FIN locking system and method

Abstract

The invention relates to a fin locking system (FLS) and its method for locking the wings or fins in the systems and / or subsystems such as all kinds of guided-unguided (ballistic) missiles and ammunition guidance kits that are launched / released from aircrafts, unmanned aerial vehicles (UAVs) or their launcher platforms, intended to hit / destroy a target / region and used in homeland defence.

Description

[0001] FIN LOCKING SYSTEM AND METHOD

[0002] Technical Field

[0003] The invention relates to a system for locking the wings or fins of guided munitions and / or guided missiles before launch from the launcher platform.

[0004] The invention relates particularly to a fin locking system and its method for locking the wings or fins in the systems and / or subsystems such as all kinds of guided-unguided (ballistic) missiles and ammunition guidance kits that are launched / released from aircrafts, unmanned aerial vehicles (UAVs) or their launcher platforms, intended to hit / destroy a target / region and used in homeland defence.

[0005] State of the Art

[0006] Today, the fin locking system (FLS) is used to lock the wings or fins within the systems and / or subsystems such as all guided-unguided (ballistic) missiles and ammunition guidance kits that are launched from platforms such as aircrafts, unmanned aerial vehicles (UAVs) or launchers, used in the field of defence industry and intended to hit a target / region. It locks the wings or fins in the process from the transportation stage from various platforms to the stage of safe separation and activation of the guidance system and opens the wings or fins simultaneously with the activation of the guidance system, ensuring that the guided ammunition begins to be guided with accurate wing angles and position. If the wings or fins are not locked before guidance, it will be impossible for the ammunition to hit the target because the initially taken angular position reference, called transfer alignment, will be incorrect, or it will cause the ammunition to fall into undesirable positions off the target with a large deviation.

[0007] FLSs are used to lock the wings or fins within the systems and / or subsystems such as guided-unguided (ballistic) missiles and ammunition guidance kits that are launched from Aircrafts, Unmanned Aerial Vehicles (UAVs) or platforms such as Launchers and used in the field of defence industry. It locks the wings or fins in the process from the transportation stage from these platforms to the stage of store separation and activation of the guidance system and opens the wings or fins simultaneously with the activation of the guidance system, allowing the guided ammunition to start guidance with error-free (zero) wing angles.

[0008] In the existing solutions used in the literature, a separate locking mechanism is used for each wing or fin. Since these mechanisms are used to lock each wing, they work as a total of four different systems, with separate subunits for each wing / fin. This reduces reliability by approximately four times and increases costs at this rate. A malfunction that may occur in the motors or solenoids that drive each wing / fin may make it difficult for the guided missile or ammunition to hit the target due to the disabled wing, or even result in failure, even if the drivers connected to the remaining wings fulfil their duties. In case of failure, it may cause bomb-loaded ammunition to fall into friendly element areas and may even have devastating consequences. With this invention, since the system is driven by a single solenoid, pin puller or motor, reliability increases up to four times when the driver operates. In addition, while reliability increases, production costs are reduced by at least one fourth. A model that can be produced more easily, assembled more easily, and integrated into any ammunition system compared to the designs in use has come out.

[0009] Since existing designs consist of many parts and four units of each subsystem are needed for an ammunition (in case of 4-wing control), production, quality control, raw material and assembly labour costs increase to higher levels. While existing systems usually require a high-level operator to integrate, the LFS system can be easily integrated by a mid-level or even low-level assembly operator.

[0010] The invention numbered GB2355440A in the state of the art relates to mobile control fins for missiles carried on aircraft, and more specifically to a system that locks the fin against aerodynamic loads and prevents the transmission of these loads through the powertrain. Attached to an outer surface of the missile are a plurality of fins placed at 90-degree intervals around the perimeter of the missile. A plurality of locking pins are used here and are adapted to extend outwards from the outer surface of the missile.

[0011] The invention numbered US2006278754A1 in the state of the art relates to an apparatus and method for locking and unlocking missile control fins. Here, where the wings are mounted on a crank arm, there is a locking latch with a locking notch integral to the crank arm. The base plate also has a plurality of locking piston recesses, when one end of the locking piston is located in the locking piston recesses, the other end of the locking piston does not reach the locking notch and therefore the fins are unlocked. In the state of the art, some patent applications have been made for wing locking systems, and a few of these applications are given below.

[0012] The invention numbered US5950963A in the state of the art relates to a mechanism for locking the wings of the missile in place. The mechanism fixes the output shafts of the missile guidance fins and deactivates them when the missile is ready to launch. To unlock the wings, a rotatably mounted cam plate operates to lift cantilevered protrusions from slots in the output shaft cone gears.

[0013] The prior art invention numbered US6073880A relates to aerofin stabilized and controlled missiles and, more specifically, to a mechanism for deploying folded aerofins after missile launch. According to the invention, the slits are designed to be shared by aerofins, with pairs of aerofins deployed along shared longitudinal slits.

[0014] In the prior art, there are mechanisms that allow the fins of missiles to be locked against aerodynamic loads. However, since a single solenoid is driven by a pin puller or motor in these mechanisms, no locking mechanism in which the reliability quadruples when the driver works, the lock pins can operate without being exposed to any friction or jamming, and prevents it, by means of the four-bar mechanism, from being subjected to load perpendicular to any axis by pulling it in the direction of the pin axis, has been found.

[0015] The Aim of the Invention

[0016] In order to eliminate the disadvantages of the state of the art, one aim of the invention is to have a compact structure consisting of fewer parts than the systems used in the literature, which reduces production, storage, and assembly costs. Since having fewer parts reduces the total ammunition weight, this decrease can be used in the useful load to further increase the effectiveness of the ammunition.

[0017] Another aim of the invention is that FLS has higher reliability since it comprises fewer components than the prior art. While the system in prior art was driven by actuator systems such as four solenoids or pin pullers for each wing, in this technique, it can be driven by a single solenoid or pin puller. Therefore, reliability empirically quadruples. While a mid-level assembly operator can assemble this system, operators for the old system must be more competent and well trained.

[0018] Another aim of the invention is that while it cannot work at very low temperatures (- 40°C and below) due to friction, this system can work at the mentioned temperatures without difficulty.

[0019] Another aim of the invention is to ensure that while the system is exposed to forces perpendicular to the pin axis while pulling the pin during work and requires higher power to pull the pin against the resulting friction loads, it can be pulled in the direction of the pin axis and operate with lower power requirements without being exposed to a load perpendicular to any axis, hence friction and jamming by means of the special four-bar mechanism used in this invention.

[0020] Another aim of the invention is that although it was developed for four-wing controlled ammunition, the angle between the arms from 90° to 120° can be easily adapted to three-wing controlled systems. As the size of the ammunition grows, more powerful pyrotechnic systems, such as pin pullers instead of solenoids in ballistic missiles, can be easily adapted to the FLS system.

[0021] In existing systems, due to the low system response (Dynamic response) at the time of driving with the ammunition computer, time losses that may occur due to friction and similar obstacles during the unlocking process reduce the target sensitivity of the platform (Missile / ammunition). In relation to this, another aim of the invention is to provide higher hit sensitivity to the platform since the response time in FLS is much faster.

[0022] In order to provide the above advantages, the invention is a fin locking system (FLS) used to lock the wings or fins in the systems and / or subsystems such as all kinds of guided-unguided (ballistic) missiles, ammunition guidance kits launched from aircraft, unmanned aerial vehicles (UAVs) or their launcher platforms, intended to hit / destroy a target / region. Description of Drawings

[0023] Figure 1 is a half-sectional side view of the components of the fin locking system (FLS) that is the subject of the invention,

[0024] Figure 2 is the side view of the fin locking system (FLS) detail B that is the subject of the invention,

[0025] Figure 3 is the perspective view of the fin locking system (FLS) that is the subject of the invention,

[0026] Figure 4 is the ammunition integration and detail view of the fin locking system (FLS) that is the subject of the invention,

[0027] Figure 5a is the side view of locked state (1ststate) of the operating states of the fin locking system (FLS) that is the subject of the invention, and

[0028] Figure 5b is the side view unlocked state (2ndstate) of the operating states of the fin locking system (FLS) that is the subject of the invention.

[0029] Description of Reference Numbers:

[0030] 1 . Lock bearing

[0031] 2. Lock bolt

[0032] 3. Washer

[0033] 4. Fastened

[0034] 5. Lock pin

[0035] 6. Lock body

[0036] 7. Lock leverl

[0037] 8. Lock Iever2

[0038] 9. Linear slide

[0039] 10. Guide pin

[0040] 1 1 . Release spring

[0041] 12. Piston Ringl

[0042] 13. Solenoid chamber

[0043] 14. Solenoid core

[0044] 15. Solenoid chamber cap

[0045] 16. Piston Ring2 17. Fastened

[0046] 18. Fastener3

[0047] 19. Fastened

[0048] 20. Fin

[0049] 21 .Tail cone

[0050] 22. Fastener5

[0051] Detailed Description of the Invention

[0052] The invention is a fin locking system (FLS) used to lock the wings or fins in the systems and / or subsystems such as all kinds of guided-unguided (ballistic) missiles and ammunition guidance kits launched (released) from aircrafts, unmanned aerial vehicles (UAVs) and / or their launcher platforms, intended to hit (destroy) a target / region and to be used in homeland defence.

[0053] The FLS that is the subject of the invention basically consists of nineteen components, as shown in a half-sectional view in Figure 1 . The FLS locks the fin (20) by entering the holes corresponding to the fin (20) on the tail cone (21 ) mounted on the tail part of the ammunition, as shown in Figure 4. The entire FLS is mounted on the tail cone (21 ) by 8 fastening elements (22) (Figure 4).

[0054] Thus, the integration of FLS with ammunition is ensured. FLS has two different operating states. To briefly summarise these states:

[0055] In State 1 shown in Figure 5a, the system is closed (no current has flowed to the Solenoid), that is, the Solenoid is at top dead centre, or the lock is in the open position. By providing current to the solenoid by the power unit, the solenoid core (14) is pushed linearly in the x-axis direction by the electric current-induced magnetic force in the tube located in the solenoid chamber (13) (Figure 5a).

[0056] While the solenoid core (14) moves linearly in the solenoid chamber (13), it moves the guide pin (10) horizontally in the linear slide (9) in the -x axis direction. The lock bolt (2), which is connected to the guide pin (10) with its piston ringl (12), also moves horizontally in the -x axis direction. The lock leverl (7) part, which is connected to the lock bolt (2) with the help of equally spaced circumferential fastened (4) and piston ring2 (16), also moves horizontally in the -x axis direction (Figure 5a). Meanwhile, the four fins (20) are locked by the guide pins (10). The connections and assembly operations of the fin locking system are provided by fasteners (4, 17, 18, 19, 22), washer (3), and piston rings (12, 16). It connects the four-rod mechanism consisting of lock bearing (1 ), lock pin (5), lock leverl (7) and lock Iever2 (8), linear slide (9) and guide pin (10) to the lock body (6). Washer (3) was used to remove the gaps within the entire mechanism and to reduce surface friction where they are used. There are 16 fastened (4) in total and the lock pin (5) is used to freely connect the lock leverl (7) and lock Iever2 (8) without rubbing against each other. The fastened (4) is locked by means of the piston ring2 (16) attached to the channel on it, preventing them from moving out of place. The lock pin (5) moves back and forth within the hole on the lock body (6) and locks or unlocks the wings by entering the channels opened on the ammunition wings, as shown in Figure 2.

[0057] The lock body (6) is a part that holds the entire structure in the fin locking system by means of the fastened (17) and fasteners (18) and provides the integration interface with the ammunition. It connects the lock Iever2 (8), lock leverl (7) and lock bearing (1 ) to each other using fastenertl (4), washer (3) and piston ring2 (16), thus ensuring that the four-rod mechanism operates on the axis of the lock pin (5).

[0058] As shown in Figure 5a, the release spring (11 ) constantly keeps the mechanism under a much lower pressure force than the solenoid, preventing it from working with backlash, as it moves from state 1 , in which the wings are locked, to state 2, in which the wings are open. In this way, the whole system works more healthily. It connects the solenoid chamber cap (15), solenoid chamber (13) and solenoid core (14) to the lock body (6) via the fastened (17) bolts.

[0059] In State 2 shown in Figure 5b, the system is on. That is, the lock is in the closed position. By providing current to the solenoid by the power unit, the solenoid core (14) is pushed linearly by electrical force within the tube located in the solenoid chamber (13). While the solenoid core (14) moves linearly in the solenoid chamber (13), it moves the guide pin (10) horizontally in the linear slide (9) in the +x axis direction. The lock bolt (2), which is connected to the guide pin (10) with piston ringl (12), also moves horizontally in the +x direction. The lock leverl (7) part, which is connected to the lock bolt (2) with the help of equally spaced circumferential fastened (4) and piston ring2 (16), also moves horizontally in the +x direction. Meanwhile, the guide pins (10), which entered the channels on the fin (20) in state 1 , come out at the same time, separating the fins from the tail cone (21 ) and making them free (Figure 4. DETAIL B). At this stage, the ammunition begins navigation, that is, the process of precise position control, and remains in this position as long as the ammunition flies.

Claims

CLAIMS1. A fin locking system to lock the wings or fins within the systems and / or subsystems such as guided-unguided (ballistic) missiles or ammunition guidance kits, comprising:• Lock bearing (1 ), which connects the four-rod mechanism consisting of lock pin (5), lock leverl (7) and lock Iever2 (8), linear slide (9) and guide pin (10) to the lock body (6),• Lock bolt (2), which moves horizontally in the +x direction, and is connected to the guide pin (10) with piston ring 1 (12),• Lock pin (5), which moves back and forth within the hole on the lock body (6) and enters the channels opened on the ammunition wings, allowing the wings to be locked or unlocked,• Lock body (6) which holds the fin locking system on top with the fastened (17) and fasteners (18) and provides the integration interface with the ammunition,• Lock leverl (7), which is connected to the lock bolt (2) circumferentially with equal spacing with the help of fastened (4) and piston ring2 (16), and can move horizontally in the -x and +x axis directions,• Lock Iever2 (8), which connects the lock leverl (7) and the lock bearing (1 ) using fastened (4), washer (3) and piston ring2 (16), thus enabling the four-rod mechanism to operate on the axis of the lock pin (5),• Linear slide (9) that allows the guide pin (10) to move horizontally in the direction of -x axis and +x axis,• Guide pin (10) that ensures the locking of the fin (20), which enables the lock bolt (2) connected to the guide pin (10) with piston ringl (12) to move horizontally in the direction of the -x axis,• Release spring (11 ) that prevents the mechanism from working with backlash by constantly keeping the mechanism under a lower pressure force than the solenoid when changing from the state in which the wings are locked to the state in which the wings are open,• Solenoid chamber (13) containing the solenoid core (14),• Solenoid core (14) that is located in the solenoid chamber (13), moves the guide pin (10) horizontally in the linear slide (9) in the -x axis direction by moving linearly, and moves the guide pin (10) horizontally in the linear slide (9) in the +x axis direction by moving linearly,• Solenoid chamber cap (15) which connects the solenoid chamber (13) and the solenoid core (14) to the lock body (6) via the fastened (17) bolts, and• Tail cone (21 ) of the fin locking system, which is mounted on the tail part of the ammunition and enables the fin (20) to be locked by entering the holes corresponding to the fin (20) on it.

2. A fin locking method to lock the wings or fins (2) that are within the systems and / or subsystems such as guided-unguided (ballistic) missiles and ammunition guidance kits, integrated with ammunition fired from aircraft, UAVs or their launcher platforms, have two different operating states, can be driven with a single solenoid or pin puller, and can operate at temperatures of -40°C and below, comprising the process steps of:• pushing the solenoid core (14) in the -x axis direction by the magnetic force originating from the electric current in the tube located in the solenoid chamber (13) when the system is closed, by providing current to the solenoid by the power unit in the solenoid top dead centre or unlocked position,• moving the guide pin (10) horizontally in the linear slide (9) in the x-axis direction by the solenoid core (14) while it moves linearly in the solenoid chamber (13),• the guide pin (10) moving horizontally in the -x axis direction of the lock slider (2) connected with the piston ringl (12),• the lock leverl (7), which is connected to the lock bolt (2) circumferentially with the help of equally spaced fastened (4) and piston ring2 (16), moving horizontally in the -x axis direction,• locking the four fins (20) by pins (10),• pushing the solenoid core (14) is pushed linearly when the system is open and the lock is in the closed position, by electrical force in the tube located in the solenoid chamber (13), by providing current to the solenoid by the power unit,• the solenoid core (14) moving the guide pin (10) horizontally in the linear slide (9) in the +x axis direction while it moves inside the solenoid chamber (13) linearly,• the lock slider (2), which is connected to the guide pin (10) with piston ringl (12), moving horizontally in the +x direction,• the lock leverl (7), which is connected to the lock bolt (2) with the help of equally spaced circumferential fastened (4) and piston ring2 (16), moving horizontally in the +x direction,• the guide pins (10) inserted into the channels on the fin (20) coming out simultaneously and separating the fins from the tail cone (21 ) and releasing them, and• locking the fin (20) by entering the holes corresponding to the fin (20) on the tail cone (21 ) mounted on the tail section of the ammunition.

3. System according to Claim 1 , comprising the solenoid core (14) that ensures that the solenoid is pushed linearly by electrical force in the tube located in the solenoid chamber (13) by providing current to the solenoid by the power unit when the system is in the open position and the lock is in the closed position.

4. System according to Claim 1 , comprising the solenoid core (14) that allows the solenoid to be pushed linearly in the -x axis direction by the magnetic force originating from electric current in the tube located in the solenoid chamber (13) by providing current to the solenoid by the power unit when the system is off, and the solenoid is in the top dead centre or unlocked position.

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