure supports three-dimensionally and consisting of tension elements (for example, ropes). The construction of this composite supporting structure should take into 5 account the special requirements arising from the individual steps of the method as a whole, insofar as this seems to be postulated and expedient. This may be, for example, the moveable mounting of the pressure supports which, only after connection to the ground via 10 the tension element bracing, is made capable of absorbing pressure forces. The uncoupling of the possible movements of the aircraft about the vertical axis from the intermediate 15 platform is achieved by means of suitable devices which may be integrated both in the system between the aircraft and intermediate platform, in the aircraft or in the intermediate platform. These may consist, for example, of a sufficient twistability of ropes or a 20 live ring. Further features of the invention and other advantageous implementations may be gathered from the further claims, the description and the drawings in 25 which exemplary embodiments of the invention are illustrated. Figures 1 - 4 show a complete method for putting down a load by the example of the load being put down from an 30 airship. The load pickup is carried out in a similar way in the reverse order of the method steps. Individual steps may expediently take place simultaneously and have been separated here merely for the sake of clarity. Furthermore, as comprehensive an 35 illustration as possible has been chosen, that is to AMENDED SHEET (RULE 91)

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WO 99/67131 - 6 - PCT/DE99/01817 say, individual steps may be dispensed with if the design implementation so allows. Steps 1 - 4 are illustrated in figure 1. 5 In step 1, the aircraft is still cruising toward the target location. In step 2, the aircraft drops to the target altitude 10 which is selected according to local conditions and requirements. In step 3, if necessary, the cargo hold is opened and the load let down. Alternatively, the load is basically 15 located below the aircraft, that is to say, does not have to be let down specially. This step is then dispensed with. In step 4, the aircraft is placed at the target 20 altitude and then has to compensate only the disturbances caused by wind and changes in lift. However, it does not have to be in a steady state, but can be in constant movement. 25 Steps 5 - 8 are illustrated in figure 2. In step 5, the three-dimensional supporting framework is prepared, if necessary, for the absorption of pressure forces. Alternatively, the supporting 30 framework is still in the extended state. In step 6, the connection to the ground is made. This is one of the method steps in which spring damper elements play a helpful part, if appropriate. 35 AMENDED SHEET (RULE 91)

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- WO 99/67131 - 7 - PCT/DE99/01817 In step 7, if necessary, the frame is braced and, at the latest from this moment, is capable of absorbing pressure forces. 5 In step 8, all the preparations for letting down the load from the intermediate platform are concluded. Steps 9 - 12 are summarized in figure 3. 10 In step 9, the load is let down. In this case, further fine adjustment is possible, if the corresponding devices are installed. In step 10, the weight of the let-down load is 15 neutralized by means of compensating ballast, if necessary. This compensating ballast may be received in many forms. Steps 11 - 16 are illustrated in figure 4. 20 In step 11, the connection to the ground is released after the possibly necessary breakup of the composite pressure-force structure has been carried out. 25 In step 12, there is once again liftoff from the ground. In step 13, if provided as a consequent of design, the composite supporting structure for mounting the 30 intermediate platform is retracted again. In step 14, the frame and the ballast, if provided, are retracted. 35 In step 15, the transition to cruising is initiated. AMENDED SHEET (RULE 91)

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WO 99/67131 - 8 - PCT/DE99/01817 In step 16, the aircraft is cruising again. Alternatively to the airship shown, the aircraft may 5 also be a balloon or a helicopter or any other aircraft which does not require horizontal movement in order to generate lift. Accordingly, the frame shown for suspending the load 10 may be dispensed with if this seems expedient in terms of said problem. AMENDED SHEET (RULE 91)

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Claims

1. A device for the targeted putting down of goods on the ground from unlanded aircraft which do not 5 require horizontal movement in order to generate lift, such as airships, balloons or helicopters, the goods being capable of being let down from an aircraft-specific intermediate platform which is suspended moveably relative to the aircraft by 10 supporting means, in particular flexible, in particular retractable and extendable supporting means, wherein the intermediate platform has supports by means of which pressure forces can be led to the ground. 15

2. The device as claimed in claim 1, wherein the load is capable of being let down further from the intermediate platform via a further system. 20

3. The device as claimed in claim 1 or 2, wherein spring and/or damping elements are integrated in the supports absorbing the pressure forces or the supports absorbing the pressure have themselves spring and/or damping properties. 25

4. The device as claimed in one of claims 1 - 3, wherein the supports absorbing the pressure are capable of being stiffened only in succession by means of suitable devices. 30

5. The device as claimed in one of claims 1 - 4, wherein the supports absorbing the pressure are made capable, by the application of an internal pressure of absorbing pressure. 35 . WO 99/67131 - 10 - PCT/DE99/01817

6. The device as claimed in one of claims 1 - 5, wherein the supports absorbing the pressure are capable of being extended telescopically. 5

7. The device as claimed in one of claims 1 - 6, wherein the intermediate platform is constructed as a three-dimensional supporting framework from pressure and tension elements. 10

8. The device as claimed in claim 7, wherein the three-dimensional supporting framework for mounting the intermediate platform while the method is being carried out is both articulated and rigid, in order to absorb pressure forces at 15 defined moments only.

9. The device as claimed in one of claims 1 - 8, wherein uncoupling of movement about the vertical axis between the aircraft and intermediate 20 platform takes place in the intermediate platform.

10. The device as claimed in one of claims 1 - 9, wherein uncoupling of movement about the vertical axis between the aircraft and intermediate 25 platform takes place in the aircraft.

11. The device as claimed in one of claims 1 - 9, wherein uncoupling of movement about the vertical axis between the aircraft and intermediate 30 platform takes place in the system between the aircraft and intermediate platform.