Distance measurement, weather and trajectory display target observation mirror

Abstract

The invention discloses a ranging, meteorological and ballistic display target scope, and relates to the technical field of target scopes, the target scope comprises an objective lens body, a meteorological sensing mechanism, a target scope light path assembly, a battery assembly, a laser light path assembly and a main control assembly, one end of the objective lens body is provided with a machine body, and the meteorological sensing mechanism is arranged at the top of the machine body; the target observation mirror light path assembly is installed in an inner cavity of the machine body in a Z-shaped path mode, the battery assembly is arranged on the outer wall of the machine body, the laser light path assembly and the target observation mirror light path assembly are coaxially arranged in a collimation mode, and the main control assembly is arranged at the end, close to the objective lens body, of the machine body. Through the arrangement mode that the objective lens body is matched with the target observation mirror light path assembly and the laser light path assembly, the laser light path and the target observation mirror light path are collimated and coaxially designed, so that laser can accurately measure the distance of a target within 2000 codes, multiple functions are truly achieved, the field shooting practical operation time is greatly shortened, and the shooting efficiency is improved. And long-distance shooting is more accurate and efficient.

Description

Technical Field

[0001] The invention relates to the technical field of target sighting scopes, and in particular to a target sighting scope that can display ranging, meteorology and ballistics. Background Art

[0002] In the field of outdoor shooting, optical target scopes are mainly used for target observation and aiming. Although the existing optical target scopes have certain magnification functions, they cannot provide accurate ranging, weather monitoring, ballistic calculation and other functions in real time.

[0003] When using traditional target scopes, shooters still need to rely on external equipment such as rangefinders and anemometers to obtain the necessary shooting parameters, then calculate through ballistic computers or mobile phone apps, and finally manually adjust the aiming point. This cumbersome operation process not only reduces shooting efficiency, but also increases the complexity of shooting, causing shooters to carry a large amount of equipment when operating on site, which not only increases the burden but also reduces operating efficiency. Especially when shooting at long distances, shooters need to frequently switch equipment to perform operations such as ranging, wind speed measurement, and trajectory calculations, which is not only time-consuming and labor-intensive, but also prone to errors, affecting shooting accuracy.

[0004] As a result, existing target viewing scopes have the problems of cumbersome operation, poor real-time performance, and limited accuracy. Existing shooting auxiliary equipment is independent of each other, and shooters need to carry multiple devices, which is inconvenient to carry and use. The equipment must be frequently switched during the shooting process, which is inefficient. In addition, the existing target viewing scopes have single functions and cannot provide ranging, meteorological data, and ballistic calculation results in real time, which increases the operation time and error probability. In addition, the coordination between multiple devices is poor. When shooters shoot at long distances, it is difficult to quickly obtain accurate shooting parameters and requires cooperation of multiple people, resulting in reduced shooting accuracy. Summary of the invention

[0005] The purpose of the present invention is to provide a ranging, meteorological and ballistic display target viewing scope to solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above object, the present invention provides the following technical solution: a rangefinder, meteorological and trajectory display target viewing scope, comprising:

[0007] An objective lens body, one end of which is provided with a body;

[0008] A weather sensing mechanism, wherein the weather sensing mechanism is arranged on the top of the fuselage;

[0009] A target-viewing scope optical path component, wherein the target-viewing scope optical path component is installed in the inner cavity of the fuselage in a Z-shaped path;

[0010] A battery assembly, wherein the battery assembly is arranged on the outer wall of the fuselage;

[0011] A laser optical path component, which is installed in the middle of the fuselage and is coaxially arranged with the target viewing mirror optical path component;

[0012] The main control component is arranged at one end of the fuselage close to the objective lens body.

[0013] Preferably, an operation panel for switch control is installed on the top of the fuselage, and a connecting base is fixedly connected to the bottom of the fuselage.

[0014] Preferably, the meteorological sensing mechanism includes a meteorological sensor module, the meteorological sensor module is installed on the top of the fuselage, and the meteorological sensor module is connected to the main control component.

[0015] Preferably, the target viewing scope optical path component includes:

[0016] A prism group, which is installed in the middle of the fuselage and is used to change the target light path;

[0017] A high-definition electronic graticule, which is installed in the inner cavity of one end of the fuselage away from the objective lens body;

[0018] An eyepiece lens assembly, wherein the eyepiece lens assembly is mounted on one end of the fuselage close to the high-definition electronic reticle;

[0019] An eyepiece body, wherein the eyepiece body is fixed to an end of the fuselage away from the objective lens body, and the eyepiece body and the objective lens body are respectively mounted at two ends of the fuselage;

[0020] The objective lens group is installed in the inner cavity of the objective lens body.

[0021] Preferably, the prism group includes:

[0022] A lower roof prism structure, wherein the lower roof prism structure is installed in the inner cavity of the fuselage and is located on the same horizontal extension line as the objective lens group;

[0023] An upper roof prism is installed on the top of the lower roof prism structure and is located on the same horizontal extension line as the high-definition electronic reticle.

[0024] Preferably, the lower roof prism structure comprises:

[0025] A first glued prism on the lower roof ridge, wherein the first glued prism on the lower roof ridge is fixed to the inner wall of the fuselage;

[0026] A second lower ridge glued prism, wherein the second lower ridge glued prism is glued and fixed to one side of the first lower ridge glued prism, and the second lower ridge glued prism is located between the upper ridge prism and the first lower ridge glued prism;

[0027] The third lower ridge glued prism, the two adjacent sides of the third lower ridge glued prism are respectively glued to the outer walls of the first lower ridge glued prism and the second lower ridge glued prism, one side of the glued surface of the second lower ridge glued prism, the first lower ridge glued prism and the third lower ridge glued prism is coated with a visible light total reflection film, and the one side of the glued surface of the first lower ridge glued prism and the third lower ridge glued prism is coated with a 905nm semi-transparent and semi-reflective film.

[0028] Preferably, the eyepiece lens assembly comprises:

[0029] The first cemented lens of the eyepiece is installed on a side close to the high-definition electronic reticle;

[0030] The second cemented lens of the eyepiece is mounted on the end of the first cemented lens of the eyepiece away from the high-definition electronic graticule;

[0031] The third lens of the eyepiece is installed on one side of the second cemented lens of the eyepiece.

[0032] Preferably, the objective lens group comprises:

[0033] The first lens of the objective lens is installed on the inner wall of the objective lens body;

[0034] The second lens of the objective lens is glued together with the outer wall of the first lens of the objective lens, and the opposite sides of the first lens of the objective lens and the second lens of the objective lens are both coated with a 905nm anti-reflection film.

[0035] Preferably, the battery assembly includes a battery compartment, which is mounted on the outer wall of the fuselage; the main control assembly includes a fine-tuning knob and a circuit board, the fine-tuning knob is mounted on the top of the outer wall of the fuselage, the fine-tuning knob is used for aiming point adjustment, the circuit board has a built-in ballistic calculation module, the circuit board is mounted on the bottom of the fuselage, and the circuit board is used for circuit system integration.

[0036] Preferably, the laser optical path component comprises:

[0037] A laser emission system, the laser emission system is installed on the fuselage on the same horizontal extension line of the objective lens group, the laser emission system comprises a laser emitter, a first laser emission lens and a second laser emission lens, the first laser emission lens is installed between the laser emitter and the second laser emission lens, and the laser emitter, the first laser emission lens and the second laser emission lens are all fixed on one side of the middle part of the fuselage;

[0038] A laser receiving system is installed on the fuselage directly below the lower roof prism structure. The laser receiving system includes a laser receiving filter and a laser receiver. The laser receiver is arranged at the bottom of the laser receiving filter. Both the laser receiving filter and the laser receiver are fixed to the bottom of the middle part of the fuselage.

[0039] Technical effects and advantages of the present invention:

[0040] (1) The present invention adopts a configuration method in which the objective lens body and the target-viewing mirror optical path component and the laser optical path component are matched with each other, so that the laser optical path component and the target-viewing mirror optical path component are collimated and coaxially arranged, and the laser optical path and the target-viewing mirror optical path are collimated and coaxially designed, and the laser ranging and aiming optical paths are organically formed into an integrated optical system. Through glass coating technology, the laser can accurately measure the distance of targets within 2000 yards. In combination with a meteorological sensing mechanism and a main control component, the present invention completely replaces the single devices required for accurate shooting composed of ordinary target-viewing mirrors, rangefinders, anemometers, ballistic computers or mobile phone APPs, etc., truly realizing one machine with multiple functions, greatly shortening the actual operation time of on-site shooting, and making long-distance shooting more accurate and efficient.

[0041] (2) The present invention adopts the coating design of the objective lens group and the prism group on the optical path assembly of the target viewing mirror, so that the emitted and received 905nm laser can accurately measure the distance to the target within 2000 yards. At the same time, it reduces the diffuse reflection between the lenses of the lens, improves the contrast and sharpness of the image, and makes the light penetration rate reach 95%, ensuring the clarity of long-distance observation of the target and improving the shooting accuracy.

[0042] (3) The present invention adopts a split design of the laser emitting system and the laser receiving system on the laser optical path component. Two lenses are designed in front of the laser emitter. The light first passes through a concave lens and then a convex lens. The divergence angle is compressed after secondary focusing, making the emitted laser beam more focused and the laser spot smaller, which is conducive to the return laser enhancement. At the same time, a filter is added in front of the laser receiver to filter out stray light and enhance the reception of 905nm laser.

[0043] (4) The present invention integrates the objective lens body, meteorological sensing mechanism, target-viewing scope optical path assembly, battery assembly, laser optical path assembly and main control assembly into an independent and highly compact integrated design through a compact and organic unified design of each component, and cleverly embeds them into the fuselage; a customized micro-meteorological sensor module is designed above the scope body to form an organic unity, which is convenient for real-time detection of meteorological data and improves the integrated multifunctional design of the target-viewing scope. When in use, there is no need to carry too much equipment, which reduces the cumbersomeness of use and improves the efficiency of the design. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1It is a schematic diagram of the overall front structure of the present invention.

[0045] Figure 2 It is a schematic diagram of the overall side structure of the present invention.

[0046] Figure 3 It is the optical path arrangement diagram of the optical path assembly of the target viewing scope of the present invention.

[0047] Figure 4 It is a schematic diagram of the front structure of the second glued prism on the lower ridge of the present invention.

[0048] Figure 5 It is a schematic diagram of the front structure of the objective lens group of the present invention.

[0049] Figure 6 It is a module diagram of the circuit system of the present invention.

[0050] Figure 7 It is a diagram of the overall working steps of the present invention.

[0051] In the figure: 1. objective lens body; 2. fuselage; 3. operation panel; 4. prism group; 41. lower ridge prism structure; 411. lower ridge first glued prism; 412. lower ridge second glued prism; 413. lower ridge third glued prism; 42. upper ridge prism; 5. meteorological sensor module; 6. high-definition electronic graticule; 7. eyepiece lens group; 71. eyepiece first glued lens; 72. eyepiece second glued lens; 73. eyepiece third lens; 8. eyepiece body; 9. battery compartment; 10. laser emission system; 101. laser emitter; 111. laser receiving filter; 112. laser receiver; 102. laser emission first lens; 103. laser emission second lens; 11. laser receiving system; 12. fine-tuning knob; 13. connecting base; 14. circuit board; 15. objective lens group; 151. objective first lens; 152. objective second lens. DETAILED DESCRIPTION

[0052] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only 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 ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0053] The present invention provides Figure 1-7A distance measuring, meteorological and ballistic display target viewing scope shown in the figure includes an objective lens body 1, a meteorological sensing mechanism, a target viewing scope optical path component, a battery component, a laser optical path component and a main control component. A fuselage 2 is installed at one end of the objective lens body 1, an operation panel 3 for switch control is installed on the top of the fuselage 2, a power on button is installed on the operation panel 3 for turning on the target viewing scope, a connecting base 13 is fixedly connected to the bottom of the fuselage 2, a meteorological sensing mechanism is arranged on the top of the fuselage 2, the meteorological sensing mechanism includes a meteorological sensor module 5, the meteorological sensor module 5 is installed on the top of the fuselage 2, and the meteorological sensor module 5 is connected to the main control component, the meteorological sensor module 5 is used for meteorological sensing of the shooting environment, the target viewing scope optical path component is installed in the inner cavity of the fuselage 2 in a Z-shaped path, the battery component is arranged on the outer wall of the fuselage 2, the laser optical path component is installed in the middle of the fuselage 2, the laser optical path component and the target viewing scope optical path component are collimated and coaxially arranged, and the main control component is arranged at one end of the fuselage 2 close to the objective lens body 1.

[0054] Among them, the target viewing scope optical path component includes a prism group 4, a high-definition electronic graticule 6, an eyepiece lens group 7, an eyepiece body 8 and an objective lens group 15. The prism group 4 is installed in the middle of the fuselage 2, and the prism group 4 is used to change the target optical path. The high-definition electronic graticule 6 is installed in the inner cavity of the end of the fuselage 2 away from the objective lens body 1. The high-definition electronic graticule 6 can display clearer and more detailed aiming marks (such as crosshairs, fine dots, etc.) to help the shooter aim at the target more accurately. The eyepiece lens group 7 is installed at one end of the fuselage 2 close to the high-definition electronic graticule 6, and the meteorological sensor module 5 is integrated with the high-definition electronic graticule 6. The high-definition electronic graticule 6 can display meteorological environmental data such as wind speed, temperature, and humidity in real time to help the shooter better evaluate the shooting conditions. The eyepiece body 8 is fixed to the end of the fuselage 2 away from the objective lens body 1, the eyepiece body 8 and the objective lens body 1 are respectively installed at the two ends of the fuselage 2, and the objective lens group 15 is installed in the inner cavity of the objective lens body 1.

[0055] Specifically, the prism group 4 includes a lower roof prism structure 41 and an upper roof prism 42. The lower roof prism structure 41 is installed in the inner cavity of the fuselage 2 and is located on the same horizontal extension line with the objective lens group 15. The upper roof prism 42 is installed on the top of the lower roof prism structure 41 and is located on the same horizontal extension line with the high-definition electronic graticule 6.

[0056] The lower ridge prism structure 41 includes a lower ridge first glued prism 411, a lower ridge second glued prism 412 and a lower ridge third glued prism 413. The lower ridge first glued prism 411 is fixed to the inner wall of the fuselage 2, the lower ridge second glued prism 412 is glued and fixed to one side of the lower ridge first glued prism 411, and the lower ridge second glued prism 412 is located between the upper ridge prism 42 and the lower ridge first glued prism 411. The adjacent sides of the lower ridge third glued prism 413 are respectively glued to the outer walls of the lower ridge first glued prism 411 and the lower ridge second glued prism 412. The lower ridge second glued prism 412 is glued to the lower ridge One side of the bonding surface where the first bonded prism 411 and the lower ridge third bonded prism 413 are bonded is coated with a visible light total reflection film, and one side of the bonding surface where the lower ridge first bonded prism 411 and the lower ridge third bonded prism 413 are bonded is coated with a 905nm semi-transparent and semi-reflective film. Through the lower ridge prism structure 41 and the upper ridge prism 42, the glasses can aim at the object in the direction of the objective lens body 1 from the direction of the eyepiece body 8, and through the 905nm semi-transparent and semi-reflective film coated between the lower ridge first bonded prism 411 and the lower ridge third bonded prism 413, the laser emitted by the laser emitting system 10 can be received by the laser receiving system 11.

[0057] In addition, the eyepiece lens group 7 includes an eyepiece first cemented lens 71, an eyepiece second cemented lens 72 and an eyepiece third lens 73. The eyepiece first cemented lens 71 is installed on a side close to the high-definition electronic graticule plate 6, the eyepiece second cemented lens 72 is installed on an end of the eyepiece first cemented lens 71 away from the high-definition electronic graticule plate 6, and the eyepiece third lens 73 is installed on one side of the eyepiece second cemented lens 72.

[0058] The objective lens group 15 includes a first objective lens 151 and a second objective lens 152. The first objective lens 151 is installed on the inner wall of the objective lens body 1, and the second objective lens 152 is glued to the outer wall of the first objective lens 151. The opposite sides of the first objective lens 151 and the second objective lens 152 are coated with a 905nm anti-reflection film to facilitate the laser line to stably pass through the first objective lens 151 and the second objective lens 152.

[0059] The battery assembly includes a battery compartment 9, which is installed on the outer wall of the fuselage 2. The main control assembly includes a fine-tuning knob 12 and a circuit board 14. The fine-tuning knob 12 is installed on the top of the outer wall of the fuselage 2. The fine-tuning knob 12 is used to adjust the aiming point. The circuit board 14 has a built-in trajectory calculation module. The trajectory calculation module can display the trajectory correction value, and the trajectory correction value can be displayed through the high-definition electronic reticle 6. The circuit board 14 is installed at the bottom of the fuselage 2. The circuit board 14 is used for the integration of the circuit system. The circuit board 14 is embedded with an angle sensor, a ranging module, a storage module, and a wireless module, and the circuit board 14 is embedded with a related control program. The circuit system includes a central processing unit, a storage module, a wireless module, a data interface, a control panel, a power module, a display module, a meteorological module, an angle sensor and a ranging module. The distance module, wherein the control panel and the display module are composed of an operation panel 3, and by turning on the relevant function keys on the operation panel 3, single or continuous distance measurement and real-time meteorological monitoring can be realized respectively, and functions such as unit switching can also be performed. The power module is composed of a battery compartment 9, and the meteorological module is composed of a meteorological sensor module 5. The operation panel 3, the meteorological sensor module 5, the high-definition electronic graticule 6, the battery compartment 9, the laser emitting system 10, and the laser receiving system 11 are respectively connected to the circuit board 14, and the circuit system is debugged after power is turned on. The circuit board 14 is designed to be miniature and highly compact, and the circuit board 14 is integrated with a communication module. At the same time, a data interface is reserved on the circuit board 14 for the convenience of users to insert ballistic programs, and the wireless module is designed with an open protocol for fast connection to other wireless devices on site.

[0060] Furthermore, the laser optical path component includes a laser emitting system 10 and a laser receiving system 11. The laser emitting system 10 is installed on the fuselage 2 on the same horizontal extension line of the objective lens group 15. The laser emitting system 10 includes a laser emitter 101, a laser emitting first lens 102 and a laser emitting second lens 103. The laser emitting first lens 102 is installed between the laser emitter 101 and the laser emitting second lens 103. The laser emitter 101, the laser emitting first lens 102 and the laser emitting second lens 103 are all fixed on one side of the middle part of the fuselage 2; the laser receiving system 11 is installed on the fuselage 2 directly below the lower roof prism structure 41. The laser receiving system 11 includes a laser receiving filter 111 and a laser receiver 112. The laser receiver 112 is arranged at the bottom of the laser receiving filter 111. The laser receiving filter 111 and the laser receiver 112 are both fixed at the bottom of the middle part of the fuselage 2 to facilitate stable emission and reception of laser energy.

[0061] Working principle of the present invention:

[0062] Due to the collimated coaxial design of the laser optical path component and the target telescope optical path component, when the target telescope is aimed at the target, the laser emitting system 10 emits a laser along the emitting optical path, which is reflected by the target and then emitted into the laser receiving system 11 along the return optical path. The distance to the target can be calculated based on the laser light speed and the time difference. At the same time, the integrated circuit collects meteorological data of the meteorological environment sensed by the meteorological sensor module 5, and processes the obtained distance and meteorological values ​​through the central processing unit and the ballistic calculation module on the circuit board 14, and finally displays the distance measurement, meteorological and ballistic values ​​on the high-definition electronic graticule 6.

[0063] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A rangefinder, meteorological and ballistic display target viewing scope, characterized in that: include: An objective lens body (1), wherein a body (2) is mounted on one end of the objective lens body (1); A meteorological sensing mechanism, wherein the meteorological sensing mechanism is arranged on the top of the fuselage (2); A target-viewing scope optical path component, wherein the target-viewing scope optical path component is installed in the inner cavity of the fuselage (2) in a Z-shaped path; A battery assembly, wherein the battery assembly is arranged on the outer wall of the body (2); A laser optical path component, the laser optical path component is installed in the middle of the fuselage (2), and the laser optical path component and the target viewing mirror optical path component are collimated and coaxially arranged; A main control component is arranged at one end of the machine body (2) close to the objective lens body (1).

2. A rangefinder, meteorological and ballistic display target viewing scope according to claim 1, characterized in that: An operating panel (3) for switch control is installed on the top of the body (2), and a connecting base (13) is fixedly connected to the bottom of the body (2).

3. A rangefinder, meteorological and ballistic display target viewing scope according to claim 1, characterized in that: The meteorological sensing mechanism comprises a meteorological sensor module (5), the meteorological sensor module (5) is installed on the top of the fuselage (2), and the meteorological sensor module (5) is connected to the main control component.

4. A rangefinder, meteorological and ballistic display target viewing scope according to claim 1, characterized in that: The target viewing mirror optical path component comprises: A prism group (4), the prism group (4) is installed in the middle of the fuselage (2), and the prism group (4) is used to change the target light path; A high-definition electronic graticule (6), wherein the high-definition electronic graticule (6) is installed in an inner cavity at one end of the body (2) away from the objective lens body (1); An eyepiece lens group (7), wherein the eyepiece lens group (7) is mounted on one end of the body (2) close to the high-definition electronic reticle (6); An eyepiece body (8), wherein the eyepiece body (8) is fixed to an end of the body (2) away from the objective lens body (1), and the eyepiece body (8) and the objective lens body (1) are respectively mounted at two ends of the body (2); An objective lens group (15), wherein the objective lens group (15) is installed in the inner cavity of the objective lens body (1).

5. A rangefinder, meteorological and ballistic display target viewing scope according to claim 4, characterized in that: The prism group (4) comprises: A lower roof prism structure (41), wherein the lower roof prism structure (41) is installed in the inner cavity of the body (2) and is located on the same horizontal extension line as the objective lens group (15); An upper roof prism (42), wherein the upper roof prism (42) is mounted on the top of the lower roof prism structure (41) and is located on the same horizontal extension line as the high-definition electronic reticle (6).

6. A rangefinder, meteorological and ballistic display target viewing scope according to claim 5, characterized in that: The lower roof prism structure (41) comprises: A first lower ridge glued prism (411), wherein the first lower ridge glued prism (411) is fixed to the inner wall of the fuselage (2); A lower ridge second glued prism (412), wherein the lower ridge second glued prism (412) is glued and fixed to one surface of the lower ridge first glued prism (411), and the lower ridge second glued prism (412) is located between the upper ridge prism (42) and the lower ridge first glued prism (411); A third lower ridge glued prism (413), wherein two adjacent sides of the third lower ridge glued prism (413) are respectively glued to the outer walls of the first lower ridge glued prism (411) and the second lower ridge glued prism (412) to form an integral whole; one side of the glued surface where the second lower ridge glued prism (412) is glued to the first lower ridge glued prism (411) and the third lower ridge glued prism (413) is coated with a visible light total reflection film; and one side of the glued surface where the first lower ridge glued prism (411) is glued to the third lower ridge glued prism (413) is coated with a 905nm semi-transparent semi-reflective film.

7. A rangefinder, meteorological and ballistic display target viewing scope according to claim 4, characterized in that: The eyepiece lens assembly (7) comprises: An eyepiece first cemented lens (71), wherein the eyepiece first cemented lens (71) is mounted on a side close to the high-definition electronic graticule (6); An eyepiece second cemented lens (72), wherein the eyepiece second cemented lens (72) is mounted on an end of the eyepiece first cemented lens (71) away from the high-definition electronic graticule (6); The eyepiece third lens (73) is mounted on one side of the eyepiece second cemented lens (72).

8. The target viewing scope with ranging, weather and trajectory display according to claim 4, characterized in that: The objective lens group (15) comprises: An objective lens first lens (151), wherein the objective lens first lens (151) is mounted on the inner wall of the objective lens body (1); The objective lens second lens (152) is glued together with the outer wall of the objective lens first lens (151) to form an integral whole, and the opposite sides of the objective lens first lens (151) and the objective lens second lens (152) are both coated with a 905nm anti-reflection film.

9. The target viewing scope with ranging, weather and trajectory display according to claim 1, characterized in that: The battery assembly comprises a battery compartment (9), the battery compartment (9) being mounted on the outer wall of the fuselage (2), the main control assembly comprising a fine-tuning knob (12) and a circuit board (14), the fine-tuning knob (12) being mounted on the top of the outer wall of the fuselage (2), the fine-tuning knob (12) being used for aiming point adjustment, the circuit board (14) having a built-in trajectory calculation module, the circuit board (14) being mounted on the bottom of the fuselage (2), and the circuit board (14) being used for circuit system integration.

10. The target viewing scope with ranging, weather and trajectory display according to claim 5, characterized in that: The laser optical path component comprises: A laser emitting system (10), the laser emitting system (10) being mounted on a fuselage (2) on the same horizontal extension line as an objective lens group (15), the laser emitting system (10) comprising a laser emitter (101), a first laser emitting lens (102) and a second laser emitting lens (103), the first laser emitting lens (102) being mounted between the laser emitter (101) and the second laser emitting lens (103), and the laser emitter (101), the first laser emitting lens (102) and the second laser emitting lens (103) being all fixed to one side of the middle of the fuselage (2); A laser receiving system (11), the laser receiving system (11) being installed on a fuselage (2) directly below a lower roof prism structure (41), the laser receiving system (11) comprising a laser receiving filter (111) and a laser receiver (112), the laser receiver (112) being arranged at the bottom of the laser receiving filter (111), and the laser receiving filter (111) and the laser receiver (112) being both fixed to the bottom of the middle portion of the fuselage (2).

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