Dual redundant directional aiming system and method for rocket launch at sea

Abstract

The invention relates to a dual-redundant directional aiming system and method for launching a rocket at sea. The system comprises a first laser strapdown inertial group, a second laser strapdown inertial group and a folding light tube fixed on an adjustable base. A first self-collimating light tube and a second self-collimating light tube are fixed on the first laser strapdown inertial group and the second laser strapdown inertial group respectively. The folding light tube is provided with a first incident port, a second incident port and an outlet coaxially symmetrically distributed with the first incident port. A semi-transparent semi-reflecting mirror matched with the first incident port and the outlet and a plane reflector matched with the second incident port are provided in the folding light tube. Reflected light of the plane reflector is directed toward the semi-transparent semi-reflecting mirror. The first self-collimating light tube is aligned with the first incident port of the folding light tube, and the second self-collimating light tube is aligned with the second incident port of the folding light tube. The system has the advantages of compact structure, strong adaptability and high reliability. The method has the advantages of simple process and high automation, and can meet the requirements for launching a rocket under dynamic sea conditions.

Description

Technical Field

[0001] The invention relates to rocket launching technology, in particular to a dual-redundancy directional aiming system for launching a rocket at sea, and an aiming method using the system. Background Art

[0002] With the development of society and technology, the sea launch of rockets has the advantages of safety, flexibility, economy and efficiency, and has been increasingly valued by technical personnel in this field. The aiming system is used to transmit the north reference signal to the inertial group on the rocket before ignition and launch. At present, the launch vehicle mainly adopts the land launch method, and its aiming system adopts the solution of using theodolite to survey and transmit the geodetic azimuth. Because the surveyed geodetic azimuth position is fixed, and the theodolite needs manual operation when transmitting the azimuth, the process is relatively cumbersome and cannot adapt to the use conditions of the shaking of the sea launch platform. In order to meet the aiming needs of sea launch, the following problems need to be solved: 1. How to achieve high-precision autonomous orientation under sea conditions; 2. How to ensure the reliability of the aiming results without a fixed surveying benchmark for calibration. The aiming systems currently used for land launch methods cannot solve the above problems. Summary of the invention

[0003] The purpose of the present invention is to provide a dual redundant directional aiming system and method for rocket sea launch. The system has the advantages of compact structure, strong adaptability and high reliability. The method has the advantages of simple process and high degree of automation, which can meet the requirements of rocket launch under dynamic sea conditions.

[0004] In order to solve the above problems existing in the prior art, the present invention provides a dual redundant directional aiming system for rocket sea launch, comprising a first laser strapdown inertial group, a second laser strapdown inertial group and a folding light tube fixed on an adjustable base, wherein a first self-collimating light tube and a second self-collimating light tube are fixed on the first laser strapdown inertial group and the second laser strapdown inertial group respectively, the folding light tube is provided with a first incident port, a second incident port and an outlet port coaxially symmetrically distributed with the first incident port, a semi-transparent semi-reflecting mirror matching with the first incident port and the outlet port and a plane reflector matching with the second incident port are provided in the folding light tube, and reflected light of the plane reflector is directed toward the semi-transparent semi-reflecting mirror, the first self-collimating light tube is aligned with the first incident port of the folding light tube, and the second self-collimating light tube is aligned with the second incident port of the folding light tube.

[0005] Furthermore, the present invention provides a dual redundant directional aiming system for sea-based rocket launch, wherein the first laser strapdown inertial group is connected to a first satellite positioning device for providing position and timing information, and the second laser strapdown inertial group is connected to a second satellite positioning device for providing position and timing information.

[0006] Furthermore, the present invention provides a dual redundant directional aiming system for sea-based rocket launches, wherein the adjustable base includes a stand, a first platen is installed on the stand through a transverse oblong hole and a matching first bolt, first support members are fixed on both transverse sides of the stand respectively, the first support member is screwed with a first hand-tightened screw for pressing the first platen through a threaded hole, a second platen is installed on the first platen through a plurality of second bolts, the plurality of second bolts are correspondingly located in arc-shaped holes arranged along the circumference of the second platen, two second support members are fixed on one longitudinal side of the first platen, the second support member is screwed with a second hand-tightened screw for pressing the second platen through a threaded hole.

[0007] Furthermore, the present invention provides a dual-redundant directional aiming system for rocket sea launch, wherein the first laser strapdown inertial group and the second laser strapdown inertial group are fixed on the second platform, and the folding light pipe is fixed on the second platform via an adapter frame.

[0008] Furthermore, the present invention provides a dual-redundant directional aiming system for rocket sea launch, wherein the first autocollimation light tube is tilted and fixed on the first laser strapdown inertial group through a first bracket, and the second autocollimation light tube is tilted and fixed on the second laser strapdown inertial group through a second bracket.

[0009] Furthermore, the present invention provides a dual-redundant directional aiming system for rocket sea launch, wherein the first laser strapdown inertial group and the second laser strapdown inertial group are arranged side by side, the first autocollimation light tube and the second autocollimation light tube are arranged in parallel, and the first incident port and the second incident port of the folding light tube are arranged to match the first autocollimation light tube and the second autocollimation light tube.

[0010] Furthermore, the present invention provides a dual redundant directional aiming system for rocket sea launch, wherein the laser source wavelength of the first autocollimation light tube and the wavelength of the sensitive light of the photosensor are λ1, and the laser source wavelength of the second autocollimation light tube and the wavelength of the sensitive light of the photosensor are λ2, and λ1≠λ2.

[0011] Furthermore, the present invention provides a dual redundant directional aiming system for rocket sea launch, wherein the first laser strapdown inertial group and the second laser strapdown inertial group are used for autonomous north finding, the first autocollimation light tube is used to measure the angle between its optical axis and the normal of the prism on the arrow, and the second autocollimation light tube is used to measure the angle between its optical axis and the normal of the prism on the arrow.

[0012] Based on the same concept, the present invention also provides a rocket aiming method, comprising the following steps:

[0013] S1. Fix the dual redundant directional aiming system at a position matching the rocket aiming window through an adjustable base and then power it on, and adjust the adjustable base so that the outlet of the folding light tube is aligned with the prism on the arrow;

[0014] S2, enabling the first laser strapdown inertial group to perform autonomous orientation, and solving the azimuth angle of the first auto-collimation light tube according to its heading angle and the fixed connection relationship with the first auto-collimation light tube; enabling the second laser strapdown inertial group to perform autonomous orientation, and solving the azimuth angle of the second auto-collimation light tube according to its heading angle and the fixed connection relationship with the second auto-collimation light tube;

[0015] S3, measuring the angle β1 between the optical axis of the first self-collimating light tube and the normal line of the prism on the arrow; measuring the angle β2 between the optical axis of the second self-collimating light tube and the normal line of the prism on the arrow;

[0016] S4, make the first laser strapdown inertial group calculate the azimuth angle A1 of the prism on the arrow according to the azimuth angle and β1 of the first autocollimation light tube, and transmit A1 and the position and timing information obtained from the first satellite positioning device to the rocket launch control system; make the second laser strapdown inertial group calculate the azimuth angle A2 of the prism on the arrow according to the azimuth angle and β2 of the second autocollimation light tube, and transmit A2 and the position and timing information obtained from the second satellite positioning device to the rocket launch control system.

[0017] Furthermore, the present invention provides a rocket aiming method, wherein, in step S2, the azimuth angle of the first autocollimation light tube refers to the angle between the optical axis of the first autocollimation light tube and the north direction, and the azimuth angle of the second autocollimation light tube refers to the angle between the optical axis of the second autocollimation light tube and the north direction; in step S4, A1 and A2 refer to the angle between the prism normal on the arrow and the north direction.

[0018] Compared with the prior art, the dual redundant directional aiming system and method for launching a rocket at sea of ​​the present invention have the following advantages: the present invention arranges a first laser strapdown inertial group, a second laser strapdown inertial group and a folding light tube fixed on an adjustable base, and correspondingly fixes a first self-collimating light tube and a second self-collimating light tube on the first laser strapdown inertial group and the second laser strapdown inertial group, so that the folding light tube is provided with a first incident port, a second incident port and an outlet coaxially symmetrically distributed with the first incident port, and a semi-transparent semi-reflecting mirror matched with the first incident port and the outlet and a plane reflector matched with the second incident port are arranged in the folding light tube, wherein reflected light of the plane reflector is directed toward the semi-transparent semi-reflecting mirror, the first self-collimating light tube is aligned with the first incident port of the folding light tube, and the second self-collimating light tube is aligned with the second incident port of the folding light tube. Thus, a dual redundant directional aiming system for sea launch of rockets is formed, which has a compact structure, strong adaptability and high reliability. In practical application, the dual redundant directional aiming system is fixed at a position matching the rocket aiming window through an adjustable base and then powered on; the first laser strapdown inertial group is autonomously oriented and the azimuth of the first autocollimation light tube is solved, and the second laser strapdown inertial group is autonomously oriented and the azimuth of the second autocollimation light tube is solved; the angle β1 between the optical axis of the first autocollimation light tube and the normal line of the prism on the arrow is measured, and the angle β2 between the optical axis of the first autocollimation light tube and the normal line of the prism on the arrow is measured; the first laser strapdown inertial group is used to solve the azimuth angle A1 of the prism on the arrow according to the azimuth angle of the first autocollimation light tube and β1, and A1 is transmitted to the rocket launch control system, and the second laser strapdown inertial group is used to solve the azimuth angle A2 of the prism on the arrow according to the azimuth angle of the second autocollimation light tube and β2, and A2 is transmitted to the rocket launch control system. The rocket aiming purpose can be achieved through the above steps. Compared with the aiming system of the rocket launch method on land, the present invention sets two sets of optical aiming combinations consisting of laser strapdown inertial groups and self-collimating light tubes, and makes the outgoing light of the two sets of optical aiming combinations simultaneously shoot to the prism on the arrow through the folding light tube, so as to achieve the technical purpose of simultaneously acquiring two aiming data and transmitting them to the rocket launch control system, so that the rocket launch control system can compare the two aiming data for mutual verification to determine the aiming result, and when the aiming data of any optical aiming combination is abnormal, the aiming data of the other optical aiming combination can be used normally as the aiming result, thereby improving the reliability of rocket aiming and the safety of rocket launch, and meeting the requirements of rocket launch under dynamic sea conditions. The rocket aiming method provided by the present invention has the advantages of simple process, high degree of automation, safety and reliability.

[0019] The following is a detailed description of a dual redundant directional aiming system and method for sea-based rocket launching of the present invention in conjunction with the specific implementation modes shown in the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic structural diagram of a dual-redundant directional aiming system for launching a rocket at sea according to the present invention;

[0021] Figure 2 The present invention is a schematic diagram of the optical path of a dual-redundant directional aiming system for launching a rocket at sea. DETAILED DESCRIPTION

[0022] First of all, it should be explained that the directional words such as up, down, left, right, front and back described in the present invention are only described according to the drawings for the convenience of understanding, and are not intended to limit the technical solution and the scope of protection of the present invention.

[0023] like Figure 1 and Figure 2 The present invention is a specific embodiment of a dual redundant directional aiming system for launching a rocket at sea, comprising a first laser strapdown inertial group 2, a second laser strapdown inertial group 3 and a folding light tube 4 fixed on an adjustable base 1, a first self-collimating light tube 5 and a second self-collimating light tube 6 fixed on the first laser strapdown inertial group 2 and the second laser strapdown inertial group 3, so that the folding light tube 4 is provided with a first incident port 41, a second incident port 42 and an outlet port 43 coaxially symmetrically distributed with the first incident port 41, a semi-transparent semi-reflecting mirror 44 matched with the first incident port 41 and the outlet port 43 and a plane reflector 45 matched with the second incident port 42 are provided in the folding light tube 4, the reflected light of the plane reflector 45 is directed toward the semi-transparent semi-reflecting mirror 44, the first self-collimating light tube 5 is aligned with the first incident port 41 of the folding light tube 4, and the second self-collimating light tube 6 is aligned with the second incident port 42 of the folding light tube 4. Among them, the first laser strapdown inertial group 2 and the second laser strapdown inertial group 3 are used for autonomous north finding, the first autocollimation light tube 5 is used to measure the angle between its optical axis and the normal of the arrow-on prism 100, and the second autocollimation light tube 6 is used to measure the angle between its optical axis and the normal of the arrow-on prism 100.

[0024] The above structural setting constitutes a dual redundant directional aiming system for sea launch of rockets which has compact structure, strong adaptability and high reliability. In practical application, the dual redundant directional aiming system is fixed at a position matching the rocket aiming window through the adjustable base 1 and then powered on; the first laser strapdown inertial group 2 is autonomously oriented and solves the azimuth angle of the first self-collimation light tube 5, and the second laser strapdown inertial group 3 is autonomously oriented and solves the azimuth angle of the second self-collimation light tube 6; the angle β1 between the optical axis of the first self-collimation light tube 5 and the normal line of the arrow prism 100 is measured, and the angle β2 between the optical axis of the second self-collimation light tube 6 and the normal line of the arrow prism 100 is measured; the first laser strapdown inertial group 2 solves the azimuth angle A1 of the arrow prism 100 according to the azimuth angle of the first self-collimation light tube 5 and β1, and transmits A1 to the rocket launch control system, and the second laser strapdown inertial group 3 solves the azimuth angle A2 of the arrow prism 100 according to the azimuth angle of the second self-collimation light tube 6 and β2, and transmits A2 to the rocket launch control system. The rocket aiming purpose can be achieved through the above steps. Compared with the aiming system of the rocket launch method on land, the present invention sets two sets of optical aiming combinations consisting of laser strapdown inertial group and self-collimating light tube, and makes the outgoing light of the two sets of optical aiming combinations simultaneously shoot to the arrow prism 100 through the folding light tube 4, so as to achieve the technical purpose of simultaneously obtaining two aiming data and transmitting them to the rocket launch control system, so that the rocket launch control system can compare the two aiming data for mutual verification to determine the aiming result, and when the aiming data of any optical aiming combination is abnormal, the aiming data of the other optical aiming combination can be used as the aiming result normally, thereby improving the reliability of rocket aiming and the safety of rocket launch, and meeting the requirements of rocket launch under dynamic sea conditions. It should be noted that autonomous north search refers to the laser strapdown inertial group to perform inertial autonomous orientation and obtain its own three attitude angles. The laser strapdown inertial group and the self-collimating light tube are both commonly used equipment in this field, and their structure and working mode are well known to those skilled in the art, and will not be repeated here. The azimuth of the first self-collimating light tube 5 refers to the angle between the optical axis of the first self-collimating light tube 5 and the north direction, the azimuth of the second self-collimating light tube 6 refers to the angle between the optical axis of the second self-collimating light tube 6 and the north direction, and the azimuth of the arrow prism 100 refers to the angle between the normal of the arrow prism 100 and the north direction; the aiming data refers to the arrow prism azimuths A1 and A2 directly obtained by the two sets of optical aiming combinations, and the aiming result refers to the final arrow prism azimuth obtained after comparing A1 and A2. It should be pointed out that the technical purpose of the present invention is limited to providing two sets of aiming data to the rocket launch control system at the same time. As for how the rocket launch control system compares the two sets of aiming data and determines the aiming result, it does not belong to the content of the present invention.

[0025] As an optimization solution, because the launch platform at sea will sway with the waves, the azimuth and posture of the prism on the arrow will also change continuously. In this specific implementation, the first laser strapdown inertial group 2 is connected to a first satellite positioning device (not shown in the figure) for providing position and timing information, and the second laser strapdown inertial group 3 is connected to a second satellite positioning device (not shown in the figure) for providing position and timing information. In this way, the aiming data of the two sets of optical aiming combinations are bound to the position and timing information, and in actual application, the two sets of aiming data are transmitted to the rocket launch control system together with the corresponding position and timing information, ensuring the effectiveness and reliability of rocket aiming. As an optimization scheme, in order to facilitate the adjustment of the outgoing light of the deflecting light tube 4 and align it with the arrow prism, the adjustable base 1 adopts the following structure in this specific embodiment: it includes a stand 11, on which a first platform 12 is installed through a transverse oblong hole and a matching first bolt, first support members 111 are respectively fixed on both transverse sides of the stand 11, and first hand screws 112 that press the first platform 12 are screwed on the first support members 111 through threaded holes; at the same time, a second platform 13 is installed on the first platform 12 through a plurality of second bolts (not shown in the figure), so that the plurality of second bolts are correspondingly located in the arc holes 131 arranged along the circumference of the second platform 13, two second support members 121 are fixed on one longitudinal side of the first platform 12, and second hand screws 122 that press the second platform 13 are screwed on the second support members 121 through threaded holes. Among them, the first laser strapdown inertial group 2 and the second laser strapdown inertial group 3 are fixed on the second platform 13, and the deflecting light tube 4 is fixed on the second platform 13 through an adapter frame 46. The adjustable base 1 of this arrangement has the characteristics of simple structure and convenient adjustment. In practical application, when adjusting the lateral position, it is only necessary to loosen the first bolt and then rotate the two first hand screws 112 at the same time, so that the first table 12 can be moved laterally relative to the table 11. After the lateral position is appropriate, the first table 12 can be fixed on the table 11 by tightening the first bolt; when adjusting the incident angle, it is only necessary to loosen the second bolt and then rotate the second hand screw 122 at the same time, so that the second table 13 can be rotated relative to the first table 12. After the incident angle is appropriate, tighten the second bolt to fix the second table 13 on the first table 12. It should be pointed out that because the oblong hole and the first bolt are inside the table 11, their contents are not shown in the figure.

[0026] As a specific implementation, in order to adapt to the prism on the arrow and facilitate the arrangement of the aiming system, the present invention generally fixes the first self-collimating light pipe 5 on the first laser strapdown inertial unit 2 by a first bracket 51, and fixes the second self-collimating light pipe 6 on the second laser strapdown inertial unit 3 by a second bracket 61. In order to ensure that the outgoing light of the first self-collimating light pipe 5 and the second self-collimating light pipe 6 are parallel to each other, the present invention fixes the first laser strapdown inertial unit 2 and the second laser strapdown inertial unit 3 side by side on the second platen 13, and sets the first self-collimating light pipe 5 and the second self-collimating light pipe 6 in parallel. Among them, the first incident port 41 and the second incident port 42 of the folding light pipe 4 are set to match the first self-collimating light pipe 5 and the second self-collimating light pipe 6. In order to avoid mutual influence between the light of the first auto-collimating light tube 5 and the light of the second auto-collimating light tube 6, in this specific embodiment, the laser source wavelength of the first auto-collimating light tube 5 and the wavelength of the sensitive light of the photosensor are λ1, and the laser source wavelength of the second auto-collimating light tube 6 and the wavelength of the sensitive light of the photosensor are λ2, and λ1≠λ2, that is, the first auto-collimating light tube 5 and the second auto-collimating light tube 6 use laser sources of different wavelength bands to emit light, and make their respective photosensors (CCD) only sensitive to the light emitted by themselves, ensuring that the first auto-collimating light tube 5 and the second auto-collimating light tube 6 can perform reliable angle measurement work at the same time.

[0027] Based on the same concept, the present invention also provides a rocket aiming method, which specifically includes the following steps:

[0028] S1. Fix the dual redundant directional aiming system at a position matching the rocket aiming window through the adjustable base 1 and then power it on. Adjust the adjustable base 1 to align the outlet 43 of the folding light tube 4 with the prism 100 on the arrow.

[0029] S2, the first laser strapdown inertial group 2 is autonomously oriented, and the azimuth of the first auto-collimation light tube 5 is solved according to its heading angle and the fixed connection relationship with the first auto-collimation light tube 5; the second laser strapdown inertial group 3 is autonomously oriented, and the azimuth of the second auto-collimation light tube 6 is solved according to its heading angle and the fixed connection relationship with the second auto-collimation light tube 6.

[0030] S3, measuring the angle β1 between the optical axis of the first self-collimating light tube 5 and the normal line of the prism on the arrow; measuring the angle β2 between the optical axis of the second self-collimating light tube 6 and the normal line of the prism on the arrow.

[0031] S4, make the first laser strapdown inertial group 2 solve the azimuth angle A1 of the prism on the arrow according to the azimuth angle and β1 of the first self-collimation light tube 5, and transmit A1 and the position and timing information obtained from the first satellite positioning device to the rocket launch control system; make the second laser strapdown inertial group 3 solve the azimuth angle A2 of the prism on the arrow according to the azimuth angle and β2 of the second self-collimation light tube 6, and transmit A2 and the position and timing information obtained from the second satellite positioning device to the rocket launch control system.

[0032] In step S2, the azimuth angle of the first autocollimator light tube 5 refers to the angle between the optical axis of the first autocollimator light tube 5 and the north direction, and the azimuth angle of the second autocollimator light tube 6 refers to the angle between the optical axis of the second autocollimator light tube 6 and the north direction; in step S4, A1 and A2 refer to the angle between the prism normal on the arrow and the north direction.

[0033] The rocket aiming method provided by the present invention has the advantages of simple process, high degree of automation, safety and reliability. It should be noted that, since the first self-collimating light tube 5 and the second self-collimating light tube 6 are fixedly connected to the first laser strapdown inertial group 2 and the second laser strapdown inertial group 3, after the heading angles of the first laser strapdown inertial group 2 and the second laser strapdown inertial group 3 are determined, the azimuth angles of the first self-collimating light tube 5 and the second self-collimating light tube 6 can be calculated according to the relationship between the inertial group coordinate system and the light tube group coordinate system, and the calculation method is well known to those skilled in the art and will not be repeated here.

[0034] Practical application shows that the present invention can produce the following beneficial effects: 1. The optical aiming combination adopted by the dual redundant directional aiming system provided by the present invention realizes the autonomous orientation of inertial navigation and the dynamic aiming of the self-collimating light tube, and provides a high-precision reference orientation for the sea launch of the carrier rocket. The optical aiming combination can adapt to the dynamic conditions of various levels of sea conditions, and improves the adaptability of the sea launch platform; 2. The dual redundant directional aiming system simultaneously outputs two sets of aiming data, so that the rocket launch control system can compare the two sets of aiming data for mutual verification to determine the correctness of the aiming result, and when the aiming data of any optical aiming combination is abnormal, the aiming data of the other optical aiming combination can be used normally as the aiming result.

[0035] The above embodiments are only descriptions of the preferred implementation modes of the present invention, and are not intended to limit the protection scope of the present invention. Without departing from the design concept of the present invention, various modifications made by those skilled in the art based on the technical solution of the present invention should fall within the protection scope determined by the claims of the present invention.

Claims

1. A rocket aiming method, the aiming method utilizing a dual redundant directional aiming system, the dual redundant directional aiming system comprising a first laser strapdown inertial group (2), a second laser strapdown inertial group (3) and a deflection light tube (4) fixed on an adjustable base (1), a first self-collimating light tube (5) and a second self-collimating light tube (6) being fixed on the first laser strapdown inertial group (2) and the second laser strapdown inertial group (3) respectively, the deflection light tube (4) being provided with a first incident port (41), a second incident port (42) and an outlet port (43) coaxially symmetrically distributed with the first incident port (41), and a second incident port (42) being provided in the deflection light tube (4) and a second incident port (43) coaxially symmetrically distributed with the first incident port (41). ) and the output port (43) matched with a semi-transparent and semi-reflective mirror (44) and a plane reflector (45) matched with the second incident port (42), the reflected light of the plane reflector (45) is emitted toward the semi-transparent and semi-reflective mirror (44), the first self-collimating light pipe (5) is aligned with the first incident port (41) of the folding light pipe (4), the second self-collimating light pipe (6) is aligned with the second incident port (42) of the folding light pipe (4), the first laser strapdown inertial group (2) is connected to a first satellite positioning device for providing position and timing information, and the second laser strapdown inertial group (3) is connected to a second satellite positioning device for providing position and timing information; characterized in that: The aiming method includes the following steps: S1, fixing the dual redundant directional aiming system at a position matching the rocket aiming window through an adjustable base (1) and then powering it on, and adjusting the adjustable base (1) so that the outlet (43) of the folding light tube (4) is aligned with the prism on the arrow; S2, enabling the first laser strapdown inertial unit (2) to perform autonomous orientation, and calculating the azimuth angle of the first autocollimation light tube (5) according to its heading angle and the fixed connection relationship with the first autocollimation light tube (5); enabling the second laser strapdown inertial unit (3) to perform autonomous orientation, and calculating the azimuth angle of the second autocollimation light tube (6) according to its heading angle and the fixed connection relationship with the second autocollimation light tube (6); S3, measuring the angle β1 between the optical axis of the first self-collimating light tube (5) and the normal line of the prism on the arrow; measuring the angle β2 between the optical axis of the second self-collimating light tube (6) and the normal line of the prism on the arrow; S4, the first laser strapdown inertial group (2) calculates the azimuth angle A1 of the prism on the arrow according to the azimuth angle β1 of the first autocollimation light tube (5), and transmits A1 and the position and timing information obtained from the first satellite positioning device to the rocket launch control system; the second laser strapdown inertial group (3) calculates the azimuth angle A2 of the prism on the arrow according to the azimuth angle β2 of the second autocollimation light tube (6), and transmits A2 and the position and timing information obtained from the second satellite positioning device to the rocket launch control system.

2. The rocket aiming method according to claim 1, characterized in that: In step S2, the azimuth angle of the first autocollimator (5) refers to the angle between the optical axis of the first autocollimator (5) and the north direction, and the azimuth angle of the second autocollimator (6) refers to the angle between the optical axis of the second autocollimator (6) and the north direction; in step S4, A1 and A2 refer to the angles between the prism normal on the arrow and the north direction.

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