A rudder wing deployment fire-powered device based on a rolling screw pair

Abstract

The present invention discloses a pyrotechnic device for deploying rudder blades based on a rolling screw pair. The device comprises an outer cylinder, a sleeve, a rotating rod, a rear end cover, a honeycomb, a connecting rod, a front end cover, steel balls, and a pyrotechnic device. The outer cylinder has a three-way structure, with chambers A and B communicating, and a throttle hole provided at the bottom of chamber C. The outer cylinder is threadedly connected to the projectile body via a mounting flange. The sleeve, rotating rod, connecting rod, and honeycomb are enclosed within chambers A and B of the outer cylinder via front and rear end covers, which are respectively threadedly connected to the ends of the outer cylinder. The sleeve and rotating rod are located within chamber A. The other end of the rotating rod is nested with the sleeve, with several steel balls provided between the rotating rod and the sleeve. The connecting rod and honeycomb are located within chamber B. The pyrotechnic device comprises an igniter and gunpowder. The gunpowder is located within chamber C. The igniter is located above the gunpowder and is threadedly connected to the outer cylinder. The present invention can simultaneously achieve the functions of locking the rudder blade, rotating and deploying it, and separating it from the rudder shaft retraction.

Description

Technical Field

[0001] The invention belongs to the technical field of pyrotechnic devices, and in particular relates to a pyrotechnic device for deploying rudder blades based on a rolling screw pair. Background Art

[0002] Pyrotechnic actuators are widely used in the military and aerospace fields. They rely on the high-temperature and high-pressure gas released by the combustion of gunpowder to drive the load movement and ultimately complete the predetermined action.

[0003] An actuator is a type of pyrotechnic actuator that converts the energy generated by gunpowder combustion into force and displacement, thereby achieving movement of connected components. Actuators that output axial displacement are the most common and are widely used in missile folding rudder deployment systems. They are a key factor influencing the proper deployment of the rudders, their speed, impact, and reliability. Currently, rudder deployment systems that use an actuator as a drive source typically place the actuator within the rudder shaft and utilize a spiral structure to achieve rudder deployment. This arrangement suffers from common drawbacks such as system complexity, significant impact upon deployment, and a large system size and weight, hindering the lightweight and miniaturization of the rudders. Summary of the Invention

[0004] The technology of the present invention solves the problem: overcomes the shortcomings of the existing technology, and provides a rudder wing deployment fire-operated device based on a rolling screw pair, which can simultaneously realize the rudder wing locking, rotational deployment and retraction and separation functions from the rudder shaft.

[0005] In order to solve the above technical problems, the present invention discloses a pyrotechnic actuating device for deploying rudder blades based on a rolling screw pair, comprising: an outer cylinder, a sleeve, a rotating rod, a rear end cover, a honeycomb, a connecting rod, a front end cover, a steel ball and a pyrotechnic device;

[0006] The outer cylinder is a three-way structure, including: cavity A, cavity B and cavity C; wherein, cavity A and cavity B are connected; a throttle hole is provided at the bottom of cavity C to achieve the communication between cavity C, cavity A and cavity B; the outer cylinder is screwed to the elastic body through the mounting flange;

[0007] The sleeve, rotating rod, connecting rod, and honeycomb are encapsulated in cavities A and B of the outer tube via the front and rear covers. The front and rear covers are respectively connected to the ends of the outer tube via threads. The sleeve and rotating rod are located in cavity A: one end of the rotating rod is a straight key that plugs into the rudder wing; the other end of the rotating rod is nested with the sleeve, and several steel balls are provided between the rotating rod and the sleeve to form a rolling spiral pair. The connecting rod and honeycomb are located in cavity B: one end of the connecting rod is threadedly connected to the sleeve, and a honeycomb is provided between the other end of the connecting rod and the rear cover.

[0008] The pyrotechnic device includes an igniter and gunpowder, wherein the gunpowder is located in a cavity C; the igniter is located above the gunpowder and is connected to the outer tube through threads.

[0009] In the above-mentioned rudder wing deployment fire-operated actuator based on a rolling spiral pair, the sleeve and the rotating rod are connected through a steel ball. A steel ball groove is provided in the circumferential direction of the sleeve for axially constraining the steel ball, and the rotating rod is provided with a spiral groove for realizing rotational motion under the action of the steel ball.

[0010] In the above-mentioned pyrotechnic device for deploying rudder blades based on a rolling spiral pair, the throttle hole is used to control the speed at which the gas flows into the low-pressure chamber to improve the working stroke of the pyrotechnic device and the energy utilization rate of the gunpowder; wherein the low-pressure chamber is a cavity formed by the connecting rod, the sleeve and the cavity B.

[0011] In the above-mentioned rudder wing deployment fire-operated device based on a rolling helical pair, N motion guide grooves are provided inside the cavity A of the outer tube; N lugs A are provided circumferentially of the sleeve; N lugs B are provided circumferentially of the part of the rotating rod that is not nested with the sleeve; the rotating rod is ensured to rotate to a specified angle by controlling the positional relationship between the motion guide groove and the lug B; after the rotating rod and the sleeve are connected by nesting steel balls, the lug A on the sleeve is aligned with the motion guide groove and inserted into the outer tube to offset the rotational torque caused by the helical pair; at the same time, the lug B on the rotating rod is restricted to the end face O of the motion guide groove to offset the axial tension caused by the helical pair; the notch of the motion guide groove is provided with a guiding slope.

[0012] In the above-mentioned pyrotechnic device for deploying the rudder wing based on a rolling spiral pair, before the pyrotechnic device is ignited, the honeycomb provides initial support force to ensure that the sleeve, rotating rod, connecting rod and outer cylinder do not move relative to each other, and at the same time the traditional shear pin structure is removed to avoid the impact caused by the shear pin shearing; after the pyrotechnic device is ignited, the gas acts on the connecting rod, and the connecting rod squeezes the honeycomb. As the honeycomb collapses, the speed of the sleeve, rotating rod and connecting rod gradually decreases, thereby reducing the impact of the pyrotechnic device on the rudder wing.

[0013] The above-mentioned rudder wing deployment fire-operated actuator based on a rolling spiral pair also includes: O-ring A and O-ring B; wherein, O-ring A is installed between the mating surface of the sleeve and the outer tube, and O-ring B is installed between the mating surface of the connecting rod and the outer tube, thereby realizing the sealing of the entire three-way structure to the gas.

[0014] In the above-mentioned pyrotechnic actuator for deploying the rudder blades based on the rolling helical pair, the helical lead of the rotating rod is 49.5 mm, the axial length corresponding to a rotation of 103° is 14.23 mm, and the helical pitch angle is 50°.

[0015] In the above-mentioned rudder wing deployment fire-operated actuator based on the rolling screw pair, the maximum rotation angle of the rotating rod is 103° and the maximum retraction stroke is 10 mm.

[0016] In the above-mentioned pyrokinetic actuator for deploying rudder blades based on a rolling screw pair, the honeycomb is a non-porous aluminum honeycomb, and the strength of the honeycomb buffer compression section is 5 to 15 MPa.

[0017] In the above-mentioned pyrotechnic device for deploying rudder blades based on a rolling screw pair, the gunpowder is a slow-burning agent DR-5.

[0018] The present invention has the following advantages:

[0019] (1) The present invention discloses a pyrotechnic device for deploying rudder wings based on a rolling screw pair. The rolling screw technology is applied to conventional pyrotechnic devices. Through structural design, the pyrotechnic device can simultaneously realize the rotation of the rudder wings and the separation from the rudder shaft during operation. The device can avoid the complicated design of the conventional missile wing deployment method that requires the combination of multiple mechanisms to realize the deployment of the rudder wings. The pyrotechnic device has the characteristics of compact structure, easy installation, high reliability, and low impact on the installation part of the missile body.

[0020] (2) The present invention discloses a pyrotechnic device for deploying rudder blades based on a rolling helical pair. Through the gas circulation and buffering design, not only is the throttling and dispersion of the gas achieved, making the gas action more moderate and thus reducing the impact, but also the use of honeycombs to provide support, eliminating the traditional shear pin structure, and achieving a buffering effect for the moving parts through the energy absorption of the honeycombs. Compared with existing traditional pyrotechnic devices, the impact of the pyrotechnic device on the projectile during operation is significantly reduced.

[0021] (3) The present invention discloses a pyrotechnic device for unfolding rudder wings based on a rolling screw pair, in which the internal moving parts are initially limited by honeycombs. According to the movement characteristics and requirements of the rudder wings, the rotation angle and retraction distance of the pyrotechnic device can be adaptively adjusted by designing and selecting honeycombs with appropriate crushing strength, which greatly improves the applicability and versatility of the pyrotechnic device. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic structural diagram of a pyrotechnic actuating device for deploying rudder blades based on a rolling helical pair according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of a state before operation of a rudder blade deployment fire-operated actuating device based on a rolling screw pair according to an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of a state of a rudder blade deployment fire-operated device based on a rolling screw pair after operation in an embodiment of the present invention;

[0025] Figure 4 This is a schematic structural diagram of an outer cylinder in an embodiment of the present invention;

[0026] Figure 51 is a schematic structural diagram of a sleeve according to an embodiment of the present invention;

[0027] Figure 6 It is a structural schematic diagram of a rotating rod in an embodiment of the present invention. DETAILED DESCRIPTION

[0028] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be described in further detail below with reference to the accompanying drawings.

[0029] One of the core ideas of the present invention is to disclose a fire-operated actuator for rudder wing deployment based on a rolling screw pair to overcome the shortcomings of the traditional rudder wing deployment system that uses an actuator as a driving source. The fire-operated actuator described in the present invention is external to the rudder wing system and is connected to the rudder shaft only by a straight key, which greatly simplifies the installation process; and through structural design, the fire-operated actuator can simultaneously realize the rotation of the rudder wing and separation from the rudder shaft during operation. The fire-operated actuator described in the present invention has the function of "rotation output-retraction separation", which greatly reduces the structural complexity of the current traditional rudder wing deployment system, and has the advantages of compact structure, convenient layout, small impact on the installation part of the projectile, and high reliability.

[0030] like Figures 1 to 4 In this embodiment, the pyrotechnic device for deploying rudder blades based on a rolling helical pair comprises an outer tube 1, a sleeve 2, a rotating rod 3, a rear end cover 8, a honeycomb 9, a connecting rod 10, a front end cover 11, a steel ball 12, and a pyrotechnic device. The outer tube 1 is a three-way structure, comprising: cavity A, cavity B, and cavity C; cavity A and cavity B are connected; a throttle hole is provided at the bottom of cavity C to connect cavity C with cavities A and B; the outer tube 1 is threadedly connected to the projectile via a mounting flange. The sleeve 2, rotating rod 3, connecting rod 10, and honeycomb 9 are encapsulated within cavities A and B of the outer tube 1 via a front end cover 11 and a rear end cover 8. The front end cover 11 and the rear end cover 8 are respectively threadedly connected to the ends of the outer tube 1. Sleeve 2 and rotating rod 3 are located within cavity A. One end of rotating rod 3 is a key that plugs into the rudder wing; the other end of rotating rod 3 nests within sleeve 2, with several steel balls 12 positioned between them, forming a rolling helical pair. Connecting rod 10 and honeycomb 9 are located within cavity B. One end of connecting rod 10 is threadedly connected to sleeve 2, while honeycomb 9 is positioned between the other end of connecting rod 10 and rear end cap 8. The pyrotechnic device comprises an igniter 5 and gunpowder 6. Gunpowder 6 is located within cavity C. Igniter 5 is positioned above gunpowder 6 and is threadedly connected to outer cylinder 1.

[0031] In this embodiment, the sleeve 2 and the rotating rod 3 are connected through the steel ball 12. The sleeve 2 is provided with a steel ball groove in the circumferential direction for axially constraining the steel ball 12. The rotating rod 3 is provided with a spiral groove for realizing rotational motion under the action of the steel ball 12.

[0032] In this embodiment, the throttle hole is mainly used to control the speed of the gas flowing into the low-pressure chamber to improve the working stroke of the pyrotechnic device and the energy utilization rate of the gunpowder; wherein the low-pressure chamber refers to: the cavity formed by the connecting rod 10, the sleeve 2 and the cavity B.

[0033] In this embodiment, if Figure 5 and Figure 6 The cavity A of the outer cylinder 1 is provided with N motion guide grooves 13; the sleeve 2 is provided with N circumferential lugs A14; and the portion of the rotating rod 3 not nested with the sleeve 2 is provided with N circumferential lugs B15. The positional relationship between the motion guide grooves 13 and the lugs B15 is controlled to ensure that the rotating rod 3 rotates to a specified angle. After the rotating rod 3 and the sleeve 2 are nested and connected via the steel ball 12, the lugs A14 on the sleeve 2 are aligned with the motion guide grooves 13 and inserted into the outer cylinder 1. At the same time, the lugs B15 on the rotating rod 3 are confined to the end surface O of the motion guide groove 13 to offset the axial tension caused by the helical pair. It should be noted that In order to ensure the structural strength of the lugs B15 on the rotating rod 3, the value of N can be 3, that is, the three motion guide grooves 13, the three lugs A14, and the three lugs B15 are all evenly distributed.

[0034] In this embodiment, in order to ensure that the rotating rod 3 can retract reliably after being rotated into position, the motion guide groove 13 has a guiding slope to prevent the ear B15 on the rotating rod 3 from rotating "out of bounds" after rotating to a specified angle.

[0035] In this embodiment, before the pyrotechnic device is ignited, the honeycomb 9 provides initial support, ensuring that the sleeve 2, rotating rod 3, connecting rod 10, and outer cylinder 1 do not move relative to each other. This eliminates the traditional shear pin structure, preventing the impact caused by shear pin shearing. After the pyrotechnic device is ignited, the gas acts on the connecting rod 10, which squeezes the honeycomb 9. As the honeycomb 9 collapses, the speed of the sleeve 2, rotating rod 3, and connecting rod 10 gradually decreases, thereby reducing the impact of the pyrotechnic device on the rudder blade. Preferably, the honeycomb 9 can be made of non-porous aluminum honeycomb, and the strength of the honeycomb buffer compression section is 5 to 15 MPa.

[0036] In this embodiment, the helical lead of the rotating rod 3 is 49.5 mm, the corresponding axial length of 103° rotation is 14.23 mm, and the helix angle is 50°. In practice, an appropriate helix angle can be selected based on the structural layout. The helix angle should be no less than 45°. A larger helix angle reduces effort and increases stability in the mechanism.

[0037] In this embodiment, the maximum rotation angle of the rotating rod 3 is 103°, and the maximum retraction stroke is 10 mm. In practice, the honeycomb 9 with a specific crushing strength can be designed and selected according to the working conditions so that the rotation angle and retraction stroke of the rotating rod 3 meet the use requirements.

[0038] In this embodiment, the helical pair of rotating rod 3 converts internal linear motion into rotational motion. To reduce resistance to the rotational motion of rotating rod 3, the helical pair is configured as a rolling helical structure. To ensure smooth helical motion and uniform force distribution, the number of helical threads in rotating rod 3 is set at six. In practice, the appropriate number of threads can be selected based on the structural layout; a greater number of threads results in smoother mechanism operation and more uniform force distribution in the spiral grooves.

[0039] In this embodiment, the number of steel balls 12 in each row is determined to be 6 according to the number of spiral ends of the rotating rod 3. Due to the limitation of the axial size of the structure, the steel balls 12 are set to 1 row. In practice, the load capacity of the rolling spiral pair can be improved by increasing the number of rows of steel balls.

[0040] In this embodiment, in order to minimize the impact after starting and actuating, the actuation time cannot be too short, and the gunpowder 6 can be selected from the slow-burning agent DR-5.

[0041] In this embodiment, the pyrotechnic actuator for deploying the rudder blades based on a rolling helical pair also includes O-rings A4 and B7. O-ring A4 is installed between the mating surfaces of the sleeve 2 and the outer tube 1, and O-ring B7 is installed between the mating surfaces of the connecting rod 10 and the outer tube 1, thereby ensuring a gas-tight seal across the entire three-way structure.

[0042] In this embodiment, the working principle of the rudder wing deployment fire-driven device based on the rolling screw pair is as follows:

[0043] In the initial state, the rotating rod 3 is confined in the axial space enclosed by the motion guide groove 13 and the front end cover 11, and the relative movement of the rotating rod 3, sleeve 2, connecting rod 10 and outer tube 1 is restricted by the honeycomb 9, thereby limiting the initial rotation of the rudder wing and bearing a certain initial load.

[0044] In working state, a) the igniter 5 ignites after receiving the ignition command, igniting the gunpowder 6. The high-temperature, high-pressure gas generated by the combustion of the gunpowder 6 flows through the throttle hole and acts on the annular surface of the connecting rod 10. With the cooperation of the lug A14 on the sleeve 2 and the motion guide groove 13, the axial movement of the connecting rod 10-sleeve 2 is realized. b) The movement of the connecting rod 10 compresses the honeycomb 9 to reduce the impact. At the same time, the pre-installed steel ball 12 in the sleeve 2 cooperates with the lug B15 on the rotating rod 3 to rotate the rotating rod 3 in place, thereby driving the rudder blade to rotate. c) When the rotating rod 3 rotates to the specified angle, the lug B15 on the rotating rod 3 falls into the motion guide groove 13, the axial limit of the rotating rod 3 is released, and the radial limit takes effect. As a result, the rotating rod 3 contracts inwardly under the action of the steel ball 12 along with the axial movement of the connecting rod 10-sleeve 2 assembly. When the contraction exceeds a certain distance, the connection between the rotating rod 3 and the rudder shaft is released to achieve separation.

[0045] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

[0046] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in this field.

Claims

1. A rudder blade deployment fire-powered device based on a rolling screw pair, characterized in that: include: An outer cylinder (1), a sleeve (2), a rotating rod (3), a rear end cover (8), a honeycomb (9), a connecting rod (10), a front end cover (11), a steel ball (12) and a pyrotechnic device; The outer cylinder (1) is a three-way structure, comprising: a cavity A, a cavity B and a cavity C; wherein the cavity A and the cavity B are connected; a throttle hole is provided at the bottom of the cavity C to realize the connection between the cavity C and the cavity A and the cavity B; the outer cylinder (1) is screwed to the elastic body through a mounting flange; N motion guide grooves (13) are provided inside the cavity A of the outer cylinder (1); N support ears A (14) are provided circumferentially on the sleeve (2); N support ears B (15) are provided circumferentially on the portion of the rotating rod (3) not nested with the sleeve (2); by controlling the motion guide groove ( The positional relationship between the lug A (13) and the lug B (15) ensures that the rotating rod (3) rotates at a specified angle; after the rotating rod (3) and the sleeve (2) are nested and connected through the steel ball (12), the lug A (14) on the sleeve (2) is aligned with the motion guide groove (13) and inserted into the outer cylinder (1) to offset the rotational torque caused by the spiral pair; at the same time, the lug B (15) on the rotating rod (3) is restricted to the end face O of the motion guide groove (13) to offset the axial tension caused by the spiral pair; the notch of the motion guide groove (13) is provided with a guiding inclined surface; The sleeve (2), the rotating rod (3), the connecting rod (10) and the honeycomb (9) are encapsulated in the cavity A and the cavity B of the outer tube (1) through the front end cover (11) and the rear end cover (8), and the front end cover (11) and the rear end cover (8) are respectively connected to the two ends of the outer tube (1) through threads; wherein, the sleeve (2) and the rotating rod (3) are located in the cavity A: one end of the rotating rod (3) is a straight key, which is plugged into the rudder wing; the other end of the rotating rod (3) is nested and installed with the sleeve (2), and the rotating rod (3) and the sleeve (2) are connected. A plurality of steel balls (12) are provided to form a rolling spiral pair; the sleeve (2) and the rotating rod (3) are connected via the steel balls (12); a steel ball groove is provided in the circumferential direction of the sleeve (2) for axially constraining the steel balls (12); and the rotating rod (3) is provided with a spiral groove for realizing rotational motion under the action of the steel balls (12); the connecting rod (10) and the honeycomb (9) are located in the cavity B: one end of the connecting rod (10) is threadedly connected to the sleeve (2), and a honeycomb (9) is provided between the other end of the connecting rod (10) and the rear end cover (8); The pyrotechnic device comprises an igniter (5) and gunpowder (6); wherein the gunpowder (6) is located in a cavity C; the igniter (5) is located above the gunpowder (6) and is connected to an outer cylinder (1) through a thread.

2. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: The throttle hole is used to control the speed of the gas flowing into the low-pressure chamber to improve the working stroke of the pyrotechnic device and the energy utilization rate of the gunpowder; wherein the low-pressure chamber is a cavity formed by the connecting rod (10), the sleeve (2) and the cavity B.

3. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: Before the pyrotechnic device is ignited, the honeycomb (9) provides an initial supporting force to ensure that the sleeve (2), the rotating rod (3), the connecting rod (10) and the outer cylinder (1) do not move relative to each other, and at the same time, the traditional shear pin structure is removed to avoid the impact caused by the shear pin shearing; after the pyrotechnic device is ignited, the gas acts on the connecting rod (10), and the connecting rod (10) squeezes the honeycomb (9). As the honeycomb (9) is crushed, the speed of the sleeve (2), the rotating rod (3) and the connecting rod (10) gradually decreases, thereby reducing the impact of the pyrotechnic device on the rudder wing.

4. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: The invention also includes: an O-ring A (4) and an O-ring B (7); wherein the O-ring A (4) is installed between the matching surfaces of the sleeve (2) and the outer cylinder (1), and the O-ring B (7) is installed between the matching surfaces of the connecting rod (10) and the outer cylinder (1), thereby achieving sealing of the entire three-way structure against gas.

5. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: The spiral lead of the rotating rod (3) is 49.5 mm, the axial length corresponding to a rotation of 103° is 14.23 mm, and the spiral lead angle is 50°.

6. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: The maximum rotation angle of the rotating rod (3) is 103°, and the maximum retraction stroke is 10 mm.

7. The pyrotechnic actuator for rudder blade deployment based on a rolling screw pair according to claim 1, characterized in that: The honeycomb (9) is a non-porous aluminum honeycomb, and the strength of the honeycomb buffer compression section is 5 to 15 MPa.

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