CN109510655B - Task-oriented formation networking distributed cooperative flight control method for near space platform - Google Patents

Abstract

The utility model provides a close to space platform and face distributed collaborative flight control method of task formation networking, including: determining constraint conditions for optimizing the targets of the multi-coding adjacent space platform; receiving input and output data fed back by a near space platform; and controlling function switching and load distribution of the adjacent space platform based on the constraint conditions and the data. The distributed collaborative flight control method for task formation networking of the near space platform utilizes multi-platform collaborative control to complete networking, can give full play to the advantage of low cost, achieves the task targets of large-range regional network coverage and information transmission, optimizes and decomposes the multi-platform targets based on constraint condition analysis, and realizes function switching and effective control of load distribution of the near space platform.

Description

Task-oriented formation networking distributed cooperative flight control method for near space platform

Technical Field

The disclosure relates to the technical field of spatial information networks, in particular to a distributed cooperative flight control method for a near space platform facing task formation networking.

Background

The spatial information network is a network system which takes a spatial platform (such as a synchronous satellite, a medium or low orbit satellite/constellation, an adjacent space aerostat or an unmanned aerial vehicle) as a carrier and acquires, transmits and processes spatial information in real time. As a national important infrastructure, the spatial information network can support the high dynamic and broadband real-time transmission of earth observation and the ultra-long-distance and large-delay reliable transmission of deep space exploration while serving the important applications of ocean navigation, emergency rescue, navigation positioning, aviation transportation, aerospace measurement and control and the like, thereby expanding the human science, culture and production activities to the space, ocean and even deep space and being a research hotspot in the global range.

The near space platform generally refers to an aerostat or an airplane running in the near space and is 17-22 km away from the ground. Such platforms have the ability to extend communication distances quickly and can serve a large number of users with less communication facilities than terrestrial networks. Therefore, the near space platform is close to the ground network, and meanwhile, the wide area coverage can be kept, which means that the near space platform has the advantages of both the ground network and the satellite communication. However, a reliable platform capable of being resident for a long time does not exist, and the application research of a near space platform in a space information network is not as active as that of a satellite platform.

1 near space aerostat platform development

The research of approaching space platform technology runs through all processes from platform design, manufacturing, flying, flight control, recovery to system support and maintenance, is typical interdisciplinary, high and new technology that comprehensive is strong, relates to a plurality of fields such as material, structure, energy, thermal control, propulsion, control, space environment, and two clear technical routes are near space aerostat and near space solar energy long-endurance unmanned aerial vehicle respectively at present. The later has the advantages that the height of the West wind 7 of the air passenger reaches 20 kilometers at present, the maximum cruising duration is 14 days, the later has certain application capability, but the effective load is less than 5kg, and the later has larger limitation. Other models have not achieved long term residence.

1.1 stratospheric airship development

The american air force climber (Ascender) airship, 11 months 2003, did not carry any payload to 30km high and returned successfully under ground control as the first airship to enter the adjacent space and complete recovery. In 11 months of 2005, the flying height of a high altitude sentinel (Hisentinel) airship at the ministry of space and flight of the army in the united states reaches 22.6km, the airship is parked in the sky for 5 hours, the powered flight is less than 1 hour, and the load is 9.1kg, so that the airship which really realizes powered flight and has the highest flying height is formed. In 11 months 2010, the improved high-altitude sentinel airship has the load of 36.3kg, the load power of 50W, the flying height of 20.21km and the flying time of 8 hours, as shown in figure 1.

By the end of 2005, the U.S. MDA announced the official launch of the HAA project. The HAA final demonstration verifies that technical indexes of the airship HALE-D (High availability Long energy-Demonstrator) are as follows: the flying height is 18.3km, the parking time is more than 15 days, and the effective load is remote sensing and ground communication equipment. HALE-D was tested in 7 months of 2011, but crashed on the day of levitation due to technical abnormality, as shown in FIG. 2.

In China, a photoelectric hospital of a Chinese academy of sciences follows a progressive development mode of 'high-altitude balloon → non-forming levitation power airship → forming levitation power airship', and systematic research work is carried out on the aspects of full flight profile measurement and control communication, flight control, avionics, track prediction and task planning of an airship in an adjacent space. Three airships of KFG30A, KFG30B and KFG44 were developed and flown in 2011, and the maximum flying height was 16.6 km. In 2012, in 8 months, the flight test of the stratospheric airship is successfully completed for the first time, the controlled stratospheric airship is the controlled stratospheric airship with the largest volume and the largest propelling power at present at home and abroad, the automatic piloting flight, the remote control flight and the forming descent test of the stratospheric height are realized internationally for the first time, and the flight test result shows that the technology of the stratospheric airship in China has reached the international first-class level, as shown in fig. 3.

Although certain progress is made on stratospheric airships domestically and abroad, the capability of long-term standing in the air for application is not achieved.

1.2 high altitude science balloon development

The research of foreign high-altitude scientific balloons starts earlier, and after decades of development, the main technology of the zero-pressure high-altitude balloon is mature, and the applied high-altitude balloon has the volume from tens of thousands of cubic meters to 100 thousands of cubic meters, the load from several kilograms to 3 tons and the flying height from 30km to 40km in the world. The overpressure balloon is the focus of the current high-altitude balloon technology development, the volume of the overpressure balloon reaches 50 ten thousand cubic meters, the flight altitude reaches 36km, the overpressure balloon in the United states creates a record of 54 days of continuous flight with 1 ton load in the south pole, and the flight record of NASA is 46 days in the mid-latitude region of the southern hemisphere, as shown in FIG. 4.

Google 2013 published the lon program, which aims to provide internet access services for remote areas through a network of overpressure balloons. The project currently uses 1250 cubic superpressure balloons that have reached 190 days maximum endurance. The overpressure balloon adopts the unique design of a 'binary overpressure ball' with an auxiliary air bag, and the net buoyancy of the balloon is adjusted by adjusting the inflation and deflation of the auxiliary air bag so as to change the height of the balloon and search different stratospheric wind directions to realize the control of the position of the balloon. Although the control precision of a single sphere is limited by meteorological conditions and cannot be very high, since the whole system is very low in cost, uninterrupted coverage of a certain area can be realized through the cooperative control of a plurality of balloons, and the scheme is the most feasible scheme at present, as shown in fig. 5.

The national high-altitude scientific balloon is originally started in 1977, in order to establish a space carrying means for the physical experiment research of high-energy celestial bodies, a unique high-altitude scientific balloon system in China is built in 1984 under the strong support of a famous scientist, Hui-Cii-academy and the specific leader of a Sai-Dong academy, and the high-altitude balloon can fly for a long time from the north of China to the southwest of Russia in 1990, wherein the continuous flying time is 72 hours, and the flying distance is more than four thousand kilometers. From 1991 to the present, the high-altitude balloon is released by a high-energy place of the Chinese academy and a photoelectric hospital combined team for 53 times, the accumulated flight time exceeds 200 hours, the success rate exceeds 90 percent (after 2000 years, the success rate is 100 percent), the records of the maximum balloon volume of 60 ten thousand cubic meters, the maximum design load capacity of 1.9 tons, the maximum flight altitude of 42km and the maximum sustained flight time of 3 days are created, the highest level of the current development of the high-altitude scientific balloon technology in China is represented, and the high-altitude long-voyage overpressure balloon technology is developed vigorously at present along with the development of the high-altitude scientific balloon, as shown in fig. 6-7.

At present, the high-altitude scientific balloon is the only aerostat which can reliably enter an adjacent space and can be resided for a long time, particularly the binary overpressure balloon, can achieve regional long-time residence through altitude adjustment, and has high networking application value in a spatial information network.

2 research progress based on communication networking of near space platform

In the early days of the research on the near space platform, researchers have proposed various schemes for communication networking of the near space platform. The system is divided into a quasi-static network requiring the platform to keep relatively static to the ground and a mobile network allowing the platform to move under the action of an external environment.

Examples of quasi-stationary networks are HAPS networks proposed by ITU and WRC, spatial station (Sky station) engineering in north america, the cananina project in the european union, the Skynet project in japan, and the like. These schemes are similar and different in networking mode, and are described here by taking space station engineering in north america as an example, as shown in fig. 8.

Space station engineering is promoted by the International space station corporation (Sky station International Inc), and aims to establish a solar adjacent space platform system covering the whole world to provide broadband wireless cellular communication services. The project uses 250 adjacent space platforms called space stations, each deployed about 21km above the world's major cities, where the number of platforms would be increased to increase system capacity. These space stations function as communication base stations to provide 3G wireless cellular communication services to terrestrial users. Cellular areas are divided into three types, urban coverage area (UAC, diameter 74km), suburban coverage area (SAC) and rural coverage area (RAC). A single platform provides wireless broadband access services of 2Mb/s uplink and 10Mb/s downlink by using a spot beam antenna, and can provide 9.6-16kb/s digital voice services and 384kb/s data communication services for mobile users, wherein the working frequency bands comprise a 2GHz frequency band and other 47/48GHz frequency bands consistent with the IMT-2000 standard. The project requires that each platform site resides in a specific airspace. According to the relevant ITU standards, the range of platform movement to ground is only up to 0.6km by 1km at most. The platform can be connected with the existing ground wired backbone network through a ground station, and the networking among the platforms can be directly realized through a wireless link among the platforms. The requirement of the networking mode on the wind-resistant fixed-point suspension staying capability of the platform close to the space greatly exceeds the level (10km multiplied by 2km) which can be achieved by the current platform control technology, so that the networking mode is not put into practical use.

The network formed by over-pressure balloons adopted in the LOON project of Google is the most typical near space network at present. The balloon plan has an altitude of 20km from the ground with an average duration of more than 100 days, as shown in figure 9.

The technical difficulty of the LOON project is how to coordinate and control the simultaneous flight of numerous balloons in the air to ensure that the area covered by the balloons is exactly where communication services are needed. In the stratosphere, there are many stable wind layers, each with different direction and speed. Google utilizes the atmospheric data acquired by the public database to control the balloon to ascend or descend through the air pump so as to enter different wind layers, so that the aim of controlling the balloon to move in the expected direction and speed is fulfilled. The Google balloon can operate entirely on renewable energy sources by wind propulsion and solar charging. Although Google balloons will drift continuously under the action of airflow, through the macroscopic regulation and control of a large amount of balloon drift, Google can still ensure that balloons above a certain area can be uniformly distributed, so that uninterrupted internet surfing service is provided for ground users, as shown in fig. 10.

Generally speaking, the LOON project is very fast in progress, and by the end of 2016, Google adopts a super-pressure balloon which is completely mature and shaped in the project, the average endurance time of a single balloon is generally more than 100 days, the longest endurance time reaches 190 days, and by the end of 2016, Google realizes fixed-point region residence of 98 days in the air of a Peru city by controlling the flying height of the balloon; in the early 2017, rare flood disasters occur in Peru, ground communication facilities are largely damaged, Google utilizes an emergency communication network consisting of overpressure balloons to provide basic internet connection for an area of 4 kilo square kilometers (equivalent to a Switzerland) within 72 hours, and data traffic of over 160GB is provided. This is by far the most successful practical application of the near space aerostat platform, as shown in figures 11-12.

An air-air link laser communication test carried by a 12-plane carrier in 2013 of national vinpocetine university makes, under the condition that the transmitting power and the flight distance are the same, the flicker variance of the received light spot is reduced along with the increase of the flight height, the mean value of the received light power is increased along with the increase of the flight height, and the atmospheric loss is reduced along with the increase of the flight height, so that the method has certain reference significance for the research of the temporary-temporary laser communication link, and is shown in fig. 13.

At present, the research on the laser communication of the temporary-temporary link mostly stays at the simulation and theoretical research stage, is limited by the maturity of the adjacent space platform, only one report about the laser communication of the adjacent space is about the LOON balloon network of Google, in 2015, the LOON team of Google has established the connection rate of GB/S between balloons with the stratosphere height being hundreds of kilometers away, and an LTE base station is used for providing mobile internet service for users below the balloons, but no specific technical data such as flight time, flight altitude, communication rate, communication time and the like exist.

In general, laser transmission characteristic analysis in the near space also depends on a large amount of flight measurement data support.

In conclusion, the prior art cannot well realize the long-term reliable standing of the adjacent space platform, the multi-platform collaborative flight path planning and the distributed collaborative flight of the adjacent space platform facing the task formation networking, so that the application requirements in the space information network cannot be well met.

Disclosure of Invention

Technical problem to be solved

In view of the above technical problems, a primary object of the present disclosure is to provide a distributed cooperative flight control method for task-oriented formation networking of a near space platform, so as to solve at least one of the above problems. (II) technical scheme

According to one aspect of the disclosure, a distributed collaborative flight control method for task-oriented formation networking of a near space platform is provided, which includes: determining constraint conditions for optimizing the targets of the multi-coding adjacent space platform; receiving input and output data fed back by a near space platform; and controlling function switching and load distribution of the adjacent space platform based on the constraint conditions and the data.

According to another aspect of the present disclosure, there is also provided a multi-platform collaborative flight path planning method, including: the target distribution layer distributes serial numbers for the platforms respectively, and gives track indexes of the platforms to targets according to the track planning layer; the cooperative control layer determines the cooperative time t of the formation platform according to the external environment condition, the variation range of the platform speed and the flight path length transmitted from the flight path planning layer, and transmits the cooperative time t and the corresponding flight path number of each platform to the flight path planning layer; the flight path planning layer determines an optimization function according to the task, and generates a flight path meeting the multi-platform cooperation requirement through the predetermined ground observation and communication conditions; the track smoothing layer generates a track which takes time as a variable and meets the requirement of cooperation and the requirement of dynamic performance of the platform; the track tracking part determines a feasible track and a corresponding control vector by using the inertial coordinate and the direction information, and sends the determined height, speed and course of the feasible track to the servo system of the automatic pilot of the platform for execution, and the control platform flies according to the planned track.

(III) advantageous effects

According to the technical scheme, the method has at least one of the following beneficial effects:

(1) through the control on the residence and the load direction, the long-term reliable residence is realized, and the application requirement in a space information network is well met.

(2) The near space backbone network serves as a concept of a space information network subnet, a laser communication link serves as a main communication means between the near space networks, the area-controllable binary overpressure balloons serve as nodes of the near space backbone network, and the requirements of large-range area coverage, starting and stopping and communication transfer are met through multi-platform cooperative control.

(3) With the significant difference in wind speed direction at different altitudes, it is advantageous to turn the disturbance into drive, unfavorably, by adjusting the altitude so that the balloon that would otherwise be far from the desired dwell center can be pulled back with the new wind direction.

(4) Networking is completed by utilizing the cooperative control of the multiple aerostat platforms, the advantage of low cost can be fully exerted, and the task targets of large-range area network coverage and information transmission are achieved.

(5) And optimizing and decomposing the multi-platform target based on constraint condition analysis, and realizing function switching and load distribution effective control of the platform in the near-to-compiling space.

(6) The multi-platform collaborative track planning method realizes the purpose of permanently providing regional ground integrated information service and well meets the application requirements in a spatial information network.

Drawings

The above and other objects, features and advantages of the present disclosure will become more apparent from the accompanying drawings. Like reference numerals refer to like elements throughout the several views of the drawings. The drawings are not intended to be to scale as practical, emphasis instead being placed upon illustrating the subject matter of the present disclosure.

Fig. 1 is a schematic view of the progress of an american stratospheric airship (wherein, (a) a climber airship of the american air force and (b) a high altitude sentinel airship of the army).

FIG. 2 is a schematic illustration of a HALE-D airship flight test.

FIG. 3 is a schematic diagram of a series of airships at the photoelectric research institute.

FIG. 4 is a schematic view of a United states NASA overpressure balloon and its flight path around the south pole.

FIG. 5 is a schematic diagram of the "binary" balloon structure employed by the Google balloon.

FIG. 6 is a schematic view of a scientific hospital with a load of 1.9 tons for high altitude scientific balloons.

Figure 7 is a schematic illustration of in-house testing of pressurized balloons at the academy of sciences photoelectric research institute.

Fig. 8 is a space station engineering schematic in north america (where (a) the cellular configuration of the space stations, and (b) two networking approaches between the space stations).

Figure 9 is a schematic diagram of a google lon balloon network.

Fig. 10 is a diagram of the ascent of the Google balloon and its networking effect.

Fig. 11 schematic representation of Google balloon residing over peru for 98 days.

Fig. 12 is a schematic diagram of the Google balloon providing emergency communication services for peru.

Fig. 13 is a schematic diagram of three laser links involved in a near space network.

Fig. 14 schematic diagram of the Google balloon performing the near space laser communication experiment.

FIG. 15 is a diagram of the effect of a superpressure balloon designed by the photoelectric research institute.

FIG. 16 is a schematic diagram of a spatial information network architecture.

Fig. 17 is a schematic diagram of a typical application of the spatial information network.

FIG. 18 is a diagram of multi-platform objective optimization decomposition, feedback coordination, and function transformation (relationship of sub-contents 1A, 1B, 1C to each other).

Fig. 19 is a schematic diagram of topology and cooperative coverage effect in dynamic position of a programmed temporary platform.

Fig. 20 is a schematic view of evaluation of the coverage effect.

FIG. 21 is a schematic diagram comparing the flying altitude change of a superpressure balloon and a zero-pressure balloon.

Figure 22 is a schematic view of the current red cube at the centre of the cube and its maximum 26 neighbouring cubes.

FIG. 23 is a statistical chart of wind speed variations at different heights in the west of China.

FIG. 24 is a schematic diagram of a multi-platform collaborative track planning model.

Detailed Description

For the purpose of promoting a better understanding of the objects, aspects and advantages of the present disclosure, reference is made to the following detailed description taken in conjunction with the accompanying drawings.

It should be noted that in the drawings or description, the same drawing reference numerals are used for similar or identical parts. Implementations not depicted or described in the drawings are of a form known to those of ordinary skill in the art. Additionally, while the present disclosure may provide examples of parameters that include particular values, it should be appreciated that the parameters need not be exactly equal to the respective values, but may be approximated to the respective values within acceptable error margins or design constraints. Directional phrases used in the embodiments, such as "upper," "lower," "front," "rear," "left," "right," and the like, refer only to the orientation of the figure. Accordingly, the directional terminology used is intended to be in the nature of words of description rather than of limitation.

One, near space backbone network

Since the near space environment is significantly different from the conventional aviation environment, and the characteristics of the aircraft are also greatly different, the hierarchical division of the near space backbone network in the aerospace information network is made clear by the method.

1. Near space laser communication backbone link

In the field of future space information network communication, an adjacent space network is in a position of starting and stopping, a series of high-requirement tasks with large communication information quantity, higher transmission rate and stronger interference resistance requirements exist, microwave communication cannot meet the current high-capacity communication requirements due to the limitation of the microwave communication, a laser communication link is adopted as a main communication means between the adjacent space networks, the space laser communication has the advantages of very high transmission rate, high bandwidth and good propagation directivity, the receiving field of laser is very small, so that information can be effectively prevented from being intercepted, and the wavelength of the laser is very small, so that the interference of some electromagnetic waves can be prevented.

A laser communication network based on a near space aerostat platform can establish 3 basic communication links: an adjacent-to-ground link, a heaven-to link, an adjacent-to link. The earth-ground link is similar to the earth-ground (or satellite-ground) laser link, but whether the earth-ground link or the air-ground link is affected by the tropospheric atmosphere, and the application has a certain limitation. The temporary-temporary link is generally considered to have much smaller atmospheric attenuation than the temporary-ground link and has greater practical value, as shown in fig. 14.

The airspace of the temporary-temporary link is positioned above the troposphere and is not influenced by the weather; meanwhile, the atmospheric mass of an airspace of 20-50 km accounts for 9.9% of the total atmosphere, so the atmospheric attenuation effect of the temporary-temporary link is obviously weaker than that of the temporary-ground, air-ground or satellite-ground link. Different from the situation that most of the near-sky link is in free space, the near-sky link has more atmospheric components and high density, for example, high-concentration ozone, certain aerosol particles and high-altitude atmospheric molecules exist, the atmospheric attenuation effect is mainly shown as the absorption effect of the ozone on laser, the scattering effect of the aerosol particles on the laser and the scattering effect of the high-altitude atmospheric molecules, but after the communication wavelength is reasonably selected, the magnitude of the attenuation effect is very small and is not more than 1 dB. The laser communication temporary-temporary link is also influenced by atmospheric turbulence, which is mainly reflected in two aspects of atmospheric flicker and arrival angle fluctuation. The atmospheric flicker is proportional to the transmission distance and inversely proportional to the communication wavelength, and the fluctuation of the arrival angle is only proportional to the transmission distance and has small magnitude.

2. Near space backbone network

The present disclosure provides a near space backbone information transmission network based on a binary overpressure balloon platform, which is in a backbone relay transmission status from top to bottom in a space information network, and is an important subnet of the space information network, as shown in fig. 15.

Wherein, the overpressure balloon loads constituting the near space backbone network node are all communication loads, such as high-speed laser communication loads (point-to-point, point-to-multipoint), microwave line-of-sight high-speed communication loads (point-to-point), PMP broadband access communication loads (point-to-multipoint) and wide/narrow band satellite communication loads, as shown in fig. 16.

The concrete link is as follows: the remote sensing satellite load obtains information, the sky-to-earth link is communicated by laser, the adjacent-to-ground link can be communicated by microwave, and the microwave link loss of a free space is reduced. The method comprises the steps that remote sensing information acquired by an air-based platform is transmitted to an adjacent space platform through an air-adjacent microwave link (the adjacent space platform is an aerostat and can be divided into two platforms, namely an stratospheric airship and an aerial scientific balloon according to the condition that no power exists), and the platform is forwarded to the rear end of the ground through a multi-hop adjacent space backbone network. The near-ground link can be selected from laser and microwave. Considering that the nodes of the backbone network in the adjacent space can be expanded, the skynet No. 1 communication link is selected as the main measurement and control link of the aerostat node, so that a large number of high-gain directional receiving antennas are not required to be arranged in a ground control center, the cost is controllable, and the speed can meet the measurement and control requirement. The position of each aerostat node can be obtained through the skyway link in the ground control center, then the network topology is dynamically adjusted according to the relative position of the aerostat node, the APT direction is changed, and the laser link path is changed.

Second, application scene of space information network based on near space platform

The application of the aerospace information network based on the near space aerostat platform is described in detail below with reference to examples.

1. Sparse road network rail transit road network monitoring and safe operation demand analysis

At present, a railway special GSM-R network is constructed in the western sparse road network to transmit necessary information such as data, voice and the like, but the large-capacity information such as videos and the like cannot be transmitted in real time due to limited bandwidth (< 400kbps), so that the high-resolution safety monitoring requirement is difficult to meet. The west sparse road network is located in plateau areas, the construction and maintenance difficulty is high, the cost is high, the perennial weather conditions of certain areas are severe, sand storm or geological disasters occur frequently, the track operation safety is threatened, and the maintenance efficiency is low only by means of manual line patrol. Therefore, a new information transmission method is urgently needed to improve the efficiency of the western sparse road network safety monitoring and operation and maintenance.

2. Typical application scenario design and construction

According to the aforementioned requirements, the composition of a typical application scenario is as follows:

table 1 spatial information network exemplary application architecture composition

According to the requirement assumption that a spatial information network based on a near space platform can cover the track range from Guinea railway gelmu to Lanzhou of about 1000 km, 4 near space aerostats are uniformly distributed along the line, the flying height is 20km, and the service range of a single aerostat is 300km in radius; the total coverage capacity is 2400km multiplied by 300km, certain reliability and redundancy are considered, a network coverage area has certain overlapping performance, and the requirement of 1200km multiplied by 200km can be met; and 2 unmanned aerial vehicles are deployed, each aircraft is in charge of a 500km road section, the distance is calculated according to the speed per hour of 150km, the round trip mileage is calculated, the routing inspection task can be completed in about 6 hours every day, and meanwhile, the system can be ready to meet the emergency response requirement at any time. The environmental video monitoring information of the unmanned aerial vehicle and the ground train can be dynamically accessed to a communication network covered by the aerostat, the video information with large data volume is forwarded between the aerostats through a laser link, and finally the video information is transmitted to the ground through a microwave line-of-sight link, as shown in fig. 17.

Therefore, in a normal operation scene, a large-bandwidth, real-time and high-reliability long-distance information transmission channel is constructed by means of a near space network, air-vehicle, vehicle-vehicle and vehicle-ground information seamless sharing is achieved, and real-time transmission and early warning processing of train operation safety monitoring information are supported.

Under a normal operation scene, an air vehicle-ground network formed by the near space aerostat and the low-altitude unmanned aerial vehicle and a conventionally used GSM-R network special for the railway independently provide communication services at the same time. Train operation related information, such as vehicle body information, line information and ground equipment information, are independently transmitted through two networks and mutually backed up, so that the rail transit safety operation principle is met. Adopt unmanned aerial vehicle independently to patrol line monitoring track safety, the high definition video accessible of shooting closes on space platform relay passback, increases substantially and patrols line monitoring efficiency.

Aiming at natural disasters such as side slope landslide, rockfall, strong wind, heavy rain, heavy snow, earthquake and the like along a railway line, and under the situation that a GSM-R network special for the railway is unavailable, an emergency network plan of an approaching empty vehicle and ground based on a near space platform is started, and the rapid on-demand networking and dynamic reconstruction technology of the emergency network is utilized to ensure the real-time operation safety of the rail transit facing to emergency.

Under the emergency condition, the unmanned aerial vehicle can shoot and return the on-site video information (through the relay return of the near space backbone network) at any time, and decision basis is provided for emergency command departments. According to different damage conditions of ground application systems along a railway, the main and standby conditions of the space-to-ground network gradually change, the space-to-ground network gradually changes from the main to the standby state to be used in a dual-network mode along with the increase of the damage conditions of the ground network, and the worst condition is changed into a network structure mainly comprising a space-to-ground information network.

Third, near space backbone network platform based on aerostat and communication

In the disclosure, a distributed cooperative flight control method for task formation networking of an adjacent space platform comprises the following steps:

determining constraint conditions for optimizing the targets of the multi-coding adjacent space platform;

receiving input and output data fed back by a near space platform; and

and controlling function switching and load distribution of the adjacent space platform based on the constraint conditions and the data. The specific process is as follows:

1. distributed cooperative flight of near space platform facing task formation networking

As shown in fig. 18, it mainly includes three parts 1A, 1B, 1C, whose relationship with each other is: 1B and 1C feed back input-output data of each editing platform to 1A, and 1A sends planning decision targets of each editing platform to 1B and 1C and distributes load tasks.

2. Multi-platform target optimization decomposition, feedback coordination and function switching

Establishing a geographical coordinate system O-xyz of the northeast by taking O at an altitude of 20km above a certain longitude latitude as an origin without loss of generality; suppose that two types of adjacent space platforms are encoded, the code of which is L_k(k-1, …, 5) with the first 3 balloons at overpressure and the second 2 balloons at motionA force airship; using boundary value x of east-west-south-north for the area required to be effectively covered_E，x_W，y_S，y_NAnd (4) showing.

As shown in fig. 19, the upper part is a dynamic topological graph of platform formation, and the lower part is a cooperative coverage graph, the cooperative coverage effect can be calculated according to the dynamic position of each platform and the coverage radius of the ground load. The coverage effect diagram is marked with an operation and safety guarantee center (indicated by a cross) and a certain ground communication station (indicated by a semicircle).

The overlay object is ranked, for example, into five levels: a certain static object (ground communication station) and a certain dynamic object (for example, a high-speed rail in the process of driving, which is indicated by five stars) are the highest 5 levels; some dynamic objects (e.g., a drone at work, denoted by four stars) are the next highest level 4; the suspected abnormal zone is grade 3; 2 grades are arranged along the railway; the others are class 1.

In addition to ranking by object, the evaluation of coverage effects is also differentiated by path loss. As shown in fig. 20, the path loss at different elevation angles can be calculated as:

L_θ＝20log(640πh_m arcsinθ)＞L_90°＝152dB，L_15°＝164dB.

the difference between the two path losses is 12 dB. That is, assuming that the mission height of the platform is 20km, and the operating frequency is 48Ghz with the largest path loss, the communication power in the case of 15 degrees and low elevation angle is 16 times that in the case of 90 degrees and high elevation angle, and it can be seen that the transmission distance has an important influence on the transmission of signals. Therefore, the communication power at the elevation angle of 90 degrees is taken as a reference, the communication power at different positions in the coverage area is compared with a reference value to be used as a multiplication factor for evaluating the communication coverage capacity, the conditions of coverage of a plurality of adjacent empty platforms are further overlapped, each monitored object is divided by the area of the monitored object after being integrated according to the area element to be taken as the corresponding average coverage quality, and finally the object level (or a direct proportional function thereof) is taken as a weighted value to be summed to be taken as the overall evaluation of the coverage quality. The dynamic change situation of the coverage quality is the first task constraint condition of the multi-platform target optimization.

The second task constraint condition of the multi-platform target optimization is the quality change of networking communication of the adjacent space platform. In a dynamic topological graph of platform formation, the distance between each platform and the adjacent platforms in front and back can be solved through the actual position measurement estimation value of each platform, and the communication quality of the distance is compared with the optimal communication quality to be used as a weighting factor, so that the communication quality evaluation value of the platform in the air communication network is obtained; and summing the communication quality evaluation values of all the platforms to obtain the efficiency evaluation of the whole adjacent space communication network.

The third constraint condition for multi-platform target optimization is multi-platform track and its wind field influence change. And comparing the nearest track of each platform with the disturbance condition of the experienced environment wind field, and evaluating the utilization/resistance of the environment wind field disturbance condition. Especially for power airship, this also relates to the magnitude of platform power consumption and endurance performance.

And finally, taking input-output feedback data of the overpressure balloons and the power airship in the formation as a coordination factor for reflecting the platform capacity, carrying out compromise between better efficiency and lower cost, and sending the compromise to each platform as a decision command for keeping the current state of each platform or planning and maneuvering a certain new specific target.

Platform function switching and its load task allocation relate to a specific task mode. E.g. as default mode, powered airship L₄/L₅Is responsible for directly transmitting the information to the ground communication station (and then transmitting the information to the operation and safety guarantee center by the ground communication station). But if L is₄/L₅The communication coverage efficiency of the ground communication station is not optimal, and the L is switched₁/L₂/L₃The communication coverage of the medium-to-ground communication station is effective and the efficiency is optimal; otherwise, all the platforms in the adjacent space are selected to transmit the satellite communication optimally.

3. Near space overpressure balloon area dwell and load pointing control

The nature of the superpressure balloon determines that it can achieve a longer dwell time at stratospheric altitudes as compared to a zero-pressure balloon, as shown in fig. 21, where the superpressure balloon is above and the zero-pressure balloon is below, and thus becomes one of the two types of near space platforms of choice in the present disclosure.

The essence of implementing control over a single superpressure balloon is search, i.e., control based on the Markov Decision Process (MDP). Specifically, the method for controlling the residence and load direction of the adjacent space overpressure balloon area comprises the following steps:

s1, decomposing the desired residing target position of the balloon according to the sub-content 1A, selecting a track space comprising the desired residing position and the range, and dividing a cubic grid (for short, a vertical element);

s2, taking each current vertical element as input (as shown in fig. 22, dark vertical element) and its adjacent vertical elements (except the boundary, there are generally 26, so this search method is called "magic cube search method") as output, respectively, and using an estimation algorithm such as Gaussian Process (GP) to predict the change of environmental big data, calculating the probability of reaching each adjacent grid after a certain time interval;

s3, performing path planning in the whole track space based on a Markov Decision Process (MDP), performing actual control (keeping height, rising height or falling height) according to the path planning, and performing reward and punishment according to the actual control result and the rolling accumulation of the planning result to influence subsequent planning and control;

and S4, and simultaneously, performing enhancement updating on the environment big data according to the actual control result.

The method utilizes the obvious difference of wind speed directions at different altitudes, and the balloon which is originally far away from the expected residence center can be pulled back by utilizing a new wind direction by adjusting the altitude, so that the disturbance is changed into driving and is unfavorable.

Fig. 23 is a statistical graph of wind speed changes at different heights in 2016 and 7 months somewhere in the west of china, and it can be seen that a significant zero wind layer exists near the height of 20km, and the wind speeds near the upper and lower parts of the zero wind layer are reversed, so that the wind speed change statistical graph has a great utilization value.

The method adopts the reinforcement learning algorithm to predict the wind speeds with different heights by utilizing Python language programming, the predicted trend is approximate to the actual test set data from the result, particularly the height is less than 10000 and more than 15000, and the predicted trend line is very consistent with the tested data point.

To achieve as long a residence time in the stratosphere as possible, the present disclosure also employs a drive steering that actively utilizes the heat transfer principle.

The payload of the superpressure balloon is mainly used for information transmission, and corresponding antenna pointing maneuvering and stabilizing control is carried out according to related tasks distributed by the sub-content 1A.

4. Multi-aerostat platform cooperative control

Although the track control precision of a single binary overpressure balloon is low, the advantage of low cost can be exerted, and the networking is completed by the cooperative control of multiple aerostat platforms, so that the task targets of large-range regional network coverage and information transmission are achieved.

When the multi-platform performs tasks in a networking manner, the control cooperativity and consistency need to be kept, and the integrity of the whole network is further ensured. During the implementation, on one hand, the redundancy of the nodes during the networking is fully ensured, and on the other hand, the intelligence and comprehensive judgment capability of various algorithms (such as a neural network, a satisfaction decision theory, an ant colony algorithm and the like) are fully utilized, so that the interference is eliminated, and the comprehensive optimization is realized.

In the aspect of cooperative control, different responsibilities are born among multiple platforms in the process of executing tasks, and the cooperation of the tasks is realized through mutual data and information interaction. In the whole cooperative task process, the platform not only needs to receive command and control information from the ground to execute the own task of the platform, but also needs to be matched with other platforms to execute the task together according to the command of the actual situation, thereby greatly increasing the workload of the platform. A simple and effective cooperative control mode is designed, and powerful guarantee is provided for task completion. Such cooperation can be accomplished in various ways, and an artificial intelligence method is one of them (in addition to a heuristic search method and an expert system method, a neural network method, a fuzzy control method, a genetic algorithm, etc.). However, in any case, a complete set of instructions must be defined to facilitate the identification, understanding, execution, and transmission of interactive information between platforms and in an inter-machine data chain. The design of the instruction set should satisfy: complete, simple and standard requirements, and lays a foundation for realizing convenient and fast information transfer among multiple platforms. In addition, collaborative situation awareness, collaborative target allocation, collaborative route planning technology, damage performance evaluation technology and intelligent decision technology should be further improved, and only on the basis of the technology, the fast and seamless connection among multiple platforms (namely, among nodes) can be realized, and finally, the multi-platform collaborative control is achieved.

As shown in fig. 24, an overall structure of the multi-platform collaborative flight path planning (a multi-aerostat platform collaborative control method) includes: the target distribution layer distributes serial numbers for the platforms respectively, and gives track indexes of the platforms to targets according to the track planning layer; the cooperative control layer determines the cooperative time t of the formation platform according to the external environment, the variation range of the platform speed and the flight path length transmitted from the flight path planning layer, and transmits the t and the corresponding flight path number of each platform to the flight path planning layer; the flight path planning layer determines an optimization function according to the task, and generates a flight path meeting the multi-platform cooperation requirement through the predetermined ground observation and communication conditions; the track smoothing layer generates a track with time as a variable, and meets the requirement of cooperation and the requirement of dynamic performance of the platform; the track tracking part determines a feasible track and a corresponding control vector by using the inertial coordinate and the direction information, sends the obtained height, the speed and the course of the feasible track to a servo system of the automatic pilot of the platform for execution, and controls the platform to fly according to the planned track. The main task of the multi-platform collaborative track planning is to complete the design of a collaborative control layer, a track planning layer and a track smoothing layer.

5. High-precision APT for near space laser communication

In an adjacent space backbone network based on an aerostat platform, an aerostat serving as a node moves at a low speed relative to the ground, the movement form depends on the change of a wind field, the prediction precision of the movement of a single node is low, the network topology changes in real time, switching is frequent even if a user does not move, and a fixed link relation does not exist among a user terminal, a satellite, the aerostat and an aviation platform. In addition, the wireless channel between the aerostat platforms is dependent on where the platforms are currently located, giving the communication channel a time-varying characteristic, requiring access network communication devices to have acquisition and aiming tracking (APT) capabilities.

APT is the most important component and key in laser communication. The method can ensure the dynamic accurate alignment of two visual axes of communication, thereby reducing the loss of communication optical power emitted by diffraction limit caused by visual axis deviation.

The APT is required to realize high-precision tracking aiming with dynamic tracking error reaching micro-radian order under the conditions of overcoming the influence of the attitude change of a floating platform in the near space, the platform jitter and the atmospheric channel characteristics and considering the real-time correction of the aiming advance angle. The influence of the near space atmosphere on laser communication mainly considers the following two points: one is atmospheric absorption and attenuation effects: the laser communication system of the atmosphere to the adjacent space generates power loss, the loss is related to the specific atmospheric condition of a receiving place, the zenith angle of a visual axis, the current wind speed and the altitude of the receiving place, and the atmospheric attenuation is related to the corresponding relation of a channel inclination angle; secondly, atmospheric deflection phenomenon: the atmosphere of the adjacent space is thin, the weather phenomenon does not exist, the communication channel condition is stable, however, the refractive index is gradually reduced along with the rise of the altitude, and the airflow layering phenomenon exists, so that the deflection phenomenon of the communication optical axis inevitably occurs, the image centering precision is further influenced, and the performance index of the APT tracking system is reduced.

Although the high-frequency interference is reduced by passive vibration reduction measures, active vibration suppression measures are also needed for the low-frequency interference and the medium-frequency interference, namely, the traditional high-bandwidth servo units such as FSMs are adopted to suppress the total tracking residual error of the system to be within 1/8 of the beam divergence angle; the method is characterized in that an initial pointing direction is established for beacon light by combining the positioning function of a space-based information network, and a coarse tracking visual axis is offset by a certain preset angle (namely, an open loop capture uncertain area is set, and the initial capture uncertain area of a system to be tested is set to be a fixed value alpha due to the limitation of test conditions), so that the scanning time of coarse tracking is cancelled, the establishment time of dynamic links is greatly shortened, and the quick aiming capture between the double dynamic links is realized.

In summary, the present disclosure provides an adjacent space backbone network based on an aerostat platform, a typical information transmission link mainly based on adjacent space laser communication, and introduces an application mode of the adjacent space backbone network, taking rail transit safety monitoring requirements as an example, by combining characteristics of an adjacent space environment. The binary overpressure balloon is proved to be suitable for networking application of an adjacent space, so that the control precision of a platform area is improved, and the comprehensive performance of a backbone network of the adjacent space is improved.

The disclosed close-space aerostat platforms have longer air residence time, faster deployment rates, more flexible maneuvering capabilities, and greater loading capabilities. The method lays a solid foundation for realizing the sharing and intercommunication of the sky-face-air-ground large-capacity information, breaking through the bottleneck problems of limited overhead time, strong channel state dependence and the like of the existing sky-ground large-capacity data transmission in China and the construction of a space-ground integrated information network.

The near space backbone network serves as a concept of a space information network subnet, a laser communication link serves as a main communication means between the near space networks, the area-controllable binary overpressure balloons serve as nodes of the near space backbone network, and the requirements of large-range area coverage, starting and stopping and communication transfer are met through multi-platform cooperative control.

It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. Furthermore, the above definitions of the various elements and methods are not limited to the specific structures, shapes or modes mentioned in the examples, and may be modified or substituted by one of ordinary skill in the art:

the above-mentioned embodiments are intended to illustrate the objects, aspects and advantages of the present disclosure in further detail, and it should be understood that the above-mentioned embodiments are only illustrative of the present disclosure and are not intended to limit the present disclosure, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.

Claims (2)

1. A task-oriented formation networking distributed cooperative flight control method for an adjacent space platform comprises the following steps:

determining a plurality of constraints for optimizing a platform target in a build-up vicinity space, wherein the constraints comprise:

the dynamic change of the coverage quality comprises a coverage range, the classification of a coverage object and path loss, and specifically comprises the steps of comparing communication power at different positions in the coverage range with a reference value to be used as a multiplication factor for evaluating the communication coverage capacity, superposing the conditions covered by a plurality of adjacent empty platforms, integrating each monitored object according to an area element, dividing the integrated monitored object by the area of the monitored object to be used as corresponding average coverage quality, summing the integrated monitored object by using the object level as a weighted value and distinguishing the monitored object by using the path loss to be used as the overall evaluation of the coverage quality;

in the dynamic topological graph of platform formation, the distance between each platform and the adjacent platforms before and after the platform is solved through the actual position measurement estimation value of each platform, and the communication quality of the distance is compared with the optimal communication quality to be used as a weighting factor to obtain the communication quality evaluation value of the platform in the air communication network; summing the communication quality evaluation values of all the platforms to obtain the efficiency evaluation of the whole adjacent space communication network;

the multi-platform track and the wind field influence change thereof are compared with the latest track of each platform and the disturbance condition of the experienced environment wind field, and the utilization/resistance wind field disturbance condition of the tracks is evaluated;

receiving input and output data fed back by a near space platform; and

controlling function switching and load distribution on the near-to-compile space platform based on the constraint conditions and the input and output data fed back by the near-to-compile space platform, taking the input-output feedback data of the near-to-compile space platforms as a coordination factor reflecting platform capability, carrying out compromise selection between better efficiency and lower cost, and issuing decision commands to each platform on the near-to-compile space platform, wherein the decision commands comprise current state maintenance or planning and maneuvering to a new specific target, and specifically comprise the following steps:

s1, obtaining an expected resident target position through multi-platform target optimization decomposition, feedback coordination and function switching (1A), selecting a track space and carrying out cubic grid division, wherein the track space comprises the expected resident position and range;

s2, respectively taking each current vertical element as input and the adjacent vertical element as output, and calculating the probability of reaching each adjacent grid after a certain time interval by using the prediction of the environment big data change, wherein the prediction of the environment big data change comprises a Gaussian process estimation algorithm;

s3, path planning is carried out in the whole track space based on the Markov decision process, actual control is carried out according to the path planning, and reward and punishment are carried out according to the rolling accumulation of the actual control result and the planning result so as to influence subsequent planning and control;

s4, performing enhancement updating on the environment big data according to the actual control result;

wherein the close space platform comprises a super-pressure balloon and/or a powered airship;

the multi-platform target optimization decomposition, feedback coordination and function switching (1A) specifically comprises the steps of performing multi-platform target optimization decomposition and function switching according to the dynamic coverage performance change of the hierarchical object, the communication quality change of the air information network, the multi-platform track and the wind field influence change of the multi-platform track;

the method comprises the following steps that a staying and load pointing control (1B) of an adjacent space overpressure balloon area receives a planning decision target and a distributed load task issued by the multi-platform target optimization decomposition, feedback coordination and function switching (1A), and feeds back input-output data to the multi-platform target optimization decomposition, feedback coordination and function switching (1A); and/or

And the near space power airship fixed point/maneuvering and load direction control (1C) receives a planning decision target and a distributed load task issued by the multi-platform target optimized decomposition, feedback coordination and function switching (1A), and feeds back input-output data to the multi-platform target optimized decomposition, feedback coordination and function switching (1A).

2. The method according to claim 1, wherein based on the constraint condition and the input and output data fed back by the on-site spatial platform, the function switching and load distribution of the on-site spatial platform are controlled according to task modes.

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