System for transporting and releasing satellites

Abstract

The invention relates to a transport and release system (100a) for a stack (50) of satellites (52a-c) and comprising a base (102); a set of connecting rods (108), each of which is mounted on the base (102) so as to be able to rotate about a first axis of rotation (10); for each connecting rod (108), an arm (104) with a proximal end (104a) fixed to a distal end (108b) of the connecting rod (108) so as to be able to rotate freely; for each arm (104), securing means (106) securing a distal end (104b) of said arm (104) to the stack (50); an actuating system (110) connected to a proximal end (108a) of each connecting rod (108) and moving each proximal end (108a); and, for each connection between a distal end (108b) of a connecting rod (108) and a proximal end (104a) of an arm (104), a drive system (112) arranged to rotate the arm (104).

Description

[0001] SATELLITE TRANSPORT AND DELIVERY SYSTEM

[0002] TECHNICAL FIELD

[0003] The present invention relates to a transport and release system for a stack of satellites, as well as to a space vehicle comprising such a transport and release system.

[0004] STATE OF THE PRIOR ART

[0005] As part of the development of satellite networks around the Earth, many satellites are simultaneously loaded onto a spacecraft such as a rocket. These satellites are usually stacked on top of each other and held in position by various attachment means arranged in the spacecraft.

[0006] When the spacecraft arrives at the satellite release location, the attachment means are released and each satellite then separates from the spacecraft to reach its allocated position.

[0007] Various attachment methods have already been implemented, but none are entirely satisfactory. In particular, it is generally necessary to use large actuators to ensure that the satellites are properly held during take-off and transport, which is a disadvantage in terms of on-board weight.

[0008] STATEMENT OF THE INVENTION

[0009] An object of the present invention is to provide a transport and release system for a stack of satellites which comprises fixing means of reduced dimensions for holding and releasing the stack of satellites.

[0010] For this purpose, a transport and release system is proposed comprising:

[0011] - a stack of satellites extending along a stacking axis between a first satellite and a last satellite,

[0012] - a base arranged to support the first satellite of said stack,

[0013] - at least one set of at least one connecting rod where each connecting rod is mounted to rotate on the base around a first axis of rotation and has a proximal end and a distal end, - for each connecting rod, an arm having a proximal end and a distal end, where the proximal end of said arm is fixed free to rotate at the distal end of said connecting rod around a second axis of rotation,

[0014] - for each arm, securing means intended to secure the distal end of said arm with the last satellite of said stack,

[0015] - for each assembly, an actuation system linked to the proximal end of the or each connecting rod of said assembly and arranged to move said or each of said proximal ends, and

[0016] - for each connection between a distal end of a connecting rod and a proximal end of an arm, a drive system arranged to move the arm in rotation around the second axis of rotation.

[0017] Advantageously, the securing means take the form of a stud secured to the distal end of the associated arm or the last satellite and respectively a housing made in the last satellite or in the distal end of the associated arm.

[0018] Advantageously, the stud is integral with the arm and is mounted to rotate freely on said arm around a third axis of rotation parallel to the second axis of rotation.

[0019] Advantageously, the actuation system comprises a slider linked in an articulated manner to the proximal end of each connecting rod of the associated assembly and mounted to move in translation on the base, and an actuator arranged to move the slider between a first position and a second position.

[0020] Advantageously, the actuator comprises a lock and a spring element arranged to push the slide towards its second position and where the lock successively takes a holding position in which it holds the slide in its first position then a free position in which it does not hold the slide.

[0021] Advantageously, the drive system takes the form of a torsion spring fixed between the associated arm and connecting rod.

[0022] Advantageously, there is a single set of connecting rods and a single actuation system.

[0023] Advantageously, the transport and release system comprises between the base and the first satellite, at least one thrust system arranged to push the first satellite away from the base.

[0024] Advantageously, the transport and release system comprises, for each thrust system, a delay device which controls the triggering of the thrust system when the arms have reached, around the second axis of rotation, a predefined angle of rotation. The invention also proposes a space vehicle comprising a structural part and a transport and release system according to one of the preceding variants where the base is integral with the structural part.

[0025] BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above-mentioned and other features of the invention will become more clearly apparent from the following description of an exemplary embodiment, said description being given in relation to the accompanying drawings, among which:

[0027] Fig. 1 is a schematic view of a transport and release system according to a first embodiment of the invention in a transport position,

[0028] Fig. 2 is a schematic view of a transport and release system according to a second embodiment of the invention in a transport position,

[0029] Fig. 3 is a schematic view of the transport and release system of Fig. 2 in a release position,

[0030] Fig. 4 is a schematic view of the transport and release system of Fig. 2 in a release position,

[0031] Fig. 5 is a detail view of the transport and release system of Fig. 2, and

[0032] Fig. 6 is a sectional view of securing means according to a particular embodiment of the invention.

[0033] DETAILED PRESENTATION OF EMBODIMENT METHODS

[0034] Fig. 1 shows a transport and release system 100a according to a first embodiment of the invention and Figs. 2 to 4 show a transport and release system 100b according to a second embodiment of the invention. The elements common to both embodiments bear the same references.

[0035] As explained below, the principle and operation of both embodiments are identical and only the number of actuation systems differs.

[0036] The transport and release system 100a-b is intended for the transport and release of a stack 50 of satellites 52a-c. The stack 50 extends along a stacking axis Z between a first satellite 52a which forms the base of the stack 50 and a last satellite 52b which forms the top of the stack 50. Between the first satellite 52a and the last satellite 52b, the stack 50 comprises a plurality of intermediate satellites 52c. Each satellite 52a-c here takes the form of a pancake but other forms are possible. The transport and release system 100a-b is part of a larger assembly which includes a space vehicle which can be a rocket, a space shuttle, etc. The space vehicle is represented here by its structural part 150 to which the transport and release system 100a-b is attached.

[0037] The transport and release system 100a-b thus comprises the battery 50 and a base 102 which is integral with the structural part 150 of the space vehicle.

[0038] The stack 50 is arranged on the base 102 so that the first satellite 52a is supported by said base 102. The base 102 here takes the form of a plate generally perpendicular to the stacking axis Z and the base 102 has a first face oriented towards the first satellite 52a and a second face oriented opposite, here towards the structural part 150.

[0039] The transport and release system 100a-b also comprises at least one set of at least one connecting rod 108 where each connecting rod 108 is mounted to move in rotation on the base 102 around a first axis of rotation 10 which is here perpendicular to the stacking axis Z.

[0040] In the first embodiment of the invention, there are two sets here, namely one to the left of the stacking axis Z and one to the right of the stacking axis Z. In the second embodiment, there is only one set.

[0041] Each connecting rod 108 has a proximal end 108a and a distal end 108b which are arranged on either side of the first axis of rotation 10.

[0042] For each connecting rod 108, the transport and release system 100a-b comprises an arm 104 which has a proximal end 104a and a distal end 104b, where the proximal end 104a of each arm 104 is fixed in free rotation to the distal end 108b of the associated connecting rod 108 around a second axis of rotation 20 which is parallel to the first axis of rotation 10.

[0043] The transport and release system 100a-b also comprises, for each arm 104, securing means 106 which are intended to removably secure the distal end 104b of the arm 104 with the last satellite 52b of the stack 50.

[0044] The connection by the connection means 106 between the distal end 104b of the arm 104 and the last satellite 52b is removable, that is to say that the release of the connection between the distal end 104b and the last satellite 52b is carried out without destruction of either one.

[0045] The securing means 106 are thus movable between a securing position in which the distal end 104b of the arm 104 is secured to the last satellite 52b of the stack 50 and a detachment position in which the distal end 104b of the arm 104 is no longer secured to the last satellite 52b of the stack 50. To ensure good holding of the stack 50 during takeoff and travel of the space vehicle, the number of arms 104 is increased. Preferably, there are four arms 104 distributed equiangularly around the stacking axis Z. These arms 104 can thus be distributed into several sets or into a single set.

[0046] Fig. 1 and Fig. 2 show the transport and release system 100a-b in a transport position, where the securing means 106 are in the securing position to secure the arm 104 with the last satellite 52b of the stack 50 to clamp the satellites 52a-c against the base 102.

[0047] Fig. 3 shows the transport and release system 100b in a release position, where the securing means 100 are in the disengagement position to release the arm 104 relative to the last satellite 52b of the stack 50 and Fig. 4 shows the transport and release system 100b in a release position, where the arms 104 are moved away from the stack 50 to clear the passage for the satellites 52a-c. Even if the transport and release system 100a according to the first embodiment is not shown in the release and release positions, the operating principle is identical.

[0048] In the transport position, each arm 104 is tightened against the stack 50 and extends generally parallel to the stacking axis Z.

[0049] In the embodiments of the invention shown in Figs. 1 to 4, the connecting rods 108 are arranged under the base 102 and radially relative to the stacking axis Z. The first axis of rotation 10 and the second axis of rotation 20 are here oriented orthoradially relative to the stacking axis Z.

[0050] For each set of connecting rods 108, the transport and release system 100a-b comprises an actuation system 110. In the first embodiment, there are thus two actuation systems 110 and in the second embodiment, there is a single actuation system 110 which limits the on-board weight.

[0051] The actuation system 110 is linked to the proximal end 108a of each connecting rod 108 of the associated assembly and is arranged so that when itself is actuated, the actuation system 110 moves the proximal end 108a of each connecting rod 108 of the assembly in order to pivot each connecting rod 108 about the first axis of rotation 10 from a first position to a second position of the connecting rod 108.

[0052] For each connection between a distal end 108b of a connecting rod 108 and a proximal end 104a of an arm 104, the transport and release system 100a-b comprises a drive system 112 which is arranged to move the arm 104 in rotation about the second axis of rotation 20 and thus to move the distal end 104b of the arm 104 away from the stack 50. The arrow 30 of Fig. 4 shows the direction of rotation applied by the drive system 112 to the arm 104.

[0053] Thus, each drive system 112 moves the associated arm 104 away from the stack 50 by moving it outwards, that is to say by moving the distal end 104b of the arm 104 away from the stack 50 and therefore away from the distal ends 104b of the other arms 104.

[0054] In the embodiments described here, when a connecting rod 108 is in its first position, the associated arm 104 is in a locking position corresponding to the position of securing the securing means 106 and to the transport position (Figs. 1 and 2).

[0055] In the same way, when a connecting rod 108 is in its second position, the associated arm 104 is in an unlocking position corresponding to the position of detachment of the securing means 106 and to the release position (Fig. 3).

[0056] Thus, in the transport position, the satellites 52a-c are held by the securing means 106 against the base 102. When the satellites 52a-c must be released, the actuation system 110 is controlled by a control unit 50 of said transport and release system 100a-b or of the space vehicle. The control unit 50 thus controls the actuation of the actuation system 110 which causes the movement of the proximal end 108a of each associated connecting rod 108. The connecting rod 108 then pivots about the first axis of rotation 10 from its first position corresponding to the transport position to its second position corresponding to the release position, which moves the arm 104 linked to the connecting rod 108, generally parallel to the stacking axis Z (arrow 40 in Figs. 1 and 2).The arm 104 then moves from its locking position to its unlocking position by moving the securing means 106 from the securing position to the unsecuring position to release the arm 104 (release position Fig. 3) and when this release occurs, the drive system 112 moves the arm 104 in rotation (release position Fig. 4) and the satellites 52a-c can then be released.

[0057] The transport and release system 100a-b proposed here is therefore relatively simple in construction and the use of the connecting rods 108 makes it possible to maneuver the arms 104 with a relatively small actuation system 110. In addition, the sequential translational and then rotational movements of the arms 104 make it possible to release the satellites 52a-c before releasing them.

[0058] In the embodiment of the invention presented in Figs. 1 to 4, the securing means 106 take the form of a stud 106a secured to the distal end 104b of the associated arm 104 and a housing 106b made in the last satellite 52b. The stud 106a has a base secured to the distal end 104b of the arm 104 and a top which is oriented towards the base 102, that is to say downwards here. The housing 106b has its opening opposite the base 102, that is to say upwards here, so that in the transport position, the stud 106a is housed in the housing 106b.

[0059] The axis of the pad 106a and the housing 106b is here parallel to the stacking axis Z.

[0060] The stud 106a and the housing 106b are shaped so that the stud 106a can freely exit the housing 106b when the connecting rod 108 tilts about the first axis of rotation 10 from its first position to its second position and the arm 104 moves from its locking position to its unlocking position.

[0061] In the secured position, the stud 106a is in the housing 106b and in the unsecured position, the stud 106a is outside the housing 106b.

[0062] The arm 104 is thus movable successively from the locking position (Figs. 1 and 2) in which the stud 106a is in the housing 106b (locking position), to the unlocking position (Fig. 3) in which the stud 106a is outside the housing 106b (unlocking position), and finally to a separated position corresponding to the release position (Fig. 4) and in which the arm 104 is separated by the drive system 112.

[0063] Of course, it is possible to reverse the stud 106a and the housing 106b. The stud 106a is then secured to the last satellite 52c and the housing 106b is made in the distal end 104b of the arm 104. The stud 106a is then oriented opposite the base 102, that is to say upwards here and the housing 106b has its opening towards the base 102, that is to say downwards here.

[0064] The securing means 106 can also take other forms, such as locks, for example electric locks controlled in closing and opening by the control unit 50.

[0065] Fig. 6 shows a particular embodiment of the securing means 106 where the stud 106a is secured to the arm 104 and mounted to rotate freely on said arm 104 around a third axis of rotation 60 parallel to the second axis of rotation 20.

[0066] Thus, when the arm 104 begins its rotation (arrow 30) about the second axis of rotation 20, the stud 106a pivots about the third axis of rotation 60 to disengage from the housing 106b. Such an arrangement ensures that even if the stud 106a is not sufficiently disengaged from the housing 106b, the arm 104 can rotate about the second axis of rotation 20.

[0067] The actuation system 110 can also take different forms.

[0068] For example, according to an embodiment not shown, the or each actuation system 110 takes the form of a jack, for example electric, controlled by the control unit 50 and mounted articulated between the base 102 and the proximal end 108a of each connecting rod 108 of the associated assembly. According to the embodiment shown here, the actuation system 110 comprises a slider 110a which is connected in an articulated manner to the proximal end 108a of each connecting rod 108 of the associated assembly. The slider 110a is mounted movable in translation on the base 102, for example parallel to the stacking axis Z, between a first position corresponding to the transport position and a second position corresponding to the release position. The translational movement of the slider 110a from its first position to its second position causes the rotational movement of each associated connecting rod 108 from its first position to its second position.

[0069] The actuation system 110 also comprises an actuator 110c controlled by the control unit 50 and which is arranged to move the slider 110a from its first position to its second position.

[0070] In the embodiment of the invention presented here, the actuator 110c comprises a latch 110d and a spring element 110e. The spring element 110e is mounted between the slider 110a and the base 102 and is arranged to push the slider 110a towards its second position. The latch 110d successively takes a holding position in which it holds the slider 110a in its first position and a free position in which it does not hold the slider 110a which is free to move.

[0071] Lock 1 lOd is controlled by control unit 50.

[0072] When the lock HOd is in the holding position, the slider 110a is in its first position corresponding to the transport position.

[0073] When the control unit 50 commands the lock HOd to ​​move to the free position, the slider 110a is released and moves to its second position under the action of the spring element 110e.

[0074] The lock 110d is for example a pyrotechnic element which secures the slide 110a and the base 102 and when the control unit 50 commands the lock 110d, the pyrotechnic element explodes to detach the slide 110a from the base 102. Of course, the lock 110d can take other forms.

[0075] The drive system 112 takes for example the form of a torsion spring fixed between the arm 104 and the connecting rod 108 associated with said drive system 112 for weight saving. But it can take other forms such as a rotary cylinder controlled by the control unit 50.

[0076] From the release position, the satellites 52a-c can be released. To assist in deployment, the spacecraft can impart to the transport system 100a-b a series of accelerations that are intended to impart motion to the satellites 52a-c so that they move away from the transport system 100a-b. In the embodiment of the invention shown in Figs. 1 to 4 and more particularly in Fig. 5, the transport and release system 100a-b comprises between the base 102 and the first satellite 52a, at least one thrust system 150 arranged to push the first satellite 52a away from the base 102.

[0077] In the embodiment of the invention presented here, each thrust system 150 takes the form of a rod 152 slidably mounted on the base 102 and mounted on a spring element which tends to push the rod 152 towards the first satellite 52a.

[0078] According to a particular embodiment of the invention, the transport and release system 100a-b comprises, for each thrust system 150, a delay device 154 which controls the triggering of the thrust system 150 when the arms 104 have reached, around the second axis of rotation 20, a predefined angle of rotation.

[0079] In the embodiment of the invention described herein, the delay device 154 acts on the movement of the rod 152.

[0080] This predefined rotation angle ensures, for example, that the arms 104 are sufficiently far from the stack 50 before pushing the satellites 52a-c.

[0081] This delay device 154 comprises, for example, a pyrotechnic element which secures the rod 152 and the base 102 and when the arms 104 have reached the predefined rotation angle, the pyrotechnic element explodes to detach the rod 152 from the base 102 and the rod 152 is then pushed by the spring element.

[0082] The delay device 154 also comprises here a linkage which is mounted articulated between an arm 104 and the pyrotechnic element and the rotation of the arm 104 causes traction on the linkage which when it has reached its maximum deployed length actuates the pyrotechnic element.

[0083] Of course, the pyrotechnic element can be triggered by other means such as for example by the control unit 50.

[0084] The spring element 110e of the actuator 110c and the spring element of the thrust system 150 may take different forms such as compression coil springs, leaf springs, etc.

[0085] In the second embodiment of the invention shown in Figs. 2 to 4, there is a single set of connecting rods 108 and therefore a single actuation system 110 and the slider 110a is mounted to move in translation coaxially with respect to the stacking axis Z.

[0086] The slider 110a comprises a connecting bar 110b which is rigidly secured to the slider 110a and which is mounted articulated with the proximal end 108a of each connecting rod. The spring element 110e is here mounted between the base 102 and the connecting bar 110b.

[0087] The connection between the proximal end 108a of a connecting rod 108 with the actuation system 110, and more particularly here with the slider 110a in the case of the first embodiment, or with the connecting bar 110b in the second embodiment, takes the form of a bilateral plane cylinder connection, which here consists of the placement of a pin secured to one of the elements of the connection (the slider 110a, the connecting rod 108) in an oblong hole of the other element of the connection (the connecting rod 108, the connecting bar 110b).

Claims

CLAIMS 1) Transport and release system (100a-b) comprising: - a stack (50) of satellites (52a-c) extending along a stacking axis (Z) between a first satellite (52a) and a last satellite (52b), - a base (102) arranged to support the first satellite (52a) of said stack (50), - at least one set of at least one connecting rod (108) where each connecting rod (108) is mounted to move in rotation on the base (102) around a first axis of rotation (10) and has a proximal end (108a) and a distal end (108b), - for each connecting rod (108), an arm (104) having a proximal end (104a) and a distal end (104b), where the proximal end (104a) of said arm (104) is fixed free to rotate at the distal end (108b) of said connecting rod (108) around a second axis of rotation (20), - for each arm (104), securing means (106) intended to secure the distal end (104b) of said arm (104) with the last satellite (52b) of said stack (50), - for each assembly, an actuation system (110) linked to the proximal end (108a) of the or each connecting rod (108) of said assembly and arranged to move said or each of said proximal ends (108a), and - for each connection between a distal end (108b) of a connecting rod (108) and a proximal end (104a) of an arm (104), a drive system (112) arranged to move the arm (104) in rotation around the second axis of rotation (20). 2) Transport and release system (100a-b) according to claim 1, characterized in that the securing means (106) take the form of a stud (106a) secured to the distal end (104b) of the associated arm (104) or to the last satellite (52b) and respectively to a housing (106b) made in the last satellite (52b) or in the distal end (104b) of the associated arm (104). 3) Transport and release system (100a-b) according to claim 2, characterized in that the stud (106a) is integral with the arm (104) and it is mounted free to rotate on said arm (104) around a third axis of rotation (60) parallel to the second axis of rotation (20). 4) Transport and release system (100a-b) according to one of claims 1 to 3, characterized in that the actuation system (110) comprises a slider (110a) connected to hinged manner at the proximal end (108a) of each connecting rod (108) of the associated assembly and mounted movably in translation on the base (102), and an actuator (110c) arranged to move the slide (110a) between a first position and a second position. 5) Transport and release system (100a-b) according to claim 4, characterized in that the actuator (110c) comprises a lock (HOd) and a spring element (110e) arranged to push the slider (110a) towards its second position and where the lock (HOd) successively takes a holding position in which it holds the slider (110a) in its first position then a free position in which it does not hold the slider (110a). 6) Transport and release system (100a-b) according to one of claims 1 to 5, characterized in that the drive system (112) takes the form of a torsion spring fixed between the associated arm (104) and connecting rod (108). 7) Transport and release system (100b) according to one of claims 1 to 6, characterized in that there is a single set of connecting rods (108) and a single actuation system (HO). 8) Transport and release system (100a-b) according to one of claims 1 to 7, characterized in that it comprises between the base (102) and the first satellite (52a), at least one thrust system (150) arranged to push the first satellite (52a) away from the base (102). 9) Transport and release system (100a-b) according to claim 8, characterized in that it comprises, for each thrust system (150), a delay device (154) which controls the triggering of the thrust system (150) when the arms (104) have reached, around the second axis of rotation (20), a predefined angle of rotation. 10) Space vehicle comprising a structural part (150) and a transport and release system (100a-b) according to one of the preceding claims where the base (102) is integral with the structural part (150).

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