MXPA06004906A - Payload launching system - Google Patents

Abstract

This invention relates to a system for launching a payload. A rotating flywheel (11) accelerates a traditionally designed rocket (16) to a significant speed. Rotational energy from the flywheel (11) is transferred in the form of kinetic energy through a spiral surface and a cable (14) to the rocket (16). The system comprises a smaller rocket (16) carrying less fuel, provided with a smaller first stage engine. All other components of the system are re-used. This leads to a simpler and more efficient design of the rocket (16) and to a considerable reduction in launch costs.

Description

UTILITY LOAD LAUNCH SYSTEM DESCRIPTIVE MEMORY This invention relates to a payload launching system for accelerating a rocket carrying or not carrying a payload, particularly but not exclusively, to reduce launch costs. In WO 0162534 a system of acceleration comprising a wheel rotatable about an axis and a cable, an end portion which is adapted to engage and release a load and an end portion remote which can engage the described steering wheel in motion. The flywheel is provided with a surface for receiving a portion of the remote cable from said end portion and the surface has a curved profile whose radial dimension progressively increases from said axis in an arched direction of said axis. Once the remote end portion of the cable engages the flywheel, the remote end portion of the cable then remains restricted near the center of the flywheel and the cable is wound along the curved profile, accelerating the load. The acceleration system provides a good solution for accelerating a heavy load with uniform acceleration and can be used to accelerate an aircraft at takeoff speed.

However, the throttle system does not describe a practical way to accelerate a rocket that may be attached to the cable, considering that the top part of the rocket usually comprises a conical cap rather light construction and sometimes a payload such as a satellite detection remote One objective of the payload launch system is to accelerate a rocket. In accordance with the present invention is provided a launching system payload comprising a cable, an end portion of which is adapted to engage and release, with a rocket, a rotary member adatado for rotation on an axis and drive means for coupled and uncoupled and uncoupled with rotating member to rotate the rotating member in the characterized axis that the rotatable element is provided with a surface for receiving a portion of the cable remote from the said end portion and the surface has a curved profile the radial dimension increases progressively of said axis in an arched direction of said axis. Means are also provided for coupling said remote end portion of the cable with the rotating element while it is rotating. The system also comprises a number of transfer means in the remote end portion of the cable that transfers the attractive force of the cable to the rocket at structurally appropriate locations in the rocket during acceleration. Below is a description as an example only and with reference to the accompanying drawings, of a method of putting the invention into practice. In the drawings: Figure 1 is a diagrammatic perspective view showing the preferred embodiment of a payload launching system at the start of acceleration. Figure 2 is a diagrammatic perspective view showing the preferred embodiment of a payload system at the end of the acceleration. Figure 3 is a diagrammatic perspective view showing the preferred embodiment of a launching system useful one moment after acceleration. Figure 4 is a diagrammatic perspective view showing another embodiment of a payload launching system at the start of acceleration. Figure 5 is a perspective view in diagram showing the rotating element at the beginning of the acceleration. Figure 6 is a diagrammatic perspective view showing the rotating element at the end of the acceleration. Figure 7 is a diagrammatic perspective view of the rocket and transference means during acceleration.

Figure 8 is a diagrammatic perspective view of the internal structure of the rocket and the transfer medium during acceleration. Now referring to figure 1, Figure 2 and Figure 3 of the drawings, which are diagrammatic conceptual representations, describe a modality of a payload launching system (10) comprising a wheel (11) rotatably mounted on an axis (12) and driven to rotate on the shaft (12) by means of a power source (not shown) that acts on the wheel (11). The wheel (11) is provided with a surface (13) for receiving the cable (14). The surface (13), when viewed axially of the axis (12), has a curved formation whose profile extends longitudinally of the surface (13) and in the radial direction from the axis (12) increases progressively from the axis (12) in arched direction of the shaft (12). A series of transfer means (15) are provided to the other end of the cable (14). The transfer means (15) is designed in such a way as to transfer the attractive force of the cable to the rocket (16) at appropriate locations in the structure of the rocket during acceleration. Figure 8 shows an example of the design of transfer media and the locations in the rocket structure where they are capable of transferring the attractive force of the cable to the rocket. Means (not shown) are provided to push an end portion of the cable (14) toward the wheel (11), in the axial direction of the wheel (11), so that the distal end of the remote rocket cable (14) (16) is restricted near the center of the wheel (11) and the end portion of the cable (14) is located on the profiled surface (13). In a starting position an end portion of the cable (14) is kept away from the profiled surface (13) of the wheel (11). The power source is then operated to rotate the wheel (11). When the rotational energy is sufficient to provide energy to accelerate the transfer means (15) and the rocket (16), then said means is operated to push the distal end of the cable (14) towards the wheel (11) so that the distal end of the remote cable (14) of the rocket (16) is restricted near the center of the wheel (11) and the end portion of the cable (14) is located on the profiled surface (13). The effect of the profile of the surface (13) is such that the cable (14) attracts the transfer means (15) and the rocket (16) in a direction towards the cable (11), initially a low speed and then a speed that increases progressively as the distance of the profile of the surface (13) of the shaft (12) increases. Now referring to Figure 4 of the drawings which is a diagrammatic conceptual representation there is shown a modality of a payload launch system (20) in accordance with the present invention for accelerating a rocket. The system comprises a wheel (21) rotatably mounted on an axis (22) and driven to rotate on the shaft (22), by means of a power source acting on the wheel (21). The wheel (21) is provided with a surface (23) for receiving a cable (24). The surface (23), when viewed axially of the axis (22), is of a curved formation whose profile extends longitudinally of the surface (23) and in a radial direction of the axis (22) increases progressively from the axis (22) in the arched direction of the shaft (22). The other cable end portion (24) rotates in an additional rotating element (25), which is adapted for rotation in a second axis (26). A second cable (27) is attached to one of its end portion to the additional rotating element (25) and is connected at its other end portion to the rocket (29). Means (not shown) are provided to push an end portion of the cable (24) toward the wheel (21), in the axial direction of the wheel (21). In a starting position, an end portion of the remote cable (27) of the additional rotating element (25) is connected to the transfer means (28) while the distal end of the cable (24) is kept away from the profiled surface. (23) of the wheel (21). The power source is then operated to rotate the wheel (21). When the rotational energy is sufficient to provide energy to accelerate the transfer means (28) and the rocket (29), then the said means operates to push the distal end of the cable (24) towards the wheel (21) so that the end portion of the remote cable (24) of the additional rotating element (25) is restricted in the center of the wheel ( 21) and the distal end of the cable (24) is located on the profiled surface (23). The arrangement is such that the additional rotary element (25) has a lighter construction than the wheel (21) and can be arranged to accommodate the length of the cable (27) more easily than the profiled surface (23).

Now referring to FIG. 5 and FIG. 6 of the drawings, which are diagrammatic conceptual representations, there is shown a system (30) that operates in accordance with the principle described with reference to FIG. 1, FIG. 2 and FIG. 3 of FIG. the drawings. The energy source, the rocket and the transfer medium are not shown. The distal end of the cable (33) is provided with a ball (35). The cable (34) is heretofore kept away from the wheel (31), rotating on the shaft (32), and is now pushed by the said coupling means in the axial direction towards the wheel (31) to locate the ball (35). ) in the space provided in the wheel (31) located adjacent to a center of the wheel (31). The ball (35) is now restricted with the rotating wheel (31) and pulls the cable (34) therewith. As the wheel (31) continues its rotation, the cable (34) is located on the surface with curved profile (33), accelerating the rocket. In Figure 6, the rotating wheel (31) is now in a final position of the operation of the payload launching system; the wheel (31) has completed about one and a quarter of a full rotation and the cable (34) are rolled on the surface with curved profile (33) and the acceleration is completed. The rocket then continues its trajectory and the wheel (31) continues its rotation with its remaining rotation energy. Figure 7 is a diagrammatic perspective view of the rocket (16, 29) and the transfer means (15, 28) attached to the cable (14, 24) during acceleration.

Now referring to Figure 8 of the drawings, there is shown a view of a traditionally designed rocket comprising, in this particular example, two stages and, in this particular example, two engines operating with liquid oxygen and liquid hydrogen; a first stage, comprising a first stage engine, a fuel tank containing liquid hydrogen (H), a fuel tank containing liquid oxygen (O), and a second stage, comprising a second stage engine, a fuel tank containing liquid hydrogen (H), a fuel tank containing liquid oxygen (O). The rocket also comprises a payload such as a remote sensing satellite and a conical cap on the upper part, which surrounds and protects the payload and provides good aerodynamic characteristics to the rocket. Two of a number of transfer means are shown by transferring the attractive force from the cable to the rocket at points located, in this particular example, after the first stage and after the second rocket stage.

Advantage of the payload launch system The transfer means are capable of transferring the attractive force of the cable to the rocket at appropriate locations in the structure of the rocket. Any type of rocket can be used with the payload launch system but it is possible, in particular, to use a traditionally designed rocket. This traditional design, shown in Figure 8, is the most efficient for most applications. The transfer means transfer the force of attraction of the cable to the rocket after the front of the rocket. The rocket starts its trajectory with a significant speed. Since significant energy is imparted to the rocket at the start of the launch, a smaller rocket, carrying less fuel, energized by a smaller first-stage engine can be used. This leads to a simpler and more efficient design of the rocket and allows, for example, to choose those fuels that have a higher specific impulse and are more expensive to produce, since they are used in smaller quantities. All this leads to a more efficient operation and considerably lower costs.

Disadvantages of payload launch system The conical shell on the top of the rocket and the structure of the rocket support higher loads due to the higher speed in the denser and lower layers of the atmosphere. The conical cap and the rocketHowever, due to their corresponding geometric structures, they can be reinforced efficiently. In several preferred embodiments of the charge release system: A particular embodiment of the payload launching system may also include means for disconnecting the cable (14, 24) from the transfer means (15, 28). In another particular embodiment of the payload launching system, these means include an explosive device. A particular embodiment of the payload launching system may also include detection means for detecting the passage of the rocket at a chosen point and operating means for disconnecting the cable (14, 24) of the transfer means (15, 28). These detection means can be located in the system or from the ground. A bucket can also be used with the payload launch system; the wheel could be on top of the bucket and the rocket in a starting position near the bottom of the bucket. Or the wheel may be on top of a structure and the rocket in a starting position on the ground or at the bottom of a cube located under the structure. A structure that rests on a volume of liquid such as water and that provides enough space for the rocket to move within it during acceleration can be used with the payload launch system. This structure can be placed in the most appropriate location and latitude. In a particular embodiment of the payload launching system, the transfer means does not continue with the rocket; the rocket continues its trajectory on its own as shown in figure 3. In one embodiment, the transfer means are designed to move away from the rocket some time after acceleration.

In another embodiment, the transfer means are attached to the rocket at some points of the rocket and means are provided to detach the transfer means. In another embodiment, the means for detaching the rocket transfer means includes an explosive device. A particular embodiment of the payload launching system may also include detection means for detecting the passage of the rocket at some chosen point and operating the means for detaching the rocket transfer means. These detection means can be located in the system or on the floor. An aerodynamic structure may be provided in a transfer means to attract and move the transfer means away from the rocket. The air flow caused by the movement of the rocket during or after the acceleration creates an aerodynamic force in the aerodynamic structure that pulls the transfer means away from the rocket. In a particular embodiment, a transfer means may be designed to contain the outer structure of the rocket near a fuel tank, so that the structure of the rocket at this point does not increase substantially due to the lateral pressure induced by the acceleration. A network laid close to the ground or a parachute in a transfer medium can be used to recover a transfer medium after acceleration.

An empty space may be provided below the rocket to allow combustion gases to accumulate in this space when the first stage engine is fired while the rocket is at the start of the acceleration. Means to keep the rocket in place at the start of the acceleration when the first stage engine is fired can be provided. External storage fuel tanks can be provided near a particular mode of the payload launch system to facilitate operation. A particular example of means for coupling an end portion of the cable with the rotating wheel is a human operator pushing this end portion towards the wheel. A clutch can be provided between the drive means and the wheel. It is not necessary in principle to start the first stage engine at the start of acceleration; the first stage engine can be turned on at any time during acceleration or after acceleration, In a particular embodiment of the payload launching system, as shown in figure 5 and figure 6, a ball at the end of the cable restricts the cable in a center of the wheel; In another embodiment of a payload launching system, the end of the cable is configured to be restrained by a series of separate projections located adjacent to a center of the wheel. In a particular embodiment of the payload launching system, means for extracting the cable from the steering wheel, while the steering wheel is turning, are provided. These means allow, in particular but not exclusively, to have the cable and the steering wheel ready for another operation quickly.

Definitions The term cable includes a string. A chain can be used instead of a cable. The term "rocket" includes any structure powered by a jet engine. The said structure may include a wing, a wing, a rudder, a manned or unmanned flight deck, a wheel or a landing ski or any combination thereof; the term jet engine includes any engine that uses a chemical fuel or chemical fuel with air, and expels it away from the engine to provide thrust. The term jet engine also includes any engine that expels any material away from it through the use of electricity or nuclear energy. The term payload includes any guidance system to guide the rocket in its trajectory, any electronic system to detect or communicate or photograph or any system to be released in space as an artificial satellite.

The expression "the front of a rocket" means that part of a rocket that is in front of the rocket with respect to the direction of movement of a rocket. The expression "after the front of a rocket" means that point of a rocket that is located after the front of a rocket with respect to the direction of movement of a rocket. That is, there exists, with respect to the direction of movement of the rocket, first the front part, then the part after the front part, then the back part of the rocket. The expression "a location after the first stage" means that part of the first stage that is the most distant from the front of the rocket. The expression "a location after the second stage" means that part of the second stage that is the most distant from the front of the rocket.

Observations In the particular embodiments of the payload launching system that are discussed and shown in all the drawings, the structurally appropriate points where the transfer medium transmits the attractive force of the cable to the rocket are located after the front of the rocket. That is, the transfer means transfer the force of attraction of the cable to the rocket at points in the rocket located after the front of the rocket. In these particular embodiments, the transfer means are rigid metal structures that extend from the end of the cable to the back of the rocket. They are also shaped that do not interfere with the front of the rocket, as shown in Figure 7 and Figure 8. At the points where they transfer the out of attraction to the rocket, these metal structures are shaped such that they comprise an extension in their structure that rests immediately below that part of the rocket that supports this force of attraction. In these examples, these transfer means are not attached to the rocket. The said extensions are shaped such that they have the shape of a hook and are restricted to the rocket while the force of attraction of the cable is transferred to the rocket due to its particular shape. In these particular embodiments, which are shown in all the drawings, the rocket is accelerated vertically and the transfer means fall away from the rocket as soon as the transfer of the pulling force from the cable to the rocket ceases.

Claims (13)

NOVELTY OF THE INVENTION CLAIMS

1. - A payload launch system comprises a cable (14), an end portion of which is adapted to releasably engage with a rocket (16), a rotating element (11) adapted for rotation on an axis (12) and drive means for coupling and decoupling with the rotating element ( 11) to rotate the rotary element (11) on the shaft (12), and the rotating element (11) is provided with a surface (13) for receiving a portion of the remote cable (14) of a rocket (16) and the The surface (13) has a curved profile, the radial invention of which increases progressively from said axis (12) in an arched direction of said axis (12) and means for coupling a portion of said remote cable (14) of a rocket (16). ) with the rotating element (11), while said rotating element is rotating, so that the portion of said remote cable (14) of a rocket (16) is located on said surface (13), while an end portion of the said cable (14) Remote rocket (16) is restricted in a location on the rotating element (11) adjacent to a center of the rotating element (11), characterized in that a rocket (16) is provided and transfer means are provided (15) between the cable (14) and a rocket (16), said transfer means (15) being adapted to transfer the attractive force of the cable (14) to the rocket (16) and the attractive force of the cable (14). ) is applied to the rocket (16) at multiple points, and at least one of said transfer means (15) transfer the said attractive force to the rocket (16) at a point located in the rocket (16) away from that particular point that is located in the rocket (16) the most in front of the front of the rocket (16), and at least one of said transfer means (15) transfers the said attractive force to the rocket (16) at a point located in the rocket (16) away from the base of the rocket (16).

2. A payload launch system comprising a cable (27), an end portion of which is adapted to releasably engage with a rocket (29), a rotating element (21) adapted to rotate on an axle (22) ) and drive means for coupling and uncoupling with the rotating element (21) to rotate the rotating element (21) on the shaft (22), and an additional rotary element (25) adapted for rotation on a second shaft (26) and an end portion of said remote cable (27) of the rocket (29) is attached to the additional rotary element (25) and a second cable (24), an end portion of which is attached to the additional rotating element (25) and the additional rotary element (21) is provided with a surface (23) for covering a portion of said remote cable (24) of the additional rotary element (25), and the surface (23) has a curved profile, whose radial dimension progressively increases said shaft (22) one in an arched direction of said shaft (22), and means for coupling a portion of said remote cable (24) of said additional rotating element (25) with said rotary element (21) while said rotary element (21) is rotating, so that the portion of the said remote cable (24) of said additional rotary element (25) is located on said surface (23) while the end portion of said remote cable (24) of the additional rotary element (25) is restricted in a location on the element rotatable (21) adjacent to a center of the rotating element (21), characterized in that a rocket (29) is provided and transfer means (28) are provided, between the cable (27) and the rocket (29), said means of transfer (28) being adapted to transfer the attractive force of the cable (27) to the rocket (29), and the attractive force of the cable (27) is applied to the rocket (29) at multiple points, and at least one of said transfer means (28) transfers said force from to rocket traction (29) at a point located on the rocket (29) away from that particular point that is located on the rocket (29) most in front of the front of the rocket (29), and at least one of said transfer means (28) transfers said attractive force to the rocket (29) at a point located in the rocket (29) away from the base of the rocket (29).

3. The payload launching system according to any of the preceding claims, further characterized in that the transfer means (15, 28) are adapted to transfer the attractive force of the cable (14, 27) to the rocket (16). , 29) in at least one point located after the first stage of the rocket (16, 29).

4. The payload launching system according to any of the preceding claims, further characterized in that the transfer means (15, 28) are adapted to transfer the attractive force of the cable (14, 27) to the rocket (16). , 29) in at least one point located after the second stage of the rocket (16, 29).

5. The payload launching system according to any of the preceding claims, further characterized in that the means of transfer means (15, 28) is adapted to transfer the attractive force of the cable (14, 27) to the rocket (16, 29) in at least one point located after a payload borne by the rocket (16, 29).

6. The payload launching system according to any of the preceding claims, further characterized in that means are provided for disconnecting the cable (14, 27) from said transfer means (15, 28).

7. The payload launching system according to any of the preceding claims, further characterized in that the means for disconnecting the cable (14, 27) include an explosive device.

8. The payload launching system according to any of the preceding claims, further characterized in that the rocket (16, 29) comprises at least one point in its structure where said transfer means (15, 28) are capable of transferring the force of attraction of the cable (14, 27) to the rocket (16, 29).

9. The payload launching system according to any of the preceding claims, further characterized in that the rocket (16, 29) comprises points in its structure where said transfer means are attached to the rocket (16, 29).

10. The payload launching system according to any of the preceding claims, further characterized in that means are provided for detaching said transfer means.

11. The payload launching system according to any of the preceding claims, further characterized in that the means for detaching a transfer means (15, 28) from the rocket (16, 29) include an explosive device.

12. The payload launching system according to any of the preceding claims, further characterized in that means are provided for moving said transfer means (15, 28) away from the rocket (16, 29) so that the rocket (16) , 29) is able to continue its trajectory without being obstructed by them.

13. The payload launching system according to any of the preceding claims, further characterized in that the means for moving a transfer means (15, 28) include an aerodynamic structure located in said transfer means (15, 28). ).