Reusable Space Transportation Systems

Abstract

A space transportation system (1) intended to be mounted on a space launcher (100) comprising a re-ignitable propulsion device (2), steerable flaps (3) arranged at a second end (12), and a monitoring unit (4), each flap (3) comprising an actuation means configured to change the orientation of said flap (3), said monitoring unit (4) being configured to: · a launch step in which the propulsion device (2) is off and the flaps (3) are in the retracted position; a return step in which the monitoring unit (4) deploys the flaps (3) and individually controls the orientation of the flaps (3) to slow down the system (1), while the propulsion device (2) is off; A landing step in which the monitoring unit (4) controls the propulsion device (2) and the actuation means to orient and slow down the flaps (3) and roll over the system (1). In order to carry out the above, the activation of the propulsion device (2) is controlled and the orientation of the flap (3) is individually controlled.

Description

[Technical Field]

[0001] The present invention relates to a reusable space transportation system intended to be installed on a space launcher. [Background technology]

[0002] Space launch missions are generally carried out by installing a transportation system carrying a payload, e.g., a satellite to be placed into orbit, on a space launcher. The transportation system thus forms the final stage of the launcher, the first stage being a propulsion stage that is removed once their mission has been carried out.

[0003] A problem commonly encountered with known transportation systems is that they are single use, i.e., a single launch and a single Earth landing.

[0004] To solve this problem, reusable transportation systems or reusable shuttles have been developed that can be retrieved and landed at a predetermined location at the end of their mission so that the transportation system can be returned to operational condition for future missions.

[0005] A problem encountered with reusable vehicle systems is the need to have the ability to monitor the orientation and velocity of the vehicle system with sufficient accuracy to allow the vehicle system to return from space and land at a desired location.

[0006] A solution for monitoring the orientation and speed of a transportation system must also be robust enough to withstand the stresses experienced during use of the transportation system, allowing the transportation system to be reused for subsequent missions. Summary of the Invention [Problem to be solved by the invention]

[0007] Therefore, the main object of the present invention is to propose a transportation solution that can solve the above problems. [Means for solving the problem]

[0008] According to a first aspect, the present invention relates to a space transportation system intended to be mounted on a space launcher, the transportation system comprising: a fuselage extending primarily along a first direction, a first end, a second end opposite the first end along the first direction, and a re-ignitable propulsion device disposed at the first end or the second end.

[0009] According to a general aspect of the invention, the transportation system comprises a plurality of steerable flaps arranged at the second end, each flap comprising an actuation means configured to change the orientation of the flap in a plane that includes at least a first direction, and a monitoring unit, the monitoring unit comprising: · A launch step with the propulsion device off and the flaps in the retracted position; a return step in which the monitoring unit controls the actuation means to deploy the flaps and orient the flaps to ensure stability and maneuver the system, the propulsion device being off; A landing step in which the monitoring unit controls the propulsion device and actuation means to orient the flaps, decelerate the transportation system and perform a rollover. To implement the above, the propulsion device is controlled and configured to individually control each actuation means and monitor the orientation of each flap.

[0010] Such a transportation system is particularly advantageous because it provides a simple and robust solution for a reusable transportation system suitable for all phases of the transportation system's mission.

[0011] The transportation system fuselage has a simple aerodynamic profile, i.e., no airfoils, which eliminates the need for an external aerodynamic fairing, thereby maximizing the internal volume of the reusable space transportation system while minimizing launcher design constraints.

[0012] This simple profile is similar to the profile of previously used non-reusable shuttle fairings, and therefore makes it possible to have a delivery system that can be fitted to current launchers without requiring changes to known launcher designs and that can be used with this type of shuttle profile.

[0013] According to one possible feature, the flap is positioned away from the fuselage of the transport system, regardless of the step. The flap is preferably positioned away from the fuselage along the first direction in the launch step. Thus, the flap is offset relative to the flow of fluid over the fuselage.

[0014] By moving the flaps away from the fuselage, the connecting layer of the aerodynamic boundary can be absorbed whatever the speed regime (and Mach) of the transport system, thus maximizing the aerodynamic efficiency of the outer surface of the transport system.

[0015] According to one possible feature, the means for actuating the flaps are curved actuators. They can describe a movement along a circular direction or form a ball joint that allows additional rotation in two different planes.

[0016] According to one possible feature, the system comprises four (three or more) flaps distributed according to axisymmetrical about the first direction.

[0017] According to one possible feature, the propulsion device comprises a plurality of exhaust nozzles distributed on the fuselage of the system along a circumferential direction around the first direction and directed between the flaps towards the second end of the system or along a direction passing between two flaps of each exhaust nozzle in the first direction.

[0018] According to one possible feature, the propulsion device generates a thrust that is variable in strength and direction and that is monitored by the monitoring unit.

[0019] According to one possible feature, the flap has a length along the first direction and in the launch step configuration that is comprised between 40% and 60% of the length of the fuselage of the system.

[0020] Flaps with such dimensional ratios in a transport system make it possible to optimize monitoring of the stability, direction and deceleration of the transport system.

[0021] According to one possible feature, each flap has a first end that is oriented toward the first end of the system during the launch step and a second end that is oriented toward the second end of the system during the launch step, and the transportation system is configured to rest on a reference surface, such as a landing base, at the end of the landing step by contact with the second end of the flap to increase ground stability during landing.

[0022] According to one possible feature, the system includes at least one central leg located at the second end of the system and surrounded by flaps, and the transport system is configured such that, at the end of the landing step, the central leg rests on a reference surface via the second end of the flaps, thereby increasing the ground stability of the transport system. Thus, the flaps do not account for much of the transport system's weight and act as additional support points, like a stand.

[0023] According to one embodiment of the present invention, the propulsion device is mounted to the first end of the fuselage. This configuration allows for maximum decoupling between the transportation system and the launcher during the launch phase, minimizes the interaction of the jet with the aerodynamic monitoring surfaces and the ground during the re-entry phase, reduces hot recirculation gas flows during the landing phase, and allows for a return of the center of gravity during the final rollover phase, thus aiding in stabilization of the transportation system during rollover maneuvers and in ground configuration.

[0024] According to another embodiment, the propulsion device is mounted at the second end of the fuselage. This configuration avoids the need for a protective cap on the nozzle to protect it from the thermal environment. Furthermore, it allows the launch phase to have the propulsion device protected by the mechanical interface between the transport system and the launcher. During the re-entry phase, this configuration avoids the impact of the propulsion jet on the outer arc surface of the fuselage or aerodynamic flaps, protecting the propulsion device from the aerothermal re-entry environment and achieving good isolation between aircraft systems.

[0025] According to a second aspect, the invention relates to an assembly comprising a system according to any one of the preceding features installed on a space launcher.

[0026] Other characteristics and advantages of the invention will become apparent from the description given below, with reference to the attached drawings, which show non-limiting examples of embodiments. [Brief explanation of the drawings]

[0027] [Figure 1] FIG. 1 shows a schematic perspective view of a transportation system in flight according to a first embodiment, with flaps in a retracted position for the launch step. [Figure 2] FIG. 2 schematically illustrates a perspective view of the transportation system of FIG. 1 in flight with the flaps in a semi-extended position for the atmospheric entry step. [Figure 3]FIG. 3 schematically illustrates a perspective view of the transportation system of FIG. 1 with the flaps in the deployed position for the landing step. [Figure 4] FIG. 4 is a schematic representation of the transportation system of FIG. 3 when the transportation system of FIG. 3 is on the ground after landing. [Figure 5] FIG. 5 is a schematic diagram of the transportation system of FIG. 1 installed on a space launcher. [Figure 6] FIG. 6 is a schematic diagram illustrating a perspective view of a transportation system in flight according to a second embodiment, with the flaps in a retracted position for the launch step. [Figure 7] FIG. 7 schematically illustrates a perspective view of the transportation system of FIG. 6 in flight with the flaps in a semi-extended position for the atmospheric entry step. [Figure 8] FIG. 8 schematically represents a perspective view of the transportation system of FIG. 6 when the transportation system of FIG. 6 is on the ground after landing. DETAILED DESCRIPTION OF THE INVENTION

[0028] As shown in Figures 1-8, which illustrate two embodiments of a transportation system 1 according to the present invention, transportation system 1 includes a propulsion device 2, a plurality of flaps 3, and a fuselage 10 extending primarily along a main direction X between a first end 11 and a second end 12 opposite the first end 11. The first end 11 of the fuselage 10 is considered to be the end disposed forward of the transportation system 1 during flight, and the second end 12 of the fuselage 10 is considered to be the end disposed aft of the transportation system 1 during flight. When transportation system 1 is mounted on a launcher 100 as shown in Figure 6, the first end 11 is free forward, and the second end is in contact with the launcher 100.

[0029] In the embodiment shown in Figures 1 to 5, the propulsion device 2 is located at the second end 12. In the second embodiment, particularly shown in Figures 7 to 10, the propulsion device 2 can be mounted at the first end 11.

[0030] In the two embodiments shown in Figures 1-5 and 6-8, the flap 3 is coupled to the second end 12 of the fuselage 10 of the transport system 1. The flap 3 has essentially the same shape in a plane of symmetry comprising a main direction and a direction orthogonal to the main direction when the flap is in a configuration relating to the launch step defined below.

[0031] The fuselage 10 is streamlined with a cross section that increases substantially in the longitudinal direction, and thus may give the transportation system 1 an ogive-like shape, for example, without wings and tapered at the first end 11.

[0032] The flap 3 extends along the main direction X between a first end 31 and a second end 32 opposite the first end 31. The first end 31 is disposed opposite the second end 12 of the fuselage 10. When the transportation system 1 is in a configuration for the launch step, the first end 31 and the second end 32 are aligned along a direction parallel to the main direction X.

[0033] Each flap 3 is fixed to the fuselage 10 via an actuator 33 which forms an articulation connection, for example provided at its end with a ball joint which cooperates with the flap 3, making it possible to change the orientation of the flap 3 along different directions.

[0034] Thanks to the actuators 33, the flaps 3 can be moved between a stowed position and a deployed position. The stowed position is used in particular during the launch step and is shown in Figures 1 and 6, in which the flaps 3 are oriented so as to be in an extension or parallel part of the fuselage 10 of the transport system 1, offering the lowest possible, or even zero, resistance to the flow of fluids over the fuselage 10. The deployed stop position shown in Figures 3, 4, and 8 is used in particular during the landing step. In this position, the flaps 3 are deployed and protrude from the contours of the fuselage 10.

[0035] The flaps 3 are not limited to two positions and may individually be in any position between the stowed position and the non-deployed position, including those subject to complex degrees of freedom. Figures 2 and 7 specifically show a schematic representation of the transportation system 1 with the flaps 3 in a semi-deployed position for the atmospheric re-entry step.

[0036] The actuators 33 are therefore configured to offset the flaps 3 relative to the fuselage 10 regardless of the step at which the transport system 1 is positioned. The actuators 33 therefore make it possible to offset the flaps 3 relative to the fuselage 10 at any time along the main direction X and / or along a direction comprised in a plane orthogonal to the main direction X.

[0037] Thus, in the launch step, the flaps 3 may be arranged in a main extension X of the space separating the first end 31 of each flap 3 from the second end 12 of the fuselage 10, as shown in Figure 1 for the first embodiment and in Figure 6 for the second embodiment.

[0038] As shown in Figure 8, which shows the transport system 1 according to the second embodiment in a configuration with respect to the landing step, the actuator 33 may comprise a rounded mechanical arm that allows the flap 3 to pivot between its retracted position and its deployed position. It may also comprise a ball joint located between the curved mechanical arm and the flap 3, which allows the orientation of the flap 3 relative to the mechanical arm to be changed.

[0039] The first end 31 of the flap 3 is therefore decoupled from the fuselage 10 and positioned away from said fuselage 10 of the transportation system 1, which makes it possible to employ complex degrees of freedom of displacement of the flap 3 according to the needs related to flight dynamics, ensuring optimal behavior of the flap 3 throughout all flight phases encountered during atmospheric re-entry and limiting the interaction between the flap 3 and the fuselage 10, in particular as shown in Figures 2 and 7.

[0040] In the two embodiments shown in Figures 1 to 8, the system 1 comprises four identical flaps 3 uniformly distributed around the main direction X. The number of flaps 3 can vary according to the embodiment but is at least equal to three.

[0041] Transportation system 1 also includes a monitoring unit 4 configured to monitor, on the one hand, the propulsion devices 2, more specifically the activation of the propulsion devices 2, and, on the other hand, individually monitor the orientation of each flap 3 by controlling actuators 33. Thus, monitoring unit 4 controls the ignition of propulsion devices 2 and the orientation of flaps 3 to monitor the speed, orientation, and trajectory of transportation system 1 to implement predetermined scenarios depending on the mission to be performed by said transportation system 1. Thus, monitoring unit 4 enables transportation system 1 to perform a rollover during descent to Earth immediately prior to landing. Monitoring unit 4 can also manage the deceleration and / or acceleration of transportation system 1 according to mission needs. Monitoring unit 4 also enables guiding transportation system 1 toward a desired landing area.

[0042] The monitoring unit 4 is particularly configured to perform a launch step, then a return step from space, then a landing step.

[0043] During the launch step, the transportation system 1 is installed on the space launcher 100 as shown in FIG. 5, the propulsion devices 2 are off, and the flaps 3 are in their stowed position to limit the overall dimensions of the transportation system 1 and its interaction on the launcher 100.

[0044] During the return step, the transportation system 1 can return to Earth and be recovered. During the return step, the monitoring unit 4 controls the actuators 33 to deploy the flaps 3 to positions that ensure stability, deceleration, and steering of the system 1 as it falls toward Earth, as shown in Figures 2 and 7, while the propulsion device 2 is off. During this step, the deployment of the flaps 3 by the monitoring unit 4 via the actuators 33 makes it possible to achieve deceleration through aerodynamic dissipation of kinetic energy in the Earth's atmosphere. Furthermore, the monitoring unit 4 can individually adapt the orientation of each flap 3 to adapt the trajectory of the system 1 and correct any deviations that may occur.

[0045] During the landing step, the system 1 continues to decelerate to perform a rollover maneuver and stop on the ground. To perform a rollover of the system 1, the control unit 4 activates the propulsion devices 2 and adapts the orientation of the flaps 3 using the actuators 33. Furthermore, once the system 1 has rolled over, i.e., the second end 12 of the fuselage 10 of the system 1 is oriented toward the ground, the control unit 4 activates the propulsion devices 2 to decelerate the system 1, in particular to place the flaps 3 in a retracted stop position, as shown in Figures 3 and 4 for the first embodiment and in Figure 8 for the second embodiment.

[0046] The actuators 33 can be actuated to have asymmetric positions of the flaps 3, particularly for the rollover phase. The flaps 3 are monitored independently of each other to allow for rollovers in which the flaps 3 each have a different angle, unlike the launch and landing positions in which the flaps 3 are positioned symmetrically relative to the main axis X.

[0047] In the two embodiments shown in Figures 1 to 8, the flap 3 may have a length L3 comprised between 20% and 40% of the length L1 of the system 1 when the flap 3 is in a retracted position in an extension of the fuselage 10 of the system 1. In other words, in the retracted position, the length L3 of the flap 3 measured along the main direction X may be comprised between 40% and 60% of the length L10 of the fuselage 10, as shown in Figures 1 and 6, and preferably about 50% of the length L10 of the fuselage 10.

[0048] Transportation system 1 has the capacity to carry a payload. The payload can include, for example, one or more satellites to be launched into orbit. The payload can also include passengers and all mission interrupt and sustainment systems necessary for passenger transportation, as well as space life support systems. Transportation system 1 can, in particular, carry both one or more satellites and passengers.

[0049] In both embodiments, the transport system 1 may comprise a hatch 5 located in a central area 13 of the fuselage 10, located between the first end 11 and the second end 12, as shown in Figures 6 to 8, said hatch 5 being movable between an open position allowing access to the cargo space and a closed position in which the cargo space is closed. The hatch 5 allows for loading and protecting a payload during transport, so that the hatch 5 can be opened when the payload must be released.

[0050] Thus, according to one possible implementation, once a satellite is loaded into the cargo space located in the central area 13 and closed by the hatch 5, the hatch 5 can be opened when the transportation system 1 reaches the transfer orbit of said satellite to position the satellite within the station, and the satellite can use its apogee motor to move, for example, to its working orbit. Once the satellite is positioned within the station, the monitoring unit 4 controls the propulsion devices 2 and the flaps 3 to ensure the return of the system 1 to Earth and perform a maneuver to land at the desired landing area.

[0051] According to another possible embodiment, the hatch 5 is open for passenger embarkation and disembarkation only before take-off, after landing and during the orbital flight phase.

[0052] Preferably, the propulsion device 2 generates variable thrust, so that the control unit 4 can adapt the amount of thrust generated by the propulsion device 2 when the propulsion device 2 is activated by said control unit 4.

[0053] The propulsion device 2 may be, for example, a liquid or hybrid propellant rocket engine.

[0054] In a first embodiment shown in Figures 1 to 5, the propulsion device 2 of the transportation system 1 is disposed at the second end 12 of the fuselage 10. In this first embodiment, the propulsion device 2 includes four exhaust nozzles 21 installed at the bottom of the transportation system 1. The exhaust nozzles 21 are therefore disposed in the spaces defined between the flaps 3 when the flaps 3 are in the retracted position.

[0055] In a second embodiment shown in Figures 6 to 8, the propulsion device 2 comprises a plurality of exhaust nozzles 21 distributed over the contour of the fuselage 10 of the transport system 1 at the level of the first end 11, more particularly on the outer surface of the fuselage 10. The exhaust nozzles 21 are directed towards the second end 12 of the fuselage 10 of the system 1 and are each arranged along an axis parallel to the main direction X and passing between two flaps 3. The flaps 3 are therefore not reached by the exhaust flow leaving the propulsion device 2.

[0056] As shown in Figure 8, at the end of landing, the flaps 3 can act as additional support to ensure increased stability on the ground during landing of the transportation system 1. Thus, the flaps 3 can be in a landing position with all flaps 3 in a deployed parked position, and the system 1 is resting by the second ends 32 of the flaps 3 on a reference surface S, which is generally the ground.

[0057] The system 1 may further comprise at least one central leg 6 arranged between the flaps 3 at the level of the second ends 12, as shown in Figure 8. The shape of the central leg 6 is adapted so that the system 1 is resting on the reference plane S by both the second ends 32 of the flaps 3 and the central leg 6 when the flaps 3 are in the landing position.

[0058] As shown in FIG. 5, the transportation system 1 can be installed on a space launcher 100 to form an assembly E.

[0059] 6 and 7, a portion 102 of one of the housings of the space launcher 100 is visible, this housing being intended to detach from the transport system 1 at the end of the launch.

[0060] Thus, the present invention makes it possible to provide a reusable transportation system whose orientation and velocity can be monitored with sufficient accuracy to enable it to land at a desired location from space, and which is robust enough to withstand the stresses experienced during flight.

Claims

1. A space transportation system (1) mounted on a space launcher (100) and intended to carry a payload, the transportation system (1) comprising: a fuselage (10) extending primarily along a first direction; a first end (11); a second end (12) opposite the first end (11) along the first direction; and a re-ignitable propulsion device (2) disposed at the first end (11) or the second end (12); the transportation system (1) comprises a plurality of steerable flaps (3) arranged at said second end (12) and a monitoring unit (4), the flaps (3) being arranged at any step away from the fuselage (10) of the transportation system (1), each flap (3) comprising an actuation means configured to change the orientation of said flap (3) in a plane that includes at least a first direction, each actuation means comprising a mechanical arm configured to pivot the respective flap about a second direction perpendicular to the first direction; a launch step with the propulsion device (2) off and the flaps (3) in the retracted position; a return step in which the monitoring unit (4) controls the actuation means to deploy the flaps (3) and orient the flaps (3) to ensure stability and steer the transportation system (1), the return step being when the propulsion device (2) is off; a monitoring unit (4) configured to control the propulsion device (2) and individually control each actuation means to monitor the orientation of each of the flaps (3) to perform a landing step in which the monitoring unit (4) controls the propulsion device (2) and the actuation means to orient the flaps (3) to decelerate and roll over the transportation system (1), wherein each flap is rotatable about a second direction during the roll over of the transportation system.

2. A system (1) as described in claim 1, wherein the flap (3) is remote from the fuselage (10) along a first direction in the launch step.

3. 3. The system (1) according to claim 1 or 2, wherein the means for actuating the flap (3) is an actuator (33) configured to maintain the flap offset from the fuselage (10).

4. The system (1) according to any one of claims 1 to 3, wherein the system (1) comprises four flaps (3) distributed according to axisymmetrical movement around the first direction.

5. 5. The system (1) according to any one of claims 1 to 4, wherein the propulsion device (2) comprises a plurality of exhaust nozzles (21) distributed on the fuselage (10) of the system (1) along a circumferential direction around a first direction and directed between the flaps (3) towards the second end (12) of the system (1) or along a direction parallel to the first direction and passing between the two flaps (3) of each exhaust nozzle.

6. The system (1) according to any one of claims 1 to 5, wherein the propulsion device (2) generates a thrust that is variable in strength and direction and that is monitored by a monitoring unit (4).

7. 7. The system (1) according to any one of claims 1 to 6, wherein the flap (3) has a length (L3) along the first direction and in the launch step configuration that is comprised between 40% and 60% of the length (L10) of the fuselage (10) of the transport system (1).

8. 8. The system (1) according to any one of claims 1 to 7, wherein each flap (3) has a first end (31) that is oriented towards the first end (11) of the system (1) during the launch step and a second end (32) that is oriented towards the second end (12) of the system (1) during the launch step, and wherein the system (1) is configured to rest on a reference surface (S) by contact with the second end (32) of the flap (3) at the end of the landing step.

9. 9. The system (1) according to claim 8, wherein the system (1) comprises at least one central leg (6) arranged at the second end (12) of the system (1) and surrounded by a flap (3), and wherein the system (1) is configured such that at the end of the landing step, the system (1) rests on the reference surface (S) by contact with the second end (32) of the flap (3) and the central leg (6).

10. 10. An assembly (E) comprising a transportation system (1) according to any one of claims 1 to 9, installed on a space launcher (100).

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