Quickly assembled internal weapon mounting device

Abstract

A rapidly assembleable internal weapon mounting device includes a self-positioning pylon lock, a lifting mechanism, and a flexible, variable-configuration weapon pylon. The self-positioning pylon lock is installed on the aircraft reinforcement frame structure of the internal weapons bay, and a lifting mechanism is installed on one side of the aircraft reinforcement frame structure of each self-positioning pylon lock. The self-positioning pylon lock and the lifting mechanism are connected to the flexible, variable-configuration weapon pylon, which allows for rapid configuration changes and pre-prepared weapon mounting for quick modular installation during combat. Simultaneously, the internal weapon mounting device has a small overall size, allowing for the mounting of more weapons of various sizes within the same internal weapons bay size. For the same payload, the internal weapons bay volume can be reduced by approximately 15%, improving the aircraft's aerodynamic and stealth performance.

Description

Technical Field

[0001] This invention relates to the field of aircraft mounting equipment technology, and more particularly to a rapidly assembleable internal weapon mounting device. Background Technology

[0002] Currently, aircraft equipped with internal weapons bays, such as the F / A-22 and F-35, are high-end fighter jets with stealth, supersonic cruise, high maneuverability, and short takeoff and landing capabilities. The use of internal weapons bays helps reduce external components, resulting in a cleaner aircraft shape, reduced aerodynamic drag and radar cross-section, and improved combat performance.

[0003] Internal weapon bays typically carry weapons with folding wings or small precision-guided weapons. The weapons can be launched either directly from inside the bay or via rails extending outside the bay. Correspondingly, there are three types of weapon mounting devices: telescopic weapon mounting devices, door-rotating weapon mounting devices, and integrated composite weapon mounting devices. However, all three types of internal weapon mounting devices have shortcomings, as detailed below.

[0004] Telescopic weapon mounting systems typically consist of structural beams, front and rear cantilever arms, rotary hinges, hydraulic actuators and valves, and missile launchers. Power is output through the hydraulic actuators, causing the front and rear cantilever arms to rotate and extend the missile launcher out of the internal weapons bay. This type of system has many components and a complex structure, resulting in high costs. The structural beams, front and rear cantilever arms, hydraulic actuators, and valves all need to be connected to the top structure of the aircraft's internal weapons bay. During use, the front and rear cantilever arms need to rotate and straighten, and the hydraulic actuators need to push the missile launcher out of the internal weapons bay, occupying a large space and having complex structural connections, which is not conducive to modular design. When selecting and replacing weapons with direct catapult or rail-launched versions, the missile launcher needs to be replaced. Because the missile launcher, front and rear cantilever arms, and hydraulic actuators all use multi-point rotary hinges, the replacement workload is large, the connections are complex, and flexible and rapid assembly is not possible.

[0005] The hatch-mounted rotating weapon system cleverly utilizes the rotation of the hatch to rotate the pylon to the outside of the hatch. By using the rotational action of the internal weapon hatch, the weapon is directly connected to the hatch. It shares a set of rotational actuation mechanisms with the hatch, thereby reducing the number of components in the internal weapon system and improving reliability. However, this also requires the weapon hatch and its rotational actuation mechanism to be designed to be strong and large enough, which also increases costs. The weapon hatch is difficult to withstand the normal load brought by ejection, and cannot achieve modular replacement and flexible and rapid assembly of mounted weapons.

[0006] The integrated composite weapon mounting device contains only one integrated mounting device, which effectively reduces the number of structural components; however, in order to meet the needs of multi-launcher mounting, it is necessary to take into account the mounting of weapons in multiple directions, which leads to an imbalance in structural force transmission. The integrated composite weapon mounting device has a complex internal structure, large size and weight, and low utilization rate of internal ammunition compartment space; at the same time, due to its large size and weight, it cannot achieve flexible and rapid assembly. Summary of the Invention

[0007] The technical problem solved by the present invention is to provide a rapidly assembleable internal weapon mounting device to solve the problems in the background art mentioned above.

[0008] The technical problem solved by this invention is achieved by the following technical solution:

[0009] A rapidly assembleable internal weapon mounting device includes a self-positioning pylon lock, a lifting mechanism, and a flexible, variable-configuration weapon pylon. The self-positioning pylon lock is installed on the aircraft reinforcement frame structure of the internal weapons bay, and a lifting mechanism is installed on the aircraft reinforcement frame structure on one side of each self-positioning pylon lock. The self-positioning pylon lock and the lifting mechanism are respectively connected to the flexible, variable-configuration weapon pylon. The specific structure is as follows:

[0010] The self-positioning beam lock includes a guide positioning pin, a hook, a beam lock connecting base, and a beam lock housing. The beam lock connecting base is installed on the aircraft reinforcing frame structure. The beam lock housing, which contains the beam lock, is installed on the beam lock connecting base. The beam lock is equipped with a hook for hooking the beam. The bottom of the beam lock housing is equipped with a guide positioning pin. After being guided and positioned by the guide positioning pin, the hook hooks the beam, so that the beam is tightly pressed against the beam lock housing and the guide positioning pin, thereby realizing the automatic positioning function of the beam lock.

[0011] The lifting mechanism includes a power rotating shaft, a steel cable, a steel cable drum, a lifting mechanism base, and a lifting mechanism housing. The lifting mechanism base is fixed to the aircraft reinforcement structure, the lifting mechanism housing is installed on the lifting mechanism base, the power rotating shaft is installed inside the lifting mechanism housing, the steel cable drum is mounted on the power rotating shaft, the steel cable is wound on the steel cable drum, and one end of the steel cable is connected to the hanging beam.

[0012] The flexible and variable configuration weapon mounting beam includes a mounting beam and a missile hook rail. The mounting beam is connected to a steel cable and a hook. The bottom of the mounting beam is equipped with a missile hook rail for flexible configuration of the missile hook. By flexibly configuring the missile hook, it can adapt to the needs of mounting weapons of different lengths and sizes. When arranging short and small weapons, multiple missile hooks are arranged in series to meet the needs of tandem mounting of multiple weapons. When arranging long and large weapons, a single missile hook is arranged in the middle of the mounting beam to mount a single weapon, achieving rapid and flexible weapon mounting.

[0013] In this invention, the guide positioning pin is cylindrical, with a cylinder at the top and a cone at the bottom. The cone is used to guide the locking direction, and the cylinder is used to accurately position the cone.

[0014] In this invention, the hanging beam is a slender, flat structure with a small volume, resulting in high space utilization of the internal weapon compartment.

[0015] In this invention, the hanging beam is provided with hanging beam lugs for connecting with hooks.

[0016] In this invention, the hanging beam is provided with a guide positioning hole that cooperates with the guide positioning pin.

[0017] In this invention, steel cable interfaces for connecting with steel cables are provided at both ends of the hanging beam.

[0018] In this invention, an auxiliary force transmission support point is arranged at the top of the hanging beam. This point can be added or removed according to the position of the aircraft's reinforcing frame structure. It is used to assist in transmitting the load in the direction perpendicular to the hanging beam during weapon ejection, thereby increasing the rigidity of the hanging beam and helping to reduce the height of the hanging beam.

[0019] In this invention, multiple bomb hooks are configured on the bomb hook slide rail.

[0020] In this invention, during bomb loading and unloading maintenance, the pylon and weapon assembly are lifted from below the bomb bay into the internal bomb bay, and the pylon or pylon and weapon assembly on the aircraft are lowered. This avoids the need for manual operation in the narrow internal bomb bay during bomb loading and unloading maintenance, improving the performance of bomb loading and unloading maintenance. When loading weapons, the pylon and weapon assembly are first transported to below the internal bomb bay. The transmission power controls the rotation of the cable reel through the power shaft to lower the cable. The cable is connected to the pylon, and the transmission power lifts the cable by rotating the power shaft in the opposite direction, thus raising the pylon and weapon assembly into the internal bomb bay to complete bomb loading maintenance. During unloading maintenance, the transmission power controls the rotation of the cable reel through the power shaft to lower the cable, releasing the pylon and weapon assembly out of the internal bomb bay to complete unloading maintenance.

[0021] Beneficial effects: The force transmission path in this invention is clear and direct, the overall volume is small, the cost is low, and the flexible and variable configuration of the weapon pylon allows for rapid configuration changes, enabling weapons to be pre-prepared and quickly modularly mounted during combat. Simultaneously, the internal weapon mounting device has a small overall volume, allowing for the mounting of more weapons of various sizes within the same internal weapon bay. For the same payload, the internal weapon bay volume can be reduced by approximately 15%, improving the aircraft's aerodynamic and stealth performance. Attached Figure Description

[0022] Figure 1 This is a cross-sectional view of the self-positioning hanging beam lock in a preferred embodiment of the present invention.

[0023] Figure 2 This is a schematic diagram of the self-positioning hanging beam lock structure in a preferred embodiment of the present invention.

[0024] Figure 3 This is a cross-sectional view of the lifting mechanism in a preferred embodiment of the present invention.

[0025] Figure 4 This is a front view of the lifting mechanism in a preferred embodiment of the present invention.

[0026] Figure 5 This is a schematic diagram of a weapon beam structure with a flexible and variable configuration in a preferred embodiment of the present invention.

[0027] Figure 6 This is a front view of a weapon beam with a flexible and variable configuration in a preferred embodiment of the present invention.

[0028] Figure 7 This is a schematic diagram of a modular configuration of multiple short weapons in a preferred embodiment of the present invention.

[0029] Figure 8 This is a schematic diagram of a modular configuration of a single long weapon in a preferred embodiment of the present invention.

[0030] Figure 9 This is a schematic diagram of a preferred embodiment of the present invention. Implementation

[0031] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below with reference to specific illustrations.

[0032] See Figures 1-9 The illustrated rapid-assembly internal weapon mounting device includes a self-positioning pylon lock M, a lifting mechanism N, and a flexible, variable-configuration weapon pylon P. The self-positioning pylon lock M is installed on the aircraft reinforcing frame structure 5 at the front and rear ends of the internal weapons bay, and a lifting mechanism N is installed on the aircraft reinforcing frame structure 5 on one side of each self-positioning pylon lock. The self-positioning pylon lock M and the lifting mechanism N are respectively connected to the flexible, variable-configuration weapon pylon P. The specific structure is as follows:

[0033] The self-positioning beam lock M includes a guide positioning pin 1, a hook 2, a beam lock connecting base 3, and a beam lock housing 4. The beam lock connecting base 3 is flatly connected to the aircraft reinforcing frame structure 5 and is bolted to the aircraft reinforcing frame structure 5. The beam lock housing 4, which has a built-in beam lock, is installed on the beam lock connecting base 3. The beam lock is provided with a hook 2 for hooking the beam. The bottom of the beam lock housing 4 is provided with a guide positioning pin 1, which is columnar with a cylindrical top and a conical bottom. The conical part is used to guide the locking direction, and the cylindrical part is used to achieve accurate positioning. After being guided and positioned by the guide positioning pin 1, the hook 2 hooks the beam, so that the beam is tightly pressed against the beam lock housing 4 and the guide positioning pin 3. Part of the load from the beam is directly transferred from the beam lock housing 4 to the aircraft reinforcing frame structure 5, thereby realizing the automatic positioning function of the beam lock.

[0034] The lifting mechanism N includes a power rotating shaft 6, a steel cable 7, a steel cable drum 8, a lifting mechanism base 9, and a lifting mechanism housing 10. The lifting mechanism base 9 is fixed on the aircraft reinforcing structure 5. The lifting mechanism housing 10 is installed on the lifting mechanism base 9. The power rotating shaft 6 is installed inside the lifting mechanism housing 10. The steel cable drum 8 is mounted on the power rotating shaft 6. The steel cable 7 is wound on the steel cable drum 8. One end of the steel cable 7 is connected to the hanging beam. It is used to lift the combination of the hanging beam and the weapon from the internal weapon compartment to the internal weapon compartment during ground loading and maintenance.

[0035] During bomb loading and unloading maintenance, the pylon and weapon assembly are lifted from below the bomb bay into the internal bomb bay, and the pylon or pylon and weapon assembly on the aircraft are lowered. This avoids manual operation in the narrow internal bomb bay and improves the performance of bomb loading and unloading maintenance. When loading weapons, the pylon and weapon assembly are first transported to below the internal bomb bay. The transmission power controls the rotation of the cable drum 8 through the power shaft 5 to lower the cable 7. The cable 7 is connected to the pylon. The transmission power lifts the cable 7 by rotating the power shaft 5 in the opposite direction, thus pulling the pylon and weapon assembly into the internal bomb bay to complete bomb loading maintenance. During unloading maintenance, the transmission power controls the rotation of the cable drum 8 through the power shaft 5 to lower the cable 7, releasing the pylon and weapon assembly out of the internal bomb bay to complete unloading maintenance.

[0036] The flexible and variable configuration weapon pylon P includes a cable interface 11, a pylon lifting lug 12, a guide positioning hole 13, a projectile hook slide rail 14, and an auxiliary force transmission support point 15. Cable interfaces 11 are provided at both ends of the pylon, and the cable interfaces 11 are connected to steel cables 7. The pylon lifting lug 12 is provided on the pylon, and the lifting lug 12 is connected to the hook 2 of the pylon lock. The guide positioning hole 13 cooperates with the guide positioning pin 1 of the pylon lock. A projectile hook slide rail 14 is provided at the bottom of the pylon, and the projectile hook slide rail 14 is used for flexibly configuring the projectile hook 16. This allows for the adaptation to the mounting requirements of weapons of different lengths and sizes. The top of the mounting beam is equipped with auxiliary force transmission support points 15, which can be added or removed according to the position of the aircraft's reinforcing frame structure 5. These points are used to assist in transmitting the load in the direction perpendicular to the mounting beam during weapon ejection, thereby increasing the rigidity of the mounting beam and helping to reduce the height of the mounting beam. When mounting short and small weapons, multiple missile hooks are arranged in series to meet the requirements of mounting multiple weapons in series. When mounting long and large weapons, a single missile hook is arranged in the middle of the mounting beam to mount a single weapon, achieving rapid and flexible weapon mounting.

[0037] In this embodiment, the hanging beam is a slender, flat structure with a small volume, resulting in high space utilization of the internal weapon compartment.

[0038] In this embodiment, the number and position of the ammunition hooks 16 can be flexibly and quickly configured on the ammunition hook slide rail 14 to quickly realize the configuration of single or multiple series weapons. When mounting weapons, the mounting beam and ammunition hooks can be configured in advance outside the internal weapon compartment and mounted on the ammunition hooks to complete the combination of the mounting beam and the weapon. After the internal weapon compartment door is opened, the lifting mechanism lowers the steel cable 7 to transport the combination of the mounting beam and the weapon horizontally to the bottom of the internal weapon compartment. The steel cable 7 is connected with the steel cable joint 11, and the lifting mechanism is pulled up to complete the mounting of the weapon.

[0039] In this embodiment, when the internal weapons bay is configured with a small arms configuration, multiple arming hooks are installed on the flexible and variable configuration weapon pylon. These hooks are arranged in a sliding tandem arrangement at the front, middle, and rear of the pylon, combining the weapons and the pylon. The combined unit is a modular configuration of multiple small arms, where B represents a small arm, such as... Figure 7 As shown, the number of ammunition hooks can be increased or decreased flexibly according to the needs of the weapon and configuration.

[0040] In this embodiment, when the internal weapons bay is configured with a long weapon, a single weapon hook is installed on the flexible and variable configuration weapon beam. This hook is slidably positioned in the middle of the beam, combining the weapon and the beam. The combined unit is a modular configuration of a single, long weapon. Figure 8 As shown, C represents a long weapon.

[0041] In this embodiment, when the ammunition bay is wide enough to accommodate multiple weapons, multiple internal weapon mounting devices are arranged side-by-side, such as... Figure 6 As shown, A is a large bomb bay; Figure 9 In the diagram, Q represents a small ammunition bay, and W represents a weapon.

[0042] In this embodiment, to achieve a compact layout of multiple weapon rows, the missile wings need to be staggered. This can be achieved by sliding and adjusting the position of the missile hooks in each row of mounting beams. Because of its small overall size, the internal weapon mounting device can accommodate more weapons of various sizes within the same internal weapon bay. With the same payload, the internal weapon bay volume can be reduced by approximately 15%, improving the aircraft's aerodynamic and stealth performance.

Claims

1. A rapidly assembleable internal weapon mounting device, comprising a self-positioning mounting beam lock, a lifting mechanism, and a weapon mounting beam with a flexible and variable configuration, characterized in that, The aircraft's internal weapons bay reinforcement frame structure is equipped with self-positioning pylon locks, and a lifting mechanism is installed on the aircraft reinforcement frame structure on one side of each self-positioning pylon lock. The self-positioning pylon locks and lifting mechanisms are connected to the flexible and variable configuration weapon pylons, as detailed below: The self-positioning beam lock includes a guide positioning pin, a hook, a beam lock connecting base, and a beam lock housing. The beam lock connecting base is installed on the aircraft reinforcing frame structure. The beam lock housing, which has a built-in beam lock, is installed on the beam lock connecting base. The beam lock is provided with a hook for hooking the beam. The bottom of the beam lock housing is provided with a guide positioning pin for guiding and positioning the beam. The lifting mechanism includes a power rotating shaft, a steel cable, a steel cable drum, a lifting mechanism base, and a lifting mechanism housing. The lifting mechanism base is fixed to the aircraft reinforcement structure, the lifting mechanism housing is installed on the lifting mechanism base, the power rotating shaft is installed inside the lifting mechanism housing, the steel cable drum is mounted on the power rotating shaft, the steel cable is wound on the steel cable drum, and one end of the steel cable is connected to the hanging beam. The flexible and variable configuration weapon pylon includes a pylon and a missile hook slide rail. The pylon is connected to a steel cable and a hook. The bottom of the pylon is equipped with a missile hook slide rail for flexibly configuring the missile hook.

2. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, The guide positioning pin is cylindrical, with a cylinder at the top and a cone at the bottom.

3. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, The hanging beam is a slender, flat structure.

4. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, The hanging beam is equipped with hanging lugs for connecting to the hook.

5. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, The hanging beam is equipped with guide positioning holes that cooperate with guide positioning pins.

6. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, The two ends of the hanging beam are respectively equipped with steel cable interfaces for connecting with steel cables.

7. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, Auxiliary force transmission support points are arranged at the top of the hanging beam.

8. The rapidly assembleable internal weapon mounting device according to claim 1, characterized in that, Multiple bomb hooks are configured on the bomb hook slide rail.

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