Rendezvous spacecraft collision avoidance device

Abstract: In the present invention four thrusters (10,11,12,13) are provided as a group of thrusters for collision avoidance (9). These thrusters contain a component of translational thrust for collision avoidance injection in their respective outputs, and are capable of simultaneously generating posture control torque around two coordinate axes, which are orthogonal to a thrust axis, in order to maintain the directional stability of the thrust axis during the injection. When abnormality arises in a group of thrusters for ordinary use (4), collision avoidance is executed by replacing all the thrusters for ordinary use (4) by these thrusters for collision avoidance (9).

Description: BACKGROUND OF THE INVENTION FIELD OF THE INVENTION The present invention relates to a collision avoidance device for preventing a rendezvous spacecraft is flying from colliding against the target when an abnormal situation arises during the flight by employing a sensor close to a target in space, a guidance and control device, thrusters, and the like. DESCRIPTION OF THE RELATED ART Fig. 5 shows the constitution of a collision avoidance device and the associated devices of a conventional rendezvous spacecraft. In the drawing, numeral 1 represents a navigation sensor (hereinafter referred to as a sensor) for measuring and computing flight conditions of the rendezvous spacecraft, such as a relative position to atarget, a posture, and acceleration. Numeral 2 represents a guidance and control device. Numeral 3 represents a circuit (hereinafter referred to as a thruster driver for ordinary use) for driving a group of thrusters (hereinafter referred to as a group of thrusters for ordinary use) which generate translation force and triaxial rotation torque in three dime nsional space. Numeral 4 represents a group of thrusters for ordinary use. Numeral 5 represents a collision avoidance device. Numeral 6 represents an abnormality determining circuit. Numeral 7 represents an avoidance operation command circuit. Numeral 16 represents a circuit (hereinafter referred to as a thruster driver for redundant use) for driving a group of spare thrusters (hereinafter referred to as a group of thrusters for redundant use) which have functions equivalent to those of the group of thrusters for ordinary use. Numeral 17 represents the group of thrusters for redundant use whose constitution is same as that of the group of thrusters for ordinary use. In the conventional constitution described above, each of those devices including the collision avoidance device 5 operates in the following manner. During a normal flight, in accordance with instrumentation signals transmitted from the sensor 1, the guidance and control device 2 computes required controlling force of six degrees of freedom in total concerning position control and triaxial posture control in three dimensional space, and then generates a drive command for each thruster. The thruster driver for ordinary use 3 drives the group of thrusters for ordinary use 4 in reply to the aforementioned drive command received. Due to a sequence of the operations, a rendezvous flight to the target is performed. However, if any one of the devices malfunctions, for example, an abnormal operation, such as a cutoff of output from the sensor 1 or an erroneous injection, is carried out, a normal rendezvous flight will not be performed. In a worst case, the chaser spacecraft and the target may collide with each other. In order to avoid such a collision during the flight, in the collision avoidance device 5, the abnormality determining circuit 6 selects a signal which the guidance and control device 2 has designated from among monitor signals concerning the flight conditions, such as a relative position, a posture, and acceleration, outputted by the sensor 1. The abnormality determining circuit 6 then compares the signal or a value computed from the signal with a reference value which has been previously set in the abnormality determining circuit 6, thereby performing a repetitive judgement on the presence of abnormality, such as a mechanical failure, an excess of posture error, and a deviation from a predetermined orbit. When any abnormality is found, the avoidance operation command circuit 7 is notified of the incident. The avoidance operation command circuit 7 then determines how to cope with the situation basing on the contents of the incident notified and a criterion showing a risk of collision, such as an estimated amount of time the spacecraft reaches the target, which is provided by the guidance and control device 2. An outcome of the judgement is transmitted to the guidance and control device 2 as a command to perform the collision avoidance. If the avoidance operation command circuit 7 determines that any failure arises or may arise in a group of thrusters although there is no sufficient time left before the spacecraft reaches the target, the group of thrusters will be switched to a group of thrusters for redundant use, and a command to perform the injection for collision avoidance will be given to the guidance and control device 2. In accordance with the command, the guidance and control device 2 computes the required controlling force of six degrees of freedom to carry out the injection for collision avoidance and maintain an appropriate posture during the period, and inputs a drive command for each thruster to the thruster driver for redundant use 16. Consequently, a group of thrusters for redundant use 17 are activated and the injection for collision avoidance is finally executed. A correlation between a direction of the injection for collision avoidance and an avoidance orbit is shown by an "equation 1." The equation 1 is a so-called Hill equation. This is an equation of motion which shows a relative position of the rendezvous spacecraft to the target by setting the coordinate origin be the target, X-axis be in the direction of the orbit of the target, and Z-axis be in the direction of the center of the earth. (Y-axis, namely, motion in the direction which deviates from the spacecraft's orbital plane is omitted because such motion does not influence collision avoidance.) Fig. 6 illustrate an example of the solution of the equation 1. In Fig. 6, numeral 15 represents the rendezvous spacecraft and numeral 18 represents the target. Coordinates X and Z are in the direction of the orbit of the target and the direction of the center of the earth, respectively, as shown in the equation 1. As shown in the drawing, if thrust is applied in the direction of orbit by the injection for collision avoidance, the rendezvous spacecraft 15 will pass over and go away in the backward direction of the target 18. If the thrust is applied in the reverse direction of the orbit, the rendezvous spacecraft 15 will pass below and go away in the forward direction of the target 18. [Equation 1] d 2 X/dt 2 -2ωdZ/dt=0 d 2 Z/dt 2 +2ωdX/dt-3ω 2 Z=0 X: Relative distance of the rendezvous spacecraft, which is moving in the forward direction, to the target Z: Relative distance of the rendezvous spacecraft, which is moving in the direction of the earth, to the target ω: Orbit angular velocity The aforementioned principle is applied to collision avoidance. In order to execute collision avoidance safely, a relative position to the target and a direction and time period of the injection according to relative velocity shall be appropriately set beforehand in the avoidance operation command circuit 7. In order to avoid such a collision, it is essential to apply thrust as previously set. Therefore, the rendezvous spacecraft is usually equipped with at least a group of thrusters for redundant use 17 by way of precaution against a failure of the group of thrusters for ordinary use 4. An example of the arrangement of the groups of thrusters is shown in Fig. 7. As shown in the drawing, for the purposes of generating three dimensional translation force and triaxial rotation torque, the constitution of a group of thrusters for rendezvous is such that a mass of thrusters are arranged in a complicated manner. Here, a solid line arrow represents one of these thrusters for avoidance, and a dashed line arrow represents one of these thrusters for redundant use. Each of these arrows shows a direction of the injection. There is another method of preventing such a collision. In this method (hereinafter referred to as a reconstitution method), none of these thrusters for redundant use 17 is prepared, but translation force and rotation torque for the collision avoidance are generated by removing a single or a plurality of broken thrusters from the group of thrusters for ordinary use 4 and then combining the remaining thrusters. This is a method which uses software logic capable of processing according to the number of combination of thrusters shown in an "equation 2." More specifically, in the guidance and control device 2 of Fig. 5, the software logic to generate required translation force and rotation torque is prepared in advance with arbitrary thrusters being excluded, and a command to perform posture control and injection for collision avoidance is generated to the thruster driver for ordinary use 3. Here, the posture control and the injection for collision avoidance are performed by a combination of thrusters which excludes the broken thruster(s) specified by the collision avoidance device 5. [Equation 2] The number of combination(C) when excluding m pieces from n pieces of thrusters: nCm= n! m!(n-m)! Example of calculation: if n is 16 and m is 2, 16 C 2 will be 120 ways. In the prior art, there are some problems. More specifically, the injection for collision avoidance and the posture control during the injection are carried out by using the group of thrusters for redundant use 17, which have a function to generate three dimensional translation force and triaxial rotation torque, equivalent to the group of thrusters for ordinary use as described above. Consequently, the prior art has superfluous functions for ensuring safety of the rendezvous spacecraft and the target and involves a complicated constitution and a comparatively high cost. On the other hand, if such injection for collision avoidance and posture control during the injection are carried out, for the purposes of solving the aforementioned problems, by an arbitrary combination of the remaining thrusters which are left after only arbitrary thrusters, namely, broken thrusters were excluded from a group of thrusters for ordinary use, there will be a large number of ways of combining thes e thrusters as shown in the equation 2. Therefore, software for processing the data will become large in scale, and costs required for the verification will increase. SUMMARY OF THE INVENTION The present invention is made in order to solve the problems described above. It is directed to provide a system which has simple constitution of thrusters and is not a burden to software by using a group of thrusters which have a minimum of essential function to avoid the collision of a spacecraft (hereinafter referred to as a group of thrusters for collision avoidance) and are independent of a group of thrusters for ordinary use. The present invention is related to a device for avoiding the collision of a rendezvous spacecraft. The present invention has a plurality of thrusters for collision avoidance separately from thrusters for ordinary use. These thrusters for collision avoidance generate translational thrust and posture control torque around two axes which are orthogonal to a translational thrust axis representing the translational thrust. When collision avoidance is required, a collision avoidance operation is carried out maintaining the generation of thrust in the direction of a translational thrust vector by driving these thrusters for collision avoidance. As described above, only the thrusters for collision avoidance are driven when such a collision is to be avoided. As it is understood that what kind of avoidance operation can be performed, decision making on the avoidance is very easy. Thrusters only for avoidance are provided, whereby a minimum of thruster necessary for collision avoidance is enough. Therefore, constitution of thrusters can be simplified an d control is easily performed. Also, a collision avoidance operation is carried out by rendering at least one of the aforementioned plural thrusters for collision avoidance inactive. Consequently, this leads to an appropriate and easily controllable avoidance operation. Also, the aforementioned plural thrusters for collision avoidance consist of at least four thrusterunits. These four thrusters contain a component of translational thrust in their respective outputs. Also, these four thrusters generate posture control torque around those two axes which are orthogonal to the translational thrust axis, and control relative outputs of the plural thrusters for collision avoid ance, whereby a collision avoidance operation is executed. It is preferable that the plural thrusters for collision avoidance mentioned above include four pieces of thrusters in the following manner: these four thrusters are arranged on two axes which are orthogonal to the translational thrust axis and also meet each other at right angles at the origin, namely, a certain point of the translational thrust axis; these thrusters are paired and each pair faces each other with the origin as the center; and each of these thrusters outputs thrust in a direction which is parallel to the translational thrust axis. It is also preferable that the plural thrusters for collision avoidance mentioned above include at least two thrusterunits for translation and at least two thrusterunits for posture control. The former are capable of outputting a component of translational thrust and at the same time generating posture control torque around the first axis which is orthogonal to the translational thrust axis. The latter independently carry out posture control around the second axis which is orthogonal to both the aforementioned translational thrust axis and the aforementioned first axis. It is also preferable that the aforementioned thrusters for translation are arranged opposite to each other with a point of intersection of the second axis and the translational thrust axis as the center, and output thrust in a direction which is parallel to the translational thrust axis, whereas the aforementioned thrusters for posture control are arranged opposite to each other with a point of intersection of the first axis and the translational thrust axis as the center, and output thrust in a reverse direction on the first axis. It is also preferable that the plural thrusters for collision avoidance mentioned above include at least one thruster for translation which outputs a component of translational thrust and at least four thrusters for posture control which independently carry out posture control around two axes being orthogonal to the translational thrust axis. It is also preferable that the aforementioned single thruster for translation includes a thruster which is provided on the translational thrust axis and outputs translational thrust, whereas the aforementioned four thrusters for posture control include a pair of thrusters and another pair of thrusters: the first pair of thrusters are arranged on one of these two axes, which are orthogonal to each other with the translational thrust axis as the origin, in such a manner that these two thrusters face each other with the origin between and output thrust in an opposite direction, respectively; and the second pair of thrusters are arranged on the other one of these two axes, which are orthogonal to each other, in such a manner that these two thrusters face each other with the origin between and output thrust in an opposite direction, respectively. In such a constitution, it is possible to maintain the generation of thrust in the direction of the thrust axis and carry out an avoidance operation by a minimum of essential thruster. Consequently, it is possible to realize a safe rendezvous spacecraft of a simplified constitution which makes a flight close to a space station or all sorts of facilities on the orbit. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a block diagram showing an embodiment 1 of the present invention. Figs. 2(a) and 2(b) are arrangement drawings of thrusters according to an embodiment 1 of the present invention. Figs. 3(a) and 3(b) are arrangement drawings of thrusters according to an embodiment 2 of the present invention. Figs. 4(a) and 4(b) are arrangement drawings of thrusters according to an embodiment 3 of the present invention. Fig. 5 is a block diagram showing a conventional device. Fig. 6 shows a correlation between a direction of injection for collision avoidance and an avoidance orbit. Fig. 7 shows an example of arrangement of thrusters according to an embodiment of the conventional device. DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiment 1 Fig. 1 shows a constitution according to an embodiment 1 of the present invention. In the drawing, numerals 1 to 4 are the same as those in Fig. 5 which show an embodiment of a conventional device. Numeral 5 is a collision avoidance device of the present invention. Numeral 6 is an abnormality determining circuit. Numeral 7 is an avoidance operation command circuit. Numeral 8 is a thruster driver for avoidance. Numeral 9 is a group of thrusters for avoidance. Figs. 2(a) and 2(b) show an arrangement of a group of those thrusters for avoidance 9 according to the embodiment 1. An illustration of a group of thrusters for ordinary use 4 is omitted. In the drawings, numerals 10, 11, 13, and 15 represent a first thruster, a second thruster, a fourth thruster, and a rendezvous spacecraft, respectively. In the embodiment 1 of the present invention, each of the devices including the collision avoidance device 6 operates in the following manner. During a normal flight, in the same manner as the prior art, a guidance and control device 2 computes required control force of six degrees freedom in total concerning position control in three dimensiona l space and triaxial posture control in accordance with a measurement signal from a sensor 1, and generates a drive command for each thruster. In reply to the drive command received, a thruster driver for ordinary use 3 drives the group of thrusters for ordinary use 4. During such a normal flight, in the collision avoidance device 5, the abnormal ity determining circuit 6 selects a signal designated by the guidance and control device 2 from among monitor signals outputted by the sensor 1 concerning flight conditions, such as a relative position, a posture, and acceleration, and compares the signal or a value calculated from the signal with a reference value previously set in the abnormality determining circuit 6. In such a manner, a repetitive judgement on the presence of abnormality, such as a mechanical failure, an excess of posture error, and a deviation from a predetermined orbit is carried out. When any abnormality is found, the avoidance operation command circuit 7 is notified of the incident. The avoidance operation command circuit 7 then determines how to cope with the situation based on the contents of the incident notified and a criterion showing a risk of collision, such as an estimated amount of time the spacecraft reaches the target, which is provided by the guidance and control device 2. An outcome of the judgement is transmitted to the guidance and control device 2 as a command to perform the collision avoidance. If the avoidance operation command circuit 7 determines that a thruster or thrusters are broken or may be broken when there is no sufficient time left before the spacecraft reaches the target, the guidance and control device 2 will receive a command not to send any drive command to the thruster driver for ordinary use, thereby preventing the thrusters for ordinary use from being used. On the other hand, in accordance with a collision avoidance operation command which the avoidance operation command circuit 7 itself generated, the avoidance operation command circuit 7 generates an injection command corresponding to an equation 3 to the thruster driver for avoidance 8. The equation 3 stands for an expression of instruction which brings about the output of translational thrust by using the first thruster 10 to the fourth thruster 14, the generation of torque around an axis Y by using the second thruster 10 or the third thruster 12, and the generation of torque around an axis Z by using the second thruster 11 or the fourth thruster 13 in the arrangement of thrusters of Fig. 2. Basing on the equation 3, the avoidance operation command circuit 8 drives the group of thrusters for avoidance 9, whereby injection for collision avoidance is carried out with the thrust axis being maintained. [Equation 3] Fx: Translational thrust Ty: Rotation torque around the axis Y Tz: Rotation torque around the axis Z F1 to F4: Thrust of the first to the fourth thrusters r1 to r4: Distance between the center of gravity of a spacecraft and a line of action of the first to the fourth thrusters, respectively a1 to a4: Drive command for the first to the forth thrusters (1=drive; 0=do not drive) However, a definition of the coordinate axes and an arrangement of thrusters shall be based on Fig. 2. The thrusters shall be arranged in such a manner that conditions "r1F1=r3F3 and r2F2=r4F4" are nearly satisfied. Example of calculation 1: In order to generate torque around an axis +Y under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F2+F3+F4, r3F3, 0)" is obtained by a drive command which is "(a1, a2, a3, a4)=(0, 1, 1, 1)." Example of calculation 2: In order to generate torque around an axis +Y and an axis -Z under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F2+F3, r3F3, -r2F2)" is obtained by a drive command which is "(a1, a2, a3, a4)=(0, 1, 1, 0)." In the aforementioned embodiment 1 of the present invention, the injection for collision avoidance and the generation of posture control torque around these two coordinate axes which are orthogonal to the translational thrust axis are carried out by using four pieces of thrusters for avoidance. However, as a matter of course, it is possible to fulfil the same function by using more than four thrusters. Embodiment 2 Constitution of an embodiment 2 of the present invention is same as that of the embodiment 1. Figs. 3(a) and 3(b) show an arrangement of the group of thrusters for avoidance 9 according to the embodiment 2, respectively. In the drawings, numerals 10, 11, 13, and 15 represent the first thruster, the second thruster, the fourth thruster, and the rendezvous spacecraft, respectively. Operations in the embodiment 2 correspond to those of the embodiment 1 except that, when any abnormality arises in a thruster or thrusters, the avoidance operation command circuit 7 generates to the thruster driver for avoidance 8 a command to execute injection for collision avoidance which is corresponding to an equation 4. The equation 4 stands for an expression of instruction which brings about the output of translational thrust by using the first thruster 10 and the third thruster 12, the generation of torque around the axis Y by using the first thruster 10 or the third thruster 12, and the generation of torque around the axis Z by using the second thruster 11 or the fourth thruster 13 in the arrangement of thrusters shown in Figs. 3(a) and 3(b). Basing on the equation 4, the avoidance operation command circuit 8 drives the group of thrusters for avoidance 9, whereby injection for collision avoidance is carried out with the thrust axis being maintained. [Equation 4] Fx: Translational thrust Ty: Rotation torque around the axis Y Tz: Rotation torque around the axis Z F1 to F4: Thrust of the first to the fourth thrusters r1 to r4: Distance between the center of gravity of a spacecraft and a line of action of the first to the fourth thrusters, respectively a1 to a4: Drive command for the first to the forth thrusters (1=drive; 0=do not drive) However, a definition of the coordinate axes and an arrangement of thrusters shall be based on Fig. 3. The thrusters shall be arranged in such a manner that condition "r1F1=r3F3" is nearly satisfied. Example of calculation 1: In order to generate torque around an axis +Y under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F3, r3F3, 0)" is obtained by a drive command which is "(a1, a2, a3, a4)=(0, 0, 1, 0)." Example of calculation 2: In order to generate torque around an axis +Y and an axis -Z under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F3, r3F3, -r4F4)" is obtained by a drive command which is "(a1, a2, a3, a4)=(0, 0, 1, 1)." In the aforementioned embodiment 2 of the present invention, a group of thrusters for avoidance are used in such a manner that the injection for collision avoidance and the generation of posture control torque around a coordinate axis which is orthogonal to the translational thrust axis are carried out by using two pieces of thrusters, whereas the generation of posture control torque around the third axis which is orthogonal to the aforementioned two axes is carried out by using two pieces of independent thrusters. However, as a matter of course, it is possible to fulfil the same function by using more than four pieces of thrusters. Embodiment 3 Constitution of an embodiment 3 of the present invention is the same as that of the embodiment 1. Figs. 4(a) and 4(b) show an arrangement of the group of thrusters for avoidance 9 in the embodiment 3, respectively. In the drawings, numerals 10, 11, 12, 13, 14, and 15 represent the first thruster, the second thruster, the third thruster, the fourth thruster, the fifth thruster, and the rendezvous spacecraft, respectively. Operations in the embodiment 3 are same as those of the embodiment 1 except that when any abnormality arises in a thruster or thrusters, the avoidance operation command circuit 7 generates to the thruster driver for avoidance 8 a command to execute injection for collision avoidance which is corresponding to an equation 5. The equation 5 stands for an expression of instruction which brings about the output of translational thrust by using the fifth thruster 14, the generation of torque around the axis Y by using the first thruster 10 or the third thruster 12, and the generation of torque around the axis Z by using the second thruster 11 or the fourth thruster 13 in the arrangement of thrusters shown in Figs. 4(a) and 4(b). Based on the equation 5, the avoidance operation command circuit 8 drives the group of thrusters for avoidance 9, whereby injection for collision avoidance is carried out with the thrust axis being maintained. [Equation 5] Fx: Translational thrust Ty: Rotation torque around the axis Y Tz: Rotation torque around the axis Z F1 to F5: Thrust of the first to the fifth thrusters r1 to r4: Distance between the center of gravity of a spacecraft and a line of action of the first to the fourth thrusters, respectively a1 to a5: Drive command for the first to the fifth thrusters (1=drive; 0=do not drive) However, a definition of the coordinate axes and an arrangement of thrusters shall be based on Fig. 4. Example of calculation 1: In order to generate torque around an axis +Y under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F5, r1F1, 0)" is obtained by a drive command which is "(a1, a2, a3, a4, a5)=(1, 0, 0, 0, 1)." Example of calculation 2: In order to generate torque around an axis +Y and an axis -Z under the condition that translational thrust is on, "(Fx, Ty, Tz)=(F5, r1F1, -r4F4)" is obtained by a drive command which is "(a1, a2, a3, a4, a5)=(1, 0, 0, 1, 1)." In the aforementioned embodiment 3 of the present invention, a group of thrusters for avoidance are used in such a manner that the injection for collision avoidance is carried out by using a piece of thruster, whereas the generation of posture control torque around a coordinate axis which is orthogonal to the translational thrust axis is carried out by using four pieces of independent thrusters. However, as a matter of course, it is possible to fulfil the same function by using more than five thrusters. In the embodiments 1 to 3, a group of thrusters for avoidance are used when abnormality arises in a group of thrusters for ordinary use. However, as a matter of course, in order to ensure the safety of a flight close to a target in a more scrupulous manner, it is also preferable in the present invention to use the following systems: a system in which when abnormality arises in all of the plural groups of thrusters equipped which are equivalent to the thrusters for ordinary use, a group of thrusters for avoidance are used as substitutes; and a system in which a group of thrusters for ordinary use and plural groups of thrusters for avoidance are equipped, and even when abnormality arises in a group of thrusters for avoidance which are used as substitutes for a group of thrusters for ordinary use, another group of thrusters for avoidance is used as further substitutes.

Claims: A collision avoidance device for rendezvous spacecraft having a plurality of thrusters for collision avoidance provided separately from thrusters for ordinary use, said thrusters for collision avoidance generating translational thrust and posture control torque around two axes which are orthogonal to a translational thrust axis representing the translational thrust, wherein when collision avoidance is required, a collision avoidance operation is carried out maintaining generation of thrust in a direction of a translational thrust vector by driving said thrusters for collision avoidance. The collision avoidance device for rendezvous spacecraft according to claim 1, wherein a collision avoidance operation is carried out by rendering at least one of said thrusters for collision avoidance inactive. The collision avoidance device for rendezvous spacecraft according to claim 1 or 2, wherein said thrusters for collision avoidance comprise at least four thrusters, each of which contains a component of translational thrust in its output, generates posture control torque around two axes being orthogonal to a translational thrust axis, and controls relative outputs of said thrusters for collision avoidance, whereby a collision avoidance operation is performed. The collision avoidance device for rendezvous spacecraft according to claim 3, wherein said thrusters for collision avoidance include four thrusters in such a manner that these four thrusters are arranged on two axes which are orthogonal to a translational thrust axis and also meet each other at right angles at a point of the translational thrust axis with the point as an origin; these four thrusters are paired and each pair faces each other with the origin as a center; and each of these four thrusters outputs thrust in a direction which is parallel to the translational thrust axis. The collision avoidance device for rendezvous spacecraft according to claim 1 or 2, wherein said thrusters for collision avoidance includes: two or more thrusters for translation which are capable of outputting a component of translational thrust and at the same time generating posture control torque around a first axis being orthogonal to a translational thrust axis; and two or more thrusters for posture control which independently carry out posture control around a second axis being orthogonal to both of said translational thrust axis and said first axis. The collision avoidance device for rendezvous spacecrafts according to claim 5, wherein said thrusters for translation are arranged opposite to each other with a point of intersection of the second axis and the translational thrust axis as a center, and output thrust in a direction which is parallel to the translational thrust axis, whereas said thrusters for posture control are arranged opposite to each other with a point of intersection of the first axis and the translational thrust axis as a center, and output thrust in a reverse direction on the first axis. The collision avoidance device for rendezvous spacecraft according to claim 1 or 2, wherein said thrusters for collision avoidance include at least one thruster for translation which outputs a component of translational thrust and at least four thrusters for posture control which independently carry out posture control around two axes being orthogonal to a translational thrust axis. The collision avoidance device for rendezvous spacecraft according to claim 7, said thruster for translation includes a single thruster which is provided on a translational thrust axis and outputs thrust, whereas said thrusters for posture control include: a pair of thrusters which are arranged on one of two axes being orthogonal to each other with the translational thrust axis as an origin in such a manner that these two thrusters face each other with the origin between, and output thrust in an opposite direction; and another pair of thrusters which are arranged on the other one of these two axes being orthogonal to each other in such a manner that these two thrusters face each other with the origin between, and output thrust in an opposite direction.

Inventors: NAKAMURA TAICHI, NAKAMURA, TAICHI
Applicants: MITSUBISHI ELECTRIC CORP, MITSUBISHI DENKI KABUSHIKI KAISHA
Application year: 1997
Main classification: B64G1
IPC codes: B64G1