RU2645179C2 - Probable satellite system for monitoring forest fire - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: system satellites located in circular orbits, are equipped with a scanning wide-angle optoelectronic IR system with a linear photodetective device for detecting a forest fire. There is also a tracking optical-electronic IR system on satellites, which is retargeted according to target designations from the scanning system. This tracking system is made wide-angle (with an IR-type "fish-eye" lens) and with several matrix photodetectors for detecting and determining the parameters of the forest fire, and the formation of a warning signal thereabout.

EFFECT: expanding the system functionality, reducing the mass-dimensional characteristics of the system satellites and reducting the costs of its creation and operation.

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Description

The invention relates to the space field, in particular to satellite systems for observing the Earth, and more particularly relates to a satellite system for providing observations of vast regions of the Earth.

The information system for remote monitoring of forest fires ISDM-Rosleskhoz of the Federal Forestry Agency of the Russian Federation is known (see Schetinsky V.E. et al. Use of the information system of remote monitoring "ISDM Rosleskhoz" for determining fire hazard in the forests of the Russian Federation (Textbook) // FGU “Aviation conservation”, Pushkino (Moscow region), 2007, p. 82).

The main disadvantages of this system are:

- lack of proprietary space assets;

- insufficient efficiency of updating information;

- insufficient reliability of fire detection;

- provision of data partially on a commercial basis.

The closest in technical essence (prototype) to the proposed invention is a satellite system for automated control and operational control (monitoring) of critical objects and territories of the Union State “Russia - Belarus” (see application for invention of the Russian Federation No. 2006143879 of December 13, 2006, IPC B64G 1/10), which has a rigid structure when each spacecraft of the system is in its “cell”.

This system has significant drawbacks associated with significant time, material and energy costs for their creation, maintenance and replenishment.

The objective of the invention is the creation of a probabilistic satellite system for monitoring forest fires, in which the technical result is to reduce the cost of creating a system and the mass-dimensional characteristics of spacecraft included in the system.

This technical result is in a probabilistic satellite system for monitoring forest fires, which includes spacecraft in circular orbits, equipped with a scanning wide-angle optical-electronic infrared system with a linear photodetector for detecting a forest fire focus and a tracking optical-electronic infrared system with a matrix photodetector, retargeted by target designation from the scanning system, to determine the parameters of the source of forest fire and generation of a forest fire warning signal, the spacecraft are equipped with one tracking wide-angle optical-electronic infrared system with several photodetector arrays for detecting and determining the parameters of a forest fire focus, as well as generating a forest fire warning signal.

In probabilistic satellite systems, the position of spacecraft varies widely, and the arrangement and subsequent maintenance of their relative position is not carried out. The necessary level of efficiency of their functioning is achieved by increasing the quantitative composition of spacecraft in the system.

Satellite systems of spacecraft, constructed according to a probabilistic (non-correctable) scheme, can mitigate the shortcomings of deterministic systems (see prototype), but their construction imposes some limitations, including the class of orbits used. As the main restrictions in this case, you can specify the following:

- the number of spacecraft in probabilistic satellite systems should be large enough to ensure the structural stability of the system;

- it is necessary to use near-circular orbits with an eccentricity close to zero, since in this case the secular departure of the argument of latitude perigee will not significantly affect the functioning of spacecraft, in particular the size of the controlled zones of the earth's surface;

- it is necessary to use low orbits with altitudes up to 2000 km, which allows, firstly, to ensure the flexibility of the structure of the system as a whole, and secondly, to simplify the onboard target equipment and spacecraft as a whole and thereby significantly reduce their overall and mass characteristics.

The following characteristics should be noted as distinctive characteristics of satellite systems of spacecraft built on the probabilistic principle:

- when constructing probabilistic satellite systems, there are no strict restrictions on the location of individual spacecraft in the orbit plane, therefore, the requirements for the accuracy of spacecraft launch can be reduced;

- the construction of probabilistic satellite systems can be carried out using batch launches or with a passing load;

- the construction of probabilistic satellite systems can be carried out using conversion ballistic missiles of a lighter class (including from submarines);

- spacecraft systems built according to a probabilistic scheme do not require correction, and therefore, spacecraft do not need a corrective propulsion system (KDU) and fuel reserves, which makes it possible to significantly reduce the cost of the system;

- the lack of the need to maintain spacecraft orbit elements within strict limits allows to reduce the load on the ground control complex (GCC), and also provides the possibility of operating probabilistic satellite systems in the event of failure of individual GCC elements;

- the exit from standing of individual spacecraft from the satellite system of spacecraft, constructed according to a probabilistic scheme, slightly reduces the efficiency of its functioning, since the quality of the solution to the target problem depends on the position in orbit of the entire set of spacecraft of the system.

The invention is illustrated by drawings, where in FIG. Figure 1 shows a possible scheme for constructing a probabilistic satellite system for monitoring forest fires, which could use a uniaxial (gravitationally) stabilized spacecraft (SC) as a base, which will include:

1 - gravitational rod, which will also be used as a receiving antenna of the inter-satellite communication system (CMC);

2 - multi-core transmitting antenna CMC;

3 - spacecraft body with solar panels;

4 - on-board optoelectronic scanning sensor (OECD);

5 - antennas for communicating with spacecraft.

The inter-satellite communication system will have to provide a constant exchange of target information and data on the individual position of each individual satellite between all the spacecraft of the system located in the line of sight. Such organization of the communication system will make it possible to use a single information reception and processing center as part of the NKU, since each spacecraft of the system available for communication with the NKU will be able to transmit to the Earth all information about the state of the system (including the data of the navigation equipment of the consumer (NAP) GLONASS , telemetry and target information). It is also possible to create a mobile switchgear, which will be able to carry out its tasks in any area served by the system.

The principle of circular scanning of the underlying surface is based on the construction and operation of the onboard OECD for detecting and determining the direction of sighting of the source of ignition. It is realized using an ultra-wide-infrared (IR) lens 6 (Fig. 2) of the “fish eye” type (fish eye) with a field of view of the order of 140 °, which ensures observation from the orbit of the spacecraft of the entire Earth’s disk (taking into account errors of the gravitational stabilization of the spacecraft), and also using a rotating prism 7 (Fig. 2) Pehana (roof prism). A variant of constructing an optical OECD scheme and a view of the focal surface 8 (FIG. 2) with photodetector devices (FPUs) located on it from the optical axis of the lens are shown in FIG. 2.

On the focal surface 8 (Fig. 2) it is proposed to arrange linear FPUs 9 (Fig. 2) with a sensitivity range of 3-5 μm to detect sources 10 (Fig. 2) of IR radiation (fire sources) within the entire accessible part of the Earth, as well as linear FPU 11 (Fig. 2) with a sensitivity range of 8-12 microns for constructing the local vertical, limited by the nadir angle range (40 ° ... 70 °), where pos. 12 (Fig. 2) is an image of the Earth’s disk. Photodetectors are located symmetrically relative to the center of the image, the rotation period of which should be several seconds.

In FIG. 3 shows a schematic diagram of the operation of the system (line A _i B _i is the direction of the axis of symmetry of the i-th spacecraft (coincides with the direction of the optical axis of the IR sensor, which is the axis of scanning of the underlying surface), A _i O _i is the local IR vertical, ϕ _i is the angle between local vertical and line of sight of the fire).

The result of processing the signals received from the FPU is the angle ϕ _i between the direction to the sources of infrared radiation and the local vertical, which together with the spacecraft location data are transmitted in real time via CMC channels to Earth. Based on the results of these measurements, as well as using NAP data in a ground-based information processing center, the geographic coordinates of fires are calculated by the triangulation method, and ignition areas are estimated based on an analysis of the power of the infrared radiation coming from them.

For the normal functioning of the system, it is necessary that each point of the controlled underlying surface (or selected fire hazardous areas) is in the visibility range of at least two spacecraft of the system. This condition will be ensured by the selection of specific parameters for the construction of a probabilistic satellite system for monitoring forest fires. However, if there are only two spacecraft of the system above the fire territory, in the course of solving the triangulation problem, in addition to the true solutions 13 (Fig. 3), false solutions 14 (Fig. 3) will arise, for the elimination of which it is enough to install a magnetometer or astro-sensor on the SC, which allows to determine the orientation SC relative to the vertical axis. In the case of processing data from three or more spacecraft of the system, false decisions 14 (Fig. 3) will be discarded in the process of processing the received data on the NKU.

Thus, the proposed probabilistic satellite system for monitoring forest fires can solve many existing problems in the field of monitoring forest fires and the environment. Given the relatively low cost, this system can provide continuous monitoring of the entire territory of our country (or the selected area) with the ability to quickly obtain and process data on the ecological condition of forest lands.

Claims (1)

A probabilistic satellite system for monitoring forest fires, which includes spacecraft in circular orbits, equipped with a scanning wide-angle optical-electronic infrared system with a linear photodetector for detecting a forest fire and a tracking optical-electronic infrared system based on a matrix photodetector, redirected by target designation from the scanning system to determine the parameters of a forest fire focus and signal generation la prevent a forest fire, characterized in that the spacecraft provided with a wide servo optoelectronic system with multiple infrared photodetector arrays for detection and parameters of a forest fire hearth, and the formation of a forest fire warning signal.

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