阅读说明：本技术 一种基于反射镜的空间定向能反射对抗方法 (Space orientation energy reflection countermeasure method based on reflector ) 是由 杨夏 郭贵松 王杰 张新 张小虎 于 2020-06-12 设计创作，主要内容包括：本发明公开一种基于反射镜的空间定向能反射对抗方法,包括如下步骤：将相机组件、定向能反射组件安装在卫星平台上；利用相机组件探测空间中的敌方定向能武器,并获取敌方定向能武器的实时图像；基于敌方定向能武器的实时图像获取敌方定向能武器的世界坐标,并根据敌方定向能武器的世界坐标调整定向能反射组件的姿态,使其反射敌方定向能武器定向能武器发射的定向能波。通过在卫星平台上安装定向能反射组件,并根据探测到的敌方定向能武器的世界坐标调整定向能反射组件的姿态,使其反射敌方定向能武器定向能武器发射的定向能波,针对定向能武器的特点,可利用光学反射原理,在太空抵近对抗中,实现对敌方定向能武器的主动防御。(The invention discloses a space orientation energy reflection countermeasure method based on a reflector, which comprises the following steps: mounting a camera assembly and a directional energy reflecting assembly on a satellite platform; detecting enemy directional energy weapons in space by using a camera assembly, and acquiring real-time images of the enemy directional energy weapons; the method comprises the steps of acquiring world coordinates of an enemy directional energy weapon based on a real-time image of the enemy directional energy weapon, and adjusting the posture of a directional energy reflection assembly according to the world coordinates of the enemy directional energy weapon to enable the enemy directional energy weapon to reflect directional energy waves emitted by the enemy directional energy weapon. The directional energy reflection assembly is mounted on the satellite platform, the posture of the directional energy reflection assembly is adjusted according to the detected world coordinate of the enemy directional energy weapon, so that the directional energy wave emitted by the enemy directional energy weapon is reflected, and the active defense of the enemy directional energy weapon can be realized in space approaching confrontation by using an optical reflection principle according to the characteristics of the directional energy weapon.)

1. A mirror-based space orientation energy reflection countermeasure method is characterized by comprising the following steps:

step 1, a camera assembly and a directional energy reflection assembly are installed on a satellite platform, wherein the directional energy reflection assembly covers the satellite platform, and the pose of the directional energy reflection assembly can be adjusted in multiple degrees of freedom on the satellite platform to be used for reflecting directional energy waves;

step 2, detecting enemy directional energy weapons in the space by utilizing the camera assembly, and acquiring real-time images of the enemy directional energy weapons;

and 3, acquiring the world coordinate of the enemy directional energy weapon based on the real-time image of the enemy directional energy weapon, and adjusting the posture of the directional energy reflecting component according to the world coordinate of the enemy directional energy weapon to enable the directional energy reflecting component to reflect the directional energy wave emitted by the enemy directional energy weapon.

2. The mirror-based space-directed energy reflex countermeasure method of claim 1, wherein in step 2, the detection of enemy-directed energy weapons in space by the camera assembly is specifically:

continuously acquiring a detection image in a space by utilizing a camera assembly, and detecting an enemy-oriented weapon in the space by utilizing a moving object detection algorithm based on the detection image, wherein the moving object detection algorithm comprises but is not limited to a frame difference method and an optical flow method.

3. The mirror-based space-directed energy reflex countermeasure method according to claim 1, wherein in step 3, the real-time image based on the enemy-directed energy weapon acquires world coordinates of the enemy-directed energy weapon, and adjusts the attitude of the directional energy reflection component according to the world coordinates of the enemy-directed energy weapon, specifically:

step 3.1, acquiring pixel coordinates (u) of any point P on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon_P，v_P)；

Step 3.2, Pixel coordinates (u) based on Point P_P，v_P) The world coordinates of point P are obtained with the calibration parameters of the camera assembly:

in the formula (X)_P，Y_P，Z_P) World coordinate of point P, d_x、d_yRepresents the length of the abscissa and the length of the ordinate of 1 pixel, f represents the focal length, z is a scale factor, c_x、c_yRepresenting the position of the center point of the first live image in the pixel coordinate system, t_x、t_y、t_zRepresenting a translation vector, r_i(i＝1～9)Representing a rotation matrix;

3.3, traversing all points on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon and repeating the step 301 and the step 302 to obtain the world coordinate of the enemy directional energy weapon;

and 3.4, obtaining the relative position of the enemy directional energy weapon and the satellite platform based on the world coordinate of the satellite platform and the world coordinate of the enemy directional energy weapon, and adjusting the posture of the directional energy reflection assembly based on the relative position.

4. The mirror-based spatial direction energy reflection countermeasure method according to claim 1, 2 or 3, characterized in that in step 1, the directional energy reflection component comprises a plurality of reflection units distributed in an array;

the reflecting unit comprises two transverse reflecting pieces and two vertical reflecting pieces, wherein the two transverse reflecting pieces are connected and mutually perpendicular, the two vertical reflecting pieces are separated and mutually parallel, the transverse reflecting pieces are mutually perpendicular to the vertical reflecting pieces, the two transverse reflecting pieces and the two vertical reflecting pieces enclose a wedge-shaped groove, and the surfaces, positioned in the wedge-shaped groove, of the two transverse reflecting pieces and the surfaces, positioned in the wedge-shaped groove, of the two vertical reflecting pieces are both made of high-reflectivity materials;

in the directional energy reflecting assembly, two adjacent reflecting units share one transverse reflecting piece or one vertical reflecting piece, the two adjacent reflecting units in the transverse direction are connected through a transverse supporting edge, and the two adjacent reflecting units in the longitudinal direction are connected through a longitudinal supporting edge, namely, each transverse reflecting piece in the directional energy reflecting assembly is connected with the transverse supporting edge, and each vertical reflecting piece is connected with the longitudinal supporting edge.

5. The mirror-based space-directed energy reflection countermeasure method according to claim 4, wherein the transverse reflector and the vertical reflector are both made of flexible materials, and the transverse supporting edge and the longitudinal supporting edge are both strip-shaped airbags, so that the directional energy reflection assembly is small in size, light in weight, portable and foldable before the satellite platform is lifted, and the directional energy reflection assembly can be unfolded after the transverse supporting edge and the longitudinal supporting edge are inflated when the satellite platform reaches a space.

6. The mirror-based spatially directed reflectively countermeasure method of claim 4, wherein the lateral reflectors are made of a rigid material, the vertical reflectors are made of a flexible material, the lateral support edges are rigid support posts, and the longitudinal support edges are strip-shaped air pockets;

in the same reflection unit, two corresponding edges connected with two transverse reflection pieces are hinged with each other, and two corresponding edges separated from the two transverse reflection pieces are respectively connected with two transverse supporting edges;

the directional energy reflecting assembly is small in size, light in weight, portable and foldable before the satellite platform is lifted, the directional energy reflecting assembly can be unfolded by inflating the longitudinal supporting edge after the satellite platform arrives at space, and the configuration of the directional energy reflecting assembly is effectively kept after the directional energy reflecting assembly is unfolded.

7. The mirror-based spatial orientation energy reflection countermeasure method according to claim 1, 2 or 3, characterized in that step 1 further comprises:

and installing a directional energy protection assembly on the satellite platform, wherein the directional energy protection assembly surrounds the optical sensing unit on the satellite platform.

8. Mirror-based spatially directed energy reflection countermeasure method according to claim 7Wherein the directional energy protection component is composed of₆₀A film material or an orientation energy protective film made of vanadium oxide.

Technical Field

The invention relates to the field of space orientation energy reflection countermeasure, in particular to a space orientation energy reflection countermeasure method based on a reflector.

Background

Since the new century, the international competition of space is becoming stronger, and the taking of the right to arrest space has been related to the core interests of the country. With the continuous development of aerospace technologies in various countries in the world, safety protection becomes an important content of aerospace missions.

The directional energy weapon (including directional energy weapon and microwave weapon) is a target weapon attacked by using directional energy emitted in a certain direction, has the excellent performances of rapidness, flexibility, accuracy, electromagnetic interference resistance and the like, and can play a unique role in photoelectric countermeasure, air defense and strategic defense. The directional weapon has no recoil and great power, so that the directional weapon becomes an ideal space weapon. In the face of enemy directional weapon attack and the like, the satellite of our party lacks effective active defense means for a long time.

Disclosure of Invention

Aiming at one or more defects in the prior art, the invention provides a space directional energy reflection countermeasure method based on a reflector, aiming at the characteristics of a directional energy weapon, and the active defense against the enemy directional energy weapon can be realized in space approaching countermeasure by using the optical reflection principle.

In order to achieve the above object, the present invention provides a mirror-based space orientation energy reflection countermeasure method, which comprises the following steps:

step 1, a camera assembly and a directional energy reflection assembly are installed on a satellite platform, wherein the directional energy reflection assembly covers the satellite platform, and the pose of the directional energy reflection assembly can be adjusted in multiple degrees of freedom on the satellite platform to be used for reflecting directional energy waves;

step 2, detecting enemy directional energy weapons in the space by utilizing the camera assembly, and acquiring real-time images of the enemy directional energy weapons;

and 3, acquiring the world coordinate of the enemy directional energy weapon based on the real-time image of the enemy directional energy weapon, and adjusting the posture of the directional energy reflecting component according to the world coordinate of the enemy directional energy weapon to enable the directional energy reflecting component to reflect the directional energy wave emitted by the enemy directional energy weapon.

In a further improvement, in step 2, the detecting enemy-oriented energy weapons in the space by using the camera assembly specifically includes:

continuously acquiring a detection image in a space by utilizing a camera assembly, and detecting an enemy-oriented weapon in the space by utilizing a moving object detection algorithm based on the detection image, wherein the moving object detection algorithm comprises but is not limited to a frame difference method and an optical flow method.

In a further improvement, in step 3, the obtaining of the world coordinate of the enemy directional energy weapon based on the real-time image of the enemy directional energy weapon, and the adjusting of the posture of the directional energy reflection assembly according to the world coordinate of the enemy directional energy weapon are specifically:

step 3.1, acquiring pixel coordinates (u) of any point P on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon_P，v_P)；

Step 3.2, Pixel coordinates (u) based on Point P_P，v_P) The world coordinates of point P are obtained with the calibration parameters of the camera assembly:

in the formula (X)_P，Y_P，Z_P) World coordinate of point P, d_x、d_yRepresents the length of the abscissa and the length of the ordinate of 1 pixel, f represents the focal length, z is a scale factor, c_x、c_yRepresenting the position of the center point of the first live image in the pixel coordinate system, t_x、t_y、t_zRepresenting a translation vector, r_i(i＝1～9)Representing a rotation matrix;

3.3, traversing all points on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon and repeating the step 301 and the step 302 to obtain the world coordinate of the enemy directional energy weapon;

and 3.4, obtaining the relative position of the enemy directional energy weapon and the satellite platform based on the world coordinate of the satellite platform and the world coordinate of the enemy directional energy weapon, and adjusting the posture of the directional energy reflection assembly based on the relative position.

In a further improvement, in step 1, the directional energy reflecting assembly includes a plurality of reflecting units distributed in an array;

the reflecting unit comprises two transverse reflecting pieces and two vertical reflecting pieces, wherein the two transverse reflecting pieces are connected and mutually perpendicular, the two vertical reflecting pieces are separated and mutually parallel, the transverse reflecting pieces are mutually perpendicular to the vertical reflecting pieces, the two transverse reflecting pieces and the two vertical reflecting pieces enclose a wedge-shaped groove, and the surfaces, positioned in the wedge-shaped groove, of the two transverse reflecting pieces and the surfaces, positioned in the wedge-shaped groove, of the two vertical reflecting pieces are both made of high-reflectivity materials;

in the directional energy reflecting assembly, two adjacent reflecting units share one transverse reflecting piece or one vertical reflecting piece, the two adjacent reflecting units in the transverse direction are connected through a transverse supporting edge, and the two adjacent reflecting units in the longitudinal direction are connected through a longitudinal supporting edge, namely, each transverse reflecting piece in the directional energy reflecting assembly is connected with the transverse supporting edge, and each vertical reflecting piece is connected with the longitudinal supporting edge.

The horizontal reflecting piece and the vertical reflecting piece are made of flexible materials, and the horizontal supporting edge and the vertical supporting edge are strip-shaped air bags, so that the directional energy reflecting assembly is small in size, light in weight, portable and foldable before the satellite platform is lifted, and the directional energy reflecting assembly can be unfolded by inflating the horizontal supporting edge and the vertical supporting edge when the satellite platform reaches a too empty opening.

In a further improvement, the transverse reflecting piece is made of a rigid material, the vertical reflecting piece is made of a flexible material, the transverse supporting edges are rigid supporting columns, and the longitudinal supporting edges are strip-shaped air bags;

in the same reflection unit, two corresponding edges connected with two transverse reflection pieces are hinged with each other, and two corresponding edges separated from the two transverse reflection pieces are respectively connected with two transverse supporting edges;

the directional energy reflecting assembly is small in size, light in weight, portable and foldable before the satellite platform is lifted, the directional energy reflecting assembly can be unfolded by inflating the longitudinal supporting edge after the satellite platform arrives at space, and the configuration of the directional energy reflecting assembly is effectively kept after the directional energy reflecting assembly is unfolded.

In a further improvement, step 1 further includes:

and installing a directional energy protection assembly on the satellite platform, wherein the directional energy protection assembly surrounds the optical sensing unit on the satellite platform.

In a further development, the directionally-guarded component is a component made of C₆₀A film material or an orientation energy protective film made of vanadium oxide.

According to the space directional energy reflection countermeasure method based on the reflector, the directional energy reflection assembly is installed on the satellite platform, the posture of the directional energy reflection assembly is adjusted according to the detected world coordinate of the enemy directional energy weapon, so that the directional energy wave emitted by the enemy directional energy weapon is reflected, and the active defense on the enemy directional energy weapon can be realized in space approaching countermeasure by utilizing the optical reflection principle according to the characteristics of the directional energy weapon.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.

FIG. 1 is a schematic diagram of a mirror-based spatially directed energy reflective countermeasure system employed in an embodiment of the present invention;

FIG. 2 is a schematic illustration of reflected directional energy waves striking an enemy directional energy weapon in an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of a directionally reflective assembly in an embodiment of the present invention;

FIG. 4 is a schematic diagram of the operation of a directionally reflective assembly in an embodiment of the present invention;

FIG. 5 is a flow chart of a mirror-based spatial orientation energy reflection countermeasure method in an embodiment of the present invention.

The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.

In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.

Aiming at the characteristics of the directional energy weapon, the embodiment can realize active defense against the enemy directional energy weapon in space approaching confrontation by using the optical reflection principle. In this embodiment, a set of mirror-based space-orientation energy-reflection countermeasure system shown in fig. 1 is adopted, which includes a satellite platform, a camera assembly carried on the satellite platform, an orientation energy-reflection assembly, and an orientation energy-protection assembly. Aiming at the attack of the enemy directional energy weapon, the directional energy wave is emitted by the enemy directional energy weapon, the satellite platform controls the directional energy reflection assembly to reflect the directional energy wave, and the reflected directional energy wave strikes the enemy directional energy weapon, namely as shown in fig. 2.

Referring to fig. 3-4, a first embodiment of a directional reflective assembly in this example includes a plurality of reflective elements arranged in an array; the reflection unit comprises two transverse reflection pieces and two vertical reflection pieces, wherein the two transverse reflection pieces are connected and are mutually perpendicular, the two vertical reflection pieces are separated and are mutually parallel, the transverse reflection pieces are mutually perpendicular to the vertical reflection pieces, the two transverse reflection pieces and the two vertical reflection pieces enclose a wedge-shaped groove, and one surfaces, located in the wedge-shaped groove, of the two transverse reflection pieces and the one surfaces, located in the wedge-shaped groove, of the two vertical reflection pieces are made of high-reflectivity materials. In the directional energy reflecting assembly, two adjacent reflecting units share one transverse reflecting piece or one vertical reflecting piece, the two adjacent reflecting units in the transverse direction are connected through a transverse supporting edge, and the two adjacent reflecting units in the longitudinal direction are connected through a longitudinal supporting edge, namely, each transverse reflecting piece in the directional energy reflecting assembly is connected with the transverse supporting edge, and each vertical reflecting piece is connected with the longitudinal supporting edge.

By the transverse reflecting piece and the vertical reflecting piece which are arranged perpendicular to each other, the reflecting unit can reflect the directional energy no matter which angle the directional energy enters. When the reflection unit is in face of the directional energy weapon, the directional energy is reflected to the maximum extent, firstly self-damage can be avoided, and secondly, the directional energy can be reflected back to the enemy directional energy weapon by adjusting the angle of the directional energy reflection unit, so that the other party is damaged.

Although the array combination structure of the directional energy reflection assembly can increase the defense area, the air resistance of the satellite in the launching process can be increased by the overlarge volume of the directional energy reflection assembly, so that the difficulty of satellite launching is improved. In view of this problem, the present embodiment provides the following second and third embodiments of the directional reflective assembly.

In a second preferred embodiment of the directional energy reflecting assembly, based on the first embodiment, the lateral reflecting member and the vertical reflecting member in the second embodiment are made of light, flexible, foldable and strong materials, and one side of the lateral reflecting member and one side of the vertical reflecting member, which are located in the wedge-shaped groove, are coated with a highly reflective layer, such as a copper or copper alloy thin film layer. The transverse supporting edge and the longitudinal supporting edge are strip-shaped air bags with good flexibility, and the air bags are made of plastics, rubber or fiber membranes; the transverse reflecting piece and the transverse supporting edge and the vertical reflecting piece and the longitudinal supporting edge are connected in a bonding mode, and valves capable of inflating and deflating are arranged on the transverse supporting edge and the longitudinal supporting edge. The directional energy reflecting assembly under the embodiment has small volume, light weight, portability and foldability before the satellite platform is lifted, and the directional energy reflecting assembly can be unfolded by inflating the transverse supporting edge and the longitudinal supporting edge when the satellite platform arrives at a space.

The second implementation of the directional energy reflecting assembly specifically includes: when the satellite platform is launched along with the rocket, the inflatable longitudinal supporting edge and the inflatable transverse supporting edge are in folded states, so that the vertical reflecting piece and the transverse reflecting piece are folded, and the minimum occupied space is obtained. When the air bag is lifted to a preset position, the inflatable longitudinal supporting edge and the inflatable transverse supporting edge are inflated, so that the air bag is expanded, and the vertical reflecting piece and the transverse reflecting piece are unfolded and flattened again.

As a third preferred embodiment of the directional energy reflecting assembly, on the basis of the first embodiment, the vertical reflecting member in the third embodiment is made of a light, flexible, foldable and high-strength material, and one surface of the vertical reflecting member, which is positioned in the wedge-shaped groove, is coated with a high light reflecting layer, such as a copper or copper alloy thin film layer; and because the energy reflected by the transverse reflecting piece is more in the process of reflecting the directional energy wave, the transverse reflecting piece is made of rigid copper or copper alloy materials, and can bear larger heat in the process of reflecting the directional energy compared with the vertical reflecting piece. The transverse supporting edges are rigid supporting columns such as copper rods or copper alloy rods, the longitudinal supporting edges are strip-shaped air bags with good flexibility, and the air bags are made of plastics, rubber or fiber membranes; and the longitudinal supporting edge is provided with a valve capable of inflating and deflating. Wherein. In the same reflection unit, two corresponding edges that two horizontal reflection pieces link to each other are articulated each other, and two corresponding edges that two horizontal reflection pieces are separated from each other are articulated continuous with two horizontal support edges respectively, and all adopt the connected mode of bonding between horizontal reflection piece and the vertical reflection piece, between vertical reflection piece and the vertical support edge. The directional energy reflecting assembly under the implementation mode has the advantages that the size is small before the satellite platform is lifted, the weight is light, the assembly is portable and foldable, the directional energy reflecting assembly can be unfolded by inflating the longitudinal supporting edge after the satellite platform reaches the outer space, the configuration of the directional energy reflecting assembly is effectively kept after the directional energy reflecting assembly is unfolded, and the service life is longer.

The operation process of the third embodiment of the directional energy reflection assembly is specifically as follows: when the satellite platform is launched along with the rocket, the inflatable longitudinal supporting edge is in a folded state, so that the vertical reflecting piece is folded, and the transverse reflecting pieces are mutually attached to obtain the minimum occupied space. When the air bag is lifted to a preset position, the inflatable longitudinal supporting edge is inflated, so that the air bag is expanded, the vertical reflecting piece is unfolded and flat again, and the transverse reflecting piece is separated.

In the embodiment, the directional energy reflecting assembly is built on the satellite platform through the flexible supporting structure, and the directional energy reflecting assembly has the function of multi-degree-of-freedom movement under the driving of the flexible supporting structure, so that directional energy waves in any direction can be reflected. However, the structure setting and control setting for setting the supporting structure to support the planar structure and changing the orientation of the planar structure by the supporting structure are conventional technical means, and therefore, the detailed description is omitted in this embodiment.

In space approaching countermeasure, an optical sensing unit on a satellite platform is an 'eye' of the satellite platform, the optical sensing unit plays a great role in tasks such as space target tracking and detection, but the optical sensing unit is easy to be attacked by high-energy directional energy due to high sensitivity of the optical sensing unit, and in order to ensure the tracking and detection of the optical sensing unit on a target, the optical sensing unit which is easy to be attacked is reinforced by a directional energy protection component. When the optical sensing unit is not irradiated by the directional energy, the directional energy protection component has high transmittance, so that the optical sensing unit continuously tracks and detects a task; but when the optical sensing unit is illuminated by the directional energy, the directional energy shield assembly transitions from highly transmissive to highly reflective. Therefore, in the embodiment, the directional energy protection component is prepared from the material which has the characteristics of extreme hardness and transparency, good infrared and ultraviolet characteristics, extremely high directional energy damage resistance threshold value and quick response.

Specifically, C is used in this embodiment₆₀An orientation energy protection film made of a thin film material or vanadium oxide is used as an orientation energy protection component. C₆₀When the thin film material is irradiated by weak light, the output light intensity is in direct proportion to the output light intensity of a person, namely, the linear relation is formed; when the human body is irradiated by strong light, the output light intensity is saturated, and the output light intensity hardly changes along with the human body input light intensity, namely, the output light intensity has a nonlinear relation. Wherein, C₆₀The preparation method mainly comprises bombarding graphite with high-power laser beam to gasify the graphite by a pyro method, generating ultrasonic wave with helium gas with 1MPa pressure, making carbon atoms gasified by the laser beam enter vacuum expansion through a small nozzle, and rapidly cooling to form new carbon molecules, thereby obtaining C₆₀. When the vanadium oxide material is heated due to the irradiation of the directional energy beam, the material undergoes a semiconductor-metal phase transition process. Along with this process, the photoelectric characteristics of the material are greatly changed, especially the infrared characteristics, and the material is converted from high transmission to high reflection. The optical performance of the vanadium oxide film is shown along with the change of temperatureThe characteristic of great change can block the attack of infrared light and electromagnetic radiation, thus realize the directional energy protection. Wherein, the preparation of the vanadium oxide can be obtained by laser-induced gas phase reaction or thermal decomposition of oxalate of vanadium.

In this embodiment, the camera component adopts a conventional detection camera, and before the detection camera is put into use, the detection camera needs to be calibrated, so as to obtain internal parameters, external parameters and the like of the camera, specifically including a focal length f, a pixel size, a translation matrix T and a rotation matrix R. In this embodiment, the calibration method of the detection camera adopts a conventional calibration method in the art: zhangzhengyou calibration method. Finally obtaining a translation matrix between the detection camera and the world coordinate system as

A rotation matrix of

Referring to fig. 5, the method for spatial orientation energy reflection countermeasure based on a mirror in the present embodiment specifically includes the following steps:

step 1, a camera assembly, a directional energy reflection assembly and a directional energy protection assembly are installed on a satellite platform.

Step 2, detecting an enemy directional energy weapon in the space by using the camera assembly, and acquiring a real-time image of the enemy directional energy weapon, wherein the detecting of the enemy directional energy weapon in the space by using the camera assembly specifically comprises:

continuously acquiring a detection image in a space by utilizing a camera assembly, and detecting an enemy-oriented weapon in the space by utilizing a moving object detection algorithm based on the detection image, wherein the moving object detection algorithm comprises but is not limited to a frame difference method and an optical flow method.

And 3, acquiring the world coordinate of the enemy directional energy weapon based on the real-time image of the enemy directional energy weapon, and adjusting the posture of the directional energy reflecting component according to the world coordinate of the enemy directional energy weapon to enable the directional energy reflecting component to reflect the directional energy wave emitted by the enemy directional energy weapon. The real-time image based on the enemy directional energy weapon acquires the world coordinate of the enemy directional energy weapon, and adjusts the posture of the directional energy reflection assembly according to the world coordinate of the enemy directional energy weapon, and the method specifically comprises the following steps:

step 3.1, acquiring pixel coordinates (u) of any point P on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon_P，v_P)；

Step 3.2, Pixel coordinates (u) based on Point P_P，v_P) The world coordinates of point P are obtained with the calibration parameters of the camera assembly:

in the formula (X)_P，Y_P，Z_P) World coordinate of point P, d_x、d_yRepresents the length of the abscissa and the length of the ordinate of 1 pixel, f represents the focal length, z is a scale factor, c_x、c_yRepresenting the position of the center point of the first live image in the pixel coordinate system, t_x、t_y、t_zRepresenting a translation vector, r_i(i＝1～9)Representing a rotation matrix;

3.3, traversing all points on the enemy directional energy weapon in the real-time image of the enemy directional energy weapon and repeating the step 301 and the step 302 to obtain the world coordinate of the enemy directional energy weapon;

and 3.4, obtaining the relative position of the enemy directional energy weapon and the satellite platform based on the world coordinate of the satellite platform and the world coordinate of the enemy directional energy weapon, and adjusting the posture of the directional energy reflection assembly based on the relative position.

The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.