Optical load cabin

Abstract

The utility model relates to an optical load cabin which comprises a load cabin shell, and the load cabin shell is provided with an optical window, an electrical interface, at least two lifting lugs and at least four stop threaded interfaces. A first antenna module, a second antenna module, an airflow internal circulation system, a link module, an imaging module, a power module, an image processing module, a control module and a liquid cooling system are arranged in the load cabin shell, the first antenna module is located in a first cabin section area, and the airflow internal circulation system is located in a second cabin section area and a third cabin section area. The link module is located in the second cabin section area, the imaging module and the power module are both located in the third cabin section area, the imaging module is arranged corresponding to the optical window, the image processing module and the control module are both located in the fourth cabin section area, the liquid cooling system is used for cooling the antenna module and the link module, and the second antenna module is located in the fifth cabin section area. According to the utility model, the adaptability of the optical load cabin and the aerial carrier platform is improved, and the structure is more compact.

Description

Technical Field

[0001] This utility model relates to the field of airborne optical remote sensing imaging technology, and in particular to an optical payload cabin. Background Technology

[0002] Currently, reconnaissance platforms mainly include fighter jets and transport aircraft equipped with optical reconnaissance equipment, as well as unmanned reconnaissance aircraft carrying such equipment. Various optical payload manufacturers provide multiple sets of reconnaissance payloads for these platforms, primarily including low-to-medium altitude and medium-to-high altitude reconnaissance payloads. These payloads are adapted to different reconnaissance platforms and are not interchangeable. The reconnaissance equipment, including reconnaissance and control equipment, storage devices, intelligent processing units, and link equipment related to the reconnaissance mission, is provided by the reconnaissance platform. The control interface for the reconnaissance equipment is determined through negotiation between the parties based on the characteristics and application habits of each reconnaissance platform and optical payload. The reconnaissance equipment is controlled by pilots in the air or by ground-based pilots operating the unmanned aerial vehicle (UAV).

[0003] The optical payload bay can carry a reconnaissance platform. It includes an antenna module, an internal airflow circulation system, a link module, an imaging module, a power supply module, an image processing module, a control module, and a liquid cooling system, forming an independent system. Existing optical payload bays have the following shortcomings:

[0004] I. The structural compactness of the optical payload compartment needs to be improved;

[0005] 2. Poor compatibility of the optical payload bay connection: The optical payload bay is connected to the carrier platform through its mechanical interface, but the compatibility of the optical payload bay connection needs to be improved. Utility Model Content

[0006] Therefore, it is necessary to provide an optical payload cabin to address the issues of structural compactness and adaptability at external connections.

[0007] To solve the above problems, the present invention adopts the following technical solution:

[0008] An optical payload bay includes a payload bay shell. The payload bay shell has an optical window, an electrical interface, at least two lifting lugs, and at least four locking threaded interfaces. The lifting lugs are located directly above the payload bay shell and are used to externally connect to a carrier platform to support the weight of the optical payload bay. The locking threaded interfaces are used to externally connect to the carrier platform to prevent the payload bay shell from swaying. The payload bay shell is internally divided into a first section area, a second section area, a third section area, a fourth section area, and a fifth section area from front to back. The payload bay shell contains a first antenna module, a second antenna module, an internal airflow circulation system, a link module, and a [missing information - likely a component name or component]. The system includes an image module, a power module, an image processing module, a control module, and a liquid cooling system. A first antenna module and a second antenna module are connected to a link module to form a link system. The first antenna module is located in the first compartment area. The internal airflow circulation system is located in the second and third compartment areas. The link module is located in the second compartment area. The imaging module and the power module are both located in the third compartment area. The power module is connected to the electrical interface. The imaging module is set according to the optical window. The image processing module and the control module are both located in the fourth compartment area. The liquid cooling system is used to cool the first antenna module, the second antenna module, and the link module. The second antenna module is located in the fifth compartment area.

[0009] In a preferred embodiment, all lifting lugs are arranged in a row along the length of the load chamber shell, with a number of locking threaded interfaces located on one side of the line containing all the lifting lugs and another number of locking threaded interfaces located on the other side of the line containing all the lifting lugs.

[0010] In a preferred embodiment, the stop threaded interface is connected to the load-bearing structure of the carrier platform via screws and bolts.

[0011] In a preferred embodiment, the lifting lug is externally connected to the carrier platform via bolts or hooks.

[0012] In a preferred embodiment, the electrical interface, all lifting lugs, and all locking threaded interfaces are located directly above the third compartment area.

[0013] In a preferred embodiment, the lifting lug is connected to the load chamber shell by M64 bolts.

[0014] In a preferred embodiment, the number of lifting lugs is two, and the distance between the two lifting lugs is 762mm.

[0015] In a preferred embodiment, a vibration damper is provided between the imaging module and the payload chamber shell.

[0016] In a preferred embodiment, the airflow internal circulation system includes: an internal circulation drive module, an air inlet channel, a left air outlet channel, a right air outlet channel, and a lower air outlet channel. The internal circulation drive module is connected to the air inlet channel, the left air outlet channel, the right air outlet channel, and the lower air outlet channel. The air outlets of the left air outlet channel, the right air outlet channel, and the lower air outlet channel are all set with light windows, and the air inlet end of the air inlet channel is set with an imaging module.

[0017] In a preferred embodiment, the liquid cooling system includes a liquid flow drive module, a circulation pipeline, and a heat dissipation module. The liquid flow drive module and the heat dissipation module are located in the fourth compartment area. The circulation pipeline connects the liquid flow drive module and the heat dissipation module and is located in the first compartment area, the second compartment area, the third compartment area, the fourth compartment area, and the fifth compartment area.

[0018] The aforementioned optical payload cabin achieves a stable connection between the optical payload cabin and the carrier platform through lifting lugs and a locking thread interface. Furthermore, the cooperation between the lifting lugs and the locking thread interface improves the compatibility between the optical payload cabin and the carrier platform, enabling the optical payload cabin to be compatible with a wider range of carrier platforms. By placing the link module at the front end of the cabin, the antenna modules at both ends, the imaging module in the middle, and the control module, image processing module, and liquid cooling system at the rear end of the cabin, the layout structure of the optical payload cabin becomes more compact. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structural composition of the optical payload compartment in one embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram showing the connection between the optical payload compartment and the hanger load-bearing structure in one embodiment of the present invention;

[0021] Figure 3 This is a schematic diagram of the beam transmission of the optical payload compartment's optical window and imaging module in one embodiment of the present invention;

[0022] Figure 4 This utility model Figure 3 Sectional view along CC;

[0023] Figure 5 This is a schematic diagram showing the positional relationship between the optical window and the imaging module of the optical payload compartment in one embodiment of the present invention;

[0024] Figure 6 This is a schematic diagram illustrating the composition and working principle of the airflow internal circulation system of the optical payload cabin in one embodiment of the present invention;

[0025] Figure 7 This utility model Figure 6 Sectional view along EE;

[0026] Figure 8 This is a schematic diagram illustrating the composition and working principle of the liquid cooling system of the optical payload compartment in one embodiment of the present invention.

[0027] The components include: 1. Payload cabin shell; 2. First antenna module; 3. Optical window: 3-L, left-tilted window; 3-R, right-tilted window; 3-D, downward-viewing window; 4. Imaging module: 4-1, folding mirror; 4-2, first vibration damper; 5. Power supply module; 6. Control module; 7. Image processing module; 8. Link module: 8-1, terminal unit; 8-2, second vibration damper; 9. Internal airflow circulation system: 9-1, internal circulation drive module; 9-2, air intake vent. 9-3L, left air outlet channel; 9-3R, right air outlet channel; 9-3D, lower air outlet channel; 10, liquid cooling system; 10-1, liquid flow drive module; 10-2, circulation pipeline; 10-3, heat dissipation module; 10-3-1, front air inlet; 10-3-2, windproof air outlet; 11, second antenna module; 12, lifting lug; 13, stop threaded interface; 14, electrical interface; 15, bracket load-bearing structure; 16, hook. Detailed Implementation

[0028] The technical solution of this utility model will now be described in detail with reference to the accompanying drawings and preferred embodiments.

[0029] See Figure 1This utility model provides an optical payload cabin, including a payload cabin shell 1. The payload cabin shell 1 is provided with an optical window, an electrical interface 14, at least two lifting lugs 12, and at least four locking threaded interfaces 13. The lifting lugs 12 are located directly above the payload cabin shell 1 and are used to externally connect to a carrier platform to support the weight of the optical payload cabin. The locking threaded interfaces 13 are used to externally connect to the carrier platform to prevent the payload cabin shell 1 from swinging. The payload cabin shell 1 is divided into a first section area, a second section area, a third section area, a fourth section area, and a fifth section area from front to back. The payload cabin shell 1 is provided with a first antenna module 2, an internal airflow circulation system 9, a link module 8, an imaging module 4, and a power supply. Module 5, image processing module 7, control module 6, liquid cooling system 10, and second antenna module 11. First antenna module 2 is located in the first compartment area. Airflow internal circulation system 9 is located in the second and third compartment areas. Link module 8 is located in the second compartment area. Imaging module 4 and power module 5 are both located in the third compartment area. Imaging module 4 is set with an optical window. Power module 5 is connected to the electrical interface 14. Image processing module 7 and control module 6 are both located in the fourth compartment area. Liquid cooling system 10 is used to cool first antenna module 2, second antenna module 11, and link module 8. Second antenna module 11 is located in the fifth compartment area. First antenna module 2 and second antenna module 11 are connected to link module to form link system.

[0030] Understandable. Figure 1 The dashed rectangular frame represents the omitted middle structure of the optical payload cabin.

[0031] In this embodiment, all lifting lugs 12 are arranged in a row (usually along the length of the load chamber shell 1) on the load chamber shell 1. The stop threaded interfaces 13 are located on both sides of the line containing all the lifting lugs 12, referred to as the left half and right half of the load chamber shell 1. Part of the stop threaded interfaces 13 are located on the left half of the load chamber shell 1, and another part are located on the right half.

[0032] In this embodiment, the electrical interface 14, all lifting lugs 12, and all locking threaded interfaces 13 are located directly above the third compartment area. As an example, the lifting lugs 12 are connected to the load compartment shell 1 by M64 bolts.

[0033] The electrical interface 14 and all the lugs 12 form a row. The electrical interface 14 is located behind the lugs 12. This can be understood as follows: the distance between the electrical interface 14 and the first antenna module 2 is greater than the distance between the lugs 12 and the first antenna module 2.

[0034] The stop threaded interface 13 serves as the constraint point for the anti-sway device, and the lifting lug 12 can be used as a hanging ring. Both the stop threaded interface 13 and the lifting lug 12 are connected to the carrier platform via the connecting bracket load-bearing structure 15. Typically, the connecting bracket load-bearing structure 15 is part of the carrier platform's structure. See also... Figure 2 A schematic diagram showing the connection of the pylon support structure 15 via the lug 12 and the stop threaded interface 13 using bolts. The anti-sway restraint points have mechanical constraints with the pylon support structure 15 of the aircraft platform to prevent the optical payload bay from experiencing significant lateral swaying during flight.

[0035] In this embodiment, there are a total of two lifting lugs 12, with a spacing of 762mm between the two lifting lugs 12, and a total of four locking thread interfaces 13. The lifting lugs 12 and locking thread interfaces 13 conform to the general standard interfaces required by GJB1C (GJB1C-2006 General Design Guidelines for Joints of Airborne Suspensions and Suspension Devices).

[0036] Preferably, a vibration damper, referred to as the first vibration damper 4-2, is provided between the imaging module 4 and the payload chamber shell 1 to attenuate vibration sources outside the imaging module 4.

[0037] The optical window is located in the area of ​​the third section of the payload compartment shell 1. Figure 3 , Figure 4 and Figure 5 This is a schematic diagram of the optical payload compartment's optical window 3 and imaging module 4 in this embodiment. Figure 3 The example in the text illustrates the downward view of the folding mirror 4-1. Figure 4 The diagram illustrates the left (dashed line) and right (solid line) viewing positions of the folding mirror 4-1. The optical window 3 comprises a left-tilted window 3-L, a right-tilted window 3-R, and a downward-viewing window 3-D, all mounted on the payload chamber shell 1. These provide the imaging module 4 with a considerable scanning imaging range and optical path. External scene images sequentially pass through the windows and the folding mirror 4-1 of the imaging module 4 before entering the imaging module 4, ultimately being acquired by the detector of the imaging module 4. The material of the optical window 3 significantly affects the spectral transmittance of the entire imaging module 4, thus limiting the functional modes of the optical imaging module 4. The material of the optical window 3 can be selected according to the functional requirements of the optical imaging module 4; typical optional materials for the optical window 3 include fused silica, multispectral ZnS, and sapphire.

[0038] The optical payload cabin is connected to the carrier platform via two lugs 12. The lugs 12 have through holes, the axis of which is parallel to the axis of the optical payload cabin, and are connected to the carrier platform. The lugs 12 are made of 40CrNiMoA steel. The mounting process of the optical payload cabin: An optical payload cabin mounting vehicle is required. The optical payload cabin is raised by the mounting vehicle, and the lifting lug 12 of the optical payload cabin is inserted into the hook 16 of the bracket support structure 15. The lifting lug 12 can be hung on the hook 16 to complete the connection between the lifting lug and the bracket support structure 15. However, in order to improve stability, the lifting lug 12 is usually connected by bolts / screws, etc. It can be understood that the bolts / screws are part of the hook 16. After the lifting lug 12 of the optical payload cabin is connected to the hook 16, it is removed from the optical payload cabin mounting vehicle. The weight of the optical payload cabin is completely borne by the hook 16 of the bracket support structure 15. The stop screws at both ends of the bracket support structure 15 are tightened to bear the yaw moment, pitch moment and lateral load of the optical payload cabin to prevent the optical payload cabin from shaking.

[0039] The internal airflow circulation system 9 is configured corresponding to the light window 3, and is used for defrosting and defogging the light window 3 and homogenizing the ambient temperature field of the imaging module 4. Homogenizing the ambient temperature field of the imaging module 4 is used to reduce the influence of the ambient temperature field on the imaging module 4.

[0040] The composition of the airflow internal circulation system 9 is as follows: Figure 6 and Figure 7Its main components include: an internal circulation drive module 9-1, an air intake channel 9-2, a left air outlet channel 9-3L, a right air outlet channel 9-3R, and a lower air outlet channel 9-3D. The air intake channel 9-2 is located on the upper side of the internal space of the payload compartment shell 1, the left air outlet channel 9-3L is located on the left side of the internal space of the payload compartment shell 1, the right air outlet channel 9-3R is located on the right side of the internal space of the payload compartment shell 1, and the lower air outlet channel 9-3D is located on the lower side of the internal space of the payload compartment shell 1. The internal circulation drive module 9-1, acting as the drive for airflow, connects the air intake channel 9-2, the left air outlet channel 9-3L, the right air outlet channel 9-3R, and the lower air outlet channel 9-3D. The internal airflow drive system 9 and the link module 8 are both located in the second compartment area. The left nozzle serves as the outlet for the left exhaust channel 9-3L, the right nozzle serves as the outlet for the right exhaust channel 9-3R, and the lower nozzle serves as the outlet for the lower exhaust channel 9-3D. The air inlet of the air inlet channel is located above the internal space of the payload compartment shell 1. The air inlet of the air inlet channel 9-2 and the three outlets of the exhaust channels are connected to the second compartment area where the imaging module 4 is located. The airflow from the three outlets can directly blow towards the light window 3. That is, the outlets of the left exhaust channel 9-3L, the right exhaust channel 9-3R, and the lower exhaust channel 9-3D are all set corresponding to the light window 3. The air inlet end of the air inlet channel 9-2 is set corresponding to the imaging module 4. The cavity in the third section area forms an internal airflow circulation system 9. Under the action of the internal circulation drive module 9-1, the airflow blowing towards the light window 3 can achieve defrosting and defogging of the light window 3. Then, it enters the internal circulation drive module 9-1 through the air inlet and the air intake channel 9-2 via the internal circulation of the third section area.

[0041] The first antenna module 2 and the second antenna module 11 together constitute an antenna module. Both the first antenna module 2 and the second antenna module 11 are connected to the link module 8, and the antenna module and the link module 8 together constitute a link system. A portion of the antenna module is located at one end inside the payload compartment shell 1, and another portion is located at the other end inside the payload compartment shell 1. The antenna needs to transmit data both to the air and to the ground, and cannot be obstructed in front or below. It is arranged at the front and rear ends of the cabin, with a wave-transparent radome on the outside.

[0042] The link module 8 is a wireless link module, and the corresponding link system is called the wireless link system. The wireless link system is a key functional module of the optical payload compartment and requires liquid cooling system 10 for cooling. The terminal 8-1 of the link module 8 is connected to the payload compartment shell 1 through the second vibration damper 8-2.

[0043] In one specific embodiment, the wireless link system has telemetry and remote control functions for the optical payload cabin, enabling remote control of the optical payload cabin via multiple ground control stations, while simultaneously transmitting visible and infrared images to the ground. The wireless link system can be equipped with different communication frequency bands as needed, and servo turntable devices can be added to modules for directional transmission.

[0044] The liquid cooling system 10 is located in the first compartment area, the second compartment area, the third compartment area, the fourth compartment area, and the fifth compartment area.

[0045] Combination Figure 8 The working principle of the liquid cooling system 10 is explained. Figure 8 The dashed cuboid in the diagram represents the omitted middle portion. The liquid cooling system 10 includes a liquid flow drive module 10-1, a circulation pipeline 10-2, and a heat dissipation module 10-3. The liquid flow drive module 10-1 and the heat dissipation module 10-3 are located in the fourth compartment region. The circulation pipeline 10-2 is located in the first, second, third, fourth, and fifth compartment regions, connecting the liquid flow drive module 10-1 and the heat dissipation module 10-3. The heat dissipation module 10-3 dissipates heat from the refrigerant in the circulation pipeline 10-2, and the liquid flow drive module 10-1 drives the flow of the refrigerant in the circulation pipeline 10-2. Under the action of the fluid flow drive module 10-1, the cooling medium flows inside the circulation pipe 10-2, cooling the first antenna module 2, the second antenna module 11, and the terminal 8-1 of the link module 8 respectively. The heat gained by the cooling medium is absorbed and carried away by the high-speed airflow flowing through the heat dissipation module 10-3. The heat dissipation module 10-3 is a fluid cavity that runs through the cabin structure, with a windward air inlet 10-3-1 on one side and a windward air outlet 10-3-2 on the other side. During flight, air enters the fluid cavity from the windward side and flows out of the fluid cavity from the windward side.

[0046] The electrical interface 14 is used for electrical connection to the carrier platform. The electrical interface 14 is electrically connected to the power module 5, which supplies power to the first antenna module 2, the second antenna module 11, the airflow internal circulation system 9, the link module 8, the imaging module 4, the image processing module 7, the control module 6, the liquid cooling system 10, and the second antenna module 11. The carrier platform supplies power to the optical payload bay through the power module 5, and simultaneously performs control, interaction, and data transmission through the electrical interface 14.

[0047] The control module 6 is used to implement functions such as task management, system maintenance, and monitoring. Its core component is a task processor, which uses an FT2000 / 4 as its central processing unit. The control module 6 is connected to the electrical interface 14, the link module 8, the imaging module 4, the power supply module 5, the image processing module 7, and the liquid cooling system 10.

[0048] The image processing module 7 is used to realize real-time processing of visible and infrared images, target detection, recognition and localization, and target slice output. The data control unit is the management and control core of the image processing module 7. The data control unit uses a programmable FPGA to acquire input data from external payloads, dynamically segment image data, and uses a Phytium D2000 / 8 processor to realize external communication such as RS422. The image processing module 7 is connected to the imaging module 4 and the link module 8.

[0049] The image information acquired by the imaging module 4 can be directly or indirectly (after being processed by the image processing module 7) interacting with the outside world through the link module 8 or with the machine through the electrical interface 14.

[0050] This invention provides an optical payload bay that achieves a stable connection between the optical payload bay and the carrier platform through a lifting lug 12 and a locking threaded interface 13. Furthermore, the lifting lug 12 and its cooperation with the locking threaded interface 13 improve the compatibility between the optical payload bay and the carrier platform, enabling the optical payload bay to be compatible with a wider range of carrier platforms. This invention places the link module 8 at the front of the bay, the antenna modules at both ends, the imaging module 4 in the middle, and the control module 6, image processing module 7, and liquid cooling system 10 at the rear of the bay. This layout of the optical payload bay results in a more rational relative positional relationship and a more compact structure.

[0051] In one specific embodiment, the center of gravity of the optical payload cabin is within 10mm of the geometric center, which fully considers the structural compactness and the weight balance of the entire cabin, and meets the requirements of GJB1C for the position of the pod's center of gravity.

[0052] It should be noted that the control module 6, image processing module 7, link module 8, power module 5, etc., are all existing technologies and therefore not described in detail. It is understood that any parts of this utility model not described in detail are existing technologies.

[0053] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0054] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. An optical payload bay, characterized in that, The system includes a payload bay shell, which has an optical window, an electrical interface, at least two lifting lugs, and at least four locking threaded interfaces. The lifting lugs are located directly above the payload bay shell and are used to externally connect to a carrier platform to support the weight of the optical payload bay. The locking threaded interfaces are used to externally connect to the carrier platform to prevent the payload bay shell from swaying. The payload bay shell is divided into five sections from front to back: a first section, a second section, a third section, a fourth section, and a fifth section. The payload bay shell contains a first antenna module, a second antenna module, an internal airflow circulation system, a link module, and an imaging module. The system includes a power module, an image processing module, a control module, and a liquid cooling system. A first antenna module and a second antenna module are connected to a link module to form a link system. The first antenna module is located in the first compartment area. The airflow internal circulation system is located in the second and third compartment areas. The link module is located in the second compartment area. The imaging module and the power module are both located in the third compartment area. The power module is connected to the electrical interface. The imaging module is set according to the optical window. The image processing module and the control module are both located in the fourth compartment area. The liquid cooling system is used to cool the first antenna module, the second antenna module, and the link module. The second antenna module is located in the fifth compartment area.

2. The optical payload bay according to claim 1, characterized in that, All lifting lugs are arranged in a row along the length of the load chamber shell. A portion of the locking threaded interfaces are located on one side of the line containing all the lifting lugs, while another portion are located on the other side of the line containing all the lifting lugs.

3. The optical payload bay according to claim 1, characterized in that, The stop threaded interface is connected to the load-bearing structure of the carrier platform via screws and bolts.

4. An optical payload bay according to claim 1, characterized in that, The lifting lugs are externally connected to the carrier platform via bolts or hooks.

5. An optical payload bay according to claim 1, characterized in that, The electrical interface, all lifting lugs, and all locking threaded interfaces are located directly above the third compartment area.

6. An optical payload bay according to claim 1, characterized in that, The lifting lugs are connected to the load compartment shell by M64 bolts.

7. An optical payload bay according to claim 1, characterized in that, The number of lifting lugs is two, and the distance between the two lifting lugs is 762mm.

8. An optical payload bay according to claim 1, characterized in that, A vibration damper is provided between the imaging module and the payload compartment shell.

9. An optical payload chamber according to claim 1, characterized in that, The airflow internal circulation system includes: an internal circulation drive module, an air inlet channel, a left air outlet channel, a right air outlet channel, and a lower air outlet channel. The internal circulation drive module is connected to the air inlet channel, the left air outlet channel, the right air outlet channel, and the lower air outlet channel. The air outlets of the left air outlet channel, the right air outlet channel, and the lower air outlet channel are all set with light windows. The air inlet end of the air inlet channel is set with the imaging module.

10. An optical payload bay according to claim 1, characterized in that, The liquid cooling system includes a liquid flow drive module, a circulation pipeline, and a heat dissipation module. The circulation pipeline connects the liquid flow drive module and the heat dissipation module, which are located in the fourth compartment area. The circulation pipeline is located in the first compartment area, the second compartment area, the third compartment area, the fourth compartment area, and the fifth compartment area.

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