Beacon equipment for surveying and mapping airdrop trajectory in complex space environment

Abstract

The utility model belongs to the technical field of data link transmission and satellite space positioning, and particularly relates to beacon equipment for surveying and mapping an air-drop track in a complex space environment, which comprises a data link transceiving antenna and a carbon fiber tube, and a data link transceiving module is fixedly mounted in the carbon fiber tube. A satellite positioning and inertial navigation assembly is fixedly installed on the side face of the data chain receiving and transmitting module, a satellite receiving antenna is arranged at one end of the data chain receiving and transmitting module, a battery assembly is fixedly installed in the carbon fiber tube, and a plug cover is fixedly installed at one end of the battery assembly. The data link transmit-receive antenna can receive signals sent by a ground work station and transmit the signals to the data link transmit-receive module, the satellite positioning and inertial navigation assembly is matched to calculate high-precision space coordinate data which can be given, and then the high-precision space coordinate data are sent to the ground work station through the data link transmit-receive antenna. The method can improve the positioning precision, thereby improving the positioning effect of the device for coping with complex conditions.

Description

TECHNICAL FIELD

[0001] The utility model belongs to data link transmission and satellite space orientation technical field, concretely relates to a beacon equipment for surveying and mapping air drop trajectory under complex space environment. BACKGROUND

[0002] High altitude air drop is mostly used in complex scenes such as emergency rescue, position combat, faces complex environment such as strong wind, heavy rain, fog, black night without light, air drop target object shape, size and weight are changeable, and it is extremely easy to influence the landing position of air drop target object.

[0003] High altitude air drop is mostly used in complex scenes such as emergency rescue, position combat, faces complex environment such as strong wind, heavy rain, fog, black night without light, air drop target object shape, size and weight are changeable, and it is extremely easy to influence the landing position of air drop target object, the space coordinate processing module in the internal of the existing high altitude air drop device is relatively stable and simple, and positioning inaccuracy can occur under extreme environment. UTILITY MODEL CONTENT

[0004] To solve the problems in the above background art, the utility model provides a beacon equipment for surveying and mapping air drop trajectory under complex space environment, which solves the problem that the space coordinate processing module in the internal of the existing high altitude air drop device is relatively stable and simple, and positioning inaccuracy can occur under extreme environment.

[0005] To achieve the above object, the utility model provides the following technical scheme: a beacon equipment for surveying and mapping air drop trajectory under complex space environment, including data link transceiving antenna and carbon fiber pipe, the inside fixed mounting of carbon fiber pipe has data link transceiving module, the side fixed mounting of satellite positioning and inertial navigation assembly has data link transceiving module, the one end of data link transceiving module is provided with satellite receiving antenna, the inside fixed mounting of carbon fiber pipe has battery assembly, the one end fixed mounting of battery assembly has plug cover, the inside fixed mounting of plug cover has transceiving module data interface, the inside fixed mounting of plug cover has satellite assembly data interface, the inside fixed mounting of plug cover has charging power supply interface, the side fixed mounting of plug cover has big flat washer, the inside of plug cover is provided with bolt, the inside of big flat washer is penetrated by bolt, and the outer side of bolt is connected with the inner wall of plug cover in screw thread.

[0006] Preferably, the inside of one end of the data link transceiving antenna is provided with a power switch, and the outer side of the power switch is movably connected with the inner wall of one end of the data link transceiving antenna.

[0007] Preferably, the bottom of the satellite receiving antenna has magnetic force and can be attached to a ferrous object.

[0008] Preferably, the inside of the carbon fiber tube is filled with heat-conducting foaming glue, and the heat-conducting foaming glue wraps outside the data link transceiver module, the satellite positioning and inertial navigation assembly and the battery assembly.

[0009] Preferably, the inside of the bolt is provided with an aircraft buckle, and the inside of the aircraft buckle is threadedly connected with the threaded bosses arranged on both sides of the bolt.

[0010] Compared with the prior art, the utility model has the beneficial effects that:

[0011] The air-drop trajectory of the target object can be positioned and surveyed, and an accurate air-drop trajectory can be surveyed according to various environments, so that the target position can be accurately air-dropped in a live scene, the beacon device sends the received satellite signal to the ground station, so that multiple beacon devices can be simultaneously used. BRIEF DESCRIPTION OF DRAWINGS

[0012] The accompanying drawings are included to provide a further understanding of the utility model, and constitute a part of the specification, and are used to explain the utility model together with embodiments of the utility model, and do not constitute a limitation to the utility model. In the drawings:

[0013] Figure 1 It is the first kind of three-dimensional structure diagram of the utility model;

[0014] Figure 2 It is the second kind of three-dimensional structure diagram of the utility model;

[0015] Figure 3 It is the wiring diagram of the utility model;

[0016] Figure 4 It is the working principle diagram of the utility model;

[0017] Figure 5 It is the aircraft cutout of the utility model;

[0018] Figure 6 It is the installation diagram of the utility model.

[0019] In the drawing: 1, data link transceiver antenna; 2, satellite receiving antenna; 3, data link transceiver module; 4, satellite positioning and inertial navigation assembly; 5, battery assembly; 6, power switch; 7, transceiver module data interface; 8, satellite assembly data interface; 9, charging power supply interface; 10, plug cover; 11, carbon fiber tube; 12, large flat washer; 13, bolt; 14, aircraft buckle; 15, heat-conducting foaming glue. DETAILED DESCRIPTION

[0020] Clearly and completely describe the technical scheme in the embodiments of the utility model with reference to the drawings in the embodiments of the utility model, apparently, the described embodiment is only a part of the embodiment of the utility model, but not all the embodiment, based on the embodiment in the utility model, all other embodiments obtained by the ordinary skill in the art without making creative labor belong to the range of protection of the utility model.

[0021] Please refer to Figures 1-6 The utility model provides the following technical scheme: a beacon equipment for surveying and mapping air drop trajectory under complex space environment, including data link transceiving antenna 1 and carbon fiber tube 11, the inside fixed mounting of carbon fiber tube 11 has data link transceiving module 3, the side fixed mounting of data link transceiving module 3 has satellite positioning and inertial navigation assembly 4, and one end of data link transceiving module 3 is provided with satellite receiving antenna 2, the inside fixed mounting of carbon fiber tube 11 has battery assembly 5, one end fixed mounting of battery assembly 5 has plug cover 10, the inside fixed mounting of plug cover 10 has transceiving module data interface 7, the inside fixed mounting of plug cover 10 has satellite assembly data interface 8, the inside fixed mounting of plug cover 10 has charging power supply interface 9, the side fixed mounting of plug cover 10 has big flat washer 12, the inside of plug cover 10 is provided with bolt 13, bolt 13 penetrates big flat washer 12 inside, and the outside of bolt 13 is connected with the inner wall of plug cover 10 by screw thread.

[0022] In the embodiment: data link transceiving antenna 1 receives the differential signal sent by ground workstation, is transmitted to data link transceiving module 3, cooperates satellite positioning and inertial navigation assembly 4 to calculate the high-precision spatial coordinate data that can be given, and is transmitted to the inside of data link transceiving module 3, and the spatial coordinate data is sent to ground workstation through data link transceiving antenna 1, which can improve the positioning accuracy, thereby improving the positioning effect of the device in complex situations.

[0023] In the embodiment: satellite receiving antenna 2 covers GPS L1 and Beidou second generation B1. The antenna structure of double feed point design is adopted. The low-noise amplifier part adopts two-stage filtering scheme, effectively suppresses the out-of-band interference, improves the reliability of the system, and satellite positioning and inertial navigation assembly 4 provides high-quality and high-reliability position and speed information for the carrier. It can simultaneously track BDS2 B1 frequency point and GPS L1 frequency point satellite signals. It has two positioning modes of BDS civilian code positioning and BDS / GPS civilian code combined positioning.

[0024] In the embodiment: data link transceiving module 3 adopts FDD frequency division duplex and FDMA frequency division multiple access dual-mode working mode, has high-speed data transmission, small feedback delay, has multi-channel communication capability, data link transceiving antenna 1 adopts omnidirectional and directional combined antenna, realizes better signal coverage and data transmission in different directions and angles, and is suitable for data transmission in high-altitude complex environment.

[0025] The working principle and use process of the utility model: after the utility model is installed, firstly confirm that the two side wing buckles of the aircraft buckle are in the unfolded state, then insert the beacon equipment into the middle of the air-drop object, the two side wing buckles of the aircraft buckle are clamped on the air-drop object by the spring tension and do not move, rotate the beacon equipment clockwise, pull the bolt to move to the inside of the plug cover, shorten the distance between the large flat washer and the aircraft buckle, the large flat washer extrudes the aircraft buckle, the two side wing buckles of the aircraft buckle are tightly buckled on the air-drop object, at this time, the beacon equipment is firmly locked on the air-drop object, the satellite receiving antenna 2 can be magnetically attracted to the surface of the air-drop object, at this time, press the power switch 6, so that the beacon equipment is in the working state, when the beacon works, the satellite signal is received through the satellite receiving antenna 2 inside, and the signal is transmitted to the satellite positioning and inertial navigation assembly 3, the differential signal sent by the ground working station is received by the data link transceiver antenna 1, and is transmitted to the data link transceiver module 3, after the processed data is transmitted to the satellite positioning and inertial navigation assembly 4, the satellite signal data is processed by the satellite positioning and inertial navigation assembly 4, the differential signal and navigation coordinate data are given by the inertial ground working station, the spatial coordinate data with higher precision is given, and the spatial coordinate data is transmitted to the data link transceiver module 3, the data of the satellite positioning and inertial navigation assembly 4 is received by the data link transceiver module 3, after the data is processed, it is transmitted to the data link transceiver antenna 1, and the spatial coordinate data is sent to the ground working station through the data link transceiver antenna 1, the beacon equipment is powered by the battery assembly 5, the battery assembly 5 is a chargeable and dischargeable battery, and charging is performed through the charging power interface 9, the transceiver module data interface 7 and the satellite assembly data interface 8 arranged in the beacon device can be used for ground data transmission and debugging, so that the use requirement is met, the beacon device can be used simultaneously, the beacon device and the ground working station are connected in series, a data link system is formed, and the working efficiency is improved, and all the electrical equipment in the device is powered by an external power supply.

[0026] Finally, it should be pointed out that: the above only for preferred embodiments of the utility model, and does not limit the utility model, although the utility model is described in detail with reference to the foregoing embodiments, for those skilled in the art, still can modify the technical scheme recorded in the foregoing each embodiment, or make equivalent replacement to part of technical features. Any modification, equivalent replacement, improvement etc. made within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. A beacon device for mapping airdrop trajectories in complex space environments, comprising a data link transceiver antenna (1) and a carbon fiber tube (11), characterized in that: A data link transceiver module (3) is fixedly installed inside the carbon fiber tube (11). A satellite positioning and inertial navigation component (4) is fixedly installed on the side of the data link transceiver module (3). A satellite receiving antenna (2) is provided at one end of the data link transceiver module (3). A battery component (5) is fixedly installed inside the carbon fiber tube (11). A plug (10) is fixedly installed at one end of the battery component (5). A transceiver module data interface (7) is fixedly installed inside the plug (10). A satellite component data interface (8) is fixedly installed inside the plug (10). A charging power interface (9) is fixedly installed inside the plug (10). A large flat washer (12) is fixedly installed on the side of the plug (10). A bolt (13) is provided inside the plug (10). The bolt (13) passes through the large flat washer (12), and the outer side of the bolt (13) is threadedly connected to the inner wall of the plug (10).

2. The beacon device for mapping airdrop trajectories in complex space environments according to claim 1, characterized in that: A power switch (6) is provided inside one end of the data link transceiver antenna (1), and the outside of the power switch (6) is movably connected to the inner wall of one end of the data link transceiver antenna (1).

3. The beacon device for mapping airdrop trajectories in complex space environments according to claim 1, characterized in that: The bottom of the satellite receiving antenna (2) has a magnetic force and can be attached to an iron object.

4. A beacon device for mapping airdrop trajectories in complex space environments according to claim 1, characterized in that: The interior of the carbon fiber tube (11) is filled with thermally conductive foam (15), and the thermally conductive foam (15) wraps around the outside of the data link transceiver module (3), the satellite positioning and inertial navigation component (4) and the battery component (5).

5. A beacon device for mapping airdrop trajectories in complex space environments according to claim 1, characterized in that: The bolt (13) is provided with an aircraft buckle (14) inside, and the inside of the aircraft buckle (14) is threadedly connected to the threaded protrusions provided on both sides of the bolt (13).

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