RU2131828C1 - Container mainly intended for landable aero-space objects - Google Patents

Abstract

FIELD: aviation; containers for landing aero-space objects. SUBSTANCE: container has framework and multi-layer envelope; first inner layer of envelope is made from high-strength flexible material; subsequent layers are made from flexible material at reducing elasticity and strength and increasing deformability in way from inner to outer layer. Invention contains versions of envelope layers. Container is durable enough to ensure preservation of landable objects and its reliable operation (voice and flight information recorders, for example). EFFECT: enhanced efficiency at high rates of landing, high temperatures and pressures. 4 cl, 1 dwg

Description

 The invention relates to aviation, and more particularly to landing containers for aerospace objects, and can be used to increase their reliability in various application conditions, in particular, can be used in the design of containers for recording devices for flight and voice information ("black boxes") to ensure their safety.

 From the patent of the Russian Federation N 2097279, cl. B 64 D 25/20, 1997. “A method for storing information in flight mode and crew conversations in the event of an accidental fall of an aircraft and an aircraft” it is known to use airborne containers for information recording devices. Such containers, being made in the form of a mono-shell, do not ensure the integrity and safety of landing objects at high flight speeds, at high ambient temperatures, and during fires.

 Known dumped container for multi-purpose use for landing cargo from an aircraft (see French patent, N 2208381, CL B 64 D 1/00, 1994). The container is made in the form of a detachable housing made of solid material. Such a container also does not ensure the safety of the cargo when landing it on a solid (mountainous) surface with large overloads.

 The well-known "Laminated sheath for providing thermal and electrostatic protection" (Russian patent N 2087392, class B 64 G 1/58, 1997), which provides for the protection of space objects of a multilayer shell made of semiconductors, polyamide fiber, heat-reflecting and heat-regulating layers. Such a shell is designed to protect against electrostatic discharges and thermal radiation, but cannot be used for landing objects, because does not ensure their integrity.

 A known container for cargoes descent from the aircraft, made in the form of a detachable body, comprising an outer shell of relatively hard and light material and an inner shell of flexible material. The outer shell is made of a material that, upon impact, is crushed with energy absorption (see US Pat. No. 4,655,418, CL B 64 D 1/14, 1987). A known container, when dropped from an aircraft, can protect the equipment being discharged. only in conditions of slight overload, because the destructible outer layer cannot absorb a significant amount of energy released during the discharge of objects at high flight speeds when it hits a hard surface. In addition, such a container is not able to withstand high thermal loads.

 The objective of the invention is to develop the design of a container for airborne cargo, which would allow landing of aerospace objects under various combinations of extreme impacts: high landing speeds, high temperatures and pressures of the medium, high strength characteristics of the surface to be dumped. In this case, the container must ensure the safety and reliability of the landing object.

 According to the invention, the stated task is achieved in that in the container, mainly for landing airspace objects containing a skeleton and a multilayer shell, the first inner layer is made of high strength elastic material, and all subsequent layers are made with decreasing elasticity and strength and increasing deformability in the direction from internal to external layer.

 Moreover, it is advisable to make the first layer of high-strength elastic steel, the second layer of ductile steel, and the third layer of tin bronze.

 Possible implementation of the outer layer of the shell of a porous material, such as porous copper.

 In addition, it is advisable that the outer layer of the shell is hollow in the form of a sheathing, supported by a frame, while the inner space of the outer layer is filled with a liquid, for example, synthetic oil based on organosilicon compounds.

 The implementation of the container in accordance with the invention allows to ensure the safety of aerospace objects during their landing in extreme conditions (high speeds, temperatures and pressures) for various types of surfaces.

 The invention is illustrated by the drawing, which shows a General view of the container with a partial cut, made in accordance with the invention.

 Information confirming the possibility of carrying out the invention.

 In accordance with the invention, the container is made in the form of a detachable housing comprising a frame 10 and a shell 11 (see drawing). The shell 11 is made in a shape close to the ball, and multilayer from several interconnected layers. The first inner layer 1 is made of high strength elastic material. All subsequent layers in the direction from the inner to the outer are made with decreasing elasticity and strength and increasing deformability.

 The number of layers and the strength of the shell are selected from the condition of ensuring the safety of the inner layer containing the airborne equipment, for example, equipment for magnetic recording of flight information, for specific conditions of landing: landing speed, surface strength, pressure and ambient temperature.

 The execution of the shell with decreasing elasticity and deformability is achieved by selecting the strength characteristics of the material of the layers and geometric parameters in order to ensure the required overload per landing equipment. This also takes into account the method of fixing the equipment inside the shell. The fastening can be carried out either by using an elastic suspension, or by fixing the space with a deformable material, for example, asboplastik.

 The best embodiment of the invention.

 The container is made of a shell 11, each containing layers 1, 2, 3, 4, and the frame 10. In this case, the frame is detachable and containing flanges 7 on each half with holes for mounting fasteners 8. The shell is also detachable and held in the assembled position of the frame 10, forming a cavity 9, which serves to accommodate the landing equipment.

 The first layer 1 is made of high tensile elastic steel, for example, high alloy hardened steel. The second layer 2 is made of viscous non-hardened chromansil steel. The third layer 3 is made of tin bronze. The fourth outer layer 4 is made hollow in the form of a sheathing 5, supported by a frame 6. The frame 10 is also made of a deformable material, such as bronze. The interior of layer 4 may be filled with liquid. As a liquid, a synthetic oil based on organosilicon compounds can be used.

 The container is also equipped with a filling nozzle with a plug for filling the cavity of the layer 4 with liquid and a tubular channel for outputting wiring from the magnetic recording apparatus located in the cavity 9 (not shown in the drawing). In the cavity of the container connector, a seal made in the form of an asboresin gasket (not shown) can be installed.

 The outer layer 4 may be made of porous metal, such as porous copper.

 When a container landed, which can happen intentionally when an aerospace object is delivered to the surface of the land or sea of the Earth or to other planets, the container collides with the landing surface.

 A similar collision occurs during an emergency ejection of a container or in an aircraft accident. In a collision, a shock occurs with the absorption of a significant amount of kinetic energy.

 At the initial moment of impact, the framework and the outer layer interact with the surface, which, when deformed, absorb part of the energy with a corresponding deceleration of the container. After this, deformation takes place in succession of all subsequent layers with a corresponding extension of the impact time and providing the required overload per landing object inside the container.

 The last inner layer perceives the impact elastically, without collapsing, ensuring the safety of the object.

 The presence of liquid (synthetic oil) allows you to provide the required temperature conditions inside the container with significant negative or positive values of the ambient temperature.

The container made in accordance with the invention ensures the safety of the landing equipment under various combinations of unfavorable factors: at landing speeds of up to 3000 km / h, on water, on the mountain surface of the earth, on an environment with a temperature of up to 750 ^o C and a pressure of up to 4 km water column.

Claims (4)

 1. The container is mainly for landing aerospace objects, made in the form of a detachable body containing a frame and a multilayer shell, characterized in that the first inner layer is made of high strength elastic material, and all subsequent layers are made with decreasing elasticity and strength and increasing deformability in the direction from inner to outer layer.  2. The container according to claim 1, characterized in that the first layer is made of high strength elastic steel, the second layer is made of malleable steel, and the third layer is made of tin bronze.  3. The container according to claim 1 or 2, characterized in that the outer layer of the shell is made of porous metal, such as copper.  4. The container according to claim 1 or 2, characterized in that the outer layer of the shell is made in the form of a casing reinforced by a frame, the inner space of which is filled with a liquid, for example synthetic oil.