Synchronous multi-axle fire working device

Abstract

The application provides a synchronous multi-link fire working device, which comprises a body, a pressure cavity arranged in the body, and a plurality of piston holes in communication with the body; a plurality of piston rods are arranged in the piston holes; high-pressure gas formed by a combustion chamber passes through a gas hole, and first pushes a synchronization cover away from the piston rod; since the synchronization cover only contacts the piston rod and the displacement direction is perpendicular to the piston rod, the synchronization cover can be pushed away from the piston rod at the moment when the high-pressure gas is filled into the pressure cavity, and the piston rod can timely extend out of a guide arm; and separation of a working cavity and the combustion chamber can ensure that only high-temperature gas enters the pressure cavity and the pressure cavity is not polluted by flue gas formed in a combustion process of a combustor in the combustion chamber.

Description

Technical Field

[0001] This invention relates to a synchronous multi-linkage firing device. Background Technology

[0002] During flight, an aircraft needs to deploy its wings, a process accomplished by a pyrotechnic actuation device. This device uses the high-temperature, high-pressure gas generated by the combustion of gunpowder to propel the load, thus enabling the deployment of the mechanism or the release of the load. Currently, the pyrotechnic actuations used on spacecraft are single-degree-of-freedom devices. These devices can only deploy a single wing surface. Since most spacecraft have four wings, when all four wings need to be locked and deployed simultaneously, four single-degree-of-freedom ignition actuators need to work in parallel. For example, a five-pushrod ignition actuator disclosed in CN206905636U locks the pushrods by setting T-shaped shear pins at the outlets of multiple pushrods. After ignition, the high-temperature and high-pressure gas pushes the piston, and the pushrods cut the T-shaped shear pins, causing the pushrods to extend out of the cylinder synchronously. First, due to the issue of machining accuracy, the shearing force required to cut the T-shaped shear pins is affected by the machining accuracy, and extremely high machining accuracy must be ensured to achieve the synchronous effect. Furthermore, a short time is required to cut the T-shaped shear pins, which has a certain impact on the timely opening of the spacecraft's wings. Summary of the Invention

[0003] To solve the above-mentioned technical problems, the present invention provides a synchronous multi-linkage fire-operating device.

[0004] The present invention is achieved through the following technical solutions.

[0005] This invention provides a synchronous multi-linkage ignition working device, comprising a body, a pressure chamber inside the body, and multiple piston holes communicating with the outside of the body; characterized in that: piston rods, the multiple piston rods are respectively installed in the piston holes; a combustion chamber, the combustion chamber is disposed on the body, the combustion chamber and the pressure chamber are connected through a gas port; an igniter, the igniter is installed on the combustion chamber and seals the combustion chamber; and a synchronization cover, the synchronization cover is disposed in the pressure chamber and simultaneously limits the multiple piston rods, so that the multiple piston rods extend out of the body to the same length.

[0006] The piston holes are on the same plane.

[0007] A guide arm is also installed at the outer end of the piston hole, and a stepped hole with the same diameter as the piston hole and coaxial is machined inside the guide arm.

[0008] The piston rod has a limiting groove machined at one end that extends into the body. The limiting grooves on multiple piston rods are combined into a circle, and the opening of the synchronization cover is locked in the limiting groove.

[0009] The gas vent is machined on the front side of the synchronous cover opening.

[0010] The main body has a circular through hole on the side opposite to the top of the synchronization cover. The synchronization cover is installed in the circular through hole, and the outer end of the cover is closed by a cap.

[0011] The piston rod has a flange machined in the middle, and a sealing ring is installed on the side of the flange.

[0012] The piston rod has a threaded connection hole machined at one end extending out of the body.

[0013] The combustion chamber contains gunpowder.

[0014] The body has a regular polyhedral shape.

[0015] The beneficial effects of this invention are as follows: the high-pressure gas formed in the combustion chamber first pushes the synchronizing cover away from the piston rod through the gas orifice. Since the synchronizing cover only contacts the piston rod and its displacement direction is perpendicular to the piston rod, the synchronizing cover can push the piston rod at the moment the high-pressure gas fills the pressure chamber, and the piston rod can also extend out of the guide arm in time. Furthermore, separating the working chamber and the combustion chamber can ensure that only high-temperature gas enters the pressure chamber and will not be polluted by the flue gas formed during the combustion of the combustibles in the combustion chamber. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of the present invention;

[0017] Figure 2 This is a schematic diagram of the internal structure of the combustion chamber and pressure chamber of the present invention;

[0018] Figure 3 This is a schematic diagram of the piston rod structure of the present invention;

[0019] In the diagram: 1-body, 2-guide arm, 3-piston rod, 4-combustion chamber, 5-igniter, 6-synchronization cover, 7-port cover, 8-sealing ring, 9-bolt, 10-pressure chamber, 11-threaded connection hole, 12-gas port, 13-limiting groove. Detailed Implementation

[0020] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0021] A synchronous multi-linkage ignition working device includes a body 1, a pressure chamber 10 inside the body 1, and multiple piston holes communicating with the outside of the body 1; characterized in that: piston rods 3, multiple piston rods 3 are respectively installed in the piston holes; combustion chamber 4, the combustion chamber 4 is disposed on the body 1, the combustion chamber 4 and the pressure chamber 10 are connected through gas holes 12; igniter 5, the igniter 5 is installed on the combustion chamber 4 and seals the combustion chamber 4; synchronous cover 6, the synchronous cover 6 is disposed in the pressure chamber 10 and simultaneously limits the multiple piston rods 3, so that the multiple piston rods 3 extend out of the body 1 to the same length.

[0022] Furthermore, the piston holes are on the same plane, ensuring that the synchronizing cover 6 can simultaneously restrict the piston rod.

[0023] Furthermore, a guide arm 2 is installed at the outer end of the piston hole. The guide arm 2 has a stepped hole with the same diameter as the piston hole and coaxial with it. The piston hole guides the displacement of the piston rod, and the stepped hole can limit the flange on the piston rod to ensure that the stroke of the piston rod is fixed and consistent.

[0024] Furthermore, a limiting groove 13 is machined at one end of the piston rod 3 that extends into the body 1. The limiting grooves 13 on multiple piston rods 3 are combined into a circle, and the opening of the synchronizing cover 6 is locked in the limiting groove 13. The synchronizing cover 6 is locked in the limiting groove and is only in contact with the piston rod. When the synchronizing cover is subjected to pressure, it will disengage from all piston rods in time, ensuring that the piston rods extend out of the piston hole in time under the thrust of the high-pressure gas.

[0025] Furthermore, the gas vent 12 is machined on the front of the opening of the synchronizing cover 6. When ignited, the high-pressure gas generated in the combustion chamber will impact the synchronizing cover 6 from the front through the gas vent. The groove of the synchronizing cover can ensure that the impact force always stays in the groove of the synchronizing cover, thus accelerating the speed at which the synchronizing cover 6 disengages from the piston rod.

[0026] Furthermore, a circular through hole is machined on the side of the main body 1 opposite to the top of the synchronization cover 6. The synchronization cover 6 is installed in the circular through hole, and the diameter of the circular through hole and the synchronization cover are the same. This ensures that the synchronization cover will not shift and supports the synchronization cover so that it will not detach from the piston rod when shaking occurs. The outer end of the passage is sealed by the port cover 7 to prevent high-pressure gas leakage, which could lead to insufficient pressure in the pressure chamber. It also serves as a depressurization port and a reset port for the port cover during the wing retraction process.

[0027] Furthermore, a flange is machined in the middle of the piston rod 3, and a sealing ring 8 is installed on the side of the flange. The side of the flange and the piston hole are sealed by the sealing ring to prevent pressure leakage.

[0028] Furthermore, the piston rod 3 has a threaded connection hole 11 machined at one end extending outside the body 1. The threaded connection hole is used to connect to the aircraft wing surface.

[0029] Furthermore, the combustion chamber 4 contains gunpowder, which can burn instantly to release energy and rapidly generate high-pressure gas.

[0030] Furthermore, the body 1 has a regular polyhedron shape with flat surfaces, which facilitates the installation of the fire-operating device inside the aircraft.

[0031] Examples, such as Figure 1 As shown, this is a four-linkage ignition working device. The main body 1 is machined into a square shape. A piston hole is machined on each of the four end faces of the main body 1 to place the piston rod 3. A circular hole is machined on the rear end face to place the synchronization cover 6. At the same time, it also guides the displacement of the synchronization cover 6 under pressure, so as to prevent the synchronization cover from tilting and moving, which would prevent the piston rod from being unlocked synchronously. The piston hole and the circular hole are combined to form a pressure chamber 10. A groove is machined in the center of its front end face as a combustion chamber 4. Multiple gas holes 12 are evenly machined between the combustion chamber 4 and the pressure chamber. An igniter 5 is installed on the combustion chamber 4 to seal the combustion chamber.

[0032] like Figure 2 As shown, the synchronizing cover 6 is secured to the end of the piston rod 3, thus supporting the piston rod 3 and preventing it from sliding inside the piston bore. After ignition, when the high-pressure gas enters the pressure chamber, the synchronizing cover can easily and quickly disengage from the piston rod 3, simultaneously releasing the constraint on the four piston rods. This achieves the effect of synchronous extension of the piston rods.

[0033] like Figure 1 and 2 As shown, in order to prevent the piston rod 3 from deviating in stroke, a guide arm 2 is installed on each piston hole. A stepped hole is machined in the guide arm to form a limit between the piston on the piston rod and the step, thus fixing the stroke size of the piston rod 3.

[0034] like Figure 3 As shown, a threaded connection hole 11 is machined at the end of the piston rod 6, which is used to connect with the wing surface of the spacecraft.

[0035] This four-linkage ignition actuator is installed on a spacecraft. The piston rod heads are designed with threaded interfaces to connect to the spacecraft's wing surfaces. After the igniter supplies power, the gunpowder is ignited. The combustion of the gunpowder generates high-temperature, high-pressure gas, which enters the gas working chamber through the gas orifice. This high-temperature, high-pressure gas drives the synchronous ring cover to move. After the synchronous ring cover moves, it releases the constraints on the four piston rods. Driven by the high-temperature, high-pressure gas, the four piston rods move outward along their axes, thus deploying the four wing surfaces.

Claims

1. A synchronous multi-linkage firing mechanism, characterized in that, include: The main body (1) has a pressure chamber (10) inside and multiple piston holes that communicate with the outside of the main body (1). Piston rod (3), multiple piston rods (3) are respectively installed in piston holes; Combustion chamber (4) is installed on the main body (1), and the combustion chamber (4) and pressure chamber (10) are connected through gas combustion port (12); Ignition device (5), the ignition device (5) is installed on the combustion chamber (4) and seals the combustion chamber (4); Synchronous cover (6) is installed in the pressure chamber (10) to simultaneously limit multiple piston rods (3), so that the lengths of multiple piston rods (3) extending out of the body (1) are the same; The piston holes are on the same plane; A guide arm (2) is also installed at the outer end of the piston hole, and a stepped hole with the same diameter as the piston hole and coaxial is machined inside the guide arm (2); The piston rod (3) has a limiting groove (13) machined at one end that extends into the body (1). The limiting grooves (13) on multiple piston rods (3) are combined into a circle, and the opening of the synchronous cover (6) is locked in the limiting groove (13). The gas vent (12) is machined on the front of the opening of the synchronizing cover (6); The main body (1) has a circular through hole on one side relative to the top of the synchronization cover (6). The synchronization cover (6) is installed in the circular through hole, and the outer end of the through hole is closed by a cap (7). The piston rod (3) has a flange machined in the middle, and a sealing ring (8) is installed on the side of the flange; The piston rod (3) has a threaded connection hole (11) machined at one end extending outside the body (1); The combustion chamber (4) contains gunpowder; The body (1) has a regular polyhedron shape.

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