Strapdown detection system based on frame integral uncooled infrared imaging

Abstract

The invention relates to a strapdown detection system based on frame integral uncooled infrared imaging, and belongs to the technical field of strapdown detection. Comprising a cabin; the optical system is connected to the front end of the cabin body and is used for focusing the infrared radiation energy of the measured target; the detection system comprises a detection support and a detector, the detection support is located on the rear side of the optical system, and the detector is connected into the detection support; the signal processing system comprises an infrared signal board, a data acquisition board and an infrared imaging mainboard, the infrared signal board is fixed with the detector and is interconnected with the detector through signals, a first flexible flat cable is connected between the data acquisition board and the infrared signal board, and the infrared imaging mainboard is connected with the data acquisition board through a plug-in; and the external connector is connected to the detection support, the infrared imaging mainboard is connected with a second flexible flat cable, and the second flexible flat cable is connected with the external connector. The infrared detector can prevent thermal radiation of heating devices in the data acquisition board and the infrared imaging mainboard from affecting the imaging quality of the infrared detector.

Description

Technical Field

[0001] The present application relates to the field of strapdown detection and technology, and in particular to a strapdown detection system based on frame-integrated uncooled infrared imaging. Background Art

[0002] The strapdown detection system is an important navigation and detection technology with the characteristics of good concealment, strong anti-interference ability and high precision. It is widely used in military, civil and intelligent transportation fields, and its performance is constantly improving with the development of technology.

[0003] The strapdown detection system is used in aircraft. When the aircraft reaches a predetermined distance, the strapdown detection system becomes an infrared imaging detection system. When it starts working, the infrared radiation energy of the observed target is focused onto the focal plane of the detector through the infrared optical system. The detector simultaneously integrates the pixels of the entire focal plane to form an infrared radiation signal. The signal processing system then converts the infrared radiation signal into an electrical signal and pre-processes it. The processed digital information is transmitted to the rear end of the aircraft in the form of digital video through an external connector to achieve precise guidance.

[0004] The signal processing system generally includes an infrared signal board, a data acquisition board, and an infrared imaging main board. The infrared signal board, the data acquisition board, and the infrared imaging main board are connected by signals and interconnected in the detector bracket through inter-board plug-ins. Generally, the infrared signal board, the data acquisition board, and the infrared imaging main board are close to the infrared detector, which results in a large heat radiation from the heating components in the data acquisition board and the infrared imaging main board. The heat radiation will affect the imaging quality of the infrared detector. Summary of the invention

[0005] The embodiment of the present application provides a strapdown detection system based on frame-integrated uncooled infrared imaging to solve the problem in the related art that the heating components in the data acquisition board and the infrared imaging main board are affected by the detector, generating large heat radiation, resulting in poor imaging quality of the infrared detector.

[0006] The embodiment of the present application provides a strapdown detection system based on frame-integrated uncooled infrared imaging, comprising: a cabin;

[0007] An optical system connected to the front end of the cabin and used to focus the infrared radiation energy of the target to be measured;

[0008] A detection system, comprising a detection bracket and a detector, wherein the detection bracket is located at the rear side of the optical system, and the detector is connected inside the detection bracket;

[0009] A signal processing system, comprising an infrared signal board, a data acquisition board and an infrared imaging main board, wherein the infrared signal board is fixed to the detector and interconnected through signals, a first flexible flat cable is connected between the data acquisition board and the infrared signal board, and the infrared imaging main board and the data acquisition board are connected through a plug-in;

[0010] An external connector is connected to the detection bracket. A second flexible cable is connected to the infrared imaging mainboard, and the second flexible cable is connected to the external connector.

[0011] In some embodiments, the optical system comprises:

[0012] A lens barrel connected to the detection bracket;

[0013] A plurality of lenses, one of which is located at the front side of the lens barrel and connected to the cabin body to serve as an optical window, and the remaining lenses are distributed on the lens barrel.

[0014] In some embodiments, the plurality of lenses are arranged to form an image at one time.

[0015] In some embodiments, vibration absorbers are distributed along the circumference of the detection bracket.

[0016] In some embodiments, a circular envelope is distributed on the detection bracket along its circumference, and the vibration absorber is located within the circular envelope.

[0017] In some embodiments, a window pressing ring is threadedly connected between the cabin and the lens.

[0018] In some embodiments, a cabin gap is provided between the lens and the cabin, a pressure ring gap is provided between the window pressure ring and the lens, and silicone rubber is provided in both the cabin gap and the pressure ring gap.

[0019] In some embodiments, a correction plate is provided on the front side of the optical system.

[0020] In some embodiments, the operating wavelength between the multiple lenses is 8-14 um.

[0021] In some embodiments, a solder pad is disposed on the second flexible cable, and the solder pad is buckled with the external connector.

[0022] The beneficial effects brought by the technical solution provided by the present application include: the embodiment of the present application provides a strapdown detection system based on frame-integrated non-cooled infrared imaging. When the aircraft reaches a predetermined distance, the strapdown detection system starts to work, and the infrared radiation energy of the observed target is focused on the focal plane of the detector through the optical system. The detector simultaneously integrates the pixels of the entire focal plane to form an infrared radiation signal, and then the infrared radiation signal is converted into an electrical signal and pre-processed by the signal processing system. The processed digital information transmits the target characteristics to the rear end of the aircraft in the form of digital video through an external connector to achieve precise guidance. The infrared signal board realizes data transmission with the data acquisition board through a first flexible cable, the infrared imaging main board is connected to the external connector through a second flexible cable, and the data acquisition board and the infrared imaging main board can be arranged as far away from the detector as possible, thereby reducing the thermal radiation effect of the heating components in the data acquisition board and the infrared imaging main board, and ensuring the imaging quality of the detector. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0024] Figure 1 A schematic diagram of the overall structure provided for an embodiment of the present application;

[0025] Figure 2 A schematic diagram showing the structure of a shock absorber provided in an embodiment of the present application;

[0026] Figure 3 A schematic diagram of the structure of the display window pressing ring provided in an embodiment of the present application;

[0027] Reference numerals:

[0028] 1. Cabin; 10. Correction plate; 20. Detection bracket; 21. Detector; 30. Infrared signal board; 31. Data acquisition board; 32. Infrared imaging main board; 4. First flexible cable; 5. External connector; 6. Second flexible cable; 60. Solder pad; 70. Lens barrel; 71. Lens; 8. Vibration absorber; 90. Window pressure ring; 91. Cabin gap; 92. Pressure ring gap; 93. Silicon rubber. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0030] The embodiment of the present application provides a strapdown detection system based on frame-integrated uncooled infrared imaging, which can solve the problem that the heating components in the data acquisition board and the infrared imaging main board are affected by the detector, generating large heat radiation, resulting in poor imaging quality of the infrared detector.

[0031] See also Figures 1 to 3 As shown, the embodiment of the present application provides a strapdown detection system based on frame-integrated non-cooled infrared imaging, including: a cabin 1, an optical system, a detection system, a signal processing system and an external connector 5; wherein the optical system is connected to the front end of the cabin 1 and is used to focus the infrared radiation energy of the target to be detected. The detection system includes a detection bracket 20 and a detector 21, wherein the detector 21 is set as a frame-integrated non-cooled detector 21, the detection bracket 20 is located at the rear side of the optical system, and the detector 21 is connected to the detection bracket 20. The signal processing system includes an infrared signal board 30, a data acquisition board 31 and an infrared imaging mainboard 32, wherein the infrared signal board 30 is fixed to the detector 21 and interconnected through signals, wherein a first flexible cable 4 is connected between the data acquisition board 31 and the infrared signal board 30, and the infrared imaging mainboard 32 and the data acquisition board 31 are connected through a plug-in, wherein the plug-in involves connecting different boards or components through connectors to realize data transmission and function expansion. The external connector 5 is connected to the detection bracket 20, and the infrared imaging main board 32 is connected to a second flexible cable 6, which is connected to the external connector 5. A solder pad 60 is provided on the second flexible cable 6, and the solder pad 60 is snapped with the external connector 5 to realize data transmission.

[0032] When the present application is used, when the aircraft reaches a predetermined distance, the strapdown detection system starts to work, and the infrared radiation energy of the observed target is focused on the focal plane of the detector 21 through the optical system. The detector 21 integrates the pixels of the entire focal plane at the same time to form an infrared radiation signal, and then the infrared radiation signal is converted into an electrical signal and pre-processed by the signal processing system. The processed digital information transmits the target characteristics to the rear end of the aircraft in the form of digital video through the external connector 5 to achieve precise guidance. In the signal processing system, the infrared signal board 30 realizes data transmission with the data acquisition board 31 through the first flexible cable 4, and the infrared imaging main board 32 is connected to the external connector 5 through the second flexible cable 6, so that the data acquisition board 31 and the infrared imaging main board 32 can be arranged as far away from the detector 21 as possible, thereby reducing the heat radiation effect of the heating devices in the data acquisition board 31 and the infrared imaging main board 32, and ensuring the imaging quality of the detector 21. In addition, under the action of the first flexible cable 4 and the second flexible cable 6, it is also convenient to route the wires in the detection bracket 20, and the signal data is transmitted by routing, which further saves the installation space and reduces the size of the whole machine.

[0033] In the present application, the detector 21 is set as a frame-integrated non-cooled detector 21. The detector 21 adopts a frame-integrated exposure method, which can realize the detection and tracking of the target scene under the non-cooled guidance system at a hypersonic speed of more than Mach 3. And the integration time of the detector 21 for the pixels of the entire focal plane simultaneously does not exceed 1.5ms, the thermal response time is not more than 3ms, the number of pixels of the detector 21 is 640x512, and the pixel size is 25um. In other implementations, the infrared terminal guidance mainly includes line-integrated non-cooled and cooled imaging systems. The line-integrated non-cooled imaging system is more suitable for subsonic scenes and matches the servo frame for image stabilization; the cooled imaging system can be strapdown or framed imaging, which can be suitable for subsonic and supersonic applications.

[0034] The line-integrated uncooled imaging system is adopted, which is limited by the line-by-line integration imaging method. The integration time of a single frame image is long. The body disturbance caused by high-speed flight will cause image smear, affecting the accurate identification and strike of the back-end. It has its limitations in high-speed and high-dynamic application fields.

[0035] Although the cooling imaging system has a short integration time and can adapt to the disturbance of high-speed flying bodies, the cooling imaging system requires a refrigerator, resulting in large size, heavy weight and high cost of the equipment, making it difficult to adapt to small supersonic aircraft. When used in compact aircraft, multi-mode composite guidance is difficult. At the same time, the cooling imaging system is expensive and difficult to apply to saturation attacks and cluster combat.

[0036] Therefore, in this application, a frame integration exposure method is adopted to control the integration time to the millisecond level, thereby reducing the integration time and improving the problem of image blur under high-speed conditions; and a non-cooled imaging system is adopted, which does not require a refrigerator, thereby realizing miniaturization and lightweight of the detection device, effectively meeting the needs of small supersonic aircraft for clear detection and tracking of targets above Mach 3 in the final stage of flight, and is conducive to realizing multi-mode composite guidance to improve guidance accuracy and anti-interference capability.

[0037] In the present application, in order to further improve the imaging quality, a correction plate 10 is also provided on the front side of the optical system. The correction plate 10 is made of aluminum alloy, and its outer surface is matte black after surface treatment. Other metal parts with matte black outer surfaces can also be substituted. The size of the correction plate 10 needs to completely cover the field of view of the optical system. The strapdown detection system starts working, and the uniform surface of the correction plate 10 is used to perform non-uniformity correction, thereby improving the detection imaging quality.

[0038] In the present application, the optical system provided includes a lens barrel 70 and a plurality of lenses 71. The lens barrel 70 is connected to the detection bracket 20. The lens barrel 70 is made of a low-expansion alloy. The low-expansion alloy generally also has good strength and hardness. It can maintain good mechanical properties and structural stability under high temperature conditions and is not easy to deform or break. The plurality of lenses 71 is provided with at least 5 lenses, and the focal length is designed to be 43 mm. The lens 71 is made of a combination of sulfur-based materials and germanium materials to eliminate the thermal difference of the system.

[0039] One of the lenses 71 is located at the front side of the lens barrel 70 and is directly connected to the cabin 1. It is used as an optical window. The optical window material is zinc sulfide and is radially installed on the aircraft cabin 1. The lens 71 is designed as an optical window. The lens 71 often has good thermal stability. The lens 71 is conformally designed with the cabin 1 to reduce air resistance, reduce the energy consumption of the aircraft, and may increase the flight speed and efficiency.

[0040] The remaining lenses 71 are distributed on the lens barrel 70. The working wavelength of the multiple lenses 71 is 8-14um, and it is set to be imaged once, which effectively controls the length of the optical system. In addition, the diameter of the optical window is designed to be 65mm. By reasonably designing the aperture of the optical window and the focal length of the optical system, the aperture of the optical system is moderate, the diameter of the entire strapdown detection system is controlled within 85mm, and the length is controlled within 120mm. The optical system is placed at the front end of the aircraft as much as possible, and the miniaturized design can make full use of the tapered space at the front end of the aircraft, which is conducive to realizing multi-mode composite guidance and improving guidance accuracy and anti-interference ability.

[0041] When the aircraft reaches the predetermined distance, the strapdown detection system starts to work, and the infrared radiation energy of the observed target is focused onto the focal plane of the detector 21 through the lens 71. The detector 21 simultaneously integrates the pixels of the entire focal plane to form an infrared radiation signal, and then the infrared radiation signal is converted into an electrical signal and pre-processed by the signal processing system.

[0042] In the present application, the aircraft isolates aerodynamic heat in the front and middle range by jettisoning the shield at the end, reducing the temperature rise of the infrared window and the seeker cabin. The shield jettisoning action is generally achieved by the explosion of pyrotechnics, and the impact generated is often of very large magnitude, causing damage to the signal processing system of the strapdown detection system. Therefore, by distributing the shock absorber 8 along the circumference of the detection bracket 20, the shock absorber 8 provides rigidity through the elastic deformation of the metal element, and the sliding friction of the metal element provides damping to achieve the purpose of vibration isolation and buffering, reducing the magnitude of vibration impact transmitted to the vicinity of the detector 21, thereby avoiding damage to the signal processing system.

[0043] In addition, a circular envelope is distributed along the circumference of the detection bracket 20, and the vibration absorber 8 is located in the circular envelope. By placing the vibration absorber 8 in the circular envelope of the detector 21 bracket, the vibration absorber 8 is conformally designed with the infrared signal board 30, the data acquisition board 31, and the infrared imaging main board 32. The signal processing system is located at the center of the four groups of vibration absorbers 8, thereby making full use of the structural space.

[0044] In the present application, when the aircraft performs the shield jettisoning action, an impact force is generated on the optical window, and in order to reduce the deformation of the optical window, the window pressing ring 90 is threadedly connected between the cabin 1 and the lens 71, and the window pressing ring 90 is conformally designed with the optical window to reduce aerodynamic resistance, and the flexible installation can also improve the reliability of high-speed guided infrared imaging detection.

[0045] In addition, a cabin body 1 gap is provided between the lens 71 and the cabin body 1, and a pressure ring gap 92 is provided between the window pressure ring 90 and the lens 71. The sizes of the pressure ring gap 92 and the cabin body gap 91 are 0.25 mm. Silicone rubber 93 is provided in both the cabin body 1 gap and the pressure ring gap 92. The silicone rubber 93 is elastic and can effectively absorb impact and convert the impact force into elastic deformation of the silicone rubber 93, which greatly reduces the risk of the optical window being broken when the cover is thrown and impacted, thereby improving reliability.

[0046] The implementation principle of a strapdown detection system based on frame-integrated non-cooled infrared imaging disclosed in the present application is: when the aircraft reaches a predetermined distance, the strapdown detection system starts to work, and the infrared radiation energy of the observed target is focused on the focal plane of the detector 21 through the lens 71. The detector 21 integrates the pixels of the entire focal plane at the same time to form an infrared radiation signal, and then converts the infrared radiation signal into an electrical signal and pre-processes it through the signal processing system. The processed digital information transmits the target characteristics to the rear end of the aircraft in the form of digital video through the external connector 5 to achieve precise guidance. The infrared signal board 30 realizes data transmission with the data acquisition board 31 through the first flexible cable 4, and the infrared imaging main board 32 is connected to the external connector 5 through the second flexible cable 6, so that the data acquisition board 31 and the infrared imaging main board 32 can be arranged as far away from the detector 21 as possible, thereby reducing the heat radiation effect of the heating components in the data acquisition board 31 and the infrared imaging main board 32, and ensuring the imaging quality of the detector 21. In addition, the detector 21 is set as a frame-integrated non-cooled detector 21. The detector 21 adopts a frame-integrated exposure method to control the integration time to the millisecond level, reduce the integration time, and improve the problem of image blur under high-speed conditions; the non-cooled imaging system is adopted, and no refrigerator is required, so as to realize the miniaturization and lightweight of the detection device. Therefore, the present application is effective in clearly detecting and imaging the target in the terminal stage of flight. The strapdown detection system is small in size, light in weight, and has strong anti-body disturbance capability. It is suitable for infrared detection in the terminal stage of single-mode and multi-mode composite seekers, and is especially suitable for compact aircraft to achieve precise guided strikes on targets.

[0047] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0048] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0049] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A strapdown detection system based on frame-integrated uncooled infrared imaging, characterized in that: include: Cabin (1); An optical system connected to the front end of the cabin (1) and used to focus the infrared radiation energy of the target to be measured; A detection system, comprising a detection bracket (20) and a detector (21), wherein the detection bracket (20) is located at the rear side of the optical system, and the detector (21) is connected inside the detection bracket (20); A signal processing system, comprising an infrared signal board (30), a data acquisition board (31) and an infrared imaging main board (32), wherein the infrared signal board (30) is fixed to the detector (21) and interconnected via signals, a first flexible flat cable (4) is connected between the data acquisition board (31) and the infrared signal board (30), and the infrared imaging main board (32) and the data acquisition board (31) are connected via a plug-in; An external connector (5) is connected to the detection bracket (20), and a second flexible cable (6) is connected to the infrared imaging mainboard (32), and the second flexible cable (6) is connected to the external connector (5).

2. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 1, characterized in that: The optical system comprises: A lens barrel (70) connected to the detection bracket (20); A plurality of lenses (71), one of which is located at the front side of the lens barrel (70) and connected to the cabin (1) to serve as an optical window, and the remaining lenses (71) are distributed on the lens barrel (70).

3. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 2, characterized in that: The plurality of lenses (71) are arranged to form an image at one time.

4. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 1, characterized in that: The detection bracket (20) has vibration dampers (8) distributed along its circumference.

5. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 4, characterized in that: A circular envelope is distributed on the detection bracket (20) along its circumference, and the vibration damper (8) is located within the circular envelope.

6. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 2, characterized in that: A window pressing ring (90) is threadedly connected between the cabin body (1) and the lens (71).

7. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 6, characterized in that: A cabin body (1) gap is provided between the lens (71) and the cabin body (1), a pressure ring gap (92) is provided between the window pressure ring (90) and the lens (71), and silicone rubber (93) is provided in both the cabin body (1) gap and the pressure ring gap (92).

8. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 1, characterized in that: A correction plate (10) is provided on the front side of the optical system.

9. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 2, characterized in that: The operating wavelength between the multiple lenses (71) is 8-14 um.

10. A strapdown detection system based on frame-integrated uncooled infrared imaging as claimed in claim 1, characterized in that: The second flexible cable (6) is provided with a soldering pad (60), and the soldering pad (60) is buckled with the external connector (5).

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