RU2745378C1 - Method for changing the trajectory of a dangerous space object - Google Patents

Abstract

FIELD: spacecraft protection.SUBSTANCE: invention relates to methods and means of protecting spacecraft (SC) from collision with objects of natural or artificial origin in the interests of increasing the duration of the spacecraft operation, as well as methods of protecting against means of destruction in the event of a hypothetical intentional or unintentional impact on the spacecraft. The technical result consists in ensuring the possibility of using the spacecraft according to its functional purpose and simultaneously performing actions that ensure the protection of the spacecraft when approaching a potentially dangerous object. The method does not lead to the formation of additional debris in outer space. To do this, in accordance with the method, a small spacecraft (SSC) and onboard space radars are placed on board the spacecraft, radar of the surrounding space is performed in orbital flight, a space object (SO) is detected near the spacecraft, and then the parameters of the relative motion of the spacecraft are measured, the orbit parameters of the detected spacecraft are determined, trajectory section identified as well as the flight time interval at which a dangerous approach of the small spacecraft and the spacecraft is possible; if the dangerous approach space is present, SSC is separated from SC, performed are orbital maneuring of SSC, then the approach and capturing of the SO detected, reactive jet propelling device of SSC is activated, the trajectory of the dangerous spacecraft is changed and protection of the spacecraft from collision provided.EFFECT: spacecraft used according to purpose and protection ensured.1 cl, 1 dwg

Description

The invention relates to methods and means of protecting spacecraft (SC) from collision with objects of natural or artificial origin in the interests of increasing the duration of the spacecraft, as well as methods of protecting against means of destruction in the event of a hypothetical intentional or unintentional impact on the spacecraft.

There is a known method of protecting space objects (SO) from means of attack (RU 2294866 C1, 10.03.2007), recommended for use mainly before the object enters the upper atmosphere [1].

The method provides that a protective screen is deployed in front of the space object at the minimum allowable distance from it in the direction of the possible use of attack means, blocking the reach of the space object with the attack means with the screen and informing the screen of the speed and flight trajectory close to the speed and flight trajectory of the spacecraft, fix the protective screen folded edges on the surface of the KO. In front of the reach zone of the attack means, these edges are imparted with acceleration with components along and away from the trajectory of the KO, ensuring the deployment of a protective screen, which is performed in the form of spaced-apart striking elements connected by flexible attachment means at distances smaller than the geometric dimensions of the attack means. The invention relates to the field of spacecraft, in particular reusable spacecraft, hypersonic aircraft, missile warheads, descent spacecraft and other means used in near space, and can be used to organize their protection from weapons before entering the upper atmosphere ...

The disadvantages of this method are:

- high probability of destruction of the protected spacecraft by fragments formed during the interaction of the screen and the means of attack;

- the ineffectiveness of using the method in the orbital flight of the spacecraft due to the need to change the orientation of the spacecraft in space to ensure the deployment of the screen in the direction of the attack vehicle, which leads to the limitation of the targeted use of the spacecraft launched into orbit to perform functional tasks;

- change in the dynamic characteristics of the spacecraft motion relative to the center of mass when the screen is separated from the object and, in connection with this, the need to take into account additional requirements for controlling the angular stabilization of the object's position in space when designing a control system for angular motion;

- the lack of reliable information about the direction of the appearance of the means of attack, which does not allow to ensure reliable protection of the KO;

- the need to control the translational movement of the protective shield to meet the deployment requirements specified in the method, necessary for the effective use of the shield;

- the formation of additional debris in outer space during the implementation of the method.

There is a known method of protecting spacecraft (RU 2374150 C1, 27.11.2009), including the formation of a protective screen, its separation from the protected device and the direction of the screen towards a potentially dangerous object (PO) [2].

The screen is formed in the form of a low-density solid by blowing gas from a polymer material with a short solidification time outside the protected spacecraft, and the polymer material or its mixture with the gas used for blowing the screen has the property of detonation when it collides with the POC, while when an approximation of the POC is detected, the overall dimensions and mass of the screen, sufficient for the destruction of a POO or a group of objects to a finely dispersed state and deflection of fragments of the destroyed object from the protected device. The method provides for the formation of several additional screens of the required mass and overall dimensions until the danger of damage to the protected device of the VET or their fragments formed during the collision of the spacecraft and the VET is eliminated.

The disadvantages of this method are:

- the complexity of a reliable assessment of the size and weight of the first and additional screens sufficient for the destruction of VET and fragments due to the lack of devices and actions that provide information about the design of VET of artificial origin or other necessary characteristics of VET;

- the lack of the possibility of reliable protection of the spacecraft during the implementation of the method, in other words, the probabilistic nature of the successful application of the protection method due to the lack of reliable methods for determining the size and mass of the screens that guarantee the destruction of the FET;

- the possibility of hitting the spacecraft by fragments formed during the interaction of the screen and the object's POT;

- the formation of additional debris in outer space during the implementation of the method.

The description of the method does not contain information on how the approximation of the LET is detected and the calculation of the overall size and mass of the screen, sufficient for the destruction of the LET.

The characteristic disadvantages of the methods involving the use of protective screens is the need to use large screens to ensure reliable protection of the spacecraft, due to the complexity of accurately determining the point of meeting between the spacecraft and the POC, which increases the spacecraft mass and the cost of launching it.

As analogues of the proposed invention, technical solutions proposed for cleaning up space debris should be considered:

- "Spacecraft for cleaning space from passive spacecraft and their fragments" - RU 2141436 C1, 20.11.1999;

- "Method for removing a non-functioning spacecraft from the geostationary orbit" - RU 2559392 C1, 08/10/2015.

In accordance with patent RU 2141436, a spacecraft for clearing space from passive spacecraft and their fragments must contain a power plant, electric rocket engines, a storage and supply system for a working fluid, an instrument and assembly compartment with a control system, a system for fixing and storing large objects of space debris, automatic manipulator, orientation and approach system based on high-thrust engines. The method provides that the onboard equipment includes an autonomous spacecraft with a control system, a passive spacecraft fixation system and docking units interacting with the corresponding docking units of the main vehicle, a manipulator and an attitude and rendezvous system based on high-thrust rocket engines. Moreover, the autonomous spacecraft is connected by a tether system to the main spacecraft.

From the description of the method it follows that the "autonomous spacecraft" as part of the main spacecraft, in essence, is not completely autonomous, since these spacecraft are mechanically connected by means of ropes. Therefore, the use of "autonomous spacecraft" affects the orbital motion of the center of mass of the main spacecraft and its spatial orientation. Thus, the disadvantage of the described method is the change in the orbital trajectory and spatial orientation of the main spacecraft during the implementation of the method, which prevents its use for performing other tasks assigned to orbital space vehicles.

There is a known method for removing a non-functioning spacecraft from a geostationary orbit (RU 2559392 C1, 08/10/2015, prototype) by capturing it and transporting it to a disposal orbit using another spacecraft, which has expired. The method provides that a spacecraft equipped with a means of observing and capturing a non-functioning spacecraft, with an additional supply of propellant components, is put into orbit. After the end of the active life, the spacecraft is transferred to a stationary position in the geostationary orbit of the non-functioning vehicle, the spacecraft is oriented relative to the non-functioning spacecraft and guidance to it, after which the non-functioning spacecraft is captured, the spacecraft engine is turned on, and the spacecraft bundle is transferred to the disposal orbit.

The disadvantage of this method is the impossibility of influencing a space object when using the spacecraft for its functional purpose. The method does not provide the performance of actions that ensure the protection of the spacecraft when approaching potentially dangerous objects and at the same time the targeted use of the spacecraft.

The priority task to be solved by the claimed invention is to ensure the protection of the spacecraft from a potentially dangerous object in such a way as to preserve the possibility of using the spacecraft to perform the functional tasks of its intended use.

The technical result achieved by the claimed invention consists in expanding the functionality of the spacecraft by simultaneously performing actions that ensure the protection of the spacecraft when approaching a potentially dangerous object while maintaining the possibility of using the spacecraft for its functional purpose. The implementation of the method does not require a change in the angular orientation of the spacecraft, the program of operation of the onboard equipment used to perform the target tasks of the orbital flight. The method does not lead to the formation of additional debris in outer space.

The technical result of the method for changing the trajectory of a dangerous space object by using a small spacecraft and means of radar of outer space is achieved by the fact that in orbital flight, radar of the surrounding space is carried out by onboard means, a space object is detected in the surrounding space near the spacecraft, the parameters of relative motion are measured by means of radar space object, determine the parameters of the orbit of the detected space object according to the parameters of the relative motion of the object and the parameters of the orbit of the spacecraft, identify the trajectory segment and the flight time interval at which a dangerous approach of the detected space object and the spacecraft is possible, and in the presence of a dangerous approach area, separate the small spacecraft from the spacecraft, perform orbital maneuvering by a small spacecraft, approach and capture the detected spacecraft objects, include the jet propulsion system of a small spacecraft, change the trajectory of a dangerous object and provide protection of the spacecraft from collision with a space object.

From the description of the proposed method, it follows that it provides the possibility of proactive interception of a dangerous SO.

Essential features that characterize the invention and provide a technical result.

1. Placement on board the spacecraft designed to perform special target tasks corresponding to the functional purpose of the spacecraft, the following additional means:

a) means of radar of the surrounding outer space, providing

- detection of a space object located near the spacecraft;

- measurement of motion parameters of the detected object relative to the spacecraft;

b) means for determining the parameters of the orbit of the detected space object, predicting the trajectories of the spacecraft and the detected object, identifying the trajectory section and the flight time interval, in which a dangerous approach of the spacecraft and the detected object is possible;

c) small spacecraft equipped

- means of orbital maneuvering and rendezvous with a space object located near the spacecraft;

- by means of capture of the detected KO;

- a jet propulsion system.

2. Implementation of the following set of sequential actions: - radar of the surrounding space by onboard spacecraft means, detection of an object located near the spacecraft;

- measurement of the parameters of the object motion relative to the spacecraft by radar means;

- determination of the parameters of the spacecraft orbit, based on the results of measuring the parameters of the relative motion and parameters of the spacecraft orbit;

- prediction of the trajectories of the spacecraft and spacecraft detected near the spacecraft;

- based on the results of predicting the movement of the spacecraft and the spacecraft, the segment and the time interval of the flight, during which a dangerous approach of the spacecraft and the detected object is possible;

- calculation of the orbital maneuvering program for the small spacecraft, which ensures the rendezvous with the spacecraft, provided that a flight segment is identified where a dangerous approach of spacecraft and spacecraft is possible;

- transfer of the orbital maneuvering program of the small spacecraft to the onboard control system of the small spacecraft;

- separation of the small spacecraft from the spacecraft;

- performance of small spacecraft for orbital maneuvering and rendezvous with spacecraft;

- capture of the detected object by a small spacecraft;

- turning on the jet propulsion system located on the small spacecraft to change the trajectory of the detected object;

It can be seen from the given sequence that the proposed protection method does not require changing the order and program of operation of the operated spacecraft used to perform the target tasks. Preservation of the possibility of using the spacecraft according to their functional purpose is the main advantage of the proposed method of protection against dangerous SC. To determine the orbit of the spacecraft based on the results of measuring the parameters of the spacecraft motion relative to the spacecraft by means of radar, the method described in the description of patent RU 2520714 can in principle be used. As the parameters of the relative motion of the spacecraft and spacecraft, the values of the radial velocity of movement of the spacecraft relative to the spacecraft or the distance between KO and KA.

In principle, the developed technical means designed to capture space debris can be used as a means of capturing the detected SC by a small spacecraft. A well-known technical solution is a special harpoon - utility model patent No. 133096. The capture of a space object is carried out when approaching it by firing a harpoon with a given force.

In addition, the following can be used to capture a space object: -metal nets developed by the "NittoSeimo" company on the instructions of the Japanese Space Agency (JAXA);

- a structure similar to that of a "space sail", based on lightweight, flexible membrane materials.

The advantages of nets and sails are:

- a high ratio of the useful area in the deployed state to the area in the folded state and due to this there is a high probability of capture by small spacecraft of the KO when they approach;

- simplicity of design and technological feasibility;

- the ability to capture without the formation of additional space debris;

- small weight and volume when folded;

- the possibility of installing such capture devices on small spacecraft of various types.

A prerequisite for the possibility of using the claimed protection method is a high level of modern technologies of space instrumentation in a number of areas:

- creation of small spacecraft with orbital maneuvering capabilities;

- development of technologies for high-precision guidance and rendezvous of an autonomously functioning spacecraft with orbital objects

- creation of reliable on-board control systems that provide the ability to perform complex technological operations of a spacecraft in a long-term autonomous flight.

The drawing shows a block diagram of a device that implements the proposed method.

The spacecraft 1 contains the means of radar of the surrounding space 2, the user navigation equipment (NAP) of the GLONASS 3 navigation system, the unit for determining the orbit parameters of the detected space object and identifying the trajectory section and the flight time interval at which a dangerous approach of the detected object and spacecraft 4 is possible, onboard digital computing machine (BTsVM) 5, devices for separating small spacecraft from spacecraft 6, small spacecraft 7, which contains onsite 8, orbital maneuvering and rendezvous device 9, device for capturing the detected object 10, propulsion system 11.

Moreover, the first input of the on-board computer 5 is connected to the output of the radar 2, the second input is connected to the output of the NAP 3, the third input is connected to the output of block 4, the first output of the on-board computer 5 is connected to the input of the radar 2, the second output of the on-board computer 5 is connected to the input of the separation device 6, the third output of the on-board computer 5 is connected to the first input of the on-board computer 8, the fourth output of the on-board computer 5 is connected to the input of block 4, the first output of the on-board computer 8 is connected to the input of the orbital maneuvering device 9, the second output of the on-board computer 8 is connected to the input of the capture device 10, the third output of the on-board computer 8 is connected to propulsion system 11, the second input of the onboard computer 8 is connected to the output of the capture device 10.

The device works as follows.

Radar means 2 carry out radar of the outer space surrounding the spacecraft, and transmit the results of the radar to the on-board computer 5. When a space object is detected near the spacecraft, the on-board computer 5 transmits a command to the unit of radar means 2 to measure the motion parameters of the detected object relative to the spacecraft. The results of measuring the parameters of the relative motion are fed to the onboard computer 5, which transmits to block 4, firstly, the parameters of the relative motion of the detected object, including the distance to the object and the rate of change in the distance, and secondly, the parameters of the spacecraft orbit coming from the NAP 3. In the block 4, firstly, the orbit of the detected object is determined, and secondly, the prediction of the spacecraft, the detected spacecraft and the identification of the trajectory section and the flight time interval, in which a dangerous approach of the detected spacecraft and spacecraft is possible. In the presence of a dangerous approach section, block 4 transfers to on-board computer 5, firstly, the parameters of the detected object's orbit, and secondly, the flight time interval at which a dangerous approach of the detected spacecraft and spacecraft is possible. In onboard computer 5, upon receipt from block 4 of the flight interval at which a dangerous approach of the detected spacecraft and spacecraft is possible, the program of orbital maneuvering and rendezvous for the small spacecraft is calculated, and the program is transmitted to the onboard computer 8, then a command is sent from the onboard computer 5 to device 6 to separate the spacecraft from the spacecraft ... After separation of the small spacecraft, the onboard digital computer 8 transmits the orbital maneuvering program to device 9, which maneuvers and approaches the small spacecraft with the detected SO, and when the small spacecraft comes into contact with the object, the device 10 captures the detected SO, then transmits a signal about the completion of the capture from the device 10 to Onboard computer 8, which, after receiving a signal, transmits a command to turn on the propulsion system 11. The operation of the propulsion system 11 provides a change in the trajectory of the detected object, as a result of which the protected spacecraft evade from colliding with the detected object.

The key technical result achieved by the claimed invention consists in the possibility of using the spacecraft for their functional purpose and simultaneously performing actions that ensure the protection of the spacecraft when approaching potentially dangerous objects. The result is achieved by placing a small spacecraft in the onboard equipment and using a small spacecraft to prevent a collision with a potentially dangerous space object.

The advantages of the claimed invention that are important for solving practical problems are:

- no need to change the spatial orientation of the spacecraft and the work program of the onboard equipment used to perform target functional tasks when implementing the method;

- the absence of the formation of additional debris in outer space. From the sequence of actions required to implement the method,

it follows that the claimed method can be used to protect the spacecraft from a potentially dangerous object and repeatedly reproduced in various kinds of similar conditions of use as intended [7-9].

The method is focused on promising implementation in the interests of the original project "Analysis and synthesis of coordination methods for decentralized management of heterogeneous groups of autonomous agents" of the Presidium of the Russian Academy of Sciences program No. 7 (30) "Theory and technologies of multi-level decentralized group management in conflict and cooperation" (modeling and assessment of opportunities methods of coordination); - with the partial support of the Russian Foundation for Basic Research, scientific project No. 19-29-09030 MK (research of new technologies for the selection and recognition of objects based on specialized tools).

Sources of information

1. RF patent RU 2294866. IPC B64G 1/52, B64G 1/56. Method of protecting space objects. Anisimov V.Yu., Borisov E.V., Roldugin V.D., Ponomarev S.A., publ. 10.03.2007.

2. RF patent RU 2374150. IPC B64G 1/52, B64G 1/56. Method of protecting space objects. Novoseltsev D.Y., publ. 11/27/2009.

3. RF patent RU 2141436. IPC B64G 1/00, B64G 1/22. Spacecraft for cleaning space from passive spacecraft and their fragments. Maslennikov A.A., publ. 20.11.1999.

4. RF patent RU 2559392 C1, IPC B64G 1/00, B64G 1/22. Method for removing a non-functioning spacecraft from the geostationary orbit. Sergeev V.E., Burdaev M.N., Golovko A.V. publ. 04/18/2014.

5. RF patent RU 2520714. IPC B64G 3/00. A method for determining the orbit of a spacecraft. Strelnikov SV., Bubnov V.I., Rodionova G.G., publ. 06/27/2014.

6. Patent for utility model No. 133096. Device for capturing space objects. Ivanov V.M., Sokolov N.L., Kozlov V.G., Zakharov P.A., Kartsev Yu.A. publ. 10.10.2013.

7. Rozhnov A.V. Information and analytical support of complex studies of heterogeneous and group unmanned platforms in the conditions of their significant target mismatch / Proceedings of the International Conference "Management of Large-Scale Systems Development" (MLSD'2019, Moscow). - M .: IPU RAN, 2019 (in press).

8. Achievement of a uniform interpretation of the right of self-defense in conformity with the Charter of the United Nations as applied to outer space as a factor in maintaining outer space as a safe and conflict-free environment and promoting the long-term sustainability of outer space activities / Committee on the Peaceful Uses of Outer Space, Fifty-eighth session, Vienna, 10-19 June 2015. - (A / AC.105 / C.1 / 2015 / CRP.22).

9. Rozhnov A.B., Karpov B.B. Development of proposals for the creation of unified technologies with promising energy sources in the space industry / Proceedings of the International conference "Management of the development of large-scale systems" (MLSD'2016, Moscow). - M .: IPU RAN, 2016.Vol. P. S. 150-154.

Claims (1)

A method of changing the trajectory of a dangerous space object by using a small spacecraft and means of radar of outer space, characterized in that in orbital flight, radar of the surrounding space is carried out by onboard means, a space object is detected in the surrounding space near the spacecraft, the parameters of the relative motion of a space object are measured by means of radar , determine the parameters of the orbit of the detected space object according to the parameters of the relative motion of the object and the parameters of the orbit of the spacecraft, identify the trajectory segment and the time interval of the flight, in which a dangerous convergence of the detected space object and the spacecraft is possible, perform orbital maneuvering with a small spacecraft, approach and capture the detected spacecraft apparatus, include the jet propulsion system of a small spacecraft, change the trajectory of the dangerous about the object and provide protection of the spacecraft from collision with a space object.

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