Orbital deployment module with three-point space propulsion system

Abstract

A propulsion system 1 with three propulsion points of a space module 10 for orbital deployment for at least one satellite, said propulsion system 1 comprising a chassis 2 having exactly three first housings 6 each formed to receive a propulsion unit 3 and at least one second housing 7 formed to receive a tank 4, at least one liquid fuel tank 4 arranged in the second housing 7, and exactly three propulsion units 3, each propulsion unit 3 arranged in one of the three first housings 6 and having at least one thruster 30.

Description

[Technical field]

[0001] The present invention relates to the technical field of space propulsion systems, and more particularly to the architecture of a propulsion system for an orbital deployment module. [Background technology]

[0002] In the field of aerospace transportation, and in other fields, those skilled in the art are continually seeking to improve the operation of their devices, particularly to simplify the physical elements that make them up and reduce their manufacturing costs.

[0003] Generally, space propulsion systems for orbitally deployed modules, such as satellites or modules carrying satellites, use as the main thrust vector either an architecture based on multiple fixed thrusters distributed over two or four points, or an architecture based on a steerable thruster and a system for controlling the orientation.

[0004] In architectures with fixed thrusters, four thrust points are generally used, distributed at the four corners of a square or rectangle depending on the distribution of the load on the orbital deployment module. This type of architecture has the advantage of having a simplified control and therefore a simplified software control architecture. This architecture makes it possible to effectively control the thrusters based on sending thrust pulses on the thrusters, with the possibility of decorrelating the thrust along each of the two axes of the orthogonal reference frame defined by the arrangement of the four thrust points.

[0005] Although the controls are simplified, this architecture is not optimal for ensuring the primary function, which is to move the deployment module in a precise direction orthogonal to the propulsion plan, with the thrusters distributed over four thrust points. Summary of the Invention [Problem to be solved by the invention]

[0006] The main object of the present invention is therefore to provide an orbital deployable space module equipped with a propulsion system, separate from the tank, that is reduced in volume and cost, and that can be intended to save space in order to increase the volume of a tank or housing intended to accommodate one or several satellites. [Means for solving the problem]

[0007] According to one object of the invention, there is provided a propulsion system with three thrust points for an orbitally deployable space module for at least one satellite, comprising: The propulsion system comprises: a chassis having exactly three first housings, each configured to receive a propulsion unit, and at least one second housing configured to receive a tank; at least one liquid fuel tank disposed within the second housing; exactly three propulsion units, each propulsion unit disposed in one of the three first housings and having at least one thruster; and a control unit configured to control the supply and power developed by each of the three propulsion units.

[0008] A three-point propulsion system allows for a significant reduction in volume and cost compared to a four-point propulsion system. However, this reduction is not obvious because it forces the use of a propulsion control logic that is completely different from the propulsion control logic of a four-point propulsion system. In particular, the pitch drive function is combined with the yaw drive function in the control logic. This reduction in volume and cost is only possible with a more complex propulsion system supervisory control.

[0009] In the propulsion system of the first embodiment, the three first housings may each be disposed at the vertices of the same triangle whose center of gravity corresponds to the center of gravity of the propulsion system.

[0010] The control of the three propulsion units can be simplified by balanced placement of the propulsion units relative to the center of gravity of the propulsion system.

[0011] Preferably, the three first housings are disposed at the vertices of the same equilateral triangle.

[0012] By using the balanced arrangement provided by the equilateral triangle, it is possible to further simplify the control of the three propulsion units.

[0013] In the propulsion system of the second embodiment, the three propulsion units may have the same number of thrusters, preferably identical thrusters.

[0014] By having identical propulsion units, the control of the three propulsion units can be further simplified.

[0015] In the propulsion system of the third embodiment, the chassis may have a shape having a number of sides equal to a multiple of three in a cross section including the three propulsion units.

[0016] The above-mentioned geometric shape of the chassis of the propulsion system makes it possible to optimize the shape of the orbital space module equipped with the above-mentioned propulsion system with respect to the space allocated by said space module.

[0017] In the propulsion system of the fourth embodiment, the chassis may have a hexagonal shape in a cut plane that includes the three propulsion units.

[0018] In the propulsion system of the fifth embodiment, the chassis may further comprise a central housing configured to receive at least one satellite intended to be placed into orbit.

[0019] In the propulsion system of the sixth embodiment, the chassis may comprise a detachable mating interface for receiving at least one satellite intended to be placed into orbit.

[0020] In the seventh embodiment propulsion system, each thruster can be oriented parallel to a main thrust direction perpendicular to a plane containing the three propulsion units, and the propulsion system further includes an auxiliary propulsion system having auxiliary thrusters oriented perpendicular to the main thrust direction.

[0021] The auxiliary propulsion system is capable of generating thrust in particular in the tangential direction and in particular of rotating the propulsion system and therefore of rotating the spatial module equipped with this propulsion system about its main axis which corresponds to the main propulsion axis of the propulsion system.

[0022] The rotation of this propulsion system, and therefore the rotation of the space module equipped with said propulsion system, makes it possible to stabilize the temperature of the space module.

[0023] In one embodiment of the propulsion system, the control unit may be configured to determine, at each maneuver of the propulsion system, the thrust that each of the three propulsion units must deploy for the desired maneuver.

[0024] Preferably, the control unit comprises a positioning sensor, for example a stellar sighting sensor, or a positioning sensor, for example a Global Positioning System (GPS).

[0025] Preferably, the control unit comprises a chopping unit configured to control propulsion torque by chopping the supply to the three propulsion units at chopping durations calculated for each of the three propulsion units.

[0026] The use of chop control of the three propulsion units can limit the temperature rise of the thrusters compared to continuous operation of the three propulsion units.

[0027] According to another object of the invention, a space module for orbital deployment for at least one satellite is proposed, comprising an enclosure configured to transport at least one satellite to be placed in a space orbit, and a propulsion system having three thrust points as described above.

[0028] Other characteristics and advantages of the invention will become apparent from the description given below, with reference to the attached drawings, which show one exemplary embodiment without being limiting, in which: [Brief description of the drawings]

[0029] [Figure 1] FIG. 1 is a schematic cross-sectional view of a propulsion system of an orbital deployment spatial module according to a first embodiment of the present invention. [Diagram 2] FIG. 2 illustrates a schematic perspective view of an orbital deployment spatial module according to one embodiment of the present invention. [Diagram 3] FIG. 3 is a schematic cross-sectional view of a propulsion system of an orbital deployment spatial module according to a second embodiment of the present invention. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0030] FIG. 1 is a schematic cross-sectional view of a propulsion system of a space module for orbital deployment according to one embodiment of the present invention.

[0031] The propulsion system 1 comprises a chassis 2, three main propulsion units 3 and three fuel tanks 4. The cutting plane in Fig. 1 cuts through the three propulsion units 3 and comprises a first direction x and a second direction y perpendicular to the first direction x. The cutting plane xy is perpendicular to a third direction z parallel to the main propulsion direction of the propulsion system 1.

[0032] The chassis 2 has a central housing 5 intended to receive one or more satellites (not shown in FIG. 1 ) intended to be put into orbit by an orbital deployment space module equipped with said propulsion system 1. The chassis 2 further has three first housings 6 each adapted to receive a main propulsion unit 3 and three second housings 7 each adapted to receive a fuel tank 4.

[0033] Each main propulsion unit 3 is disposed at a vertex of an equilateral triangle 8, represented by imaginary lines. The propulsion system thus forms a three-point propulsion system.

[0034] Furthermore, in the embodiment shown in Figure 1, each main propulsion unit 3 comprises two thrusters 30. In one variant, each main propulsion unit 3 may comprise a single thruster 30 or at least three thrusters 30. In another variant, the propulsion units 3 may comprise a different number of thrusters.

[0035] The thrusters 30 of the propulsion units may be of the same type or of different types: they may be, for example, gas-ejecting nozzles or electric or ion thrusters.

[0036] 1, the chassis 2 has a hexagonal shape having three first sides 22 and three second sides 24, where the length of the second sides 24 is longer than the length of the first sides 22, and where each first side 22 is adjacent to two separate second sides 24. In other words, each first side 22 is separated from two other first sides 22 by two second sides 24.

[0037] Each main propulsion unit 3 is mounted on a first side 22 and each tank 4 extends along a second side 24 between two main propulsion units 3, on the one hand, and between the second side 24 and the central housing 5, on the other hand.

[0038] The tank 4 can have any possible shape.

[0039] In one variant illustrated in FIG. 3, each main propulsion unit 3 can be mounted on the second side 24, with the three main propulsion units 3 positioned at the vertices of a triangle whose geometric center of gravity corresponds to the center of gravity of the propulsion system 1.

[0040] FIG. 2 is a schematic perspective view of an orbital deployment spatial module 10 equipped with the propulsion system 1 of FIG.

[0041] The orbital deployment spatial module 10 comprises an enclosure 11 having a hexagonal shape in the plane xy corresponding to the hexagonal shape of the chassis 2 of the propulsion system 1 of Figure 1. The enclosure 11 comprises an upper surface 110, a lower surface 112, three first sides 114, and three second sides 116 that are longer than the three first sides 114.

[0042] The upper surface 110 includes a recess 50 that communicates with the central housing 5 of the chassis 2 of the propulsion system 1 of FIG.

[0043] Furthermore, each second side 116 comprises two orifices 118 located respectively in the vicinity of the first side 114. The propulsion system 1 further comprises auxiliary thrusters, each of which is mounted on the chassis 2 facing an orifice 118 of the enclosure 11 of the space module 10. The auxiliary thrusters allow a monitored rotation of the space module 1 about its main axis parallel to the third direction z. This rotation of the space module 1 allows a temperature equalization of the orbital deployment space module 1.

[0044] Preferably, the auxiliary thrusters on the same second side point in opposite directions, with one auxiliary thruster being used to initiate a rotation in one direction and the other auxiliary thruster being used to initiate a rotation in the opposite direction or to stop a current rotation.

[0045] Thus, the present invention makes it possible to provide an orbital deployable space module having a propulsion system, separate from the tank, that is reduced in volume and cost, and that can be intended to save space in order to increase the volume of the tank or housing to accommodate one or several satellites.

Claims

1. A propulsion system (1) with three thrust points for an orbital deployment space module (10) for at least one satellite, The propulsion system (1) comprises: a chassis (2) having exactly three first housings (6) each configured to receive a propulsion unit (3) and at least one second housing (7) configured to receive a tank (4); at least one liquid fuel tank (4) disposed within said second housing (7); exactly three propulsion units (3), each of which is arranged in one of the three first housings (6) and has at least one thruster (30); a central housing (5) configured to receive a satellite intended to be put into orbit; a control unit configured to control the supply and power deployed by each of the three propulsion units, the control unit comprising control logic that couples pitch and yaw drive functions.

2. 2. The propulsion system (1) according to claim 1, wherein the three first housings (6) are each arranged at a vertex (80) of the same triangle (8) whose center of gravity corresponds to the center of gravity of the propulsion system (1).

3. 3. The propulsion system (1) according to claim 2, wherein the three first housings (6) are respectively arranged at vertices (80) of the same equilateral triangle (8).

4. 2. The propulsion system (1) according to claim 1, wherein the three propulsion units (3) have an equal number of thrusters (30).

5. 2. The propulsion system (1) according to claim 1, wherein the chassis (2) has a shape having a number of sides (22, 24) equal to a multiple of three in a cutting plane (xy) including the three propulsion units (3).

6. 2. The propulsion system (1) according to claim 1, wherein the chassis (2) has a hexagonal shape in a cross-section (xy) including the three propulsion units (3).

7. 2. A propulsion system (1) according to claim 1, wherein the chassis (2) further comprises a removable coupling interface (51) for receiving a satellite intended to be placed into orbit.

8. 2. The propulsion system (1) of claim 1, wherein each thruster (30) is oriented parallel to a main thrust direction (z) perpendicular to a plane (xy) containing the three propulsion units (3), and the propulsion system (1) further comprises an auxiliary propulsion system having auxiliary thrusters oriented perpendicular to the main thrust direction (z).

9. 2. The propulsion system (1) of claim 1, wherein the control unit is configured to determine, at each maneuver of the propulsion system (1), the thrust that each of the three propulsion units (3) must deploy for a desired maneuver.

10. 10. The propulsion system (1) according to any one of claims 1 to 9, wherein the control unit comprises a chopping unit configured to control the propulsion torque by chopping the supply to the three propulsion units (3) with a chopping duration calculated for each of the three propulsion units (3).

11. 11. A space module (10) for orbital deployment for at least one satellite, comprising an enclosure (11) configured to transport at least one satellite to be placed into space orbit, and a propulsion system (1) with three propulsion points according to any one of claims 1 to 10.

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