RU2613376C2 - Device for separation of elements of aircraft plane designs - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to space technology, namely to the devices intended for the controlled separation of structural elements of aircraft planes. The device for the separation of elements of aircraft planes designs contains electrostatic lock (ESL) held in the closed position by force of electrostatic attraction that occurs between electrical charges of opposite sign. The main element of ESL is a contact pair of electrodes separated by a dielectric layer. With the help of ESL division of structural elements of the aircraft plane descends very naturally and smoothly. When a signal is applied for the separation and the opening of ESL holding force of elements in a single design instantly reduces.

EFFECT: invention allows to separate constructions smoothly and to reduce the possibility of additional static or dynamic loads in the elements or between the elements of the aircraft plane.

2 cl

Description

Technology Section

The present invention is a device for the separation of structural elements of aircraft relates to devices designed for the controlled separation of structural elements of aircraft and the controlled separation from the main body of the aircraft of spent modules: stages of missiles, equipment, ballast, etc.

Industrial applicability

The invention can be applied in space and aviation technology.

State of the art

In the vast majority of devices that are used to separate structural elements of aircraft and are currently used, the main element is a pyrotechnic lock (pyrotechnic device) - a pyro bolt, or a pyro cartridge - a fixing bolt, in the core of which a cavity is created next to the head, filled with blasting explosive with electric detonator. When a current pulse is applied to the electric detonator, an explosion occurs that destroys the bolt rod, as a result of which its head comes off, and the structural elements of the aircraft, which previously connected the pyro-bolt, are separated. The amount of explosive in the pyro-bolt is carefully dosed to ensure that the bolt head is torn off without damaging the aircraft.

The main disadvantage of such a device is the large shock load (shock wave) resulting from the explosion of the pyro-bolt, and other "stressful" consequences of the explosion for the aircraft, which together is a source of increased risk of an accident. An even greater danger arises if the explosion is not strong enough to tear off the bolt head. In this case, the normal separation of the structural elements of the aircraft does not occur, which, as a rule, leads to the destruction of the aircraft. There are other disadvantages: an increase in the mass and dimensions of the aircraft; Although the response time of the pyrotechnic device is several microseconds, it is still not instantaneous.

Disclosure of invention

A device for locking and fixing elements of various mechanisms is known - an electrostatic lock (ZES), the holding force of which in the closed state is the electrostatic (Coulomb) force of attraction between electric charges of opposite signs. The main element of the ZES is a contact pair of electrodes separated by a fairly narrow dielectric layer. When a potential difference (voltage) is applied to the electrodes brought into a state of close contact with each other through a dielectric separating them, electric charges of opposite signs are formed on the electrodes and an electrostatic attraction force arises between them, and the ZES goes into a closed state. To open the ZES, you need to remove the voltage from the electrodes, for which it is enough to short-circuit them. A number of additional technical solutions are known that serve to increase the efficiency and reliability of the Western Economic Zone: RF patents for invention No. 2519877 and No. 2542794. Also, the use of ferroceramic materials as a dielectric in the ZES, which are currently widely used in the production of ceramic capacitors, allows one to obtain abnormally high specific retention forces for these devices - about a ton per square cm, the contact surface of the electrodes. This opens up great opportunities for the use of ZES in devices for the separation of structural elements of aircraft.

However, many types of locking devices, which are quite obvious for this and are intended, for example, ordinary mechanical latches, can create a large holding force. Therefore, it must be emphasized that the main and decisive advantage of the ZES over pyro locks and other types of locking devices - the advantage that makes the ZES an ideal device for the controlled connection and disconnection of structural elements of aircraft, is that they do not use any - either types of mechanical forces or actions on the parts of the locking device, unlike other devices: the opening of the pyro-bolt occurs by the destruction of its rod and subsequent separation of the bolt head, which, as already described above, creates an increased risk of accident; to open the mechanical latch, it is necessary to move the lock bolt with sufficient force, which holds the latch in the closed state, which creates a high risk of jamming the lock at high tangential loads, which is exactly what happens in aircraft, the mass of which can reach tens of tons or more. In the ZES, the closing and opening is controlled only by electric voltage, the disconnection of which leads to the complete opening of the lock, but does not cause any other mechanical stresses or movements, which is ideal for an aircraft operating in conditions of high overloads and turbulent air flows and sensitive to the impact of external and internal nonequilibrium processes, the consequences of which are often impossible to calculate.

The implementation of the invention

Based on the foregoing, the following simple construction of the Device for separating structural elements of aircraft can be made and described: Electrostatic lock (ZES), which contains a contact pair of electrodes of the ZES, separated by a narrow dielectric layer.

In this case, the ZES can be in two states: in the closed state, when an electric voltage is applied to the contact pair of the electrodes of the ZES brought into contact with each other through the dielectric separating them, while the electrodes of the opposite sign are formed and the electrodes are held in this the state of adjacency to each other by the force of electrostatic attraction between the electrodes, and this force, therefore, is the force of holding the ZES in the closed state; and the ZES can be in the open state when the voltage is removed from the contact pair of the electrodes of the ZES and the electrodes can be freely separated from each other.

In this case, the ZES consists of two parts that are connected and held in a connected state by the electrostatic holding force of the ZES, and the ZES is in the closed state, and into which the ZES is divided upon transition to the open state. At the same time, one of these parts of the AES can be connected to one of the shared structural elements of the aircraft, and the other part can be connected to another structural element of the aircraft, so that when the ZES is closed, these elements are held in a connected state by the holding force of the ZES, and when the ZES is opened, the data structural elements of the aircraft go into an unbound state and can be separated from each other.

Technical Results Achieved

With the help of a ZES, the separation of structural elements of an aircraft takes place naturally and smoothly, the holding force of these elements in a single structure instantly decreases to almost zero, and no additional static or dynamic loads occur in the elements or between the elements of the aircraft, which is the main technical result of the present invention. As a result, the risk of an accident when separating structural elements of aircraft is greatly reduced.

In addition, the ZES has a number of advantages that actualize its use for fixing structural elements of the aircraft: the ZES is capable of creating a retention force of tens and hundreds of tons, while it is quite light and compact, has a very high specific power (retention force per unit weight), it is easy to control and opens really instantly, since the speed of propagation of potentials in the network is equal to the speed of light.

The best dielectrics for use in the ZES are ferroceramic dielectrics, the relative permittivity of which reaches 10 ³ -10 ⁴ units. However, in outer space, other types of dielectrics may also be useful: ordinary ceramics, glass, mica, polyimides, polyamides, polymers, plastics, teflon.

Claims (5)

1. A device for separating structural elements of aircraft, consisting of at least one electrostatic lock (ZES); wherein the ZES is a device that contains at least one contact pair of electrodes of the ZES, separated by a narrow dielectric layer; in this case, the ZES can be in two states: in the closed state, when an electrical voltage is applied to the contact pair of the electrodes of the ZES brought into contact with each other through the dielectric separating them, while the electrodes of the opposite sign are formed and the electrodes are held in this the state of adjacency to each other by the force of electrostatic attraction between the electrodes, and this force, therefore, is the force of holding the ZES in the closed state; and the ZES can be in the open state when the voltage is removed from the contact pair of the electrodes of the ZES and the electrodes can be freely separated from each other; wherein the ZES consists of at least two parts that are connected and held in a connected state with each other by the electrostatic holding force of the ZES, and the ZES is in this case closed, and into which the ZES is divided upon transition to the open state; in this case, one of these parts of the ZES can be connected to one of the shared structural elements of the aircraft, and the other part can be connected to another structural element of the aircraft, so that when the ZES is closed, these elements are held in a connected state by the holding force of the ZES, and when the ZES is opened, the data structural elements of the aircraft go into an unbound state and can be separated from each other. 2. A device for separating structural elements of aircraft according to claim 1, characterized in that in the ZES, as the dielectric separating the contact pair of the electrodes of the ZES, it contains any combination of the following dielectric materials: ferro-ceramic dielectric, ceramic, glass, mica, polyimides, polyamides , polymers, plastics, teflon.