PROPULSION ASSEMBLY FOR A ROCKET

Abstract

A propulsion assembly for a rocket includes a propellant tank configured to contain a propellant and an engine comprising a combustion chamber configured to subject the propellant to combustion and generate exhaust gases. The propulsion assembly further includes a supply circuit and an exhaust gas circuit. The supply circuit is disposed between the propellant tank and the combustion chamber, and the supply circuit is configured to supply the combustion chamber with the propellant. The exhaust gas circuit is disposed between the combustion chamber and the propellant tank, and the exhaust gas circuit is configured to convey at least part of the exhaust gases from the combustion chamber to the propellant tank to provide pressurization of the propellant tank.

Claims

1. A propulsion assembly for a rocket, the propulsion assembly comprising: a propellant tank configured to contain a propellant; an engine comprising a combustion chamber configured to subject the propellant to combustion and generate exhaust gases; a supply circuit disposed between the propellant tank and the combustion chamber, the supply circuit configured to supply the combustion chamber with the propellant; and an exhaust gas circuit disposed between the combustion chamber and the propellant tank, the exhaust gas circuit configured to convey at least one portion of the exhaust gases from the combustion chamber to the propellant tank to provide pressurization of the propellant tank.

2. The propulsion assembly according to claim 1, wherein the exhaust gas circuit comprises an expansion device that is adjacent to the propellant tank and configured to regulate an inlet flow rate of the exhaust gases in the propellant tank.

3. The propulsion assembly according to claim 2, wherein the expansion device is a pressurization plate.

4. The propulsion assembly according to claim 3, wherein the pressurization plate comprises at least one pressure regulation valve.

5. The propulsion assembly according to claim 3, wherein the propulsion assembly comprises a device for measuring the pressure of the propellant tank.

6. The propulsion assembly according to claim 1, wherein the propulsion assembly comprises a pump arranged at an outlet of the propellant tank and a turbine arranged at the outlet of the combustion chamber, the turbine being configured to drive the pump.

7. The propulsion assembly according to claim 1, wherein the propulsion assembly comprises a pump arranged at an outlet of the propellant tank and the engine, the engine being configured to drive the pump.

8. The propulsion assembly according to claim 1, wherein the exhaust gas circuit comprises a heat exchanger configured to cool the exhaust gases leaving the combustion chamber.

9. A method of pressurizing the propellant tank of the propulsion assembly of claim 1, the method comprising: supplying the propellant into the combustion chamber from the propellant tank containing the propellant, combusting the propellant in the combustion chamber to generate exhaust gases, and conveying the exhaust gases from the combustion chamber to the propellant tank to maintain a pressure in the propellant tank such that the pressure is equal to a predetermined value.

10. The method according to claim 9, wherein the propellant is a mono-propellant.

11. The method according to claim 9, wherein the propellant is a metastable poly-nitrogenated mono-propellant.

12. The method according to claim 9, further comprising cooling the exhaust gases in a heat exchanger.

13. The method according to claim 9, further comprising regulating the pressure inside the propellant tank, wherein regulating the pressure inside the propellant tank further comprises: determining a pressure value to be maintained inside the propellant tank prior to supplying the propellant into the combustion chamber, measuring the pressure inside the propellant tank while supplying the propellant into the combustion chamber, and controlling a position of one or more pressure regulation valves to divert at least one portion of the exhaust gases outside the propellant tank, wherein the one or more pressure regulation valves are closed when the pressure measured inside the propellant tank is lower than the predetermined value, and the one or more pressure regulation valves are opened when the pressure measured inside the propellant tank is higher than the predetermined value.

Description

DRAWINGS

[0034] In order that the disclosure may be well understood, there will now be described various forms thereof, given by way of example, reference being made to the accompanying drawings, in which:

[0035] FIG. 1 is a schematic illustration of a propulsion assembly for a rocket according to the present disclosure; and

[0036] FIG. 2 is a schematic illustration of a propulsion assembly for a rocket according to the present disclosure.

[0037] The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

[0038] The following description is merely exemplary in nature and is not intended to limit the present disclosure, application, or uses. It should be understood that throughout the drawings, corresponding reference numerals indicate like or corresponding parts and features.

[0039] For simplicity, identical elements are identified by identical reference signs in all figures.

[0040] In the example represented in FIG. 1, the propulsion assembly is made on the basis of a Tap-off type engine, that is to say an engine in which exhaust gases are drawn from the combustion chamber to supply energy to certain portions of the engine.

[0041] The propulsion assembly 1 comprises a tank 2 and a rocket engine comprising a combustion chamber 3.

[0042] The propellant tank 2 is configured to contain a propellant. This propellant is in liquid form in the propellant tank 2. In one form, the propellant is a metastable poly-nitrogenated mono-propellant.

[0043] The propulsion assembly 1 comprises a supply circuit 4 disposed between the propellant tank 2 and the combustion chamber 3. The supply circuit 4 connects the propellant tank 2 to the combustion chamber 3. The supply circuit 4 is formed in a conventional manner by a propellant circulation pipe 40. The supply circuit 4 provides for the supply of the combustion chamber 3 with propellant from the propellant tank 2.

[0044] The supply circuit 4 comprises a pump. In the present example, the pump is a turbopump 5 arranged at the outlet of the propellant tank 2. The turbopump 5 is configured to pressurize the liquid propellant at the outlet of the propellant tank 2 before injection thereof into the combustion chamber 3. The turbopump is driven by a turbine 6 disposed at the outlet of the combustion chamber 3.

[0045] The turbine 6 is actuated by the exhaust gases leaving the combustion chamber 3 and passing through the turbine 6. The operation of the turbine 6 causes the actuation of the turbopump 5.

[0046] As illustrated in FIG. 2, the propulsion assembly 1 may be deprived of the turbine 6 and comprise an electric motor 62 configured to drive the turbopump 5.

[0047] A flow rate regulation valve 7 for regulating the flow rate of propellant is arranged adjacent to the turbopump 5. This flow rate regulation valve 7 allows regulating the flow rate of propellant entering the combustion chamber 3.

[0048] The propulsion assembly 1 comprises an exhaust gas circuit 8 arranged at the outlet of the combustion chamber 3. The exhaust gas circuit is disposed between the combustion chamber 3 and the propellant tank 2.

[0049] The exhaust gas circuit 8 provides for conveying at least one portion of the exhaust gases from the combustion chamber 3 to the propellant tank 2 to provide pressurization thereof. The exhaust gas circuit 8 is formed in a conventional manner by an exhaust gas circulation pipe 80.

[0050] The exhaust gas circuit 8 may comprise a heat exchanger 9. The heat exchanger 9 is configured to cool the exhaust gases leaving the combustion chamber 3. Cooling of the exhaust gases in the heat exchanger 9 is provided by a cold source. The cold source of the heat exchanger 9 is provided by propellant coming from the supply circuit 4, which provides for removing an external cold source branch. In addition, the heat exchanger 9 may be connected to the supply circuit 4.

[0051] The exhaust gas circuit 8 may comprise an expansion device 10. In the present example, the expansion device 10 is a pressurization plate. This pressurization plate is arranged between the turbine 6 and the inlet of the propellant tank 2. This pressurization plate is configured to regulate the flow rate of exhaust gas entering the interior of the propellant tank 2.

[0052] The inlet flow rate of the exhaust gases is regulated according to the pressure measured inside the propellant tank 2. For this purpose, the pressure measurement system or device refers to pressure sensors (not represented) that may be disposed inside the propellant tank 2. Other equivalent devices or systems deemed compatible by those skilled in the art could be used as pressure measurement device or system. The pressure measurement system or device maintains a constant pressure inside this tank.

[0053] The exhaust gas circulation pipe 80 is divided, at the pressurization plate, into a plurality of channels 81, 82, 83 comprising one or several pressurization valve(s) 11. One of the channels 83 opens outside the propellant tank 2 in the direction of the arrow “a”. The channel 83 opening outside the exhaust gas circuit comprises a pressure regulation valve 11. The regulation valve is movable between a closed position to provide for closing the channel 83 and an open position to provide for opening the channel 83 to divert at least one portion of the flow of the exhaust gases outside the tank when it is opened. This provides for regulating the flow rate of exhaust gas entering the propellant tank 2 according to the pressure measured in the propellant tank 2.

[0054] The expansion device of the present disclosure is not limited to a pressurization plate and may include, for example, an expander such as a hydraulic expander. The expander provides for removing the pressure sensors in the tanks. The expander is configured to determine the pressure inside the tank in a standalone manner due to a membrane system and is configured to open and close regularly to maintain the pressure inside the tank at a constant value.

[0055] In operation, the propellant tank 2 filled with propellant delivers the fuel. The fuel passes through the propellant circulation pipe 40 of the supply circuit 4 from the propellant tank 2 up to the combustion chamber 3.

[0056] When the propellant passes through the supply circuit 4, the propellant passes through the turbopump 5. The passage through the turbopump 5 allows compression of the fuel so that the propellant enters the combustion chamber 3 under optimum pressure, speed and temperature conditions.

[0057] The propellant then enters the combustion chamber 3 in which it undergoes combustion. The combustion of the propellant generates exhaust gases.

[0058] A portion of the exhaust gas leaving the combustion chamber 3 is evacuated through a nozzle 32 so as to generate a thrust causing the propulsion of the engine and that of the vehicle on which it is fixed.

[0059] Another portion of the exhaust gas is conveyed to the turbine 6 through the exhaust gas circulation pipe 80 of the exhaust gas circuit 8.

[0060] The exhaust gases are cooled beforehand in the heat exchanger 9 disposed between the combustion chamber 3 and the turbine 6.

[0061] The passage of the exhaust gases in the turbine 6 provides for the turbine 6 to be put into operation, which in turn causes the activation of the turbopump 5.

[0062] At the outlet of the turbine 6, the exhaust gases are conveyed to the tank through the exhaust gas circulation pipe 80 to provide pressurization thereof.

[0063] Before entering the tank, the exhaust gases pass through the pressurization plate (as the expansion device 10) comprising the pressure regulation valves 11.

[0064] The change in the position of the pressure regulation valves is driven by the pressure value measured inside the propellant tank 2. The pressure inside the tank could vary, for example, during the fuel delivery.

[0065] The pressure inside the propellant tank 2 is measured using the pressure measuring system or device located inside the propellant tank 2. The interest being to maintain a constant pressure inside the tank for the duration of fuel delivery.

[0066] In the case where the pressure measured inside the propellant tank 2 is higher than a predetermined value, that is to say when the propellant tank 2 is under overpressure, the pressure regulation valve 11 arranged on the channel 83 of the exhaust gas circuit opening outside the tank opens. Thus, at least one portion of the exhaust gases is diverted outside the propellant tank 2. The rate flow of exhaust gas is reduced, and the pressure inside the propellant tank 2 decreases.

[0067] In the case where the pressure measured inside the propellant tank 2 is lower than a predetermined value, that is to say when the propellant tank 2 is under-pressure, the pressure regulation valve 11 arranged on the channel 83 of the exhaust gas circuit opening outside the propellant tank 2 closes. The exhaust gases are directed entirely inside the propellant tank 2. The flow rate of exhaust gas is increased, and the pressure inside the propellant tank 2 increases.

[0068] As could be understood in light of the foregoing, the propulsion assembly according to the present disclosure provides for using a portion of the exhaust gases to pressurize the propellant tank and thus may provide for a simplified structure of the propulsion assembly.

[0069] The present disclosure is not limited to the examples that have just been described and many arrangements could be made to these examples without departing from the scope of the present disclosure. In particular, the different features, forms, variants and forms of the present disclosure could be associated with each other in various combinations insofar as they are not incompatible or exclusive of each other.

[0070] Unless otherwise expressly indicated herein, all numerical values indicating mechanical/thermal properties, compositional percentages, dimensions and/or tolerances, or other characteristics are to be understood as modified by the word “about” or “approximately” in describing the scope of the present disclosure. This modification is desired for various reasons including industrial practice, material, manufacturing, and assembly tolerances, and testing capability.

[0071] As used herein, the phrase at least one of A, B, and C should be construed to mean a logical (A OR B OR C), using a non-exclusive logical OR, and should not be construed to mean “at least one of A, at least one of B, and at least one of C.”

[0072] In this application, the term “controller” and/or “module” may refer to, be part of, or include: an Application Specific Integrated Circuit (ASIC); a digital, analog, or mixed analog/digital discrete circuit; a digital, analog, or mixed analog/digital integrated circuit; a combinational logic circuit; a field programmable gate array (FPGA); a processor circuit (shared, dedicated, or group) that executes code; a memory circuit (shared, dedicated, or group) that stores code executed by the processor circuit; other suitable hardware components (e.g., op amp circuit integrator as part of the heat flux data module) that provide the described functionality; or a combination of some or all of the above, such as in a system-on-chip.

[0073] The term memory is a subset of the term computer-readable medium. The term computer-readable medium, as used herein, does not encompass transitory electrical or electromagnetic signals propagating through a medium (such as on a carrier wave); the term computer-readable medium may therefore be considered tangible and non-transitory. Non-limiting examples of a non-transitory, tangible computer-readable medium are nonvolatile memory circuits (such as a flash memory circuit, an erasable programmable read-only memory circuit, or a mask read-only circuit), volatile memory circuits (such as a static random access memory circuit or a dynamic random access memory circuit), magnetic storage media (such as an analog or digital magnetic tape or a hard disk drive), and optical storage media (such as a CD, a DVD, or a Blu-ray Disc).

[0074] The apparatuses and methods described in this application may be partially or fully implemented by a special purpose computer created by configuring a general-purpose computer to execute one or more particular functions embodied in computer programs. The functional blocks, flowchart components, and other elements described above serve as software specifications, which can be translated into the computer programs by the routine work of a skilled technician or programmer.

[0075] The description of the disclosure is merely exemplary in nature and, thus, variations that do not depart from the substance of the disclosure are intended to be within the scope of the disclosure. Such variations are not to be regarded as a departure from the spirit and scope of the disclosure.