CN111692920A - Space orientation energy reflection countermeasure method based on reflector - Google Patents

Abstract

The invention discloses a mirror-based space directional energy reflection confrontation method, comprising the following steps: installing a camera assembly and a directional energy reflection assembly on a satellite platform; using the camera assembly to detect enemy directional energy weapons in space, and obtain enemy directional energy weapons The real-time image of the directed energy weapon; based on the real-time image of the enemy directed energy weapon, the world coordinates of the enemy directed energy weapon are obtained, and the posture of the directed energy reflection component is adjusted according to the world coordinate of the enemy directed energy weapon, so that it reflects the enemy. Directed energy weapons Directed energy waves emitted by directed energy weapons. By installing a directional energy reflection component on the satellite platform, and adjusting the posture of the directional energy reflection component according to the detected world coordinates of the enemy's directional energy weapon, it reflects the directional energy wave emitted by the enemy's directional energy weapon. The characteristics of directed energy weapons can use the principle of optical reflection to achieve active defense against enemy directed energy weapons in the approach and confrontation in space.

Description

A mirror-based spatial directed energy reflection countermeasure method

technical field

The invention relates to the field of spatial directional energy reflection confrontation, in particular to a mirror-based spatial directional energy reflection confrontation method.

Background technique

Since the beginning of the new century, the international competition in space has intensified, and the acquisition of air dominance has already involved the core interests of the country. With the continuous development of space technology in countries around the world, safety protection has become an important part of space missions.

Directed energy weapon (including directed energy weapon and microwave weapon) is a kind of weapon that uses directed energy launched in a certain direction to attack the target. It has excellent performance such as fast, flexible, precise and anti-electromagnetic interference. can play a unique role. Directed energy weapons are recoilless and powerful, making them ideal space weapons. In the face of enemy directed energy weapon attacks, our satellites have long lacked effective active defense means.

SUMMARY OF THE INVENTION

In view of one or more deficiencies in the above-mentioned prior art, the present invention provides a mirror-based space directional energy reflection countermeasure method. According to the characteristics of the directional energy weapon, the principle of optical reflection can be used, and the method can be used in space approach countermeasures. , to achieve active defense against enemy directed energy weapons.

In order to achieve the above object, the present invention provides a mirror-based spatial directional energy reflection countermeasure method, comprising the following steps:

Step 1: Install the camera assembly and the directional energy reflection assembly on the satellite platform, wherein the directional energy reflection assembly covers the satellite platform, and the pose of the directional energy reflection assembly can be multi-degree-of-freedom on the satellite platform. Adjusted for reflected directed energy waves;

Step 2, use the camera assembly to detect the enemy directed energy weapon in space, and obtain the real-time image of the enemy directed energy weapon;

Step 3: Obtain the world coordinates of the enemy directed energy weapon based on the real-time image of the enemy directed energy weapon, and adjust the posture of the directed energy reflection component according to the world coordinates of the enemy directed energy weapon, so that it reflects the directed energy of the enemy directed energy weapon Directed energy waves emitted by weapons.

In a further improvement, in step 2, the use of the camera assembly to detect enemy directed energy weapons in space is specifically:

The camera assembly is used to continuously acquire detection images in space, and based on the detection images, a moving target detection algorithm is used to detect enemy directed energy weapons in space, wherein the moving target detection algorithm includes but is not limited to frame difference method and optical flow method.

In a further improvement, in step 3, the world coordinates of the enemy directed energy weapon are obtained based on the real-time image of the enemy directed energy weapon, and the posture of the directed energy reflection component is adjusted according to the world coordinates of the enemy directed energy weapon, specifically:

Step 3.1, obtaining the pixel coordinates (u _P , v _P ) of any point P on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon;

Step 3.2, based on the pixel coordinates (u _P , v _P ) of the point P and the calibration parameters of the camera component to obtain the world coordinates of the point P:

In the formula, (X _P , Y _P , Z _P ) is the world coordinate of point P, d _x , _dy represent the length of abscissa and ordinate of 1 pixel, f represents the focal length, z is the scale factor, c _x , c _y represents the position of the center point of the first real-time image in the pixel coordinate system, t _x , _ty , and t _z represent translation vectors, and ri _{(i=1 to 9)} represent rotation matrices;

Step 3.3, traverse all the points on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon and repeat steps 301-302 to obtain the world coordinates of the enemy directed energy weapon;

Step 3.4, based on the world coordinates of the satellite platform and the world coordinates of the enemy directed energy weapon, obtain the relative orientation of the enemy directed energy weapon and the satellite platform, and adjust the attitude of the directed energy reflection component based on the relative orientation.

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

The reflecting unit includes two lateral reflecting members and two vertical reflecting members, wherein the two lateral reflecting members are connected and perpendicular to each other, the two vertical reflecting members are separated from each other and are parallel to each other, and the lateral reflecting members are The two lateral reflecting members and the two vertical reflecting members are perpendicular to each other, and the two lateral reflecting members and the two vertical reflecting members form a wedge-shaped groove. Made of highly reflective material;

In the directional energy reflective assembly, two adjacent reflective units share a horizontal reflector or vertical reflector, two adjacent reflective units in the horizontal direction are connected by a horizontal support edge, and two adjacent reflective units in the longitudinal direction are connected by a horizontal support edge. Connected by the longitudinal support edges, that is, each transverse reflector in the directed energy reflection assembly is connected with the transverse support edges, and each vertical reflector is connected with the longitudinal support edges.

In a further improvement, the lateral reflector and the vertical reflector are made of flexible materials, and the lateral and vertical support edges are both strip-shaped airbags, so that the directional energy reflector assembly is small before the satellite platform lifts off. , Light weight, portable and foldable, when the satellite platform reaches the space port, the directional energy reflection component can be expanded by inflating the horizontal and vertical supporting sides.

In a further improvement, the lateral reflector is made of rigid material, the vertical reflector is made of flexible material, the lateral support edges are rigid support columns, and the longitudinal support edges are all strip-shaped airbags;

In the same reflecting unit unit, two corresponding sides connected with the two lateral reflectors are hinged to each other, and the two corresponding sides separated from the two lateral reflectors are respectively connected with the two lateral support sides;

In order to make the directional energy reflection component small in size, light in weight, portable and foldable before the satellite platform lifts off, and after the satellite platform reaches space, the directional energy reflection component can be expanded by inflating the longitudinal support edge, and it is effective after the directional energy reflection component is deployed. maintains its configuration.

Further improved, step 1 also includes:

A directed energy shielding assembly is mounted on the satellite platform, the directed energy shielding assembly encircling the optical sensing unit on the satellite platform.

In a further improvement, the directed energy protection component is a directed energy protection film made of C ₆₀ thin film material or vanadium oxide.

The present invention provides a mirror-based space directional energy reflection countermeasure method, by installing a directional energy reflection component on a satellite platform, and adjusting the posture of the directional energy reflection component according to the detected world coordinates of the enemy's directional energy weapon, so that the It reflects the directed energy wave emitted by the enemy directed energy weapon. According to the characteristics of the directed energy weapon, the principle of optical reflection can be used to achieve active defense against the enemy directed energy weapon in the space approach confrontation.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained according to the structures shown in these drawings without creative efforts.

1 is a schematic diagram of a mirror-based spatial directional energy reflection countermeasure system adopted in an embodiment of the present invention;

Fig. 2 is the schematic diagram that the directed energy wave reflected in the embodiment of the present invention strikes the enemy directed energy weapon;

3 is a schematic structural diagram of a directed energy reflection assembly in an embodiment of the present invention;

FIG. 4 is a working principle diagram of a directed energy reflection component in an embodiment of the present invention;

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

The realization, functional characteristics and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relationship between various components under a certain posture (as shown in the accompanying drawings). The relative positional relationship, the movement situation, etc., if the specific posture changes, the directional indication also changes accordingly.

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

In the present invention, unless otherwise expressly specified and limited, the terms "connected", "fixed" and the like should be understood in a broad sense, for example, "fixed" may be a fixed connection, a detachable connection, or an integrated; It can be a mechanical connection, an electrical connection, a physical connection or a wireless communication connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction between the two elements. unless otherwise expressly qualified. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but must be based on the realization by those of ordinary skill in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered that the combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

In view of the characteristics of the directed energy weapon, this embodiment can utilize the principle of optical reflection to realize active defense against the enemy directed energy weapon in the approach and confrontation in space. This embodiment adopts a mirror-based space directional energy reflection countermeasure system as shown in FIG. 1 , which includes a satellite platform and a camera component mounted on the satellite platform, a directional energy reflection component and a directional energy protection component. For the attack of the enemy's directed energy weapon, the directed energy wave is launched by the enemy's directed energy weapon, and the satellite platform controls the directed energy reflection component to reflect the directed energy wave, and the reflected directed energy wave strikes the enemy directed energy weapon, such as shown in Figure 2.

Referring to FIGS. 3-4 , the first implementation of the directional energy reflection assembly in this embodiment includes a plurality of reflection units distributed in an array; the reflection unit includes two lateral reflection members and two vertical reflection members, wherein the two The lateral reflectors are connected and perpendicular to each other, the two vertical reflectors are separated from each other and parallel to each other, the lateral reflectors and the vertical reflectors are perpendicular to each other, the two lateral reflectors and the two vertical reflectors form a wedge-shaped groove, and the two The surfaces of the transverse reflectors and the two vertical reflectors located in the wedge-shaped grooves are made of highly reflective materials. In the directional energy reflective assembly, two adjacent reflective units share a horizontal reflector or vertical reflector, two adjacent reflective units in the horizontal direction are connected by a horizontal support edge, and two adjacent reflective units in the longitudinal direction are connected by a horizontal support edge. Connected by the longitudinal support edges, that is, each transverse reflector in the directed energy reflection assembly is connected with the transverse support edges, and each vertical reflector is connected with the longitudinal support edges.

With the transverse reflector and the vertical reflector arranged perpendicular to each other, the reflective unit can reflect the directional energy no matter which angle the directional energy is incident from. The reflection unit reflects the directional energy to the maximum extent when facing the attack of the directional energy weapon. First, it can avoid its own damage. Secondly, by adjusting the angle of the directional energy reflection unit, the directional energy can be reflected back to the enemy's directional energy weapon, causing damage to the opponent.

Although the array combination structure of the directional energy reflection components can increase the defense area, the excessively large area of the directional energy reflection components will increase the air resistance of the satellite during the launch process, thus making it difficult to launch satellites. In response to this problem, this embodiment provides the following second and third embodiments of the directed energy reflection component.

As a further preferred second embodiment of the directional energy reflection assembly, on the basis of the first embodiment, in the second embodiment, the horizontal reflector and the vertical reflector are made of light weight, good flexibility, foldable, strong It is made of high-quality material, and the side of the lateral reflector and the vertical reflector located in the wedge-shaped groove is coated with a high-reflection layer, such as copper or copper alloy thin film layer. The lateral support edge and the longitudinal support edge are flexible strip airbags, and the airbag material is selected from plastic, rubber or fiber film, etc.; and the horizontal and vertical support sides are provided with valves capable of inflating and deflating. The directional energy reflection assembly in this embodiment is small in size, light in weight, portable and foldable before the satellite platform lifts off, and the directional energy reflection assembly can be unfolded by inflating the lateral and vertical support sides when the satellite platform reaches the space port.

The working process of the second embodiment of the above-mentioned directional energy reflection assembly is as follows: when the satellite platform is launched with the rocket, the inflatable longitudinal support edge and the lateral support edge are in a folded state, so that the vertical reflector and the lateral reflector are folded, to get the smallest footprint. When lifted to a predetermined position, the airbag is inflated into the inflatable longitudinal support edge and the lateral support edge to expand the airbag, and both the vertical reflector and the lateral reflector are re-deployed and flattened.

As a further preferred third embodiment of the directional energy reflective component, on the basis of the first embodiment, the vertical reflector in the third embodiment is made of a material with light weight, good flexibility, foldability and high strength , and the side of the vertical reflector located in the wedge-shaped groove is coated with a highly reflective layer, such as a copper or copper alloy thin film layer; while in the process of reflecting directional energy waves, the lateral reflector reflects more energy, so the lateral reflection The element is made of a rigid copper or copper alloy material and can withstand greater heat in the process of reflecting directed energy than a vertical reflector. The lateral support edge is a rigid support column, such as copper rod or copper alloy rod, etc. The longitudinal support edge is a flexible strip airbag, and the airbag material is selected from plastic, rubber or fiber film, etc.; gas valve. in. In the same reflection unit unit, the two corresponding sides of the two lateral reflection members are hinged to each other, the two corresponding sides of the two lateral reflection members that are separated from each other are hingedly connected to the two lateral support sides, and the lateral reflection member is connected to the vertical reflection member. Adhesive connection is adopted between the parts, between the vertical reflector and the longitudinal support edge. The directional energy reflective component in this embodiment is small in size, light in weight, portable and foldable before the satellite platform is lifted into space. After the satellite platform reaches space, the directional energy reflective component can be unfolded by inflating the longitudinal support side, and the directional energy reflective component can be expanded after the satellite platform reaches space. The assembly effectively maintains its configuration after deployment and has a longer service life.

The working process of the third embodiment of the above-mentioned directional energy reflection assembly is as follows: when the satellite platform is launched with the rocket, the inflatable longitudinal support edge is in a folded state, so that the vertical reflector is folded, and the lateral reflector is attached to each other, so that the It obtains the smallest footprint. When lifted to a predetermined position, the inflatable longitudinal support side is inflated to expand the airbag, the vertical reflector is re-deployed and flat, and the lateral reflector is separated.

In this embodiment, the directional energy reflection component is built on the satellite platform through a flexible support structure, and the directional energy reflection component has the function of multi-degree-of-freedom movement driven by the flexible support structure, and can reflect directional energy waves in any direction. However, how to set the support structure to support the planar structure and change the orientation of the planar structure through the support structure is a conventional technical means, so it will not be repeated in this embodiment.

In the space approach confrontation, the optical sensing unit on the satellite platform is the "eye" of the satellite platform. The optical sensing unit plays a huge role in space target tracking, detection and other tasks, but due to the high sensitivity of the optical sensing unit , making it vulnerable to high-energy directed energy attacks. In order to ensure the tracking and detection of the target by the optical sensing unit, a directed energy protection component is used in this embodiment to reinforce the vulnerable optical sensing unit. When the optical sensing unit is not irradiated by directed energy, the directed energy protection component has high transmittance, allowing the optical sensing unit to continue to track the detection task; but when the optical sensing unit is illuminated by directed energy, the directed energy protection component is highly transmissive. Converted to high reflection. Therefore, in this embodiment, materials with extremely hard and transparent characteristics, good infrared and ultraviolet characteristics, extremely high anti-directed energy damage threshold, and rapid response are used to prepare the directed energy protection components.

Specifically, in this embodiment, a directed energy protective film made of C ₆₀ thin film material or vanadium oxide is used as the directed energy protective component. When the C ₆₀ film material is irradiated by weak light, the output light intensity is proportional to the input light intensity, that is, there is a linear relationship; when exposed to strong light, the output light intensity is saturated, and the output light intensity hardly follows the input light intensity. change, that is, there is a nonlinear relationship. Among them, the preparation of C ₆₀ is mainly through the pyrotechnic method, bombarding graphite with a high-power laser beam to make it gasify, and using helium gas with a pressure of 1MPa to generate ultrasonic waves, so that the carbon atoms gasified by the laser beam enter the vacuum through a small nozzle to expand, and Rapid cooling forms new carbon molecules, resulting in C ₆₀ . When the vanadium oxide material is heated by directional energy beam irradiation, the material will undergo a semiconductor-metal phase transition process. With this process, its optoelectronic properties will change greatly, especially the infrared properties, which will be transformed from high transmission to high reflection. Directed energy protection can be achieved by blocking the attack of infrared light and electromagnetic radiation by utilizing the characteristic that the optical properties of vanadium oxide films show large changes with temperature. Among them, the preparation of vanadium oxide can be obtained by laser-induced gas-phase reaction or pyrolysis of vanadium oxalate.

旋转矩阵为

In this embodiment, the camera assembly adopts a conventional detection camera. Before the detection camera is put into use, the detection camera needs to be calibrated to obtain the internal parameters and external parameters of the camera, including the focal length f, pixel size, translation matrix T and Rotation matrix R. In this embodiment, the calibration method of the detection camera adopts a conventional calibration method in the field: Zhang Zhengyou's calibration method. Finally, the translation matrix between the detection camera and the world coordinate system is obtained as

The rotation matrix is

Referring to FIG. 5 , a mirror-based spatial directional energy reflection countermeasure method in this embodiment specifically includes the following steps:

Step 1, install the camera assembly, the directed energy reflection assembly, and the directed energy protection assembly on the satellite platform.

Step 2, using the camera assembly to detect the enemy directed energy weapon in the space, and obtain the real-time image of the enemy directed energy weapon, wherein the using the camera assembly to detect the enemy directed energy weapon in the space is specifically:

The camera component is used to continuously acquire detection images in the space, and based on the detection images, a moving target detection algorithm is used to detect enemy directed energy weapons in the space, wherein the moving target detection algorithm includes but is not limited to the frame difference method and the optical flow method.

Step 3: Obtain the world coordinates of the enemy directed energy weapon based on the real-time image of the enemy directed energy weapon, and adjust the posture of the directed energy reflection component according to the world coordinates of the enemy directed energy weapon, so that it reflects the directed energy of the enemy directed energy weapon Directed energy waves emitted by weapons. Wherein, obtaining the world coordinates of the enemy directed energy weapon based on the real-time image of the enemy directed energy weapon, and adjusting the posture of the directed energy reflection component according to the world coordinates of the enemy directed energy weapon, specifically:

Step 3.1, obtaining the pixel coordinates (u _P , v _P ) of any point P on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon;

Step 3.2, based on the pixel coordinates (u _P , v _P ) of the point P and the calibration parameters of the camera component to obtain the world coordinates of the point P:

In the formula, (X _P , Y _P , Z _P ) is the world coordinate of point P, d _x , _dy represent the length of abscissa and ordinate of 1 pixel, f represents the focal length, z is the scale factor, c _x , c _y represents the position of the center point of the first real-time image in the pixel coordinate system, t _x , _ty , and t _z represent translation vectors, and ri _{(i=1 to 9)} represent rotation matrices;

Step 3.3, traverse all the points on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon and repeat steps 301-302 to obtain the world coordinates of the enemy directed energy weapon;

Step 3.4, based on the world coordinates of the satellite platform and the world coordinates of the enemy directed energy weapon, obtain the relative orientation of the enemy directed energy weapon and the satellite platform, and adjust the attitude of the directed energy reflection component based on the relative orientation.

The above descriptions are only the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Under the inventive concept of the present invention, the equivalent structural transformations made by the contents of the description and drawings of the present invention, or the direct/indirect application Other related technical fields are included in the scope of patent protection of the present invention.

Claims (8)

1. a mirror-based space directional energy reflection confrontation method, is characterized in that, comprises the steps: Step 1: Install the camera assembly and the directional energy reflection assembly on the satellite platform, wherein the directional energy reflection assembly covers the satellite platform, and the pose of the directional energy reflection assembly can be multi-degree-of-freedom on the satellite platform. Adjusted for reflected directed energy waves; Step 2, use the camera assembly to detect the enemy directed energy weapon in space, and obtain the real-time image of the enemy directed energy weapon; Step 3: Obtain the world coordinates of the enemy directed energy weapon based on the real-time image of the enemy directed energy weapon, and adjust the posture of the directed energy reflection component according to the world coordinates of the enemy directed energy weapon, so that it reflects the directed energy of the enemy directed energy weapon Directed energy waves emitted by weapons. 2. The mirror-based space directed energy reflection confrontation method according to claim 1, wherein in step 2, the camera assembly is used to detect enemy directed energy weapons in space, specifically: The camera assembly is used to continuously acquire detection images in space, and based on the detection images, a moving target detection algorithm is used to detect enemy directed energy weapons in space, wherein the moving target detection algorithm includes but is not limited to frame difference method and optical flow method. 3. The mirror-based space directional energy reflection confrontation method according to claim 1, wherein in step 3, the world coordinates of the enemy directional energy weapon are obtained based on the real-time image of the enemy directional energy weapon, and according to the The world coordinates of the enemy directed energy weapon adjust the posture of the directed energy reflection component, specifically: Step 3.1, obtaining the pixel coordinates (u _P , v _P ) of any point P on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon; Step 3.2, based on the pixel coordinates (u _P , v _P ) of the point P and the calibration parameters of the camera component to obtain the world coordinates of the point P:

In the formula, (X _P , Y _P , Z _P ) is the world coordinate of point P, d _x , _dy represent the length of abscissa and ordinate of 1 pixel, f represents the focal length, z is the scale factor, c _x , c _y represents the position of the center point of the first real-time image in the pixel coordinate system, t _x , _ty , and t _z represent translation vectors, and ri _{(i=1 to 9)} represent rotation matrices; Step 3.3, traverse all the points on the enemy directed energy weapon in the real-time image of the enemy directed energy weapon and repeat steps 301-302 to obtain the world coordinates of the enemy directed energy weapon; Step 3.4, based on the world coordinates of the satellite platform and the world coordinates of the enemy directed energy weapon, obtain the relative orientation of the enemy directed energy weapon and the satellite platform, and adjust the attitude of the directed energy reflection component based on the relative orientation. 4. The mirror-based spatial directional energy reflection countermeasure method according to claim 1, 2 or 3, characterized in that, in step 1, the directional energy reflection assembly comprises several reflection units distributed in an array; The reflecting unit includes two lateral reflecting members and two vertical reflecting members, wherein the two lateral reflecting members are connected and perpendicular to each other, the two vertical reflecting members are separated from each other and are parallel to each other, and the lateral reflecting members are The two lateral reflecting members and the two vertical reflecting members are perpendicular to each other, and the two lateral reflecting members and the two vertical reflecting members form a wedge-shaped groove. Made of highly reflective material; In the directional energy reflective assembly, two adjacent reflective units share a horizontal reflector or vertical reflector, two adjacent reflective units in the horizontal direction are connected by a horizontal support edge, and two adjacent reflective units in the longitudinal direction are connected by a horizontal support edge. Connected by the longitudinal support edges, that is, each transverse reflector in the directed energy reflection assembly is connected with the transverse support edges, and each vertical reflector is connected with the longitudinal support edges. 5 . The mirror-based spatial orientation energy reflection countermeasure method according to claim 4 , wherein the lateral reflector and the vertical reflector are both made of flexible materials, and the lateral support edge and the longitudinal support edge are both made of flexible materials. 6 . It is a strip-shaped airbag, so that the directional energy reflector assembly is small in size, light in weight, portable and foldable before the satellite platform lifts off. When the satellite platform reaches the space port, the directional energy reflector assembly can be deployed by inflating the horizontal and vertical support sides. 6 . The mirror-based method for counteracting spatial directional energy reflection according to claim 4 , wherein the lateral reflector is made of rigid material, the vertical reflector is made of flexible material, and the lateral support The sides are rigid support columns, and the longitudinal support sides are all strip-shaped airbags; In the same reflecting unit unit, two corresponding sides connected with the two lateral reflectors are hinged to each other, and the two corresponding sides separated from the two lateral reflectors are respectively connected with the two lateral support sides; In order to make the directional energy reflection component small in size, light in weight, portable and foldable before the satellite platform lifts off, and after the satellite platform reaches space, the directional energy reflection component can be expanded by inflating the longitudinal support edge, and it is effective after the directional energy reflection component is deployed. maintains its configuration. 7. The mirror-based spatial directional energy reflection countermeasure method according to claim 1 or 2 or 3, characterized in that, in step 1, further comprising: A directed energy shielding assembly is mounted on the satellite platform, the directed energy shielding assembly encircling the optical sensing unit on the satellite platform. 8 . The mirror-based spatial directed energy reflection countermeasure method according to claim 7 , wherein the directed energy protection component is a directed energy protection film made of C ₆₀ thin film material or vanadium oxide. 9 .

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