RU2372252C2 - Device to carry and mount cargoes by flying vehicles - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering, particularly to helicopter equipment intended for carrying cargoes on external suspension. Proposed device comprises crosspiece with cargo ropes at its ends, coupled with flying vehicle lock via links converging nearby aforesaid lock, flexible links of cargo horizontal orientation that connect aforesaid crosspiece ends with drives via deflecting blocks fixed on flying vehicle fuselage at maximum tolerable distance from aforesaid lock. Additionally, two groups of blocks are introduced for every flexible link to be mounted on one-way power cylinder arranged between the drive and deflecting blocks. Power cylinder housing is attached to fuselage and furnished with one group of aforesaid additional blocks. Note that the other group of additional blocks is attached to the rod other end and aforesaid flexible link envelopes successively two groups of additional blocks to make pullet block.

EFFECT: higher reliability.

2 cl, 2 dwg

Description

The invention relates to aircraft, in particular to the equipment of helicopters used to transport cargo on an external sling and to perform construction and installation works.

A device for mounting cargo by an aircraft according to the patent of the Russian Federation No. 2028968, class. B64D 9/00, Е04Н 12/34, 1992, including a traverse with cargo ropes at the ends, connected to the lock of the aircraft through ties converging at the lock, and a cargo orientation system in the horizontal plane (in azimuth). The latter is made in the form of two rigid telescopic rods with a drive attached to the traverse. This design of the azimuthal orientation system ensures that the cargo rotates in azimuth in the mode of helicopter hovering during installation work. The disadvantages of the device are the small angle of rotation of the load (not more than ± 30 °), ineffective use of traction from the drive, specially installed on the aircraft. The large dimensions of the device make it difficult to use on helicopters with low clearance.

The closest in technical essence (prototype) is a device for mounting cargo by an aircraft according to the patent of the Russian Federation No. 2136547, class. B64D 9/00, 1996, including a traverse with cargo ropes at the ends, connected to the lock of the aircraft through ties converging at the lock, and a cargo orientation system in the horizontal plane. The latter is made in the form of two flexible rods connecting the ends of the beam with drives (winches) by means of deflecting blocks. To provide better conditions for the transfer of control efforts and increase torque, deflecting blocks are mounted on the fuselage of the aircraft at the greatest distance from the castle. As shown by many years of operation, such a design of the azimuthal orientation system provides rotations of the load in the horizontal plane by an angle of ± 80 ° in the mode of helicopter hovering above the installation site.

The disadvantage of this device is the lack of the ability to automatically compensate for changes in the length of flexible rods when the load fluctuates in the horizontal flight of the helicopter. Flexible traction are auxiliary (non-load-bearing) cargo connections with a helicopter, designed for efforts several times less than in cargo ropes. Since at constant length they (flexible traction) limit the natural fluctuations of the load in flight, the load in them may be higher than the permissible limits, which can lead to their destruction or breakdown of the helicopter. For example, during acceleration (speed-setting by helicopter), the load on the external slope deviates backward (towards the deflecting blocks), which leads to a weakening of the tension of the flexible rods and the appearance of freedom of rotation (yaw) of the load around the vertical axis. To stabilize the position of the load, it is necessary to pull up the flexible rods with winches (to shorten their length) depending on the flight speed (on the angle of the load backward). When the flight speed (braking) decreases, the load, together with the external suspension, is inertially deflected forward in flight, which can lead to excessive tension of the flexible rods. In order to exclude the destruction of flexible rods, in this case they must be loosened (increase length) with the help of winches. Obviously, the operation of the known device is associated with the need to constantly monitor the tension of the flexible rods and adjust their length, depending not only on the flight speed, but also on the acceleration or deceleration of the horizontal component of the flight speed. Strict requirements for the simultaneous control of two drives of flexible rods can complicate the work of the crew and distract from the main functions.

Therefore, the scope of the known device is limited to the area of the installation site with the movement of cargo at low speed with minimal acceleration. However, in the practice of construction and installation work with the use of helicopters, they often set the task of transporting cargo over long distances from the pick-up point and installing it at remote sites (up to 100 km). To solve such problems, a device is provided that is presented in the materials of this application for an invention.

The objective of the present invention is to remedy these disadvantages and achieve a new technical result.

In the proposed device, a new technical result consists in increasing the reliability of the device by preventing the prerequisites for its breakdowns in flight, increasing the safety of work and simplifying the work of the crew, as well as in increasing the radius of the helicopter due to the possibility of transporting cargo over long distances at maximum permissible speeds flight. A new technical result is ensured by the introduction of additional elements (essential features) installed on the aircraft and in a certain way interconnected with the existing ones.

This technical result in a device for transporting and mounting cargo by an aircraft, including a beam with cargo ropes at the ends, connected to the lock of the aircraft by means of ties converging at the castle, two drives and two flexible rods of the cargo orientation system in the horizontal plane, connecting the ends of the beam with drives by means of deflecting blocks mounted on the fuselage of the aircraft at the greatest distance from the lock, is achieved by the fact that for each flexible thrust introduced two groups of additional additional units mounted on a single-acting power cylinder between the drive and the deflecting unit, the single-acting power cylinder body attached to the fuselage and provided with one group of additional blocks, at the end of the single-acting power cylinder another group of additional blocks is fixed, and the flexible rod sequentially bends around both groups of additional blocks with the formation of a chain block.

At the same time, the value of the full stroke of the rod of each single-acting actuator satisfies the following condition:

S≥c / k,

where S is the full stroke of the ram cylinder;

C is the linear displacement of the beam in flight;

k - the ratio of the chain hoist.

The invention is illustrated by drawings, where in Fig.1 shows a General view of a helicopter with a device (side view with possible deviations of the cargo in flight); figure 2 - node a in figure 1.

The proposed device consists of the following main nodes.

Aircraft - helicopter 1 is equipped with an external suspension, including a traverse 2 with cargo ropes 3, which are equipped with load grips 4 from the bottom (hooks or electric locks). Traverse 2 through two converging connections 5, the swivel and the tip with cardans (not shown) are hooked to the main lock 6 of the helicopter. The specified external suspension is designed to pick up the load 7. In addition, the device contains an orienting system, which includes two flexible rods 8, connecting the ends of the crosshead 2 with two drives 9. The presence of two drives 9 (hereinafter referred to as winches) with executive links made in the form of flexible rods 8, provides rotations of the traverse 2 around the axis of suspension of the load 7, i.e. in azimuth.

To create the maximum value of the horizontal components of the forces (i.e., to ensure the maximum value of the torques) acting on the crosshead 2 from the rods 8, the latter are passed through the deflecting blocks 10 mounted on the fuselage at the greatest distance from the lock 6, for example, on the rear cargo ramp (Figures 1 and 2 show one flexible rod 8, and, accordingly, one winch 9 and one deflecting unit 10). For each flexible rod 8 between the winch 9 and the deflecting unit 10 by means of the rack 11, a single-acting power cylinder 12 is installed on the fuselage. The casing 13 of the actuator cylinder 12 and the yoke 14 is attached to the strut 11, on which a group of additional units is mounted 15. On the spring-loaded rod 16 of the actuator cylinder 12, a yoke 17 is fixed with another group of additional units 18. The rod 16 tends to take the highest position. The value of the full stroke of the rod 16 from the upper to the lowest position is S. This flexible rod 8 can be extended without turning on the drive - winch 9. However, extending the rod 8 equal to the value of S may not be enough, because linear displacement “c” of the crosshead 2 during fluctuations of the load 7 in flight is a quantity that depends on many reasons: the length of the links 5, acceleration of acceleration or deceleration of the helicopter 1, dimensions (windage) of the load 7, the speed of the oncoming air flow, etc.

Therefore, each flexible rod 8, released from the winch 9, is sequentially stored through additional blocks 15 and 18 with the formation of a chain block, and then through the envelope block 10 is attached to one of the ends of the beam 2. The chain block provides an increased change in the length of the flexible rod 8 with a limited stroke of the power rod cylinder 12 and thereby ensures the reliability and safety of the device, excluding device breakdowns (for example, breaks in flexible rods 8) when operating limits are exceeded.

In this case, the linear displacement S of the additional blocks 18 (i.e., the full stroke of the rod), multiplied by the multiple gear "k", must be at least the value of the possible linear displacement "c" of the yoke 2 in flight when the load 7 oscillates on the external load. The power cylinders 12 are selected taking into account their respective characteristics (for example, the stiffness of the springs 19, the stroke of the rod 16) in order to provide the necessary tension of the flexible rods 8 at any position of the yoke 2, and the maximum forces in the flexible rods 8 are within the permissible strength limits.

The housing 13 of the power cylinder 12 can be further attached to the fuselage by means of spacers 20.

The device operates as follows. After the take-off of the helicopter 1 by turning on the winches 9, the crosshead 2 is set to a position in which, together with the converging links 5, it is in the transverse plane of the helicopter 1 passing through the main lock 6. With this suspension arrangement, the helicopter 1 enters the load hitch 7. After the load hooks 4 cargo 7 is raised above the ground. In the helicopter hovering mode, when the load 7 and the entire external suspension with traverse 2 are in the vertical (initial) position, by changing the length of the flexible rods 8 with the help of winches 9, the rods 16 are set to a neutral position, i.e. in the middle between two extreme positions (upper and lower).

When transporting cargo 7 at the acceleration section of the helicopter 1, the cargo deviates from its original position back together with the entire external suspension, including tilts back the yoke 2, for example, by a value of "c / 2". Possible weakening of the tension of the flexible rods 8 is eliminated due to the action of the springs 19, which raise the rods 16 with additional blocks 18 upward, thereby pulling the flexible rods 8. This ensures that the load 7 is held in a predetermined position, thereby depriving the load of freedom of rotation (yaw) and ensuring its optimal position, for example, a position with minimal aerodynamic drag.

When the speed (braking) of the helicopter 1 decreases, the load 7 is deflected forward by the action of inertia forces. When the beam 2 is deflected forward (for example, by "c / 2"), the necessary extension of the flexible rods 8 while maintaining their tension is ensured by reducing the distance between the upper group of blocks 18 and the lower group of blocks 15 by moving the rod 16 down.

The full linear deviation "c" of the crosshead 2 during acceleration and braking of the helicopter 1 is provided by the full stroke S of the rods 16 with additional blocks 18 and the corresponding tension of the flexible rods 8 by the springs 19.

When the helicopter 1 hangs with cargo 7 above the installation site, the mismatch between the axes of the cargo and the foundation is eliminated by turning the beam 2 to the required angle in azimuth. For this, winches 9 are turned on in opposite directions. In this case, the possible mismatch along the length of the flexible rods 8 is compensated by the different stroke of the rods 16. Then, by lowering the helicopter 1, the load 7 is placed on the foundation and the uncoupling hooks are uncoupled 4. Returning the crosshead 2 to its original position, the helicopter 1 is sent for landing.

The proposed device was manufactured and tested in flight tests on a Mi-26 helicopter. As single-acting power cylinders, pneumatic-hydraulic shock absorbers of the main landing gear of the An-2 aircraft were used, which have the necessary characteristics. At the same time, a device with a chain hoist of up to 8 ensured automatic tension of flexible rods during acceleration during transportation of cargo weighing up to 17 tons to a distance of 35 km at a speed of up to 140 km / h and with subsequent extinction of the flight speed to zero (hovering during cargo installation).

The proposed device extends the radius of the helicopter during construction and installation work, because provides transportation of cargo and its installation at facilities remote from the point of hitching. At the same time, the safety of work is increased due to the elimination of the possibility of overtension and breaks of flexible rods, as well as possible damage to the helicopter. The work of the crew has been facilitated. the operation of the proposed device is not associated with the need for constant monitoring of the tension of flexible rods and adjusting their length depending on the acceleration of acceleration or deceleration of the helicopter, dimensions (windage) of cargo, speed of oncoming air flow, etc.

Claims (2)

1. A device for transporting and mounting cargo by an aircraft, including a traverse with cargo ropes at the ends, connected to the lock of the aircraft through ties converging at the castle, two drives and two flexible rods of the cargo orientation system in the horizontal plane, connecting the ends of the beam with the drives by deflecting blocks mounted on the fuselage of the aircraft at the greatest distance from the lock, characterized in that for each flexible traction introduced two groups of additional blocks, mount ovannyh on single-acting power cylinder between the drive and diverting pulleys, the housing of the actuator is attached to the fuselage and provided with one additional group of blocks at the end of the rod is fixed, another group of additional units, and the flexible rod sequentially encircles both groups of additional units to form a chain hoist. 2. The device according to claim 1, characterized in that the total stroke of the rod of each power cylinder satisfies the following condition:
S≥c / k,
where S is the full stroke of the ram cylinder;
C is the linear displacement of the beam in flight;
k - the ratio of the chain hoist.

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