A reusable orbital vehicle including a crew escape vehicle for forward extraction.

Abstract

The reusable orbital vehicle (14) for the space transportation system (10) includes a fuselage (22) having a shape that widens in a direction from a forward end (24) of the reusable orbital vehicle to an aft end (26) of the fuselage (22), a housing (32) defined within the fuselage (22), and a crew escape vehicle (34) housed within the housing (32) in a state oriented for extraction from the housing (32) in a direction (D1) oriented from the aft end (26) of the fuselage (22) toward the forward end (24) of the reusable orbital vehicle (14).

Description

[Technical Field]

[0001] The present invention relates generally to the field of human space transportation.

[0002] The present invention relates, inter alia, to a reusable orbital vehicle that allows the crew to be ejected in the event of a mission abort, and to a method for ejecting the crew of such a vehicle. [Background technology]

[0003] Manned space missions are generally carried out by space transportation systems that include a reusable orbital vehicle that houses a crew mounted on a space launcher. "Reusable vehicle" means any space vehicle that is designed to undergo atmospheric re-entry and to land at the end of its mission, without this excluding the possibility that certain components of the vehicle may need to be replaced before a new space mission can be carried out with it.

[0004] In some cases, the orbital vehicle is mounted on top of a launcher, thus forming its final stage, the first stage being a propulsion stage intended to sequentially separate from the launcher during or at the end of the ascent phase after expending its fuel.

[0005] One important aspect of this type of space transportation system relates to the possibility of ejecting the crew in case of a problem during the space mission.

[0006] In currently operational systems, the reusable orbital vehicle is used to eject the crew in the event of a launcher failure during the takeoff or ascent phase. For this purpose, the thrusters equipped on the reusable orbital vehicle are fired to detach the reusable orbital vehicle from the space launcher as quickly as possible.

[0007] However, the speed of this maneuver is limited due to the potentially large mass of the orbital vehicle, which must contain all the equipment necessary to accomplish the mission in orbit.

[0008] Additionally, in the event of a failure of the reusable orbital vehicle itself during a subsequent phase of a space mission, the prior art has only proposed rescue capsules as a solution for crew evacuation, the use of which is only possible during the approach phase when the orbital vehicle has been sufficiently decelerated. Additionally, the use of such capsules can pose a risk when the orbital vehicle is not properly oriented. Summary of the Invention [Problem to be solved by the invention]

[0009] The object of the present invention is a reusable orbital vehicle that makes it possible to at least partially ameliorate these problems, and a method for evacuating the crew of such a vehicle. [Means for solving the problem]

[0010] To this end, the present invention proposes a reusable orbital vehicle for a space transportation system, the reusable orbital vehicle comprising a fuselage and a crew escape vehicle, the fuselage having a shape that widens in a direction from a forward end of the reusable orbital vehicle toward an aft end of the fuselage, a housing defined within the fuselage that extends to the forward end of the fuselage, and the crew escape vehicle housed within the housing in an orientation such that it can be extracted from the housing in a direction oriented from the aft end of the fuselage toward the forward end of the reusable orbital vehicle.

[0011] In general, the fact that the crew escape vehicle is ejected forward from the reusable orbital vehicle in the reusable orbital vehicle's nominal direction of motion enables this extraction not only during the ascent phase, but also while on the launch pad prior to takeoff, and during the approach and landing phases, and following landing, because the likelihood that the reusable orbital vehicle will have an attitude compatible with such extraction is thus maximized.

[0012] In a preferred embodiment of the invention, the fuselage includes a fairing, the fairing surrounding the housing and extending from the forward end of the fuselage toward the aft end of the fuselage, the fairing being truncated to define an opening that emerges into the housing, and the crew escape vehicle includes a fuselage having a nose that extends through the opening to form the nose of the reusable orbital vehicle.

[0013] Preferably, the nose extends in aerodynamic continuity with the fairing.

[0014] Preferably, the fuselage of the crew escape vehicle has a step formed in the base of said nose, with the truncated forward end of the fairing positioned axially facing said step.

[0015] Preferably, the fairing is formed by an annular array of panels joined in pairs by frangible joints which define suitable rupture zones.

[0016] In a preferred embodiment of the present invention, the reusable orbital vehicle includes a baffle skirt having a generally frusto-conical shape and extending into the housing to surround and be disposed aft of the crew escape vehicle, facing axially toward a propulsion means of the crew escape vehicle configured to generate thrust in said direction.

[0017] The present invention also provides a method for evacuation of a crew member of a reusable orbital vehicle of the type described above, the method comprising: A) installing a reusable orbital vehicle crew member into a crew escape vehicle; and B) evacuating the crew by moving the crew escape vehicle in said direction to extract the crew escape vehicle from the housing; The present invention relates to a method comprising the steps of:

[0018] In a preferred embodiment of the present invention, the crew escape vehicle takes the nose of the reusable orbital vehicle with it during step B.

[0019] In a preferred embodiment of the present invention, the crew escape vehicle causes rupture of said frangible connection during step B.

[0020] In a preferred embodiment of the present invention, the crew escape vehicle causes the baffle skirt to rupture during step B.

[0021] In a preferred embodiment of the present invention, step B is performed during any one of takeoff, ascent, end of atmospheric re-entry, final approach, landing, and post-landing phases.

[0022] The invention will be better understood and other details, advantages and features will become apparent from reading the following description, given by way of non-limiting example and with reference to the accompanying drawings, in which: [Brief explanation of the drawings]

[0023] [Figure 1A] 1 is a schematic diagram of a space transportation system including a reusable orbital vehicle. [Figure 1B] 1 is a schematic diagram of a reusable orbital vehicle at the end of a space mission. [Figure 2]FIG. 1 is a perspective schematic view of the forward part of the reusable orbital vehicle, providing a view through the fuselage of the reusable orbital vehicle to the crew escape vehicle housed therein. [Figure 2A] FIG. 3 is a larger scale view of a portion of FIG. 2. [Figure 3] FIG. 3 is a schematic side view of the forward part of the reusable orbital vehicle of FIG. 2, also providing a view of the crew escape vehicle through the fuselage of the reusable orbital vehicle. [Figure 4] FIG. 3 is a view similar to FIG. 2 without the crew escape vehicle. [Figure 4A] FIG. 5 is a larger scale view of a portion of FIG. 4. [Figure 5] FIG. 4 is a view similar to FIG. 3 without the crew escape vehicle. [Figure 6] 1 is a perspective schematic diagram of a crew escape vehicle in a first configuration intended for incorporation into a reusable orbital vehicle; FIG. [Figure 7] FIG. 2 is a schematic diagram in longitudinal section of the crew escape vehicle in a first configuration. [Figure 8] 1 is a perspective schematic view of the crew escape vehicle in a second configuration intended for flight; FIG. [Figure 9] FIG. 2 is a schematic diagram in longitudinal section of the crew escape vehicle in a second configuration. DETAILED DESCRIPTION OF THE INVENTION

[0024] FIG. 1A illustrates a space transportation system 10 that generally includes a space launcher 12 having a reusable orbital vehicle 14 mounted atop the space launcher 12.

[0025] The space launcher 12 typically includes one or more propulsion stages 16 .

[0026] The reusable orbital vehicle 14 includes an aerodynamic fuselage 22 having an overall shape that widens in a direction from the reusable orbital vehicle's forward end 24 toward its aft end 26. The opposite direction (which is thus oriented from the aft end 26 toward the forward end 24) constitutes the vehicle's nominal direction of motion D1, which is, for example, parallel to the vehicle's mean longitudinal axis 27. In this specification, this axis 27 serves as a reference for defining a cylindrical coordinate reference system {R, C}, where the radial direction R is the direction that is orthogonal to and passes through the axis 27 at all points, and the orthoradial direction C is the direction that is orthogonal to the axis 27 and the radial direction R at all points.

[0027] It should therefore be understood that the reusable orbital vehicle 14 is designed to travel in direction D1 during all phases of the space mission, including the atmospheric re-entry phase, and is designed so as not to need to reverse except during the final approach phase with a view to landing from the rear of the vehicle. In order to bestow an optimal profile on the reusable orbital vehicle 14, the reusable orbital vehicle 14 is provided with a nose 28, which is preferentially in the form of a cap, or more generally in the form of a truncated cone with a rounded apex, forming the forward end 24 of the vehicle, as will appear more clearly hereinafter.

[0028] The reusable orbital vehicle 14 further includes propulsion means 30, including, for example, one or more rocket engines. These propulsion means 30 are capable of generating, among other things, thrust directed in the nominal direction of travel D1. It should be noted that when the reusable orbital vehicle 14 is mounted on the space launcher 12 as shown in FIG. 1A, the nose 28 of the reusable orbital vehicle constitutes the overall forward end of the space transportation system 10, while the aft end 26 of the fuselage 22 is positioned facing the launcher's propulsion stage 16.

[0029] During a typical mission, the complete space transportation system 10 is launched from a launch pad and propelled by one or more propulsion stages 16. The one or more propulsion stages 16 successively deactivate and separate from the space transportation system 10, using their propulsion means 30 as needed to make trajectory adjustments, until the reusable orbital vehicle 14 is released to continue its trajectory and reach the target orbit. At the end of the mission, the reusable orbital vehicle 14 uses its propulsion means 30 to leave its orbit and to position itself on an atmospheric re-entry trajectory that will enable it to reach the target landing zone. To this end, a means for orienting the reusable orbital vehicle 14 (which may be, for example, the propulsion means 30 or a movable aerodynamic surface) is used to orient the reusable orbital vehicle 14 to place its fuselage 22 at an angle of incidence that allows the fuselage 22 to generate lift. Throughout this phase, the reusable orbital vehicle points its nose 28 forward in its direction of travel, such that the nose 28 contributes to the thermal protection of the reusable orbital vehicle. On approach to the target landing zone, the reusable orbital vehicle 14 performs an inversion maneuver and then positions itself by orienting its nose 28 upward and orienting the aft end 26 of the fuselage 22 toward the ground.

[0030] The present disclosure generally aims to present means for improving crew rescue arrangements in the event of a problem during a space mission.

[0031] To this end, with reference to Figures 2-5, the reusable orbital vehicle 14 includes a housing 32 surrounded by the fuselage 22, in which a crew escape vehicle 34 is disposed (also visible alone in Figures 6 and 7), such that said crew escape vehicle 34 can be extracted from the reusable orbital vehicle 14 and fly independently therefrom. As will appear more clearly hereinafter, the crew escape vehicle 34 is intended to enable the escape of crew members from the reusable orbital vehicle 14 not only during the ascent phase, but also when on the launch pad, before and at the moment of takeoff, as well as during the final approach and landing phases, and following landing.

[0032] The use of such a dedicated vehicle for crew evacuation, instead of the reusable orbital vehicle itself at takeoff or while on the launch pad, is particularly advantageous because the dedicated evacuation vehicle can have a significantly reduced mass compared to the mass of the reusable orbital vehicle, which must incorporate all the equipment intended to accomplish the crew's various missions in orbit, as well as the equipment and components necessary to enable atmospheric re-entry. The gain in terms of extraction acceleration allowed by such a mass reduction can prove to be crucial for rescuing the crew, especially in the event of an explosion of the space launcher 12 during the takeoff or ascent phase. This gain also makes it possible to extend the ballistic trajectory of the crew evacuation vehicle, which is advantageous in cases where the zone surrounding the launch pad does not provide the necessary safety conditions for retrieving the crew evacuation vehicle. In certain embodiments, the crew escape vehicle can therefore travel several kilometers (e.g., 3.5 km in one exemplary implementation, or 5 km in another exemplary implementation) away from the launch pad in case of triggering an escape procedure on the launch pad.

[0033] The presence of a specialized escape vehicle during the final approach and landing phase, as well as following landing, makes it possible to envisage crew escape in case of a problem on board the reusable orbital vehicle, which is obviously not possible in cases where such a dedicated vehicle is not provided and where the possibility of escape during a space mission must be carried out by the reusable orbital vehicle itself.

[0034] Compared to extraction towers known from the prior art (e.g., those of Apollo, Soyuz, or Orion), which are disposed entirely forward of the orbital vehicle, accommodating the crew escape vehicle within the orbital vehicle makes it possible to keep the crew escape vehicle available throughout the mission, while extraction towers, which are not adapted to perform atmospheric re-entry maneuvers, are generally detached during the ascent phase.

[0035] The crew escape vehicle 34 advantageously includes a cabin provided therein with control equipment (not visible in the figures) and means for interfacing this equipment with components and / or equipment of the reusable orbital vehicle 14 (other than those forming part of the crew escape vehicle 34), in particular the propulsion means 30 and, where applicable, means for orienting the reusable orbital vehicle (if these are different from the propulsion means 30), so that the reusable orbital vehicle 14 is controlled by the crew in the crew escape vehicle 34 by means of said control equipment.

[0036] Additionally, the crew escape vehicle 34 includes a roughly bullet-shaped fuselage 36 that defines a nose 38 at one end of the crew escape vehicle (designated its forward end 39 in consideration of the crew escape vehicle's nominal direction of travel D2). The fuselage 36 extends in the opposite direction to an aft wall 40 that defines the aft end of the fuselage 36. The aft wall 40 extends, for example, transversely to an axis 42 of the crew escape vehicle, which axis 42 constitutes, for example, an axis of symmetry for the fuselage 36. Between the nose 38 and the aft wall 40, the fuselage 36 has a slightly flared shape, at least in its forward portion, in the direction from the nose 38 to the aft wall 40 in order to best comply with area rules, as will become more clear hereinafter. The fuselage 36 therefore defines an aerodynamic profile with an elongated shape along the crew escape vehicle's axis 42, which therefore defines the vehicle's longitudinal direction. Such a shape is optimized to favor the crew escape vehicle's acceleration through the atmosphere, particularly in the case of a mission abort on the launch pad or during the launch phase, when the speed of its extraction and its distance from the launcher are of paramount importance. The crew escape vehicle's nominal direction of movement D2 is parallel to the axis 42, as will become more apparent hereinafter.

[0037] Finally, the crew escape vehicle 34 includes a propulsion means 44 attached to its fuselage 36 that, as will become more apparent hereinafter, allows the crew escape vehicle 34 to be extracted from its housing 32 within the reusable orbital vehicle 14 and allows for optional adjustment of the crew escape vehicle's trajectory.

[0038] Moreover, the reusable orbital vehicle 14 advantageously includes a workspace 46 (FIG. 1B) defined aft relative to the housing 32 and intended to be accessible to the crew during non-critical phases of orbital flight, for example, by an airlock 48, which opens into a hatch located in the aft wall 40 of the crew escape vehicle fuselage 36.

[0039] The landing mode of the crew escape vehicle 34 is not the subject of this disclosure and can be of a conventional type, such as by one or more parachutes to brake the crew escape vehicle until it lands flat or nose-first on land or at sea.

[0040] According to a first aspect of the present disclosure, the housing 32 of the reusable orbital vehicle 14 extends to the forward end of the reusable orbital vehicle fuselage 22, and the crew escape vehicle 34 is disposed within the housing 32 of the reusable orbital vehicle 14 with the crew escape vehicle 34 oriented to permit extraction of the crew escape vehicle 34 in the nominal direction of movement D1 of the reusable orbital vehicle. In particular, the crew escape vehicle 34 is disposed such that its nominal direction of movement D2 coincides with the nominal direction of movement D1 of the reusable orbital vehicle 14.

[0041] To this end, the crew escape vehicle 34 is disposed such that, inter alia, its axis 42 extends parallel or substantially parallel to the nominal direction of movement D1 of the reusable orbital vehicle 14, preferably with its axis 42 centered on the longitudinal midplane P of the reusable orbital vehicle. In the illustrated embodiment, the crew escape vehicle axis 42 coincides with, inter alia, the median longitudinal axis 27 of the reusable orbital vehicle. In addition, the crew escape vehicle 34 is oriented such that its nose 38 is located on the same side as the forward end 24 of the reusable orbital vehicle and its rear wall 40 is located on the opposite side (i.e., on the same side as the aft end 26 of the fuselage 22). Moreover, the propulsion means 44 of the crew escape vehicle 34 are advantageously configured to generate thrust directed in the nominal direction of movement D2 of the crew escape vehicle 34, and thus in the direction of the forward end 24 of the reusable orbital vehicle.

[0042] In the preferred example shown, the nose 38 of the crew escape vehicle 34 constitutes the nose 28 of the reusable orbital vehicle 14 .

[0043] To this end, the fuselage 22 of the reusable orbital vehicle 14 includes a fairing 50 that surrounds the reusable orbital vehicle's housing 32 and extends flared from a truncated forward end 52 (FIGS. 4 and 5) of the fuselage 22, which defines an opening 54 emerging into the housing 32, toward the aft end 26 of the fuselage. In addition, the nose 38 of the crew escape vehicle 34 extends through the opening 54 in aerodynamic continuity with the fairing 50. The crew escape vehicle 34 therefore occupies a space or housing that extends to the forward end 24 of the reusable orbital vehicle 14, which space strictly speaking corresponds to the space occupied by the housing 32 and by the nose 38.

[0044] Such continuity between the crew escape vehicle nose 38 and the fairing 50 of the reusable orbital vehicle fuselage 22 is obtained, for example, by a step 56 formed at the base of the nose 38 of the crew escape vehicle fuselage 36, with the truncated forward end 52 of the fairing 50 disposed facing the step 56 (Figures 3, 6, and 7).

[0045] Since the shape of the crew escape vehicle 34 is generally widened towards its rear, its extraction from the housing 32 means that the rear part of the crew escape vehicle (wider than the opening 54) collides with the fairing 50, causing it to break. To best facilitate this process and therefore optimize the speed of the crew escape vehicle's extraction, the fairing 50 is designed to favor its fragmentation under the impact of a collision with the crew escape vehicle 34. For this purpose, the fairing 50 is made up of, for example, an annular row of panels joined in pairs by frangible connections 58 that constitute suitable rupture zones. Three of these panels 50A-50C can be seen in FIGS. 2 and 4. The fairing 50 extends rearward, for example, to a forward fuselage frame R1 extending transversely to the axis 42. Beyond the fairing 50 in the rearward direction, the fuselage 22 is formed, for example, by a cowl or cowl assembly 51, which can be of a conventional type. 2 to 4 also reveal a rear fuselage frame R2 that also extends transversely to axis 42. Fuselage frames R1 and R2 are intended to stiffen the fuselage, in a manner known per se. Frames R1 and R2 are advantageously arranged axially on either side of the location of the center of gravity of crew escape vehicle 34 when the latter is installed in housing 32. Frames R1 and R2 therefore serve to limit the effects of loss of balance.

[0046] The fact that the crew escape vehicle 34 is extracted forward from the reusable orbital vehicle 14, generally in the nominal direction of motion D1 of the reusable orbital vehicle or, if applicable, in the overall nominal direction of motion D1 of the space transportation system 10, enables this extraction not only during the ascent phase, but also while on the launch pad prior to takeoff, as well as during the approach and landing phases and following landing, since the likelihood that the reusable orbital vehicle 14 will have an attitude compatible with such extraction is thus maximized (attitude here means the vehicle's orientation according to the Earth's coordinate system). Forward extraction on the launch pad or during the ascent phase is particularly advantageous because it generally results in the crew departing in a direction opposite to the launcher's propulsion stage 16 and, therefore, to hazards located below the reusable orbital vehicle 14. This is all the more remarkable since escape on the launch pad or during the ascent phase is a case of escape requiring maximum reaction speed, given the general explosive nature of the hazard at this stage.

[0047] To make the escape maneuver tolerable by the crew in terms of apparent load factor while also allowing the crew to withstand the inherent thrust at takeoff, the crew escape vehicle includes, inter alia, seats with modifiable orientation to allow crew members to be oriented to feel thrust at their backs during any critical phase with a high load factor (whether nominal or not) during a possible escape by the crew escape vehicle 34, for example.

[0048] Additionally, the fact that the nose 38 of the crew escape vehicle 34 also serves as the nose 28 for the reusable orbital vehicle has the added advantage of avoiding having to destroy the nose of the reusable orbital vehicle 14 when the crew escape vehicle 34 is extracted from the reusable orbital vehicle. Indeed, it should be understood that when the crew escape vehicle 34 is extracted from the reusable orbital vehicle 14, the crew escape vehicle takes with it the nose 38 that previously served as the nose 28 of the reusable orbital vehicle. This is particularly advantageous because the nose 28 of the reusable orbital vehicle 14 constitutes the forward end part of the vehicle and is therefore subject, among other things, to thermal heating as well as mechanical stresses during the atmospheric re-entry phase. Therefore, the nose 28 of the reusable orbital vehicle 14 must be a particularly heat-resistant and mechanically strong element, e.g., more so than the rest of the fuselage 36. Therefore, not having to destroy such elements when the crew escape vehicle 34 is extracted (an action that is preferably performed as quickly as possible) is a significant advantage.

[0049] In a variant, the reusable orbital vehicle 14 could nevertheless include a nose 28 different from the nose 38 of the crew escape vehicle 34 without departing from the scope of the present disclosure. In this case, it should be understood that the fuselage 22 is closed at its forward end so as to define the nose 28 of the reusable orbital vehicle 14 forward of the nose 38 of the crew escape vehicle 34. In this case, as in the previous case, the housing 32 extends to the forward end of the fuselage 22, which is now defined by the nose 28 formed by the fuselage 22. It should be noted that, similar to the space occupied by the crew escape vehicle 34 in the previous case, the housing 32 can now be considered to extend to the forward end 24 of the reusable orbital vehicle 14, apart from the thickness of the nose 28.

[0050] According to a second aspect of the present disclosure, the crew escape vehicle 34 includes a stabilizing device 59, and more specifically a stabilizing fin 60, which are movable between a retracted position along the fuselage 36 (FIGS. 6 and 7) to allow the crew escape vehicle 34 to be stored in a housing 32 provided for this purpose in the reusable orbital vehicle 14, and a deployed position (FIGS. 8 and 9) towards the rear of the crew escape vehicle, the stabilizing fin 60 being positioned aft of the position of the center of gravity GC of the crew escape vehicle (FIG. 8) to generate a "shuttlecock" effect (also referred to as a "skirt effect").

[0051] The "shuttlecock" effect generally results from the fact that, in ballistic flight, the crew escape vehicle 34 spontaneously orients itself with its nose 38 pointing forward and therefore spontaneously moves in its nominal direction of movement D2.

[0052] Generating such an aerodynamic effect makes it possible to avoid, as far as possible, the crew escape vehicle (which is not designed to generate lift during flight) from suffering from uncontrolled parasitic movements, such as rotational movements about its axis 42, which may be detrimental to the survival of the crew.

[0053] The stabilizing fins 60 are preferably regularly distributed around the axis 42, for example four in number. Configurations with only three of these stabilizing fins 60 (or even five or more) are also possible.

[0054] 6-9 , the stabilizing fins 60 have respective free first ends 62 and respective second ends 64 by which the stabilizing fins 60 are pivotally mounted to the fuselage 36 on respective pivot axes 61 such that the stabilizing fins 60 are movable between their retracted and deployed positions. In the retracted position, the second ends 64 are positioned aft relative to the first ends 62. Additionally, the first edges 66 of the stabilizing fins 60 extend along the exterior surface of the fuselage 36, and the second edges 68 of the fins (opposite the first edges 66) are farther from the exterior surface of the fuselage 36 than the first edges 66. In the deployed position, the first ends 62 of the fins are farther from the exterior surface of the fuselage 36 than when the fins are in the retracted position and are positioned aft relative to the second ends 64. To this end, the pivot axis 61 is advantageously in an orthogonal radial direction containing the axis 42 of the crew escape vehicle 34 .

[0055] The proposed stabilizing fin 60 configuration is particularly remarkable because it makes it possible to obtain a "shuttlecock" effect over a very wide range of flight speeds, ranging from the subsonic to hypersonic regimes, thus covering the range of speeds encountered during space missions involving atmospheric re-entry.

[0056] Deployment of the stabilizing fins 60 is designed to occur as soon as the crew ejection vehicle 34 is extracted from its housing 32. To this end, each of the stabilizing fins 60 is acted upon by elastic means, such as, for example, a torsion spring 69 (illustrated very diagrammatically in FIG. 6 ) acting about the fin's pivot axis 61 so as to permanently bias the fin 60 towards its deployed position. Retention means (examples of retention means will be described hereinafter) make it possible to retain the stabilizing fin 60 in its retracted position as long as the crew ejection vehicle 34 is positioned within the housing 32.

[0057] In the illustrated preferential example, the stabilizing device 59 (in particular the second edge 68 of each of the stabilizing fins 60) protrudes relative to the fuselage 36 in the retracted position.

[0058] This particularity is advantageously utilized to guide the crew escape vehicle 34 during its extraction from the reusable orbital vehicle 14 by means of a guide structure 70 fixed to the fuselage 36, protruding into the housing 32 ( FIGS. 4 , 4A, and 5 ), and configured to constitute a lateral stop for the crew escape vehicle's stabilizing device 59 ( FIGS. 2 , 2A, and 3 ). As will appear more clearly hereinafter, "lateral stop" should be understood to mean a structure forming an obstacle to movements of the stabilizing device 59 in a direction perpendicular to the stabilizing device's midplane (i.e., in the orthogonal radial direction C) (such as, for example, movements resulting from a rotation of the crew escape vehicle 34 about its axis 42).

[0059] In the illustrated preferred example, the guide structures 70 each include rails 72, each centered on a plane RP passing through the axis 42, and each including a groove portion, hereafter referred to as a main groove portion 74, which is, for example, centered on a corresponding plane RP passing through the axis 42.

[0060] The guide structure 70 is preferably further configured to exert an inward radial abutment against the second edge 68 of the stabilizing fin 60 of the crew escape vehicle 34, contributing in whole or in part to centering the crew escape vehicle 34 within the housing 32 and retaining the stabilizing fin 60 in its retracted position.

[0061] To smooth the movement of the crew escape vehicle 34 during extraction of the crew escape vehicle 34, contact between the guide structure 70 and the stabilizing device 59 is advantageously provided by rollers.

[0062] In the illustrated preferential example, the guide structure 70 therefore comprises respective first rollers 76, which are preferably carried by the rail 72 in the vicinity of its forward end. These first rollers 76 each project relative to the bottom 74A of the corresponding main groove 74 (said bottom is visible in FIGS. 2A and 4A) and each comprise, for example, a notch 76A (see FIGS. 2A and 4A) in which the second edge 68 of the corresponding stabilizing fin 60 is engaged, the sides of which constitute lateral stops for the stabilizing fin 60 in accordance with the definition given above, while the bottom of the central notch 76A exerts the above-mentioned radial abutment against the second edge 68 of the fin during the process of extracting the crew evacuation vehicle, as explained above. In a variant, the first roller 76 described above can be replaced by two rollers, with the second edge 68 of the corresponding stabilizing fin 60 sandwiched between the two rollers. Such an arrangement advantageously utilizes the radially outward bias of the fin 60 by the elastic means described above, and the slightly flared nature of the fin 60 radially inward from the second edge 68, to create a wedge effect between the first roller and the side of the fin 60 described above.

[0063] Additionally, the stabilizing device 59 includes second rollers 78 (FIGS. 6 and 7) that are positioned rearward relative to the first rollers 76 when the crew escape vehicle 34 is installed in the housing 32. These second rollers 78 are positioned to engage lateral grooves 80 formed adjacent to the main grooves 74 (FIGS. 2A and 4A) by the rails 72. Each lateral groove 80 is defined by a bottom 80A and two lateral ribs 80B, 80C.

[0064] For example, each stabilizing fin 60 has two associated second rollers 78, which are disposed on each side of the fin, for example, adjacent the rear end of the fin, and which are engaged in two lateral grooves 80 of the corresponding rail 72, respectively.

[0065] The lateral ribs 80B, 80C of the lateral grooves 80 therefore constitute lateral stops for the stabilizing fins 60 in accordance with the definition given above, while the respective bottoms 80A of the lateral grooves 80 form running tracks for the second rollers 78 and thus contribute to the centering of the crew escape vehicle 34 within the housing 32.

[0066] When the crew escape vehicle 34 is extracted, the second rollers 78 follow the forward movement of the crew escape vehicle by running against the bottoms 80A of the respective lateral grooves 80, and finally leave the lateral grooves 80 through the forward ends thereof. Such an arrangement therefore makes it possible to avoid any interference between the first rollers 76 and the second rollers 78, the first rollers 76 being fixed relative to the reusable track vehicle 14 and disposed in the central grooves 74 of the respective rails 72, and the second rollers 78 being carried by the crew escape vehicle 34 and, for example, disposed in the lateral grooves 80 of the respective rails 72, laterally offset relative to the first rollers 76.

[0067] In the illustrated preferred example, the stabilizing devices 59 each include a fixed structure 90 that extends, for example, longitudinally and projects radially relative to the vehicle's fuselage 36. The fixed structures 90 define grooves 92 ( FIGS. 8 and 9 ), into which the first edges 66 of the stabilizing fins 60 are housed in the retracted position. The fixed structures 90 are, moreover, advantageously contoured to contribute to the aerodynamic stabilization of the crew escape vehicle 34 in combination with the stabilizing fins 60 in the deployed position. In addition, the fixed structures 90 strengthen the fuselage 36, which is particularly advantageous in view of the high mechanical stresses that the fuselage must endure during maneuvers to extract the crew escape vehicle. Finally, the fixed structures 90 advantageously have a tapered shape, for example, in the radial and circumferential directions, toward the front of the crew escape vehicle 34, contributing to the fulfillment of the area rule by the crew escape vehicle.

[0068] In the example shown, the second roller 78 is carried by a fixed structure 90 .

[0069] According to another aspect of the present disclosure, the reusable orbital vehicle 14 includes a baffle skirt 100 having a roughly annular shape, e.g., a substantially frustoconical shape, flared in the aft direction, extending into the housing 32 and adapted to surround the fuselage 36 of the crew escape vehicle 34 when the crew escape vehicle 34 is housed therein, while being disposed aft of and axially facing the propulsion means 44 attached to the crew escape vehicle fuselage 36. To this end, the propulsion means 44 (which may, for example, consist of a plurality of rocket engines) is preferably located in the forward part of the fuselage 36, aft of and adjacent to the base of the nose 38.

[0070] The baffle skirt 100 therefore protects the reusable orbital vehicle 14 by diverting the jets of gas produced by the propulsion means 44 at the beginning of a maneuver to extract the crew escape vehicle, thus ensuring its mechanical and structural integrity. During such a maneuver, the roughly aft-splayed configuration of the crew escape vehicle 34 means that aft parts of the vehicle will collide with at least radially inner parts of the baffle skirt 100, causing its fragmentation. The baffle skirt 100 is therefore designed to facilitate such fragmentation by suitable rupture zones defined at the joints between the panels that make up the skirt, for example, in a manner similar to that described above with respect to the fairing 50.

[0071] In the illustrated example, the baffle skirt 100 has an aft end that is connected to the forward fuselage frame R1, which therefore absorbs, among other things, the forces caused by the deflection of the gas jets created by the propulsion means 44.

[0072] In the illustrated example, the stabilizing fins 60 extend forward beyond the baffle skirt 100. The baffle skirt 100 is thus provided with elongated openings 102 in the radial direction R, through which the forward end parts of the fins 60 extend (FIGS. 2A and 4A).

[0073] Alternatively, the propulsion means 44 may be located in the aft part of the crew escape vehicle 34 without departing from the general scope of the present disclosure.

[0074] In light of the above, and therefore, a method for ejecting a crew member from a reusable orbital vehicle 14 of the type described above generally comprises: A) a step of installing the crew of the reusable orbital vehicle 14 in the crew escape vehicle 34; this step A may correspond, inter alia, to the initial installation of the crew in the reusable orbital vehicle 14 before takeoff, in cases where the escape occurs at takeoff or during the ascent phase; in cases where the escape occurs during a subsequent phase of the space mission, step A may consist, inter alia, of the crew returning to the crew escape vehicle 34 after spending time in another part of the reusable orbital vehicle 14, such as the workspace 46; B) Ejecting the crew by moving the crew escape vehicle 34 in said direction D1 to extract the crew escape vehicle 34 from the housing; step B can be performed during any one of the takeoff, ascent, end of atmospheric re-entry, final approach, landing, and post-landing phases of the space mission; It should be understood that the method includes steps consisting of:

[0075] If applicable, the crew escape vehicle 34 takes the reusable orbital vehicle nose 28 with it during step B, as described above.

[0076] If applicable, the crew escape vehicle 34 causes rupture of the frangible connection 58 during step B, as described above.

[0077] If applicable, the crew escape vehicle 34 causes the baffle skirt 100 to rupture during step B, as described above.

[0078] If applicable, the stabilizing fins 60 move from the retracted position to the deployed position during step B, as described above.

[0079] If applicable, and as explained above, crew escape vehicle 34 is prevented from rotating about its axis 42 during step B by guide structure 70. [Explanation of symbols]

[0080] 10 Space Transportation Systems 12 Space Launcher 14 Reusable Orbital Vehicles 16 propulsion stage 22 Torso 24 Front end 26 Rear end 27 Midline Longitudinal Axis 28 Nose 30 Propulsion means 32 Housing 34 Crew Escape Vehicle 36 Torso 38 Nose 39 Front end 40 Rear wall 42 axis 44 Propulsion means 46 workspace 48 Airlock 50 fairing 50A~50C Panel 52 Front end 54 Opening 56 steps 58 Fragile Connections 59 Stabilizing Device 60 stabilizing fins 61 Pivot axis 62 First end 64 Second end 66 First edge 68 Second Edge 69 Torsion Spring 70 Guide structure 72 Rail 74 Main groove 74A bottom 76 First Roller 76A Notch 78 Second Roller 80 Lateral groove 80A bottom 80B horizontal rib 80C horizontal rib 90 Fixed Structures 92 Groove 100 baffle skirt 102 Opening C Orthogonal radial direction D1 Nominal direction of travel D2 Nominal direction of movement GC center of gravity P Longitudinal midplane R Radial direction R1 forward fuselage frame R2 rear fuselage frame RP plane

Claims

1. 1. A reusable orbital vehicle (14) for a space transportation system (10), the reusable orbital vehicle (14) including a fuselage (22) having a shape that widens in a direction from a forward end (24) of the reusable orbital vehicle (24) toward an aft end (26) of the fuselage (22), a housing (32) defined within the fuselage (22) that extends to a forward end (52) of the fuselage (22), and the crew escape vehicle (34) contained within the housing (32) in a state oriented for extraction from the housing (32) from the aft end (26) of the fuselage (22) toward the forward end (24) of the reusable orbital vehicle (14).

2. the fuselage (22) includes a fairing (50) surrounding the housing (32) and extending flared from the forward end (52) of the fuselage (22) toward the aft end (26) of the fuselage (22), the fairing (50) being truncated to define an opening (54) emerging into the housing (32); 2. The reusable orbital vehicle of claim 1, wherein the crew escape vehicle includes a fuselage having a nose extending through the opening to define the nose of the reusable orbital vehicle.

3. The reusable orbital vehicle of claim 2, wherein said nose (38) extends in aerodynamic continuity with said fairing (50).

4. 3. The reusable orbital vehicle of claim 2, wherein the fuselage (36) of the crew escape vehicle (34) has a step (56) formed at the base of the nose (38), and the forward end (52) of the fairing (50) is positioned axially facing the step (56).

5. 3. The reusable orbital vehicle of claim 2, wherein the fairing (50) is formed by an annular array of panels (50A-50C) joined in pairs by frangible connections (58) that define suitable rupture zones.

6. 2. The reusable orbital vehicle of claim 1, wherein the reusable orbital vehicle includes a baffle skirt (100) having a generally frusto-conical shape, extending into the housing (32) to surround the crew escape vehicle (34) and to be disposed aft, and facing axially toward a propulsion means (44) of the crew escape vehicle configured to generate thrust in the direction (D1).

7. 10. A method for evacuating a crew member of a reusable orbital vehicle (14) as recited in claim 1, comprising: A) installing the crew of the reusable orbital vehicle (14) into the crew escape vehicle (34); and B) evacuating the crew by moving the crew escape vehicle (34) in the direction (D1) so as to extract the crew escape vehicle (34) from the housing (32); A method comprising the steps of:

8. 8. The method of claim 7, wherein the reusable orbital vehicle is a reusable orbital vehicle as defined in claim 2, and wherein the crew escape vehicle takes the nose of the reusable orbital vehicle with it during step B.

9. 8. The method of claim 7, wherein the reusable orbital vehicle is a reusable orbital vehicle as defined in claim 5, and the crew escape vehicle causes rupture of the frangible connection during step B.

10. 8. The method of claim 7, wherein the reusable orbital vehicle is a reusable orbital vehicle as defined in claim 6, and wherein the crew escape vehicle causes the baffle skirt to rupture during step B.

11. 8. The method of claim 7, wherein step B is performed during any one of takeoff, climb, end of atmospheric re-entry, final approach, landing, and post-landing phases.

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