RU2628282C1 - Docking unit of detachable objects of aircrafts - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: docking unit of detachable objects of aircrafts (AC) contains a body with clamps to fix the detachable element on a spherical surface. Each clamp is a sleeve containing a plunger stop, held in the sleeve by a ball lock. The plunger stop is based in the sleeve along the conjugate diameters, which form the differential area of the actuator for removing the fixation of the junction of the detachable objects. The activation of the clamps is provided by the simultaneous supply of pressure to the ball-type locks, which release the plunger stops. Detaching objects is carried out by moving the plunger stops.

EFFECT: reliable docking of aircraft objects without stresses from the allowed and possible deviations of the objects to be docked.

2 dwg

Description

The invention relates to rocket technology and can find application in the design of separation systems of objects of aircraft (LA) - stages of cruise missiles, spacecraft, etc. In modern systems of separation of objects of aircraft, much attention is paid to reducing shock loads and impulse from the action of the separation means to final stages object, which affects the accuracy of its derivation on the calculated parameters of the flight path. This is also influenced by the design of the unit for docking shared objects with uniform speed with the collector activation of pyromechanical devices.

Known are the devices for docking shared objects of aircraft, providing for their fastening together, containing locking mechanisms from arbitrary separation and software separation of objects using pyromechanical devices:

1. Quick release ball lock [1. A.S. 516847, IPC F16B 2/16. Quick Release Ball Lock / Yu.G. Shlepneva, V.V. Volsky, A.N. Volcifer. - Publ. 07/12/07.].

The disadvantages of the device are as follows:

- connection by cylindrical conjugation of shared objects does not exclude lateral components of force and disturbances during separation, especially at high loads;

- multi-row ball locks do not give stable results on the separation function (according to the experience of working out such structures by the authors);

2. The pusher lock [2. A.S. 576443, IPC F16B 2/16. Pusher castle / E.I. Alekseev, B.C. Fire - Publ. 10.20.77.].

The disadvantages of the device:

- does not exclude lateral forces and disturbances during separation;

- for heavy loads in the connection is not intended.

3. The device described in the article [3. Improving the separation systems of modern spacecraft to reduce shock loads. Fig. 1. Scheme pirozamka-pusher with ball locking elements. / V.V. Efanov, A.S. Biryukov, O.G. Demenko, V.V. Gorovtsov // “Flight”. - 2014. - No. 4. - S. 30-36.].

The disadvantage of this device: the design dampens forces, but does not exclude shock loads during separation.

4. A device for separating elements of a spacecraft [4. Pat. RU 2167796 C1, IPC B64G 1/64, F16B 2/16. A device for separating elements of a spacecraft / D.D. Samusev, L.K. Deryuzhkin, A.S. Averyanov. - Publ. 05/27/2001.].

The disadvantages of the device:

- the design does not provide shockless separation of objects;

- liners with engagement along the annular teeth and a cylindrical sleeve will not ensure the stability of the separation of objects due to possible distortions when moving.

The closest technical device, selected as a prototype, is described in the patent for the invention [5. Pat. RU 2196712 C2, IPC B64G 1/64, F16B 2/16. A device for separating the elements of the spacecraft Samusev, S.N. Shtukaturkin. - Publ. 01/20/2003.].

The device is a hinged detachable connection on a spherical surface, fixed to the body using a latch.

The prototype has the following disadvantage: the separation is carried out along the trajectory of the detachable element in one plane, provided by articulation with the spacecraft; in the case of using the device when the object is completely separated, a lateral force perpendicular to the separation plane can occur, excluding the shock-free separation of the object. This limits the options for using the device in aircraft, especially when it is necessary to fix it rigidly, which eliminates distortions and ensures separation of objects without the mutual influence of disturbing forces.

The aim of the invention is the creation of a reliable docking unit for shared aircraft objects, eliminating distortions and manufacturing inaccuracies when securing shared objects between themselves and ensuring their free separation during linear and angular movements relative to the X, Y, Z axes without the mutual influence of disturbing forces.

The achievement of this goal is achieved by the fact that the docking station of the shared objects of the aircraft is a detachable connection on the spherical surface using latches in the form of quick-release ball locks, where the separation of the objects of the aircraft is achieved by releasing the fastening of the objects of the aircraft with clamps on the joined shared surfaces simultaneously along linear and angular displacements relative to the axes X, Y, Z.

The invention is illustrated by drawings, where in FIG. 1 shows the docking assembly of the shared objects of the aircraft in the operating position, comprising the housing 1 of the detachable object, latches 2 located symmetrically relative to the bracket 3 of the attachment of the detachable object. The latch 2 is similar to the known [2] and contains a sleeve 4 with channels 5 and 6, a plunger-stop 7 with channels 8 and holes (separator) 9, and a sleeve 4 and a plunger-stop 7 with a difference of mating diameters D and d form a channel 10, balls -Locks 11 located in the holes 9 of the stop plunger 7, a rod 12, which locks the lock balls 11 into the annular grooves 13 of the sleeve 4, whereby the sleeve 4 is connected to the stop plunger 7. The rod 12 is connected to the stop plunger 7 with a cut-off check 14 and contains a conical groove 15, interacting with the separation of the node with the cylinder-trap 16 of the sleeve 17, which is at the same time a seal in the connection between the support nut 18 and the sleeve 4, as well as an annular groove 19 for rolling out the ball-locks 11. Installation (suspension) of the detachable object is provided by installing clamps 2 along thread 20 on thread sealant, for example, Anaterm 117, up to the stop with the plunger-stop 7 in the bracket 3 along the sphere 21. The housing 1 of the detachable object contains a manifold 22 for supplying working gas to the retainer 2 with a pipe 23 for a squib, gas generator or other type of pressure source.

In FIG. 2 shows the interaction of the structural elements of the node in the undocked position of the detachable object.

The principle of operation of the device. The starting position corresponds to FIG. 1. When applying pressure (the method is not indicated) to the latch 2 through the pipe 23, the manifold 22, channels 5, 6, 10, 8, the rod 12 moves and the checks are cut 14. The further movement of the rod 12 is accompanied by the connection of the rod 12 with the sleeve 17 during expansion trap cylinder 16 along the conical groove 15 and rolling out the ball-locks 11 into the groove 19, as a result of which the fixation of the connection of the plunger-stop 7 on the sleeve 4 is removed. Further, under the action of pressure from the differential area on the plunger-stop 7, equal to

stop plungers 7 simultaneously move all the way into the nuts 18, thereby freeing the fastening of the detachable object along the joined shared surfaces 21 without disturbing forces during linear and angular movements with respect to the axes X, Y, Z.

The docking node for shared aircraft objects provides:

- reliable docking of objects without stresses from the allowed and possible deviations of the joined objects;

- compensation for deviations of the axes of shared objects;

- free, without mutual disturbance, separation of objects;

The proposed device can be performed using standard equipment and materials of domestic production. Thus, the claimed device meets the criterion of "industrial applicability".

Sources taken into account

1. A.S. 516847, IPC F16B 2/16. Quick Release Ball Lock / Yu.G. Shlepneva, V.V. Volsky, A.N. Volcifer. - Publ. 07/12/07.

2. A.S. 576443, IPC F16B 2/16. Pusher castle / E.I. Alekseev, B.C. Fire - Publ. 10.20.77.

3. Improving the separation systems of modern spacecraft to reduce shock loads. Fig. 1. Scheme pirozamka-pusher with ball locking elements. / V.V. Efanov, A.S. Biryukov, O.G. Demenko, B.V. Horovtsov. // “Flight”. - 2014. - No. 4. - S. 30-36.

4. Pat. RU 2167796 C1, IPC B64G 1/64, F16B 2/16. A device for separating elements of a spacecraft / D.D. Samusev, L.K. Deryuzhkin, A.S. Averyanov. - Publ. 05/27/2001.

5. Pat. RU 2196712 C2, IPC B64G 1/64, F16B 2/16. A device for separating elements of a spacecraft / D.D. Samusev, C.N. Shtukaturkin. - Publ. 01/20/2003.

6. A.S. 699244, M. Cl. F16B 2/20. Pusher castle / R.F. Akhtareev, A.D. Gorbachev. - Publ. 11/30/1979.

7. A.S. 836396, M. Cl. F16B 2/16. Pusher castle / R.F. Akhtareev. - Publ. 06/10/1981.

8. A.S. 889917, M. Cl. F16B 2/16. Pusher castle / L.K. Melnikov, B.I. Poroshina, B.C. Smirnov. - Publ. 12/15/1981.

9. A.S. SU 1767243, M. Cl. F16B 2/16. Ball-lock / V.I. Gerov, V.Ya. Khokhlov, A.V. Ruchkin. - Publ. 10/07/1992.

10. A.S. 134060, M. Cl. 42k, 20. Device for remote separation of two elements of an object in flight during aerodynamic research / E.Ya. Pivkin, A.P. Chernyshev, Yu.A. Merenkov. - Publ. - 1960. - Bull. Number 23.

11. A.S. 195893 Cl. 62B, 24/02. Lock for mounting removable parts of the aircraft / Yu.P. Andreev. - Publ. 07/04/1967.

12. A.S. 364767, M. Cl. F16B 2/16. Lock / S.A. Goryainov, N.I. Galkin, I.S. Pustovalov. - Publ. 02/23/1973.

13. A.S. 436181, M. Cl. F16B 2/16. Device for interlocking female and male parts. / G.I. Konovalov, A.I. Centsiper. - Publ. 12/09/1974.

14. A.S. 458662, M. Cl. F16B 2/16. Ball-lock / Yu.V. Nazarov, A.S. Voronin. - Publ. 03/07/1975.

15. A.S. 540064, M. Cl. F16B 2/16. Castle device / Yu.G. Shlepneva and others. - Publ. 02/07/1977.

16. A.S. 731101, M. Cl. F16B 2/16. Locking device / A.E. Cohan et al. - Publ. 04/30/1980.

17. A.S. 1808105, M. Cl. F16B 2/16. Quick disconnect unit / M.V. Luzgachev, I.A. Mordvinnikov, V.V. Volsky. - Publ. 04/07/1993.

18. Pat. RU 2 509 682, M. Cl. B64C 3/56, F16B 2/16 The mechanism of connection-separation of the elevon of the folding wing of the aircraft / S.A. Shestakov, V.A. Zemskov. - Publ. 03/20/2014.

Claims (1)

A docking assembly for shared objects of the aircraft, comprising a housing with locks for securing a detachable element on a spherical surface, characterized in that each lock is a sleeve containing a stop plunger held in a sleeve by a ball lock, the stop plunger is based on the mating diameters in the sleeve, forming the differential area of the drive to remove the fixation of the docking station of shared objects.

Images