Divided-aperture composite semi-physical simulation system for radar infrared double-spherical-surface opposite movement

Abstract

The invention provides a sub-aperture composite semi-physical simulation system for radar infrared double-spherical-surface opposite movement. The sub-aperture composite semi-physical simulation system comprises a five-axis rotary table in a darkroom, a radar target simulator system and an infrared target simulator. The aircraft is mounted on the five-axis turntable, three axes in the five-axis turntable simulate the flight attitude of the aircraft, and two axes outside the five-axis turntable are used for driving the infrared target simulator to simulate the sight angle motion of an infrared target; the outer second shaft rotates around the rotation center of the three-shaft rotary table, the motion envelope of the outer second shaft is a spherical surface, and the center of the spherical surface is the rotation center of the three-shaft rotary table; a radio frequency antenna array of the radar target simulator system is arranged as a spherical surface, the center of the spherical surface coincides with the rotation center of a rotary table, a radio frequency target movement spherical surface and an infrared target movement spherical surface are concentric, the position of a radio frequency target changes, an infrared target moves reversely, a radio frequency target radiation signal and an infrared target signal are collinear, and the signal propagation direction points to the rotation center. The method has the effect of solving the full-route closed-loop semi-physical simulation of the sub-caliber composite aircraft in a set of semi-physical simulation system.

Description

Technical Field

[0001] This invention belongs to the field of aircraft guidance technology, specifically, it relates to a split-aperture composite hardware-in-the-loop simulation system based on radar infrared target dual-sphere facing motion simulation. Background Technology

[0002] The "radar-infrared split-aperture composite guidance aircraft" is a composite guidance aircraft where the physical receiving apertures of the radar sensor and the infrared sensor are separate. That is, the radar antenna aperture and the infrared optical system aperture of the aircraft are not shared, and they are spatially independent. Currently, there are three main hardware-in-the-loop simulation systems for radar-infrared split-aperture composite guidance aircraft both domestically and internationally: one is a joint hardware-in-the-loop simulation system based on both radar and infrared hardware-in-the-loop simulation systems; the second is a composite simulation system based on an infrared hardware-in-the-loop simulation system; and the third is a composite simulation system based on a radar hardware-in-the-loop simulation system.

[0003] The first approach requires disassembling the aircraft's detection component into two parts: a radar sensor and an infrared sensor. These are placed in two separate hardware-in-the-loop (HIL) simulation systems. A logically integrated simulation experiment is achieved through dual-sensor communication and coordinated control of the two systems. However, this approach suffers from several drawbacks: it requires the resources of two HIL simulation systems, there are differences in the dynamic performance of the two flight attitude simulation turntables, and signal delays occur when the two HIL simulation systems are far apart.

[0004] The second approach requires replacing the infrared target simulator in the traditional infrared hardware-in-the-loop simulation system with a radar-infrared dual-mode composite target simulator. Since the aircraft uses a split-aperture composite system, the target simulator needs a sufficiently large infrared field of view and pupil coverage, as well as a sufficiently wide RF beam to cover the equivalent aperture of both sensors during the aircraft's roll motion. Essentially, this equates split-aperture composite to common-aperture composite. Several issues arise: First, the increased equivalent aperture puts pressure on the load of the flight attitude simulation turntable. For example, placing an infrared sensor located on the side of the aircraft at the center of rotation of the turntable requires the turntable's aperture to be approximately twice the aircraft diameter, and the significant off-center loading during motion makes it prone to structural interference with the common-aperture composite target. Second, it puts pressure on the design of the common-aperture composite target, requiring an increased optical exit pupil aperture and RF working area, as well as real-time compensation measures for the lever arm effect. Third, common-aperture composite targets typically use beamforming devices, which, along with their supporting structures, introduce significant errors.

[0005] The third approach requires introducing an infrared target simulation system into the anechoic chamber. For example, the dual-mode infrared / radar hardware-in-the-loop test assets at the Johns Hopkins University Applied Physics Laboratory (O'Bannon, TE, SA Gearhart. Dual-mode infrared and radar hardware-in-the-loop test assets at the Johns Hopkins University Applied Physics Laboratory. 1996. Vol:2741) simulates the line-of-sight motion of an infrared target through a multi-stage optical system and tilting mirrors. However, its infrared scanning field of view is only 10°, making it difficult to simulate large-angle rolls of aircraft. The hardware-in-the-loop missile simulation facility of the Japanese Ministry of Defense (Eguchi, H., K. Obana, M. Kamiya. Hardware-in-the-loopmissile simulation facility. 1998. Vol:3368) uses a fixed infrared target method, requiring the infrared line-of-sight angle signal to be forcibly applied to the gyroscope, thus disrupting the product's functionality.

[0006] For example, patent document CN106556288A discloses a five-axis turntable-based aero-optical infrared imaging target simulation system for testing and hardware-in-the-loop simulation of infrared imaging detection and guidance systems for high-speed aircraft within the atmosphere. To overcome the shortcomings of existing infrared imaging target simulation systems in simulating aero-optical effects, this system converts the aero-optical effects applied to the device under test into the infrared imaging target simulation system based on the principle of optical transformation. By simply using software calculations, a dynamic infrared target scene containing aero-optical effects can be generated within the existing infrared imaging target simulation system. This five-axis turntable-based aero-optical infrared imaging target simulation system can simulate aero-optical effects to verify and evaluate the impact of aero-optical effects on the performance of infrared imaging detection and guidance systems.

[0007] Patent document CN106556288A and other domestic units have adopted a scheme in which a five-axis turntable drives a beam combiner and an infrared target simulator to follow the beam. By biasing the combiner, the infrared signal is reflected to the infrared entrance pupil. If the aircraft rotation angle is too large, the infrared beam cannot illuminate the infrared sensor pupil. Therefore, the turntable roll axis usually needs to be locked during the simulation process, which makes it impossible to simulate the aircraft rotation attitude and thus impossible to achieve full-route simulation.

[0008] To address the problem of full-course closed-loop hardware-in-the-loop simulation of a split-aperture composite aircraft within a hardware-in-the-loop simulation system, this invention designs a split-aperture composite hardware-in-the-loop simulation system with opposing radar and infrared dual spherical surfaces, thus resolving the aforementioned issues. Summary of the Invention

[0009] To address the shortcomings of existing technologies, the purpose of this invention is to provide a split-aperture composite hardware-in-the-loop simulation system for the facing motion of dual spherical radar infrared surfaces.

[0010] According to the present invention, a split-aperture composite hardware-in-the-loop simulation system for radar infrared dual-sphere facing motion includes: an anechoic chamber and a five-axis turntable, a radar target simulator system and an infrared target simulator disposed in the anechoic chamber; The aircraft is mounted on a five-axis turntable. The inner three axes of the turntable simulate the aircraft's flight attitude, while the outer two axes drive the infrared target simulator to simulate the infrared target's line-of-sight angle movement. The outer two axes rotate around the rotation center of the three-axis turntable, and their motion envelope is a sphere, with the center of the sphere being the rotation center of the three-axis turntable. The radio frequency antenna array of the radar target simulator system is spherical, with the center of the sphere coinciding with the rotation center of the turntable. The moving sphere of the radio frequency target is concentric with the moving sphere of the infrared target. When the position of the radio frequency target changes, the infrared target moves in the opposite direction. The radio frequency target radiated signal and the infrared target signal are collinear, and the signal propagation direction points towards the rotation center.

[0011] Preferably, a real-time simulation control system is provided between the five-axis turntable, the radar target simulator system, and the infrared target simulator. The real-time simulation control system controls the three components by sending and receiving signals.

[0012] Preferably, the infrared sensor of the aircraft performs backward detection by converting the optical path of the infrared sensor through a lens group and transforming it.

[0013] Preferably, the transformation mirror group includes a first reflecting mirror, a second reflecting mirror, a third reflecting mirror, and a fourth reflecting mirror.

[0014] Preferably, the transformation mirror group includes a first reflecting mirror, a second reflecting mirror, a first lens, a second lens, a third reflecting mirror, and a fourth reflecting mirror.

[0015] Preferably, the transformation mirror assembly includes at least one curved reflector.

[0016] Preferably, the transformation mirror assembly includes a lens and at least one curved reflector.

[0017] Preferably, the infrared sensor of the aircraft is installed in reverse for rearward detection.

[0018] Preferably, the five-axis turntable is an integrated five-axis turntable.

[0019] Preferably, the five-axis turntable is formed by adding two axis turntables to the original three-axis turntable.

[0020] Compared with the prior art, the present invention has the following beneficial effects: 1. Compared with joint simulation of two sets of hardware-in-the-loop simulation systems, it saves resources, eliminates the relative projectile attitude simulation error caused by two sets of flight attitude simulation turntables, and has a small signal delay.

[0021] 2. The system has high precision. The simulation of radio frequency targets and infrared targets is no different from traditional independent radio frequency and infrared hardware-in-the-loop simulation systems, avoiding the errors introduced by equivalent common aperture composite.

[0022] 3. The system structure is relatively simple and can be achieved by adding a two-axis target arm and a matching optical folding mirror assembly to the existing radio frequency anechoic chamber. Attached Figure Description

[0023] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a top-view schematic diagram of the radar-infrared composite simulation system of the present invention (the composite target is located at zero position).

[0024] Figure 2 This is a top-view schematic diagram of the radar-infrared composite simulation system of the present invention (simulating the line of sight of the composite target).

[0025] Figure 3 This is a schematic diagram of the optical path transformation of the infrared sensor of the present invention.

[0026] Figure 4 This is a schematic diagram of the infrared sensor of the present invention installed in reverse. Detailed Implementation

[0027] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0028] like Figures 1-4 As shown, a split-aperture composite hardware-in-the-loop simulation system for radar infrared dual-sphere facing motion includes: an anechoic chamber and a five-axis turntable, a radar target simulator system, an infrared target simulator, and a real-time simulation control system installed inside the anechoic chamber.

[0029] The composite guidance aircraft is mounted on a five-axis turntable. Three axes within the turntable simulate the aircraft's flight attitude, while the other two axes drive an infrared target simulator to simulate the line-of-sight motion of an infrared target. The two outer axes rotate around the rotation center of the three-axis turntable, their motion envelope being a sphere, with the center of the sphere being the rotation center of the three-axis turntable. The radio frequency antenna array of the radar target simulator system is also spherical, with its center coinciding with the rotation center of the turntable. The spherical surface of the radio frequency target's motion is concentric with the spherical surface of the infrared target's motion. As the position of the radio frequency target changes, the infrared target moves in the opposite direction. The radiated signals from the radio frequency target and the infrared target are collinear, and their propagation direction points towards the rotation center.

[0030] A real-time simulation control system is installed between the five-axis turntable, the radar target simulator system, and the infrared target simulator. This system controls the three by sending and receiving signals.

[0031] The working principle of this application is as follows: an integrated five-axis turntable or a five-axis turntable composed of a three-axis turntable and a two-axis turntable is placed in an anechoic chamber. The composite guidance aircraft is mounted on the inner three-axis roll axis of the five-axis turntable. The radar target radio frequency signal is radiated to the radar sensor aperture by the radio frequency antenna array of the radar target simulation system (requiring the aircraft's radar to detect forward). The infrared target radiation beam is radiated to the optical entrance pupil of the aircraft's infrared sensor by the infrared target simulator mounted on the target arm of the five-axis turntable (requiring the aircraft's infrared sensor to detect backward). This scheme fully utilizes two concentric opposing spherical surfaces: the spherical surface where the radio frequency antenna array is located realizes the radio frequency target motion, and the spherical surface where the infrared target motion is realized by the target arm of the five-axis turntable. The two spherical surfaces do not interfere with each other. On the spherical surfaces, the radio frequency target and the infrared target move synchronously in opposite directions, keeping the electrical axis of the radio frequency target and the optical axis of the infrared target coaxial and opposite, thus realizing the composite target simulation for the multi-aperture composite aircraft.

[0032] Specifically, the composite-guided aircraft is mounted on a five-axis turntable. Three axes within the turntable simulate the aircraft's flight attitude, while the other two axes drive an infrared target simulator to simulate the line-of-sight motion of an infrared target. The two outer axes rotate around the rotation center of the three-axis turntable, and their motion envelope is a sphere, with the center of the sphere being the rotation center of the three-axis turntable. The radio frequency antenna array of the radar target simulator system is also spherical, with its center coinciding with the rotation center of the turntable. The line-of-sight motion of the radio frequency target is achieved by controlling the antenna triplets or multi-element arrays. Therefore, the spherical surface on which the radio frequency target moves is concentric with the spherical surface on which the infrared target moves.

[0033] like Figure 2As shown, to achieve spatiotemporally consistent radar-infrared composite target simulation, when the radio frequency target moves, the infrared target must move in the opposite direction to ensure that the radio frequency target's radiated signal and the infrared target's signal are always collinear, and that the signal propagation direction always points towards the rotation center. Taking a two-dimensional top view as an example, when the radar target rotates by an angle θ relative to the zero position (with the antenna array center as the zero position), the infrared target moves in the opposite direction by an angle -θ.

[0034] To achieve backward detection by the aircraft's infrared sensor, an optical path folding and transformation method is employed, which involves folding and transforming the optical path of the infrared sensor. For example... Figure 3 As shown, the implementation involves assembling the radar and infrared sensors in a layout consistent with the aircraft. The radar sensor is positioned in front, while the infrared sensor is behind it and viewed obliquely downwards. The optical path is folded using a first, second, third, and fourth reflector, ensuring the optical axis aligns with the aircraft's axis of rotation and the turntable's roll axis, as well as with the radar sensor's electrical axis. To ensure the infrared sensor's optical parameters match those of the infrared target simulator's optical system, a transformation mirror group can be added as needed within the folded optical path to achieve optical transformation. This enables forward detection by the radar sensor and equivalent backward detection by the infrared sensor.

[0035] In one embodiment, the transformation lens group includes at least one lens assembly.

[0036] In one embodiment, the transformation mirror group includes a first lens and a second lens, which are arranged sequentially between a second reflector and a third reflector. The optical path is transformed by the sequence of first reflector-second reflector-first lens-second lens-third reflector-fourth reflector, ensuring that the optical axis is consistent with the aircraft axis and the turntable rotation axis, and also with the electrical axis of the radar sensor.

[0037] In one variation, the transformation mirror assembly comprises at least one curved mirror, which simultaneously performs the functions of mirror folding and optical transformation.

[0038] In one variation, the transformation mirror assembly comprises a lens and at least one curved mirror.

[0039] In one variation, to achieve backward detection by the aircraft's infrared sensor, tooling fixtures are used to install the infrared sensor in reverse. For example... Figure 4 As shown, the implementation method is to install the infrared sensor in reverse during installation, and ensure that the optical axis is consistent with the electric axis, machine axis and turntable rotation axis, so as to realize forward detection of the radar sensor and equivalent backward detection of the infrared sensor.

[0040] In one embodiment, the five-axis rotary table is an integrated five-axis rotary table.

[0041] In one variation, the five-axis turntable is formed by adding two axis turntables to the original three-axis turntable.

[0042] This invention integrates the functions and components of a radar-guided hardware-in-the-loop (HIPL) system and an infrared-guided HIPL system, formally combining two independent systems into one. Based on a three-axis flight attitude simulation turntable within the anechoic chamber of the radar-guided HIPL system, a two-axis turntable concentric with the three-axis turntable is added to form a five-axis turntable. An infrared target simulator is then installed on the two axes outside the five-axis turntable. Simultaneously, optical path reversal and reverse mounting techniques are employed to convert the original forward-looking infrared sensor into a backward-looking sensor. The spherical radio frequency array of the traditional radar-guided HIPL system serves as the forward-looking radar sensor to simulate radio frequency target interference scenarios, while the spherical motion of the two-axis turntable and the infrared target simulator on the two-axis turntable serve as the backward-looking infrared sensor to simulate infrared imaging scenarios. This achieves the simulation of the opposing motion of radar and infrared composite targets, thus realizing a spatiotemporally consistent simulation of composite targets.

[0043] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0044] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0045] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A split-aperture composite hardware-in-the-loop simulation system for the facing motion of dual spherical radar infrared surfaces, characterized in that, include: A darkroom, and a five-axis turntable, radar target simulator system, and infrared target simulator installed inside the darkroom; The aircraft is mounted on a five-axis turntable. The inner three axes of the turntable simulate the aircraft's flight attitude, while the outer two axes drive the infrared target simulator to simulate the infrared target's line-of-sight angle movement. The outer two axes rotate around the rotation center of the three-axis turntable, and their motion envelope is a sphere, with the center of the sphere being the rotation center of the three-axis turntable. The radio frequency antenna array of the radar target simulator system is spherical, with the center of the sphere coinciding with the rotation center of the turntable. The moving sphere of the radio frequency target is concentric with the moving sphere of the infrared target. When the position of the radio frequency target changes, the infrared target moves in the opposite direction. The radio frequency target radiated signal and the infrared target signal are collinear, and the signal propagation direction points towards the rotation center.

2. The radar infrared dual-sphere facing direction motion split-aperture composite hardware-in-the-loop simulation system according to claim 1, characterized in that, A real-time simulation control system is provided between the five-axis turntable, the radar target simulator system, and the infrared target simulator. The real-time simulation control system controls the three components by sending and receiving signals.

3. The radar infrared dual-sphere facing direction motion split-aperture composite hardware-in-the-loop simulation system according to claim 1, characterized in that, The aircraft's infrared sensor backward detection involves the optical route of the infrared sensor being transformed by a lens group and then folded and transformed.

4. The radar infrared dual-sphere facing direction motion split-aperture composite hardware-in-the-loop simulation system according to claim 3, characterized in that, The transformation mirror group includes a first reflecting mirror, a second reflecting mirror, a third reflecting mirror, and a fourth reflecting mirror.

5. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 3, characterized in that, The transformation mirror group includes a first reflecting mirror, a second reflecting mirror, a first lens, a second lens, a third reflecting mirror, and a fourth reflecting mirror.

6. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 3, characterized in that, The transformation mirror assembly includes at least one curved reflector.

7. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 3, characterized in that, The transformation mirror assembly includes a lens and at least one curved reflector.

8. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 1, characterized in that, The aircraft's infrared sensor for rearward detection is installed with the infrared sensor mounted in reverse.

9. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 1, characterized in that, The five-axis rotary table is an integrated five-axis rotary table.

10. The radar infrared dual-sphere facing motion split-aperture composite hardware-in-the-loop simulation system according to claim 1, characterized in that, The five-axis turntable is formed by adding two axis turntables to the original three-axis turntable.

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