LV12629B

LV12629B - Self-gripping load clip for outer free suspension of aircraft

Info

Publication number: LV12629B
Application number: LVP-00-168A
Authority: LV
Inventors: Juris LOGAČEVS; Aivars BEBRIŠS
Original assignee: Juris LOGAČEVS; Aivars BEBRIŠS
Priority date: 2000-12-08
Filing date: 2000-12-08
Publication date: 2001-07-20
Also published as: AU2002221193A1; LV12629A; WO2002046039A1

Abstract

An invention concerns the aeronautical engineering area, namely, an aircraft self-gripping load clips of the outer free suspension. In order to decrease the flight time, to simplify significantly piloting of the aircraft when directing and placing the open load clip on a load, e. g., a log, as well as to increase the response of opening and closing of the self-gripping load clip (1) of the outer free suspension (3), it is offered the following: to equip the self-gripping load clip with a sufficiently long elastic guide tail (4) having a ballast load and the end of the tail provided with bright colouring; to attach the basis (6) of the initial section (5) of the tail to the self-gripping load clip through an appropriate system of co-ordinated hinges (I), (II) and (III) for sufficiently free deflection of this section by the opposing skew of the load, e. g., log, in the closed position of self-gripping load clip; to apply a fast-response pneumatic power cylinder (8) with power feed from a source onboard the aircraft as a drive for opening and closing of the self-gripping load clip. In order to simplify the suspension and reduce pressure losses of the compressed air or gas, the alternative is to arrange a power feed source of said cylinder near to the self-gripping load clip or directly on it.

Description

1 LV 12629

AIRCRAFT SELF-GRIPPING LOAD CLIP OF OUTER FREE SUSPENSION

The ofFered invention concems the aeronautical engineering area, namely, to an aircraft self-gripping load clip of the outer free suspension.

The outer free suspension of helicopters is widespread for transportation of loads having large overail dimensions and transportation of different loads in conditions which are difficult of access. Such a suspension can be also used for other vertical take-off and landing aircrafts. The free suspensions have a carrier cable or a cable system, upper ends of which with emergency release locks are hingedly connected to the helicopter, and lower ends are equipped with load catching devices or load clips (see descriptions of helicopters to be used, for example, Mi-8TV Helicopter, for example, V.A.Danilov, etc. - M.: Transport, 1995. Pages 93 - 94. Loads on these suspensions can freely deflect relative to the helicopter. To remove twist of the suspension čabies, their longitudinal hinges named "swivels" are applied. In order to protect from impact loading, a shock-absorber is included in the suspension. A rather widespread prototype of application of the outer free suspension with a self-gripping load clip is logging by helicopters and other similar activities. Sufficiently large length of the suspension, for example, 50- 100 m, is necessary frequently. Power drive feed of the clip and its control system are usually from the helicopter's cabin along a cable-suspension.

Load clips are for a long time used for different lifting activities (see, for example, Small Soviet Encyclopedia. 3rd Edition, Volume 3, page 159). The aircraft self-gripping load clips ensure gripping/releasing loads vvithout ground human controllers. Such self-gripping load clips usually have a power drive for opening and closing them, a power feed system for a drive and a control system of operation of the drive. The aircraft self-gripping load clip of the outer free suspension with a hydraulic power drive, for example, prospectus of Corporation Canam Aerospace, is known.

Main deficiencies of the known aircraft self-gripping load clips of free outer suspensions are difficult piloting when directing and placing an open clip on a load, for example, a log, and insufficient response of closing and opening of the clip as it also 2 increases the flight time. Free deflection, tum, and oscillations of the clip on the outer suspension rather hamper directing to a load, e. g., a log, and placing on it. Attempts to introduce an additional link of the clip with a helicopter are unpromising. Such a Iink helps* only to direct the clip in respect of the helicopter and demands the appropriate orientation of the latter in respect of a load, e. g., a log, and that creates certain difficulties. Realization of a similar connection rather complicates the construction and activity of the outer suspension, especially if it has large length. The hydraulic power drive of the grip, having insufficient reliability of its feed supply is used frequently. Any leakage of the working fluid upsets the safety and ecology.

In order to simplify piloting significantly when directing and placing the open load clip on a load , e. g., a log, it is offered to equip any aircraft self-gripping load clip with a guide tail having necessaxy length and sufficient elasticity and provided with a ballast load. When the helicopter descends, an end of the tail leans on ground or other objects, and that ensures directing and placing the open clip on a load, e. g., a log, in the following flight, irrespective of orientation of the helicopter in respect of the load.

Afiter the closed load clip moves away from the center of mass of the long load, e. g., log, the upper short end of the latter more strongly approaches to the suspension, and that promotes a skew of the load in the clip. More rigid initial section of the tail, vvhich has got in the opposing position, precluding from the specified skew of the load, can expose itself to excessive loading. In order to eliminate this deficiency, the sufficiently free deflection of the tail basis by an opposing skew of the load after placing and closing the clip is provided, and that is achieved by a connection of the tail basis with the load clip by means of the system of appropriate coordinated hinges. If there is a short and flexible initial section of the tail, it is enough to use two hinges. An additional hinge is generally necessary.

In order to iiicrease the response of opening and closing of the self-gripping load clip and to eliminate deficiencies of the hydraulic drive, it is recommended to use a pneumatic or gas power cylinder, vvhich is povvered from the helicopter board, as a power drive of the clip. Hovvever, compressed air or gas feed to a significant distance is accompanied by pressure losses and that complicates the feed. This deficiency can be eliminated by 3 LV 12629 carrying the source of compressed airorgas to the suspension near the load clip or directly on the load clip.

Realization of the offered engineering Solutions is illustrated in schemes in Figurēs 1, 2,3, and 4.

In Fig. 1, a self-gripping load clip 1 connected by its adapter 2 to an end of the free suspension 3 of the helicopter is shown. The self-gripping load clip 1 is equipped with a sufficiently long and elastic tail 4 , whose end, when the helicopter descends, touches with ground or other objects and directs the open self-gripping load clip 1 to a load, e. g., a log, in the following flight. When the construction of the self-gripping load clip 1 or the technique of application of it eliminates an opportunity of excessive loading in an initial section 5 of the tail 4 by the opposing skew of the load/log , in the closed self-gripping load clip 1, the basis 6 of the tail 4 can be rigidly fasten to the self-gripping load clip 1 by any kind of connection, e. g., weldings, bolts, etc. More rigid initial section 5 and an opportunity that it will tum around the basis 6 promotes deflecting the tail 4 from the self-gripping load clip 1 and directing the later to the load. An appropriate hose can be used as the tail. Bright colouring of the tail end 4 and the ballast load (not shown) improves control during directing the open self-gripping load clip 1 to a load by the pilot.

In Fig. 2, the deflection of a tail 4 with an initial section 5 by the opposing skew of the load/log, in the closed self-gripping load clip 1 is shown. A more rigid section S with basis 6 fixed on the self-gripping load clip 1 offers the main resistance to the skew of the load. The sufficiently free deflection of the section 5 is provided with an appropriate hinged connection of its basis 6 with the self-gripping load clipl γ -angle is deflection of an axis of the basis 6 of the tail 4 from the working position by skew of the load in the self-gripping load clip 1. A scheme of the specified hinged connection is given in Fig. 3. On a hinge I of the self-gripping load clip 1, a hinge (Π) is freely suspended. The hinge axis (I) is perpendicular to the facade of the self-gripping load clip 1 or parallel to the load clip axis, and the hinge axis (II) is parallel to this facade. On a hinge (II), a flat heel 7, parallel to the facade of the self-gripping load clip 1 and freely bearing on iri with its lovver protuberance when the tail 4 is balanced by gravity. The lovver leg of the heel 7 on the self-gripping load clip 1 unloads hinges (I) and (II). 4

Deviation of a sufficiently short and flexible initial section 5 of the tail 4 from the opposing skew of the load is quite ensured with hinges (I) and (Π). At that, the basis 6 is rigidly fastened to a bearing heel 7. Such a hinged system does not prevent the main application of the tail 4.

Generally, with increasing the length and rigidity of an initial section 5 of the tail 4, the third hinge shown in Fig. 3 is necessary. A hinge (ΠΙ), with an axis parallel to the facade of the self-gripping load clip 1 and perpendicular the axis of the hinge (II), connects the basis 6 of the section 5 to the bearing heel 7. Hinges (II) and (ΠΙ) guarantee ffee deflection of the section 5 of the tail 4 by the opposing skew of a load, e. g., log, in the self-gripping load clip 1. However, the hinge (III) can prevent the main application of the tail 4, therefore, an elastic element holding the hinge (III) in a neutral position is provided.

In Fig. 4, there is an optimized tong-type self-gripping load clip 1 connected by its adapter 2 with a free outer suspension 3 of the helicopter. For increasing the response of opening and closing of the self-gripping load clip 1, a pneumatic or gas power cylinder 8 is used as its power drīve. Power feed of the cylinder 8 moves along the free suspension in a pipeline 9 from a source of compressed air gas, e. g., from previously charged tank, compressor, ordnance system, or other onboard the helicopter. The operation control of the drive 8 of the self-gripping load clip 1 can be realized from the helicopter board by a pilot or automatically by sensors of the self-gripping load clip 1. An operation switch of the power cylinder 8 is on the self-gripping load clip 1. Various methods, e. g„ by using radio, electrical, mechanical, hydraulic means, etc. in order to control the drive 8 of the self-gripping load clip 1 can be used. In Fig. 4, as an example, the wiring 10 of electrical control from the helicopter board is shown.

When approaching to a load , e. g., a log, the self-gripping load clip 1 is transported on the outer free suspension 3. Then, by piloting the helicopter, the open self-gripping load clip 1 on the suspension 3 is directed and placed on the load, e. g., a log. When the helicopter descends, a leg of a cone of the tail 4 touches ground or other objects and that considerably helps to direct the self-gripping load clip 1 to a load in the following flight, irrespective of orientation of the helicopter in respect of the load. A more rigid initial section 5 of the tail 4 and an opportunity of its tum around the basis 6 on the self-gripping 5 LV 12629 load clip 1 promote keeping the tail 4 away from the self-gripping load clip 1 and placing the later on the load. Bright colouring of an end of the tail 4 facilitates observation during piloting. By a control signal of the pilot or automatically, the self-gripping load clip 1 placed on the load is closed. Then lifting and transportation of the load are carried out on the outer free suspension 3 to a destination. The opposing skew of the load, e. g., log, in the closed self-gripping load clip 1 automatically placed on the load self-gripping load clip 1 is closed. Then lifting and transportation of the load on the outer free suspension 3 to a destination is carried out. The opposing skew of the load, for example, of the log, in the closed self-gripping load clip 1 sufficiently freely deflects an initial segment 5 of the tail 4 in the case of realization of the recommended hinged connection of its basis 6 with the self-gripping load clip 1. The above hinged connection does not reducē efficiency of the main application of the tail 4. After placing the transported load, the self-gripping load clip 1 is open by its power drive 8 after a control signal or automatically.

The present aircraft self-gripping load clip of the outer free suspension may be industrially produced and used in the aeronautical engineering area.

Abstract

An invention concerns the aeronautical engineering area, namely, an aircraft self-gripping load clips of the outer free suspension. In order to decrease the flight time, to simplify significantly piloting of the aircraft when directing and placing the open load clip on a load, e. g., a log, as well as to increase the response of opening and closing of the self-gripping load clip (1) of the outer free suspension (3) , it is offered the following: to equip the self-gripping load clip with a sufficiently long elastic guide tail (4) having a ballast load and the end of the tail provided with bright colouring; to attach the basis (6) of the initial section (5) of the tail to the self-gripping load clip through an appropriate system of co-ordinated hinges (I), (II) and (III) for sufficiently free deflection of this section by the opposing skew of the load, e. g., log, in the closed position of self-gripping load clip; to apply a fast-response pneumatic power cylinder (8) with power feed from a source onboard the aircraft as a drive for opening and closing of the self-gripping load clip. In order to simplify the suspension and reduce pressure losses of the compressed air or gas, the alternative is to arrange a power feed source of said cylinder near to the self-gripping load clip or directly on it. 6 LV 12629

CLAIMS 1. An aircraft self-gripping load clip (1) of the outer free suspension, which includes an adapter (2) for jointing vvith a suspension (3), a power drive (8) for opening - closing it, a povver feed system of the drive and an operation control system of the drive, characterized by that in order to simpliiy piloting when directing and placing the open self-gripping load clip to a load, for example, a log , the self-gripping load clip is equipped with a sufficiently long and elastic guide tail (4), whose end touches ground or other objects, when descending, and directing the open self-gripping load clip (1) to the load in the following flight, irrespective of orientation of the aircraft in respect of the load. 2. The aircraft self-gripping load clip of the outer free suspension according to Claim 1 characterized by that an initial section (5) of the tail (4) is made as more rigid one in comparison vvith other parts of the tail vvith an opportunity of its tum around the basis (6) on the self-gripping load clip (1). 3. The aircraft self-gripping load clip of the outer free suspension according to Claim 1 or Claim 2 characterized bythat anendofthetail(4)hasbrightcolouring. 4. The aircraft self-gripping load clip of the outer free suspension according to any of the previous Claims characterized by that an end of the tail (4) is provided vvith a ballast load. 5. The aircraft self-gripping load clip of the outer free suspension according to any of the previous Claims characterized by that in order to provide required deflection of a short and flexible initial section of the tail by the opposing skew of the load, for example, of the log, in the closed self-gripping load clip, an appropriate hinged connection of the basis (6) of an initial section (5) of the tail (4) vvith the self-gripping load clip (1) is used, the second hinge (II), vvhich is parallel to this facade, hangs on the first hinge (I) of the self-gripping load clip, vvhich is perpendicular to the facade of the later, and the heel (7) of the basis of the tail (4), vvhich hangs on the second hinge (II), is parallel to the said facade and freely lies on it with a Iower protuberance vvith the tail (4) balanced by gravity. 7 6. The aircraft self-gripping load clip of the outer firee suspension according to any of the previous Claims characterized by that in order to provide sufficiently free deflection of an initial section of the tail by the opposing skew of the load, for example, of the log, in the closed self-gripping load clip with increasing its Iength and rigidity, in the hinged connection between a bearing heel and a basis of the initial section of the tail, the third hinge (ΙΠ), which is parallel to the facade of the self-gripping load clip (1) and perpendicular to the second hinge (Π), with an elastic element holding it in a neutral position, is added. 7. The aircraft self-gripping load clip of the outer free suspension according to any of the previous Claims characterized by that in order to increase the response of opening and closing of the self-gripping load clip, as a pneumātic or gas power cylinder (8) is applied its power drīve, which supplies the power feed (9) along the free suspension (3) from one of the follovving selected sources: previously charged tank, compressor, ordnance system, or other that is onboard the aircraft, and the operation control of the power cylinder, effected by a pilot or automatic, is realized by any of the known ways. 8. The aircraft self-gripping load clip of the outer free suspension according to any of the Claims from Claim 1 to Claim 6 characterized by that in order to reduce any main pressure losses of compressed air or gas and simplifying the free suspension, power source of the power cylinder (8) of the drive of the self-gripping load. clip is Iocated on the suspension (3) near the self-gripping load clip or directly on the self-gripping load clip (1). 1/4

ļoīeUoopte' X LV '26Z9

2/4 LV 12629

To helicopter

3/4 LV 12629

4/4

To helicopter LV 12629 3 10 % w 1

Claims

EN 12629 A self-sealing device (1) for the outer sealing of the outer seal (1), comprising transverse links (2) for coupling to the suspension (3), its opening-closing force drive mechanism (8), a drive power supply system, and a drive control system, differ with the intention of simplifying piloting by moving and stacking an open self-propelled 5 load (logs), it is equipped with a flexible lengthwise guide link (4) of appropriate length so that it can press against the ground or other objects with its lower end lowering height and shifting the open self-propelled (1) to the load on the next flight regardless of the aircraft orientation towards the load.

2. Self-propelled external freewheeling self-propelled. 10, characterized in that the initial step (5) of the stepping link (4) is formed by the possibility of turning around its base (7) onto the self-gripper (1), wherein its initial phase (5) is formed with increased rigidity compared to the rest its stages.

3. An external freewheeling self-propeller according to claim 1 or 2, characterized in that the tip of the stepped link (4) is made with a bright color. 15

An external freewheeling aerial self-gripper according to any one of the preceding claims, characterized in that ballast weights are attached to the end of the tail link (4).

5. An external freewheeling self-propeller according to any one of the preceding claims, characterized in that, in order to provide the required deflection of the short and 20 elastic strut start portions according to the opposite deflection of the load, the self-closing tailgate (4) initial stage (5) is connected. by means of a self-closing (1) articulated coupler, at which a second chameleon (II) parallel to this facade is suspended at the first self-locking shaker (I), which is perpendicular to its facade, and a foot (6) of the base (6) of the toothed link (4). ), with which said second chameleon (II) is connected and parallel to said facade, freely relies on it with a lower projection, having an equilibrium joint (4) under the influence of its gravity.

6. An external sealing self-propeller according to any one of the preceding claims, characterized in that, in order to provide a sufficient free-to-start linkage with an increased length and toughness, the required deflection according to the opposite load offset in the closed self-closing device is provided with a third coupling. a chameleon (ΙΠ) parallel to the facade of the self-gripper (1) and perpendicular to the second chameleon (Π) and with a flexible element that holds it in a neutral position. 10

7. An external freewheeling self-propeller according to any one of the preceding claims, characterized in that, in order to accelerate the self-opening of the self-closing device, the pneumatic or gas force cylinder (8) with an automatic or pilot controlled power supply is used as a power drive. feed (9) along the bpvo suspension (3) from a source selected from the following sources: 15 pre-charged reservoir, compressor, red system, etc., disposed in the aircraft with the capability to control the force cylinder operation by any known means.

8. A self-locking spreader of an external freewheel according to any one of claims 1 to 6; with the difference that in order to reduce the compressed air or gas main losses and to simplify the free suspension, the self-closing power drive 20 power supply cylinder (8) is located on the suspension (3) near the self-gripper or directly on the self-gripper (1). .