Modular, poolable multi-launcher launch pad

Abstract

A multi-launcher space launch assembly includes a movable platform for the assembly, transporting, and vertical positioning of varied launchers. The platform cooperates with a fixed table and a jet deflector, which are situated in a launch area. The infrastructure also includes adaptable fluid refuelling modules compatible with various flow and pressure profiles. The system is adapted to accommodate variations in the height and diameter of launchers by way of modular components.

Description

Modular and shareable multi-launcher firing range Scope of the invention

[0001] The present invention relates to the field of space launch infrastructure, and more particularly to launch complexes enabling the accommodation and operation of different types of space launchers within the same installation. State of the art

[0002] Traditionally, space launch systems are designed specifically for a given launch vehicle. Each launch vehicle is associated with a complete launch complex, including an assembly building, a launch pad, refueling facilities, support infrastructure (electricity, air conditioning, water treatment), and a control center. This approach leads to a proliferation of infrastructure when several types of launch vehicles wish to use the same launch site. It also requires significant available land, often difficult to expand, which hinders the development of a more diversified and adaptable space activity.

[0003] In practice, expanding existing infrastructure is particularly complex and costly (land requirements, environmental impacts, risks to local populations). The need for specific facilities for each launcher model leads to a duplication of equipment and resources, resulting in a rapid increase in installation and operating costs. Furthermore, for an operator wishing to deploy its launchers at different sites, the required investments increase considerably due to the need to adapt or rebuild dedicated launch complexes.

[0004] Faced with these drawbacks, there is a growing need for solutions to optimize the use of space infrastructure. In particular, it would be beneficial to be able to share launch equipment for various launch vehicles while maintaining flexibility to accommodate the specific technical requirements of each. Such a solution would not only reduce the required surface area but also streamline the costs of constructing, maintaining, and operating launch sites.

[0005] The present invention therefore aims to provide a multi-launcher system, designed from mostly common elements, capable of accommodating different types of launchers while effectively adapting to their specific constraints.

[0006] To this end, a launch assembly designed to accommodate different types of space launch vehicles is proposed according to a first aspect of the present invention. A launch structure can be understood as a device designed to support launch vehicles, generally large and complex, throughout their integration, transport, and launch processes. This launch structure aims to guarantee optimal stability of the launch vehicle during all critical stages prior to its actual launch.

[0007] It may be envisaged that this launch structure will include a mobile launch platform, capable of receiving a launcher in a first configuration for assembly and transport from an integration area to a launch area, and of positioning and maintaining the launcher in a second configuration.

[0008] A mobile launch platform can be understood as a surface or vehicle on which a launcher is placed, thus enabling flexible transport and precise positioning. One advantage of this feature is that it promotes efficient and safe handling of the launcher during the transport and positioning phases, while also facilitating fine adjustments to optimize stability and safety before launch.

[0009] This launch structure may also be designed to include a fixed table configured to integrate the mobile launch platform. In this context, a fixed table is defined as a stable support that maintains the mobile launch platform in a stable and precise position during launch. This fixed table helps ensure that the platform and the launcher remain in a precise and stable configuration, thus limiting the risk of mechanical malfunctions or deviations that could impact the ground-to-aircraft links and affect the launch.

[0010] A jet deflector can also be positioned at the bottom to divert and channel the gas and heat flows generated during rocket engine ignition. One of the advantages of such a deflector is that it not only protects the launch structure from potential damage due to intense heat and pressure, but it also allows for better management of heat dissipation, thus extending the lifespan of the equipment and reducing launch-related risks.

[0011] The mobile launch platform may be designed to include a main mechanical frame forming a base that integrates fluid lines, cable trays, and ventilation systems for connection to the launcher. This main mechanical frame is a robust support structure that serves as the foundation for the system. Such a frame ensures the overall platform's stability and allows for the orderly and secure integration of all systems necessary for the launcher's proper operation, including fluid lines, electrical cables, and ventilation ducts. A major advantage of this feature is the optimization of space and resource management, thereby reducing the risk of malfunctions due to a poorly designed installation.

[0012] This platform may also be designed to include retention systems attached to the main mechanical frame, intended to longitudinally position and secure the launcher. These retention systems can be viewed as locking or fastening devices that ensure the launcher remains stable throughout the launch process. An advantage of this feature is that it guarantees the launcher is correctly held in position during all critical stages, while also being easily adjustable to suit the launcher's specific configuration. This stability is essential to prevent any unwanted movement that could endanger the launcher (and its launch area) or alter the launch trajectory.

[0013] This launch platform may also be designed to include a mast. A mast is a vertical structure that supports mounting or positioning devices. The mast can be used to increase the height of the launch platform and provide additional anchor points for securing the launcher. One of the advantages of a mast is that it allows for greater flexibility in adapting the launch platform to different types of launchers, while maintaining optimal stability.

[0014] It may also be planned that this launch platform will include integration cradles fixed to the mast, designed to align and support the launcher during its assembly in the first configuration and until its positioning in the second configuration. The integration cradles are supports intended to hold the launcher during assembly and transport. The advantage of an integration cradle is that it offers a stable and secure means of precisely aligning the launcher, while minimizing the risk of mechanical damage due to unexpected movements during the assembly or transfer phase.

[0015] This launch platform may be designed to include upper support arms, intended to stabilize the upper part of the launcher during transfer and against wind once it is in a vertical position on the launch pad. These upper support arms are mechanical devices that secure the launcher at strategic points during transfer and until the final moments before launch. A key advantage of these support arms is that they stabilize the upper part of the launcher, which is often more vulnerable to movement and oscillations, thus minimizing the risk of damage to this critical component.

[0016] This launch platform may also be designed to include adjustable retention systems that allow the launcher's attachment and support to be adapted to its height and diameter. These adjustable retention systems are mechanical components that allow the position or size of the attachment points to be modified to accommodate various launcher configurations. The advantage of this feature is that it offers great flexibility in using the same launch structure for different types of launchers, while ensuring secure and customized support for each type of spacecraft.

[0017] The flexibility of the mobile launch platform allows for versatile use, thus reducing the need to build dedicated infrastructure for each type of launcher, resulting in a significant reduction in costs.

[0018] The platform's ability to switch from an initial configuration for assembly and transport to a second configuration for launch optimizes logistics operations and minimizes the time between assembly and launch.

[0019] Thus, each element of this launch structure contributes to creating a safe, adaptable and optimized environment for the handling and launch of different types of space launch vehicles, allowing for better resource management and a reduction of technical risks during the complex space launch process.

[0020] It may be provided that the launch assembly includes a jet deflector that can be moved between a rearward and a forward position.

[0021] The mast can be designed to consist of modular sections, allowing its height to be adjusted according to the launcher's height. A mast made of modular sections can be understood as a vertical structure composed of detachable or assemblable segments that allow the overall height to be adjusted to meet the specific needs of each launcher. This feature provides flexibility in adapting the launch structure to different types of launchers with varying heights.

[0022] One of the advantages of this feature lies in its ability to quickly customize the launch structure to accommodate launchers of varying sizes. By adjusting the mast height to suit the specific launcher, it is possible to optimize space and stability during the launch process, reducing the risk of imbalance or instability that could result from a mast that is too short or too high for a given launcher. This modular system also offers greater logistical and operational flexibility, allowing for versatile use of the same platform for different types of space missions. This can translate into cost savings and reduced time required to adapt the launch structure to each mission.

[0023] The launch assembly may be designed to include adjustable retention systems, comprising a radial support system to accommodate different launcher diameters. A radial support system can be understood as a set of supports arranged around the launcher, capable of being adjusted to accommodate variations in its diameter. This feature ensures that the launcher is held securely, regardless of its size or specific characteristics.

[0024] According to a second aspect of the invention, a method is proposed for implementing a launch assembly intended to accommodate different types of space launchers according to the first aspect of the invention, or one or more of its improvements.

[0025] The first step may involve assembling a launcher onto a mobile launch platform in an assembly configuration. Assembling a launcher onto a mobile launch platform can be understood as the process of securing and preparing the launcher onto a mobile structure that will subsequently facilitate its transport and positioning. One of the advantages of this step lies in the possibility of performing the assembly in a dedicated integration area, thus optimizing conditions for a safe and controlled assembly.

[0026] Next, the mobile launch platform with the assembled launcher can be moved to a launch site using a trailer. In this context, a trailer can be understood as a vehicle specifically designed to transport the mobile launch platform and launcher. A major advantage of this step is that it allows for the efficient and safe movement of the assembled launcher from one site to another, while ensuring stability and safety during transport. This reduces the risks associated with uncontrolled movements that could affect the integrity of the launcher before launch.

[0027] It may also be possible to coordinate the mobile launch platform with a fixed table to position the launcher for launch. This cooperation can be understood as the action of stabilizing and securing the launcher on the fixed table, thus ensuring its optimal position for launch. One of the advantages of this step is that it ensures a smooth and precise transition between transporting the launcher and its final positioning on the fixed table, guaranteeing the launcher's stability and safety before liftoff. This also optimizes the launcher's alignment, minimizing the risk of errors that could occur during the positioning and / or erection process.

[0028] Thus, each step of the process helps to simplify, secure and optimize the process of implementing a launch assembly, allowing increased control over each phase of the operation, from assembly to positioning the launcher for launch.

[0029] The process may include a step where the launcher is assembled on integration cradles that support it horizontally on the main mechanical frame of the mobile launch platform. One advantage of this step is that it allows the launcher to be assembled in a horizontal configuration, ensuring greater stability and ease of handling. This arrangement optimizes the assembly process, as it allows easier access to the various parts of the launcher while reducing the risk of deformation or damage during assembly.

[0030] The process may also include a step of longitudinally securing the launcher to the mobile platform using the mobile launch platform's retention systems. An advantage of this step is that it ensures the launcher is securely fixed and stabilized during all critical phases, particularly during the movement of the mobile platform and the positioning of the launcher, thereby reducing the risk of displacement or instability that could occur during the launch phases.

[0031] The process may include a step involving the transport of the mobile platform on a trailer to the launch site. In this context, a trailer is a vehicle designed to transport the mobile platform and launcher to the launch site. An advantage of this step is that it allows for the easy and safe movement of the mobile platform and launcher, while ensuring that the structure remains stable and controlled during transport. This reduces the time and costs associated with moving the launcher to the launch site, while minimizing the risk of damage during transport.

[0032] It may also be planned that the launch positioning process will include a stage of tilting the launcher from a horizontal to a vertical position using a tilting mechanism associated with the fixed receiving infrastructure. A tilting mechanism is a device designed to tilt or rotate the launcher from a horizontal to a vertical position to prepare it for launch. One of the advantages of this stage is that it allows for a precise and controlled transition between the different launcher configurations, ensuring that the launcher reaches the optimal launch position while maintaining the stability of the entire platform. This helps reduce the risks associated with an imprecise tilting that could compromise the safety and integrity of the launcher. Brief description of the figures

[0033] Other features and advantages of the invention will become apparent during the reading of the detailed description which follows, for the understanding of which reference will be made to the attached drawings on which: illustrates a schematic overview of an overall launch assembly according to the invention, comprising the integration area, the mobile launch platform and the launch area; illustrates a general view of a propellant storage;illustrates a general view of the launch area; illustrates an overall view of a launch structure; illustrates a general view of a mobile launch platform; illustrates a general view of a launcher assembly on the mobile launch platform; illustrates a general view of the mobile launch platform in its transfer configuration; illustrates a general view of the launch platform's table and deflector configuration; illustrates a view of the mobile launch platform during the table insertion stage; illustrates a view of the mobile launch platform during the verticalization stage; illustrates a view of the mobile launch platform in a pre-lift configuration; illustrates a mobile launch platform mast configuration according to the launcher's height; illustrates a support structure within the pallet; and illustrates examples of retention system configurations. Detailed description of the invention

[0034] An embodiment of an overall launch assembly 1 of a launcher 2 according to the invention is now described.

[0035] The overall launch complex 1 includes: an integration area 3 allowing the assembly of a launcher, propellant storage areas S1, S2, a launch area 4, and an operations control station 5.

[0036] As illustrated on, the propellant storage areas S1, S2 are located at a sufficient distance from launch area 4, with regard to the risk of possible explosion.

[0037] Depending on the propulsion technology used, the installation includes at a minimum the oxidizer propellant storage area S1, generally liquid oxygen. The installation may be supplemented by the fuel propellant storage area S2, such as liquid methane, kerosene, etc.

[0038] Each propellant storage area includes a connection and flow management module. n -1, to which propellant tanks S are connected n -2, as well as a support tank for pressurization S n -3, generally nitrogen gas.

[0039] The Sn-1 connection and flow management module allows for the connection and management of tanks of appropriate size and quantity depending on each launcher.

[0040] The output flow (fluid flow rate and pressure) is also adjustable to adapt to different types of launchers. If necessary, a flare stack S n -4 allows the excess gas collected by the connection module to be burned.

[0041] As illustrated on, on launch area 4 there are various means of proximity P1, P2 and a launch structure 6.

[0042] The proximity means P1, P2 include in particular: a terminal part of the propellant management modules, modules enabling the delivery of other necessary fluids (helium, butane, ...), and a "deluge" water management module.

[0043] Depending on the configuration of the launch site, the distribution of modules around the launch structure 6 can be adjusted.

[0044] Launch structure 6 is a part that allows it to interface with launcher 2, to connect it to proximity means P1, P2, and to give access to operators.

[0045] As illustrated above, the launch structure 6 consists mainly of: a mobile launch platform 61 on which the launcher 2 is integrated in a first horizontal configuration for assembly and transport and allowing it to be transported from an integration area to the launch area 4 and to maintain the launcher in a second vertical configuration until takeoff; a fixed table 62 on which the mobile launch platform 61 is positioned; an access platform 63 giving access to the base of the launcher 2 once it has been put in the vertical position; and a jet deflector 64 allowing the jet flow from the launcher 2 to be channeled and diverted in the first moments of takeoff.

[0046] As illustrated, the mobile launch platform 61 comprises: a main mechanical frame 611 serving as support for the other components below, as well as for fluid lines, cable trays, ventilation, ...; retention systems 612 fixed to the main mechanical frame 611 allowing the launcher 2 to be positioned longitudinally and held until the launch order is issued; a mast 613; integration cradles 614 fixed to the mast 613 allowing the launcher 2 to be aligned and supported during its horizontal assembly and until it is placed vertically on the launch area 4; upper support arms 615 ensuring the stability of the upper part of the launcher 2 during the transfer and until the start of the final sequence before takeoff.

[0047] The jet deflector 64 can be moved between a rearward and a forward position.

[0048] As illustrated, initially, the mobile launch platform 61 is in a horizontal position in an assembly building in the integration area 3. The upper support arms 615 are open and the launcher 2 is placed on the integration cradles 614. The various elements of the launcher 2 are thus positioned, aligned and assembled together.

[0049] Once the launcher is fully assembled, the upper support arms 615 are closed to secure the launcher 2 and the retention systems 612 are locked.

[0050] If necessary, the 614 integration cradles that have become unnecessary are removed.

[0051] The connections between the mobile launch platform 61 and the launcher 2 are also made and tested.

[0052] As illustrated on, during this phase, the mobile launch platform 61 is placed on ground supports 7 allowing space to be maintained from the ground and permitting the placement of a flatbed trailer 8.

[0053] The flatbed trailer 8 is equipped with a platform height adjustment system. Once in position, it can therefore lift the mobile launching platform 61 in order to release the supports 7 for removal.

[0054] As illustrated, on the launch area, the fixed table 62 and the jet deflector 64 are configured to accommodate the mobile launch platform 61. Verticalization arms 621 of the table 62 are in the lowered position, and a rear gate 622 of the table 62 is open. The jet deflector 64 is in the forward position to allow sufficient space for a tractor vehicle and its trailer 8.

[0055] As illustrated, once in the launch zone, tilting axes of the mobile launch platform 61 are placed in pivot interfaces 623 of the fixed table 62. Verticalization brackets A5 of the mobile launch platform 61 then arrive at the level of the verticalization arms 621.

[0056] With reference to the, the verticalization arms 621 are then unfolded in order to tilt the mobile launching platform 61. The tractor vehicle can then be removed.

[0057] At the end of this step, the rear gate 622 is closed in order to support the rear part of the mobile launch platform 61 and the deflector 64 is put back into position under the launcher.

[0058] Connections between proximity means and the launcher can then be made via access platform 63.

[0059] With reference to the, the system is then ready to begin the launch operations. A few moments before takeoff, the upper support arms 615 are opened and the mast of the mobile launch platform 61 is tilted backward to clear the trajectory of the launcher 2. The tilting of the mast 613 is done by gravity, by bringing the verticalization arms 621 back.

[0060] When the takeoff order is received, the 612 retention systems open and release the launcher for takeoff.

[0061] Following the reverse operational logic, the mast 613 of the mobile launch platform 61 is returned to the vertical position by the verticalization arms. The mobile launch platform 61 can then be disconnected from the proximity equipment, the rear gate 622 of the table 62 is opened, the jet deflector 64 is advanced, and the tow truck 9 is returned to position. The mobile launch platform 61 is then lowered to a horizontal position, freed from the fixed table 62, and returned to the assembly building.

[0062] The multi-launcher compatibility of the launch assembly according to the invention is now being demonstrated.

[0063] In terms of fluids, compatibility with multiple launchers relies in particular on modules capable of managing flow rates, pressures, etc., covering a wide range of needs. The combination of modules implemented allows for the handling of the different types of fluids required for each launcher.

[0064] This architecture therefore allows for compatibility with several launchers, with mostly shared resources. Only the final connection to the launcher will need to be adapted according to the vehicle's specifications.

[0065] Regarding the control system, the integration is relatively straightforward. It is, in fact, possible to define a standardized communication protocol exchanging generic commands. For example: "Fill x liters of LOX at a flow rate 'q' and a pressure 'p'." This instruction is directly interpreted and processed by the relevant module, without the operator needing to understand the operational details.

[0066] At the mechanical level, the compatibility issues only affect the mobile launch platform 61. The fixed table 62 and the deflector 64 not being in direct interface with the launcher, they can be defined independently to cover the maximum required.

[0067] With reference to the, the height of launcher 2 is managed by adding 613n extensions in a quantity adapted to the base section of the 613 mast.

[0068] With reference to the, to adapt to the diameter of the launcher, radial retention systems S are arranged radially on a pallet P around a hole allowing the evacuation of the flow from the launcher's engines 2.

[0069] The number and position of the 612 retention systems can thus be adjusted according to need. If necessary, additional supports are added between the base of the mobile platform and the retention systems to compensate for the overhang.

[0070] The diagram illustrates different retention configurations, one with 3 retention systems spaced at 120° angles, and a second with 6 retention systems spaced at 60° angles. Other configurations are possible: for example, a configuration with 4 retention systems spaced at 90° angles.

[0071] The retention system mechanism is sized based on assumptions about the largest launcher considered. Only the part that interfaces with the launcher is designed specifically for it.

[0072] At the integration cradle level 614, the section containing the adjustment systems (actuators, guide rails, etc.) is defined independently of the launcher and designed to be as compact as possible. This positioning assembly 6141 is dimensioned with the maximum mass and travel and is therefore common to all launchers.

[0073] To accommodate different diameters, only a specific interface piece 6142 is required. Depending on the distance between the launcher and the mast, an additional support 6143 may be added.

[0074] The 6141 positioning assembly or the 6143 support is fixed to the mast via a clamp system, allowing it to be freely positioned at the desired location along the mast.

[0075] Pooling the entire launch infrastructure reduces investment and operating costs for launch sites by limiting infrastructure duplication.

[0076] The modularity of the system allows for rapid and economical adaptation to different types of launchers, while ensuring high operational flexibility.

[0077] Standardizing fluid supply methods reduces launch preparation times and increases safety.

[0078] Finally, the transportable design of certain elements facilitates the deployment of the infrastructure on different sites, thus increasing the attractiveness of the whole for a wide range of space operators.

[0079] Of course, the different features, variants and embodiments of the invention can be combined with each other in various ways as long as they are not incompatible or mutually exclusive.

Claims

A launch assembly designed to accommodate different types of space launchers, comprising: a mobile launch platform (61) capable of receiving a launcher (2) in a first configuration for assembly and transport from an integration area (3) to a launch area (4), and of positioning and maintaining the launcher (2) in a second configuration; a launch structure (6) in the launch area (4), comprising a fixed table (62) arranged to cooperate with the mobile launch platform (61); and a jet deflector (64) arranged to channel and deflect the jet flow from the launcher (2); the mobile launch platform (61) comprising: a main mechanical frame (611) forming a base integrating within it fluid lines, cable trays and ventilation intended to be connected to the launcher (2);adjustable retention systems (612) fixed to the main mechanical frame (611) intended to longitudinally position the launcher (2) and hold it, a mast (613); integration cradles (614) fixed to the mast (613) intended to align and support the launcher (2) during its assembly in the first configuration and until its positioning in the second configuration, upper support arms (615) intended to stabilize an upper part of the launcher (2) during transfer,; Launching assembly according to claim 1, comprising a jet deflector (64) movable between a rearward position and an advanced position. Launching assembly according to any one of the preceding claims, wherein the mast (613) is made up of modular sections allowing the height of the mast to be adjusted according to the height of the launcher (2). Launch assembly according to any one of the preceding claims, wherein the adjustable retention systems (612) include a radial support system for adapting to different launcher diameters (2). A method for implementing a launch assembly designed to accommodate different types of space launchers according to any one of the preceding claims, comprising the steps of: (C1) assembling a launcher (2) onto a mobile launch platform (61) in an assembly configuration, (C2) moving the mobile launch platform with the assembled launcher to a launch area (4) using a tractor vehicle and a trailer (8), (C3) cooperating the mobile launch platform with a fixed table (62) in order to put the launcher (2) into the launch position, Method according to claim 5, comprising a step where the assembly of the launcher (2) is carried out on integration cradles (614) supporting the launcher in a horizontal position on the main mechanical frame (611) of the mobile launch platform (61). Method according to any one of claims 5 or 6, comprising a step of longitudinally fixing the launcher (2) on the mobile platform (61) by means of the retention systems (612) of the mobile launch platform (61). Method according to any one of claims 5 to 7, comprising a step of moving the mobile platform (61) on a trailer (8) to the launch area (4). A method according to any one of claims 5 to 8, wherein the launching positioning includes a step of tilting the launcher from a horizontal position to a vertical position by means of a tilting mechanism associated with the fixed receiving infrastructure.

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