UA72416A - Method and device for avoiding the collision of a spacecraft with an extraterrestrial object - Google Patents

Abstract

A method for avoiding the collision of a spacecraft with a dangerous extraterrestrial object is based on the increase of the distance between these bodies to the safe value. Prior to the admission to the area of uncertainty of location of the extraterrestrial object the spacecraft is divided into two parts, they are connected between them by flexible links, for example, cables, then they are separated in opposite sides from each other and the cables are released for the length with possibility of their passage beyond the limits of dangerous area. Then the length of cables is reduced in order to connect the parts into one final structure, and dangerous area is defined by association of areas of uncertainty of location of the object and spacecraft, for example, as geometric sum of mean-square deviations of characteristic dimensions of these areas. The device for implementation of the method includes flexible links, for example, cables connected with separable parts of the spacecraft, and the device for removal of links beyond the limits of the spacecraft. The spacecraft is made of two parts connected between them by flexible links, for example, cables. Between the parts of the spacecraft the pushers are mounted, for example, springs, at least on one part the electric winch is mounted, on which the cables are reeled, the length of these cables is greater than the double value of maximal characteristic dimension of the area of uncertainty of location of the extraterrestrial object.

Description

Description of the invention

The invention relates to space technology, specifically to space vehicles (SC) moving in 2 orbits, where there is a significant probability of collision with another space object (SC).

As a result of the growing space activities of various countries, the probability of a collision between space vehicles and

KA, which can lead to its failure to fulfill its functional purpose and, as a result, to significant material losses.

At this time, there are three methods of protecting a spacecraft from a collision with any space object (CO): interception 70 of it by on-board means |1), shielding and an evasive maneuver (2). The disadvantages of the first two methods are as follows: - anti-missile interception is effective only for large-sized spacecraft, because to carry out such an operation, which is accompanied by large overloads, it is necessary to interrupt the operation of the target equipment, which reduces the effectiveness of the mission, - shielding is carried out only for particles with linear dimensions up to 1 cm, for larger sizes, the mass of 12 screens increases unacceptably and leads to a decrease in the efficiency of space exploitation.

The closest analogue is the method of protecting a spacecraft from a collision with a CO by dodging |2), that is, changing the target trajectory of movement to one that ensures an increase in the distance between them to a safe value, and returning to the original trajectory after the danger is over. This change is performed using the propulsion system (RU) of the spacecraft. Despite the universality and effectiveness of the method, the following disadvantages are inherent: - reduction of the time of the active existence of the spacecraft due to the use of the working body (RT) of the RU to perform evasive maneuvers instead of targeted maneuvers; - the impossibility of conducting an evasive maneuver after the loss of all RT and, as a result, an increase in the risk of a collision; - reduction of the target effectiveness of the spacecraft mission due to the need to interrupt the work of the target equipment 22 during the evasion maneuvers and return to the original orbit due to the equipment not being on the "target trajectory."

Known self-propelled missiles equipped with RU (1), screens |Z| and means of interception |1), the disadvantages of using which coincide with those given for the methods they implement.

The closest analogue is the so-called cable systems - several space vehicles connected by cables |41. ee, 30 their disadvantage is that the design of the spacecraft does not have autonomous means to avoid a collision and does not provide "- the technical possibility of returning to the original (before the separation of the spacecraft) design.

The invention is based on the task of developing a method of evading a spacecraft from a collision with a dangerous CO, which excludes the use of RU and the consumption of RT, i.e. ensures evasion regardless of the presence of RT reserves and the effect of RU, Ga, and also ensures the finding of the target equipment in the target orbit during the maneuver, which excludes interruptions in 39 t work. in

The task is solved by the fact that in the method of avoiding a collision with a dangerous space object based on increasing the distance between these bodies to a safe value, before entering the zone of uncertainty of the space object's location, the spacecraft is divided into two parts, with connect them with each other with non-rigid ties, for example, cables, separate them in opposite directions from each other, and at the same time release the cables to a length with the possibility of passing parts outside the dangerous zone, after passing through the dangerous zone, the length of the cables is reduced to the connection parts into a single original structure, and the dangerous zone is determined by combining the zones of uncertainty of the location of the object and the device, for example, as a geometric sum of the mean square deviations of the characteristic sizes of these zones. To reduce, they are divided into parts that are close in mass (since the distances of the parts from the center of mass on the initial trajectory are inversely proportional to their weights). In order to exclude damage to the KO cables, in the method the cables are brought out of the dangerous zone 7, for example using levers. To reduce the required length of the cables, the parts of the spacecraft are separated in the plane normal to the vector of the relative velocity of the spacecraft and the dangerous space object. To ensure that the spacecraft remains at the given flight height, parts of the space vehicle are deployed along the line of intersection of the plane of the local horizon and the plane normal to the relative velocity vector - 20 of the space vehicle and the dangerous space object. To ensure the minimum required length of the cables, in the case of a non-spherical shape of the dangerous zone, parts of the space vehicle are extended along the direction of the minimum diameter of the projection of this zone on the plane normal to the vector of the relative speed of the space vehicle and the dangerous space object.

The task is solved by the fact that in the device for implementing a method of evasion, which includes non-rigid connections, for example, cables connected to the separable parts of the spacecraft, and a device for outputting in. connections outside the device, the spacecraft is made of two parts connected by non-rigid connections, for example, cables, pushers, such as springs, are installed between the parts of the spacecraft, at least one part has an electric winch on which the cables are wound, and their length is more than twice the value of the maximum characteristic size of the zone of uncertainty of the location of the space object. In order to bring the cables out of the dangerous zone, they are placed in the device on levers, for example, retractable rods, and the lengths of each rod are made larger than the maximum characteristic diameter of the zone of uncertainty of the location of the space object. In order to reduce the required power of the winch, non-rigid connections are made with elastic properties.

The essence of the invention is demonstrated in the drawings. because Fig. 1 shows the scheme of implementation of the method.

Figure 2 shows a diagram of one limit implementation of the method.

Figure 3 shows a diagram of another limit implementation of the method.

Figure 4 shows the design of the device in a static state.

Figure 5 shows the design of the device in the active state.

Fig. 6 shows a variant of the implementation of the method in case of a head-on collision.

The claimed invention is implemented in the following way.

Spacecraft 1 (in Fig. 1) moves along orbit 2, which is crossed by Spacecraft 3 with its orbit 4 at location 5. The relative distances are small, so the orbits are close to the straight lines given by the velocity vectors of Spacecraft 2 tako ia - The crossing conditions are the parallelism of the movement of the line of relative position KA and KO 6 and equations

Mroov(2)-Me (1) where 2 is the angle between the velocity vectors KA y and KO ia .

The location of the CO 3 is determined with an error, therefore, only its nominal trajectory 4 and the location uncertainty zone (LOU) 7 are known on the spacecraft, which can be approximated by a spatial parallelepiped 8 described around 7. The KA 1 can intersect with the KO 3 at any location of the LO 8. Since, according to the desired technical result 2, it is necessary to bring the apparatus beyond the intersection of the zone with the plane of the orbit of the spacecraft (in order not to complicate the drawing of Fig. 1 ZNM 8 depicts this intersection), the spacecraft 1 is divided into two parts 9 and 10 and connected by non-rigid ties, for example cables 11. At the same time, the center of mass (CM) 12 of the space vehicle in the undivided and in the separated state remains unchanged (as the center of mass of the system of its parts) and its movement as well. At the moment of the crossing of orbits 2 and 4, parts of the spacecraft 9, 10 have already been removed from the ZNM. Only cables 11 can be damaged, but the probability of such an event is much less than a collision with a spacecraft (based on the ratio of the sizes of the spacecraft, spacecraft and cables and the volume of zone 8). After passing through the dangerous zone (we consider the ZNM in any position that contains point 5), the parts of the spacecraft are connected by reducing the length of the undamaged cables into a single original structure 13.

According to equation (1), the speed of movement of the left 14 (according to the location in Fig. 2, C) and right 15 boundaries of ZYM 8 coincides with the speed of CM 12 and parts of the spacecraft 9, 10. At the nominal moment of time, orbits 2 and 4 will cross, which zo corresponds to point 5, CM 12 can be at any random point relative to the boundaries of ZNM 8 inside it.

Fig. 2 illustrates the right limit position of CM 12, and Fig. 3 - the left. The actual location of the CM is unknown. Therefore, in order to exclude damage to parts of the spacecraft, they must be removed from the ZNM: for Fig. 2, the left part 9 is slightly beyond the left border of zone 14, and the right part 10 (in Fig. 3) is slightly beyond the right 15. Such an arrangement should be at any location of CM 12 inside ZNM 8, therefore the length of the cables should be greater than twice the value of

Зз5 of the maximum characteristic size of 4 ZNM KO, as can be seen from the drawings in Fig. 1...3. The dimensions of the ZNM are determined by the measurement characteristics of the observation equipment, which is based on the spacecraft or on the Earth, and will be the same for all possible COs. Since the relative location of the parts of the spacecraft from its CM when they are diluted by the internal impulse of force is inversely proportional to their masses, the more massive part must be moved to a distance greater than 4. Therefore, to reduce the required lengths and, as a result, the mass of the cable, the parts of the spacecraft are made "close in mass . In order to exclude further damage to the cables, they must be removed from the ZNM with the help of retractable rods, as described below for the device that implements the method.

Fig. 4 shows the CA 1, made of two parts 9, 10, connected to each other by cables 11. Pushers, for example, spring 16, are installed between the parts of the CA, an electric winch 17 is installed on part 10, on the shaft 18 of which cables 11 are wound, and their lengths are more than double the maximum characteristic size of ZNM KO 4. On the outer surface of CA 1 there are retractable rods 19 in the folded state. The cables are placed on a device for their removal outside the device, for example, a system of blocks 20.

After detecting the possibility of a collision of CA 1 and KO 3: o - the apparatus 1 is turned in advance by the longitudinal axis 21 of the springs 16 in an orientation perpendicular to the plane of movement of the CA, x, -oUu 70 - the electric winch 17 is started, the lengths of the cables increase, - the rods are extended and the cables are released to a length sufficient for the beginning of separation, 4" - the spring pushes parts 9 and 10 apart - under the action of the impulse of the forces from the spring, the parts diverge to the maximum distance, given by the length of the cables, as shown in Fig. 5, where KA 1 is depicted in a separated state during the passage of KO Z between the cables, by 2o the length of each rod must be greater than the maximum characteristic size of the ZNM KO (for the same reasons as for the length of the cables), - KO Z passes between the cables 11, - after the danger disappears, the length of the cables is reduced with the electric winch 17 to the connection of the corresponding surfaces of the parts of the spacecraft, the rods 19 are pulled to the initial position, 60 - connect the parts of the spacecraft into the original structure 13 (Fig. 1), - further act according to the flight program.

Thus, in times of danger, the safety system of the KA 1 is quickly deployed, and without causing any damage

RU and consumption of RT mass. The power supply system is the source of energy. Electric energy can be "mined" in orbit, in contrast to RT DU, which is renewed only by launches of KA - tankers. Parts of the spacecraft 1 remain in the 65th orbit throughout the flight, except for periods of deployment and retraction of the cables and rods, and the spacecraft's equipment will continue to perform its mission. The probability of a spacecraft collision is small, the necessary maneuvers will be rare, and the supply of cables will be enough for the entire time of the active existence of the apparatus. Fig. b6 shows the movement (from left to right) of KA 1 on trajectory 2 during a head-on collision with KO Z (its trajectory 4 actually coincides with 2): KA 1 is turned in the horizon plane by 90", diverges along the normal to the plane of its orbit, passes ZNM 8 (KO Z itself and its movement are conditionally not shown), connect the parts to the original structure 1 and return to the original orientation. The example of a head-on collision corresponds to the case of an extreme orientation of the relative speed of the "KA-KO" system for the safety of the spacecraft.

Sources of information 1. Remeza A.Y., Hekai V.M. Evaluation of the possibility of using small transport spacecraft 7/0 for launching space objects from geostationary orbit, including large-sized elements of the space rocket // Cosmonautics and rocket dynamics. - 2000. - Mo18. - P.187-192. 2. Perspective! studies of the problems of man-made pollution of near-Earth outer space /

V.V. Alaverdov, Yu.E. Levitskyi, V.I. Lukyashchenko and others / Cosmonautics and rocket dynamics. - 2000. - Mo18. - P.7-11. 3. Protection of the service module of the International Space Station from meteor and man-made particles /

A.V. Horbenko, L.V. Zinchenko, N.G. Panychkin / Cosmonautics and rocket dynamics. - 2000. - Mo18. - P.158-165. 4. Dynamics of small space cable systems stabilized by rotation / A.P. Alpatov, V.V.

Beletsky, V.I. Dranovsky et al. / Technical mechanics. - 2001. - Mo1. - P.85-100. b-where to t

ICC

/ z Z s 9 2 cho ia I | i | 5 she is still PE l. / -- west m. in " is

Fegg1 and pt- tru 12 E («e) «-

Ha oh I - y

Fig 2 with her 5 tv m 2-1 2 is, pk g srieg Z « 1 u - z w SHI «shchi V SHI and tv ; :» /

ON I nenya o - in y. !

A / t 1-3) g". re to e shchi fa - 50 same t / (42; AK

Y KI) vn. Shi B

Reve sreg 5 60 b5 lo 7 4 8 / и - - g

Me M, 2

Feg. is

Claims (9)

The formula of the invention 1. The method of evading a space vehicle from a collision with a dangerous space object, which is based on increasing the distance between these bodies to a safe value, which is distinguished by the fact that before entering the zone of uncertainty of the location of the space object, the space vehicle is divided into two parts, with they are connected to each other by non-rigid ties, for example, cables, they are brought to opposite sides from each other and at the same time, the cables are released to a length with the possibility of passing parts outside the dangerous zone, after which the lengths of the cables are reduced to connect the parts into a single original structure , and the dangerous zone is determined by combining the uncertainty zones of the location of the object and the device, for example, as the geometric sum of the mean square deviations of the characteristic sizes of these zones. 2. The method according to claim 1, which differs in that the spacecraft is divided into parts that are similar in mass. C. The method according to claims 1, 2, which differs in that the ropes are brought out of the dangerous zone, for example, with the help of levers. 4. The method according to claims 1-3, which differs in that the parts of the spacecraft are separated in a plane normal to the vector of the relative speed of the spacecraft and the dangerous space object. 5. The method according to claim 4, which differs in that parts of the space vehicle are separated along the line of intersection of the plane of the local horizon and the plane, the normal vector of the relative speed of the space vehicle and the direction of the dangerous space object. 6. The method according to claim 4, which differs in that the parts of the space vehicle are separated along the direction "- the minimum diameter of the projection of the dangerous zone on the plane normal to the vector of the relative speed of the space vehicle and the dangerous space object. 7. A device for implementing the method according to claim 1, which includes non-rigid connections, for example, cables connected to separable parts of the spacecraft, and a device for outputting connections outside the device, which is characterized by the fact that the spacecraft is made of two parts connected to each other by non-rigid connections, for example cables, pushers, for example springs, are installed between the parts of the spacecraft, at least one part has an electric winch on which the cables are wound, and their lengths are more than twice the maximum characteristic size of the zone uncertainty of the location of « 20 space object. from the village 8. The device according to claim 7, which differs in that the cables are placed on levers, for example, retractable rods, and the lengths of each rod are made larger than the maximum characteristic diameter of the uncertainty zone и. . and the location of the space object. 9. The device according to claim 7, which is characterized by the fact that the non-rigid connections are made with elastic properties. triigya i " : " " : : pov -I Official Bulletin "Industrial Property". Book 1 "Inventions, useful models, topographies of integrated microcircuits", 2005, M 2, 15.02.2005. State Department of Intellectual Property of the Ministry of Education and Science of Ukraine . sh" - 70 4) 60 b5