RU2349509C1 - Pneumatic shock absorber for cargo airdropping - Google Patents

Abstract

FIELD: aeronautical engineering.

SUBSTANCE: invention relates to aviation, particularly to paradropping equipment, primarily to paradropping platformless systems and can be used for salvage and rescue operations in areas of liquidation of incidents and disasters, as well as in military operations of whatever scale. The proposed shock absorber comprises a base with primary and auxiliary inflatable enclosures furnished with slits with preset sizes selected subject to actual operating load. It is also incorporates a carcass made up of the front, rear and lengthwise beams selected to satisfy the cargo sizes and shape. The front and rear beams are furnished with fastening assemblies matching those of cargo to be airdropped. The aforesaid frame represents a multi-frame structure with skis and rolling-contact bearings. Each of the aforesaid frames as well as primary enclosures feature orifices to communicate their inner spaces with atmosphere. Primary enclosures upper parts are attached to the aforesaid carcass, while their lower parts are fastened to the multi-frame base. The carcass is fastened to the base with the help of wires to ensure horizontal stability.

EFFECT: smooth trouble-free touchdown (splashdown) of airdropped cargo with minimum chances of cargo tipping over, no use of outer compressed air sources for inflation of pneumatic shock absorbers.

8 dwg

Description

The present invention relates to aviation, and in particular to parachute-landing equipment, mainly to parachute-strapdown systems, and can be used in emergency rescue operations in the zones of liquidation of consequences of accidents and disasters, as well as during military operations of any scale.

The main problems during the landing of cargo and equipment from the aircraft are the following:

- the problem of safe separation of the landed cargo from the aircraft and its descent with a reduced vertical speed;

- the problem of short-term energetic braking of the descent at the moment of landing of the landing cargo with the ground (water) without destruction and breakdowns with permissible overloads;

- the problem of eliminating the horizontal displacement speeds of the landed cargo at the moment it touches the surface of the earth (water), leading to the capsizing of the cargo;

- the problem of reducing the mass and volume of equipment that ensures accident-free landing (water landing) of the landing cargo, its compact placement in cargo dimensions;

- the problem of independence from sources of compressed air and the completeness of filling the shells of shock-absorbing systems, the reliability of their operation at the moment of touching the ground or water surface with a landing cargo.

Several approaches to solving these problems are known.

So known pneumatic shock absorber for landing cargo from aircraft (US patent No. 2964139, NKI 188-87, MKI B64D 1/14, B64D 1/00, 05/01/57), containing a platform with mounted on it landing gear, which is attached to the slings of the parachute system. The upper parts of the inflatable shells with bottom openings closed by non-return valves are attached to the lower plane of the platform. Shells in an inadvertent state are folded under the platform and fixed. The lower parts of the shells are connected in pairs by rigid bases with inlet openings communicating the internal cavities of the shells with the atmosphere. Before landing, the fixed shells are released from fixation and carried away by the mass of rigid bases straighten out, filling with air.

The disadvantages of this device are the presence of a large cargo platform, leading to an increase in the area of the parachute system, as well as the lack of a single base and means of eliminating horizontal displacements of the cargo upon landing, leading to its capsizing and breakage in the conditions of the drift of the cargo by the wind. This design does not provide high performance and reliability.

Also known is a damper to mitigate the impact of a landing object (RF patent No. 2158698 of March 12, 1999, class B64D 1/14, B64G 1/62), which contains a gas-tight elastic shell with an internal cavity filled with air. The inner cavity of the shell is divided by a gas-tight elastic vertical partition into two chambers of equal volume. Each chamber is equipped with at least one adjustable valve, detachable joints and couplers. The couplers are attached at one end by means of detachable connections to the partition along its upper and lower edges, respectively, and the other to the shell.

The disadvantage of such a damper is the need to fill it with air under excess pressure from a compressor or cylinder, which complicates the preparation of the damper for its use and limits the discharge height of the landing equipment due to the effect of low temperatures on the filling system.

The closest to the proposed invention in terms of essential features is a shock-absorbing device (US patent No. 2713466 from 01.31.49, NKI 244-138, MKI B64D 1/14, B64D 1/00), containing many perforated with membranes of inflatable membranes placed between the landing cargo and the base. Shells can self-fill with air through bottom openings with check valves. The lower parts of the shells when the device is triggered are able to disconnect from the base under the action of horizontal displacements. The device in the folded state stands for the dimensions of the landing cargo and is equipped with special holding flaps, which must be changed every time after use.

The main disadvantages of this device is the large number of elements replaced after application, the complexity of their installation and configuration.

The objectives of the invention are: to increase the safety of separation of the airborne cargo from the side of the aircraft, in which the nodes and the shock-absorbing system do not protrude beyond the dimensions of the airborne cargo, and after separation of the cargo from the side of the plane take the necessary characteristics, including reducing the vertical speed and the possibility of tipping cargo. In addition, the task is to ensure short-term vigorous braking of the descent of the landing cargo with acceptable overloads, which guarantee the complete safety of the cargo, the operability of the crew inside the landing cargo, and its readiness to perform ground tasks.

The third task is to create such a design of a pneumatic shock absorber (shock-absorbing system), which would eliminate the horizontal displacement speeds of the landing cargo at the moment it touches the surface of the earth (water), leading to deformation of the shells of the pneumatic shock and its capsizing.

The fourth task is to create such a shock-absorbing system that could be folded compactly in a stowed position and placed, for example, under the bottom between the tracks of an airborne combat vehicle or an all-terrain vehicle, etc., and when landing, perform its functions of energy absorption when touching the ground (water) surface.

The fifth task is to create a pneumatic shock absorber with reliable, independent of onboard (external) sources of compressed air, filling the shells.

The tasks are solved as a result of the fact that the pneumatic shock absorber for cargo landing, containing the base with inflatable shells with slots fixed on it, is made of a number of main and additional shells communicating with each other with slots of the calculated size, depending on the current load, while the pneumatic shock absorber is equipped with a frame made up from the front, rear and longitudinal beams, adapted to the dimensions and design of the load, where the front and rear beams are equipped with mating fasteners reciprocating with the cargo the base is made multi-frame with skis and rolling bearings, each of the frames being equipped with holes joint with the main shells communicating their internal cavities with the atmosphere, which together with the slits provide an excess of the pressure drop rate in the main shells over the pressure drop rate in the additional shells, In this case, the main shells are attached with their upper parts to the frame and the lower parts to the multi-frame base, and the frame is connected to the base by means of braces that provide resistance to th horizontal displacements.

The frame, soft shells and the base during transportation have the ability to be compactly pressed against each other, and during landing they can be removed from each other, forming a volume filled with air, resistant to horizontal displacements within the lengths of the braces between the frame and the base.

Thus, the claimed design of the pneumatic shock absorber meets the criteria of the invention of "novelty." Comparison of the claimed solution not only with the prototype, but also with other technical solutions protected by patents in this technical field, did not allow to reveal in them the features that distinguish the claimed solution from the prototype, which allows us to conclude that the criterion is “inventive step”. The inventive solution is suitable for industrial implementation.

The invention is illustrated by drawings, where

- figure 1 is a General view of the pneumatic shock absorber in a state ready for operation;

- figure 2 is a General view of the pneumatic shock absorber when folded;

- figure 3 is a General view of a multi-frame base;

- figure 4 is a General view of the soft primary and secondary shells in a state ready for operation;

- figure 5 is the moment of separation of the landing equipment from the aircraft;

- in Fig.6 - the process of filling the main domes of the parachute system and the beginning of filling the pneumatic shock absorber for airborne cargo;

- in Fig.7 - descent of the landing technique by means of the main domes of the parachute system with a filled pneumatic shock absorber under the bottom;

- in Fig.8 - the descent of the landing equipment from the pneumatic shock absorber after landing to perform ground tasks.

The present invention, “Air shock absorber for cargo landing” in accordance with the structural solutions contains: a number of soft main shells 1 with additional soft shells 2. The upper parts of the soft shells 1 are attached to the frame formed by the front beam 3, the rear beam 4 and the longitudinal beams 5. The front and the rear beams 3 and 4 are made with attachment points reciprocal with the air cargo. The lower parts of the soft shells 1 are attached to the multi-frame base 6. The lower parts of the soft shells 1 are provided with inlets 7 that coincide with holes of the same size 8, made in the multi-frame base 6, communicating the internal cavities 9 of the shells 1 with the atmosphere. The multi-frame base 6 consists of several frames 10, which are attached to the skis 11 on one side and are connected to each other by the rolling bearings 12. Each ski 11 is equipped with brackets 13.

The lateral surfaces 14 of the main soft shells 1 and the surface 15 of the additional soft shells 2 are provided with holes made in the form of slots 16 of the calculated size and reinforced with collars 17 and 18. The upper part of the soft main shells 1 contains covers 19, 20 through which longitudinal beams 5 are passed Shell 1 is equipped with cord rings 21 and cord rings with brakes 22 to tie them to the lower base 6.

The pneumatic shock absorber has tacking cables 23, as well as side braces 24, central braces 25 and a jumper 26. The braces 24, 25 and jumpers 26 serve to prevent the multi-frame base 6 and shells 1 from slipping when the landing cargo is demolished.

Soft main shells 1 together with additional shells 2 in an unfilled state are able to compactly fold into a flat bag 27 together with the front beam 3, rear beam 4 and longitudinal beams 5, as well as base 6 (Figure 2). The pneumatic shock absorber, folded in the form of a flat package 27, is attached to the bottom of the dumped load 28. In this case, the front beam 3 is connected to the front bracket of the load, the rear beam 4 is mounted on the bracket of the towing cargo unit. The base 6 with the sheaths 1 and 2 laid is pressed to the bottom of the load and held in this position by means of special clamps located on the front beam 3 and brackets located on the rear beam 4.

Airborne cargo 28 is delivered to the ground by means of a parachute system 29, consisting of an exhaust parachute 30, an additional exhaust parachute 31, a main parachute 32, a brake parachute 33, a cable system 34.

Pneumatic shock absorber for cargo landing works as follows.

A pneumatic shock absorber for cargo landing, prepared for landing, is attached to the bottom of the cargo 28. Its front beam 3 is connected to the front load securing unit 28. The rear beam 4 is mounted on the towing load securing unit 28. Multi-frame base 6 with soft shells 1, 2 pressed against the bottom of the load 28 and is held in this position by the latches of the front beam 3 and the brackets of the rear beam 4. The landed cargo 28, prepared for landing, is mounted by skis 11 of the multi-frame base 6 on the roller tracks carrier and is fixed on the monorail by attachment points of the front 3 and rear beams 4, as well as a special mount lock belonging to the carrier.

Under the action of the thrust of the filled exhaust parachute 30 (Figure 5), the landing cargo 28 leaves the carrier along the rollers of the roller conveyor equipment. When the load 28 from the load carrier, the levers of the rear beam 4 hit the carrier rolls and deploy the parachute system 29. The exhaust parachute 30 and the additional exhaust parachute 31 pull the brake domes 33 and the main 32 parachutes to full length. After filling the domes of the main parachutes 32, the load 28 decreases with the necessary (permissible) speed. Under the influence of the mass of the landing cargo 28, the cable system 34 is connected, connected with the stripping cables 23, and the air shock absorber is laid, laid in a flat package 27 under the bottom of the cargo 28. The base of the air shock absorber 6, separating from the front 3 and rear 4 beams, thereby straightens the laid soft main 1 additional 2 shells attached to the base 6 by lacing through rings 21 and rings with brakes 22. Under the action of its mass, the base 6 provides self-filling with air through the inlets 7 in the shells and holes 8 in the base 6 of the internal cavities 9 of the main 1 and 2 additional shells. This provides an additional flow of air from a vertically incident air stream, as well as from air suction through openings made in the form of slots 16 of the calculated size, depending on the current load. The pneumatic shock absorber as a result of its filling takes the form and volume shown in figure 1; four; 7, and its soft shells 1, 2 at the moment of landing of the load 28 are able to absorb most of the kinetic energy, providing its soft landing.

At the moment of contact of the “airborne cargo-pneumatic shock absorber” system with the ground (water), compression (deformation) of the shells 1, 2 begins through the inlets 7, 8, air begins to escape intensively, forming an air cushion under the base 6. At the same time, compression and an increase in pressure in the shells 1, 2 causes air to flow from the shells 1 into the shells 2 through the slots 16, thereby unloading the shells 1. As the damping rate of the load 28 is extinguished, the air flow rate decreases in both shells 1 and shells 2, but in the shells 1, the air flow is much higher than in the shells 2, and therefore the pressure in the shells 1 is much less than in the shells 2. Since the main shells 1 are located in the central part of the pneumatic shock absorber, and the additional shells 2, filled with air under high pressure downward, on the periphery, the additional shells 2 hold the landing cargo 28 from possible tipping over, creating a moment of opposite sign.

The lateral surfaces 14 of the main shells 1 and the surfaces 15 of the additional shells 2, provided with slots of a design size 16, experiencing significant loads at the time of landing of the load 28, are reinforced with collars 17 and 18.

To prevent possible displacement of the base 6 and shells 1 in the horizontal plane, leading to the possible overturning of the landing cargo 28 under the conditions of landing with demolition, braces 24, 25 made of a cable and jumpers 26 made of a special tape were used.

After the landing of the airborne cargo 28 from its cabin, the auto-coupler based on pyrotechnic devices is turned on and the parachute system 29 is disconnected. Then the crew transfers to its regular places, starts the engine, and the airborne cargo 28 moves forward, while the pneumatic shock absorber and all its elements are separated from the bottom. Landing cargo 28 is ready to perform ground tasks.

The essence of the invention is to provide increased efficiency of the pneumatic shock absorber regardless of external (airborne) sources of compressed air, with a soft landing of the landing cargo with smaller areas of the parachute system. This result is achieved by the implementation of a pneumatic shock absorber from a number of soft shells 1, the bottom parts of which are equipped with inlet openings 7, which ensure self-filling of the main shells 1 with air, and additional soft shells 2 equipped with slotted holes of a design size 12 that communicate with the main shells 1.

The implementation of the pneumatic shock absorber from a number of soft shells 1, 2 with the possibility of self-filling allows you to completely abandon the forced filling systems of the shells, which generally allows you to reduce the cost of the device and eliminate the elements of a possible failure.

The execution of the bottom parts of the soft shells 1 and the base 6 with inlet openings 7, 8, in addition to the air inlet and outlet through them, also allows to obtain a “perforation effect”, which creates additional aerodynamic resistance to the landing cargo 28 and, as a result, a slight decrease in the vertical speed of its decrease. The implementation of the pneumatic shock absorber from a number of soft shells 1, attached with their upper parts to the frame (3, 4, 5), the lower parts to the multi-frame base 6, allows them to be folded compactly in the form of a flat package 27 and placed, for example, under the bottom of the combat vehicle landing, all-terrain vehicle, etc. between caterpillars, not speaking for their dimensions. This design improves the safety of separation of the landing cargo 28 from the carrier.

Using the same openings 7, 8 to fill the pneumatic shock absorber and release air when it touches the ground under the action of the mass of the airborne cargo 28 allows you to store in the shells 1 the amount of air necessary for the short-term formation of powerful air jets, the reaction of which has a braking effect on the cargo 28 equivalent in magnitude to the generated impulse by pyrotechnic brake devices.

When using this pneumatic shock absorber for landing a cargo 28 on a water surface, its efficiency is further enhanced by short-term sealing of the inlet-outlet openings 7, 8 and the formation of a powerful foam-air cushion that absorbs the kinetic energy of the water-loaded cargo 28.

The use of lateral braces 24 in the design of the pneumatic shock absorber ensures parallel movement of the load 28 relative to the base 6 at the time of its operation and prevents the displacement of the base 6 when the load 28 is landed (splashed) with side drift.

The use of the design of the central braces 25 prevents the displacement of the base 6 from under the bottom of the load 28 when it lands (splashes) with longitudinal drift.

Jumpers 26 prevent the displacement of the shells 1 along the longitudinal beams 5 in one direction or another.

Thus, the design of a pneumatic shock absorber for cargo landing has been created, which provides higher safety and reliability of cargo delivery from the carrier to the ground due to the use of a group of soft shells with self-filling in the process of reducing the airborne cargo to the earth (water) surface, with different rates of pressure drop in them cavities in contact with the ground.

In this design of the pneumatic shock absorber there is no danger of rupture of the shells before they come in contact with the earth (water) surface, delay or failure of the filling system.

The technological effectiveness of servicing the pneumatic shock absorber increases, the time for its preparation for use and repair in the field is reduced. Due to the compactness of the pneumatic shock absorber and its independence from compressed air sources, installation, dismantling and replacement in the field are provided.

The pneumatic shock absorber does not affect the safe operation of the carrier and does not require special measures.

The design of the pneumatic shock absorber allows you to expand its scope of application, both in defense structures and in the civilian sector of the economy.

The present invention is at the stage of experimental development, working drawings are issued, suitable for industrial implementation.

Claims (1)

A pneumatic shock absorber for cargo landing, comprising a base with inflatable shells fixed with slits on it, characterized in that it is made of a number of main and additional shells communicating with each other with slots of a calculated size, depending on the current load, while the pneumatic shock absorber is equipped with a frame made up of a front , rear and longitudinal beams, adapted to the dimensions and structure of the cargo, where the front and rear beams are equipped with attachment points reciprocal with the air cargo, and the base is made it is multi-frame with skis and rolling bearings, and each of the frames is equipped with holes joint with the main shells, communicating their internal cavities with the atmosphere, which together with the slots provide an excess of the pressure drop rate in the main shells over the pressure drop rate in the additional shells, while the main shells are attached their upper parts to the frame and the lower ones to the multi-frame base, and the frame with the base are connected by cable braces, which provide resistance to horizontal premises.

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