RU2123457C1 - Method of dripping cargo from high-speed flying vehicle - Google Patents

Abstract

FIELD: dropping cargoes from low altitudes in an emergency or in combat. SUBSTANCE: cargo is secured by two ropes whose attachments are located in tail and nose sections of flying vehicle; at dropping nose rope is released; disconnection of cargo is effected at vertical position of rope secured in tail section of flying vehicle. Rope located in tail section holds stabilizing weight. method provides for automatic stabilization of cargo in space. EFFECT: enhanced efficiency. 2 cl

Description

 The invention relates to domeless trigger methods for moving cargo from a high-speed aircraft to a selected site and can be used to lower cargo from a low altitude (from about 100 meters), when there is a need for urgent evacuation in an emergency or when it is impossible to lower cargo from a significant height, using widely known parachutes in a combat setting. The invention can also be used to select cargo from the soil surface. A known method of lowering cargo from a high-speed aircraft is that the cargo is simultaneously secured to the cables of the tail and nose of the aircraft, then when descending, the load is disconnected from both cables (US patent N 3351325, B 64 D 191/00 1967 )

 The disadvantage of the described system can be considered the lack of stabilization of the descent system in space.

The objective of the invention is:
- descent of the cargo at zero relative speed with the landing area of the cargo,
- automatic stabilization of the cargo position in space.

 The specified technical result is achieved by simultaneously securing the load on the tail cable and on the nose cable of the aircraft, while stabilizing weight is fixed on the cable of the tail of the aircraft above the descent load, both cables are pulled, the bow cable is released and the load is disconnected from both cables with the vertical position of the tail cable, which is performed along the length, ensuring the safety of the cargo after it is disconnected from the cables and contacts with the landing pad.

 With a short fuselage of the aircraft, a rod is pulled out of it and a tail cable is supported on it.

 The method is implemented as follows.

 After releasing the bow cable, the load will act like a pendulum, moving along a radius that corresponds to the length of the tail cable. At the bottom point there will be a maximum speed, the vector of which is opposite to the direction of movement of the aircraft, and this speed will not depend on the mass of the cargo, but will depend only on the length of the free part of the tail cable, and it will be determined only by the distance from the place of cargo securing on the additional bow cable . With a length of, for example, 50 meters, this speed will be approximately 10 km / h.

 This speed is quite suitable for a helicopter.

где V - скорость набегающего потока воздуха;
γ - его плотность;
F - площадь взаимодействия потока и груза.If the aircraft has a high speed, then it is necessary to increase the speed at the lower point. This is automatically obtained because the laden air will always be affected by the incoming air flow and the force of impact will be determined by the formula

where V is the speed of the incoming air flow;
γ is its density;
F is the area of interaction of the flow and cargo.

 To eliminate the influence of the average density of the load, a stabilizing load is provided, which, at a low density of the launched load, will create a force that will always pull the tail cable. The area of the stabilizing cargo should provide the total speed for a given design speed so that at the ground it is equal to the speed of the aircraft or even exceeds it, but because since the total speed is directed in the direction opposite to the movement of the aircraft, the load will stop relative to the ground, which allows it to be disconnected and it will fall further under its own weight. If this distance is insignificant (1-2 meters), then the cargo will not be damaged. Therefore, it is necessary to choose a flight altitude over an equal surface slightly larger than the length of the attached tail cable. The stabilizing load itself is best to have in the form of a ball so that its position does not affect the force from the incoming flow.

 The descent of the cargo will be smooth with increasing speed in the opposite direction of the aircraft. The disconnection of the load from the load stabilizing it should be carried out in automatic mode, for example, by undermining the connection between the load and the descent system from the tail position sensor (the contacts close when the cable is in vertical position).

 Possible descent of a person who cuts the strap near the ground at a relative speed of about zero. It is possible to lift the load, but then it should be installed at a point where the relative speed is close to zero, and the coupled couple should have a snap-on grip and a loop. Choosing the front additional cable, the load is pulled into the front of the aircraft. A person on the go can also be raised. When lifting and lowering a person, a stabilizing load is necessary. There should be a calculation table of the speed and length of the tail cable, as well as lead in order to get to the selected point. All operations must be carried out at permissible low speeds for a given aircraft.

Claims (2)

 1. The method of lowering cargo from a high-speed aircraft, which consists in simultaneously securing the cargo on the tail cable and on the cable of the nose of the aircraft, disconnecting the load from both cables, characterized in that the cable is secured on the tail of the aircraft above the landing load stabilizing load, disconnect the bow cable, and the load is disconnected from both cables in the vertical position of the tail cable, which is performed along the length, ensuring the safety of the cargo after it is disconnected inenia from cables and contact with the landing pad.  2. The method according to claim 1, characterized in that the rod is extended on the aircraft and a tail cable is supported at its end.