System and method of auxiliary power generation unit for rocket motor

Abstract

To provide a rocket motor auxiliary power generation unit system and method without batteries.SOLUTION: A method for generating electric power for a rocket system includes burning a primary solid propellant particulate to create a primary high pressure gas for providing thrust to the rocket, opening a first valve to divert a portion of the primary high-pressure gas to an auxiliary solid propellant particulate for igniting the auxiliary solid propellant particulate, where the auxiliary solid propellant particulate is disposed in a housing separate from the primary solid propellant particulate, and burning the auxiliary solid propellant particulate to create an auxiliary high-pressure gas for turning a turbine. The method further includes driving a generator with the turbine and generating electric power with the generator.SELECTED DRAWING: Figure 1A

Description

Technical Field

[0001] The present disclosure generally relates to solid fuel rocket propulsion systems, and more particularly, to systems and methods for power generation in rocket motor systems.

Background Art

[0002] Solid propellant motors for rocket propulsion vehicles contain solid propellant particles that generate high-pressure gas, which is released from the nozzle to generate the thrust of the rocket. Rocket propulsion vehicles typically include various electrical systems. Power supply to the electrical systems for rocket propulsion vehicles has conventionally been achieved using battery technology.

Summary of the Invention

Means for Solving the Problems

[0003] A system connectable to a rocket is disclosed herein. The system includes a primary motor containing primary solid propellant particles configured to burn to generate a primary high-pressure gas, an auxiliary gas generator containing auxiliary solid propellant particles disposed in a housing separate from the primary solid propellant particles, a first valve, a generator, and a turbine coupled to the generator. In response to the first valve moving to an open position, the primary motor is in fluid communication with the auxiliary gas generator to ignite the auxiliary solid propellant particles. In response to the auxiliary solid propellant particles being ignited by the primary high-pressure gas, the auxiliary solid propellant particles are configured to burn to generate an auxiliary high-pressure gas.

[0004] In various embodiments, the system further includes a second valve for metering the auxiliary high-pressure gas to the turbine.

[0005] In various embodiments, the auxiliary high-pressure gas is configured to be directed towards the turbine in response to the second valve moving to an open position.

[0006] In various embodiments, the system further comprises a third valve for releasing pressure from the housing to extinguish auxiliary solid propellant particles.

[0007] In various embodiments, auxiliary solid propellant particles are sealed from primary solid propellant particles in response to the first valve moving to the closed position.

[0008] In various embodiments, the system further includes a controller configured to control at least one of a first valve, a second valve, and a third valve in order to selectively supply power to a generator.

[0009] In various embodiments, the system further includes a power supply configured to supply a second power to the controller.

[0010] An auxiliary power generator disclosed herein includes auxiliary solid propellant particles disposed within a housing, a first valve configured to move to an open position to direct a primary high-pressure gas toward the auxiliary solid propellant particles and ignite the auxiliary solid propellant particles, a generator, and a turbine connected to the generator. The auxiliary solid propellant particles are configured to burn to generate auxiliary high-pressure gas for rotating the turbine.

[0011] In various embodiments, the auxiliary power generation device further includes a second valve that is in fluid communication with the turbine.

[0012] In various embodiments, the auxiliary power generator further comprises a third valve for releasing pressure from the housing to extinguish auxiliary solid propellant particles.

[0013] In various embodiments, the auxiliary solid propellant particles can be reignited after being extinguished.

[0014] In various embodiments, auxiliary solid propellant particles are sealed away from primary solid propellant particles in response to the first valve moving to the closed position.

[0015] In various embodiments, the auxiliary power generator further comprises a controller configured to control at least one of a first valve, a second valve, and a third valve in order to selectively supply power to the generator.

[0016] In various embodiments, the auxiliary power generator further includes a power supply configured to supply a second power to the controller.

[0017] In various embodiments, the second valve is configured to meter auxiliary high-pressure gas to the turbine.

[0018] In various embodiments, the third valve is configured to direct the auxiliary high-pressure gas towards the surrounding environment.

[0019] A method for generating power for a rocket-propelled vehicle is disclosed herein. The method includes burning primary solid propellant particles to generate primary high-pressure gas for supplying thrust to a rocket; opening a first valve to divert a portion of the primary high-pressure gas to auxiliary solid propellant particles in order to ignite the auxiliary solid propellant particles, the auxiliary solid propellant particles being located in a separate housing from the primary solid propellant particles; burning the auxiliary solid propellant particles to generate auxiliary high-pressure gas; using the auxiliary high-pressure gas to rotate a turbine; driving a generator with the turbine; and generating power with the generator.

[0020] In various embodiments, the method further includes closing a first valve, sealing auxiliary solid propellant particles from primary solid propellant particles in response to the closing of the first valve, opening a second valve, and directing auxiliary high-pressure gas across the turbine in response to the opening of the second valve.

[0021] In various embodiments, this method further includes closing a second valve, opening a third valve to reduce the pressure inside the housing, and extinguishing auxiliary solid propellant particles in response to the pressure drop inside the housing.

[0022] In various embodiments, the method further includes closing a third valve, reopening a first valve to divert a second portion of the primary high-pressure gas to the auxiliary solid propellant particles, and reigniting the auxiliary solid propellant particles in response to the second portion of the primary high-pressure gas being diverted to the auxiliary solid propellant particles.

[0023] Unless otherwise specified, the foregoing features and elements may be combined in various combinations without exclusivity. These features and elements, and their operations, will become more apparent in light of the following description and the accompanying drawings. However, it should be understood that the following description and drawings are intended to be illustrative in nature and non-limiting.

[0024] The subject matter of the present disclosure is specifically shown and distinctly claimed in the concluding portion of this specification. However, a more complete understanding of the present disclosure can be best obtained by reference to the detailed description and the claims when considered in connection with the figures of the drawings.

Brief Description of the Drawings

[0025] [Figure 1A] A schematic diagram of a rocket propulsion system including a primary motor and an auxiliary power generation device including an auxiliary gas generator according to various embodiments is shown. [Figure 1B] A schematic diagram of the rocket system of FIG. 1A with an auxiliary power generation device in ignition mode according to various embodiments is shown. [Figure 1C] A schematic diagram of the rocket system of FIG. 1A with an auxiliary power generation device in power generation mode according to various embodiments is shown. [Figure 1D] A schematic diagram of the rocket system of FIG. 1A with an auxiliary power generation device in fire extinguishing mode according to various embodiments is shown. [Figure 2] A method for generating power for a rocket system according to various embodiments is shown. [Figure 3]A block diagram of an exemplary turbine generator assembly according to various embodiments is shown.

Best Mode for Carrying Out the Invention

[0026] The detailed description of the various embodiments herein refers to the accompanying drawings which illustrate the various embodiments. These various embodiments are described in sufficient detail to enable those skilled in the art to practice the present disclosure, but it is to be understood that other embodiments may be realized and that logical, chemical, and mechanical changes may be made without departing from the scope of the present disclosure. Accordingly, the detailed description herein is presented for purposes of illustration only and not of limitation. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented.

[0027] Furthermore, any reference to the singular includes the plural, and any reference to two or more components or steps may include a singular embodiment or step. Also, any reference to attached, fixed, connected, etc. may include permanent, removable, temporary, partial, complete, and / or any other possible attachment options. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact.

[0028] Typically, a rocket propulsion vehicle includes an on-board power source that includes conventional battery technology (e.g., lithium-ion batteries, or any other suitable battery) and / or thermal batteries. Conventional batteries and thermal batteries tend to have limitations in power density, environmental performance, size, performance, lifespan, and on and / or off functionality. Due to the limitations of current battery technology with respect to weight, volume, cost, and reliability, there is a need to develop a more affordable power source with high power / energy density.

[0029] This disclosure provides an auxiliary power generation unit comprising solid fuel. The auxiliary power generation unit is located separately from the primary rocket motor that generates thrust during the flight of the rocket motor. In various embodiments of this disclosure, the auxiliary power generation unit includes an auxiliary gas generator containing solid propellant particles that are ignited by gas from the primary motor. In various embodiments of this disclosure, the auxiliary power generation unit comprises a plurality of valves for selectively igniting the auxiliary solid propellant particles of the auxiliary gas generator, generating power when the auxiliary solid propellant particles are ignited (i.e., burned), and extinguishing the auxiliary solid propellant particles. In this way, the auxiliary power generation unit of this disclosure can be ignited and extinguished on demand (i.e., multiple individual uses are possible during a single flight of the rocket). In various embodiments of this disclosure, the primary motor is used to ignite the auxiliary solid propellant particles of the auxiliary gas generator and is not used to supplement, replenish, or recharge the auxiliary solid propellant particles. In this way, according to various embodiments, the auxiliary solid propellant particles are separated and independent from the primary solid propellant particles.

[0030] The auxiliary power generation unit of this disclosure can be used in addition to (i.e., to supplement) conventional onboard power sources (e.g., conventional batteries and / or thermal batteries). In this regard, this disclosure provides a system and method for generating the necessary power as needed, utilizing solid propellant particles and a small turbine generator. The system and method of this disclosure tends to reduce the weight of the rocket's power source as the propellant is consumed during the power generation process. Propellant particles are efficient for power generation due to their high volume / weight-to-energy ratio. Conventional batteries tend to have difficulties with the extreme environments that solid propellant particles can withstand. The auxiliary power generation unit of this disclosure can start an auxiliary gas generator using hot gas from a primary motor and extinguish the auxiliary gas generator using ambient air, thereby reducing the complexity and additional components that would otherwise be required. The system of this disclosure can also be sized and adjusted according to the expected power consumption needs.

[0031] This disclosure provides a turbine generator for supplying power to a system, a turbine for driving the generator, and auxiliary solid propellant particles for generating auxiliary high-pressure gas to rotate the turbine, the generator generating electricity in response to rotation.

[0032] Referring to Figure 1A, various embodiments of a rocket-propelled vehicle 100 (also referred to herein as a rocket), including a primary motor 102 and an auxiliary power generation unit 130, are shown schematically in Figure 1A. In Figure 1A, electrical connections (e.g., conductive materials, wires, cables, busbars, etc.) are shown with dashed lines, while fluid connections (e.g., conduits, channels, etc.) are shown with solid lines. The primary motor 102 schematically shown in Figure 1A may include a solid propellant rocket motor 110, including solid propellant particles 115 (also referred to herein as primary solid propellant particles), according to various embodiments. The rocket 100 may have a front end 190 and an exhaust end 192. The rocket 100 may include an aerodynamic body 104. The propellant particles 115 may extend along the longitudinal axis of the solid propellant rocket motor 110 between the exhaust end 192 and the front end 190. The propellant particles 115 may be core-burning propellant particles, end-burning propellant particles, or propellant particles of any other suitable configuration. In various embodiments, when the propellant particles 115 are core-burning propellant particles, the propellant particles 115 include a hollow core region, generally referred to as a central bore. The central bore may define a bore extending longitudinally through the core-burning propellant particles. Ignitioners may be positioned in or on the propellant particles 115 to ignite the propellant particles 115 and generate thrust for the rocket 100. Note that ignitioners and electrical connections are not shown at this point. Specific ignitioners and electrical connections are well known in the art and can be selected according to the specific propellant / oxidizer used and other desired design features.

[0033] The front end 190 of the rocket 100 may be sealed, and the exhaust end 192 may be terminated by a nozzle structure 195. When ignited (e.g. by an igniter), the surface of the propellant particles 115 begins to burn, thereby becoming the combustion front, which is the surface of the propellant particles to be burned or ablaze at any given time. The combustion then continues at high temperature and pressure, producing gaseous combustion byproducts (also referred to herein as primary high-pressure gases). The discharge of these gaseous combustion byproducts through the nozzle structure 195 supplies thrust to the primary motor 102 and the rocket 100.

[0034] The rocket 100 may further comprise a control unit 120 for controlling various electronic components of the rocket 100. The control unit 120 includes one or more controllers (e.g., processors) and one or more tangible non-temporary memories capable of implementing digital or programmable logic. In various examples, for example, one or more controllers may be one or more general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gates, transistor logic, or discrete hardware components, or various combinations thereof. In various embodiments, the control unit 120 controls at least various parts of the flight and operation of various components of the rocket 100. For example, the control unit 120 can control various components of the auxiliary power generator 130 schematically shown in Figure 1A, and / or various flight parameters such as the thrust system, electrical system, environmental system, hydraulic system, lighting system, pneumatic system, trim system, actuator system, etc.

[0035] In various embodiments, the rocket 100 further comprises a power supply 122 (also referred to herein as a primary power supply) for supplying power to a controller 120 and / or other electronic components mounted on the rocket 100. In various embodiments, the primary power supply 122 may include one or more batteries (e.g., alkaline, zinc-carbon, lithium, mercury oxide, silver oxide, zinc-air, lithium-ion (Li-ion), nickel-metal hydride (NIMH), nickel-cadmium (NiCD), lead-acid, etc.), capacitors (e.g., ceramic, film, electrolyte, supercharger, etc.), thermal cells (e.g., phase-change, encapsulated, grounded heat exchanger (GHEX) - unencapsulated, etc.). The primary power supply 122 may be electrically coupled to the control unit 120 to supply power. The primary power supply 122 may have limitations in terms of power density, environmental capability, size, performance, lifespan, and ability to be switched on / off.

[0036] In various embodiments, the auxiliary power generator 130 includes an auxiliary gas generator 132 containing propellant particles 135 (also referred to herein as auxiliary solid propellant particles) located in a separate housing 134 from the primary solid propellant particles 115. In various embodiments, the auxiliary power generator 130 further includes a turbine generator 140 for supplying power to the control unit 120 and / or onboard electrical components 124, such as actuators, payloads, separation systems, guidance systems, or any other onboard electrical or electromechanical components of the rocket. In response to the need for additional power to the rocket 100, the control unit 120 may cause the auxiliary power generator 130 to generate additional power to produce the required power, as will be described in more detail herein.

[0037] The housing 134 may include any suitable structure for housing the propellant particles 135. The housing 134 may also have a casing for the propellant particles 135. The housing 134 can be made of either metal (e.g., high-resistance steel or high-strength aluminum alloy) or composite material (e.g., glass fiber, aramid fiber, and / or carbon fiber).

[0038] The auxiliary power generator 130 may further include a first valve 151 that provides a passage for primary high-pressure gas between propellant particles 115 and propellant particles 135. The first valve 151 may be controlled by a control unit 120. The first valve 151 may be connected between the primary motor 102 and the auxiliary gas generator 132. The first valve 151 may include a needle valve, a ball valve, a gate valve, a butterfly valve, or any other suitable valve that can withstand the high temperature of the primary high-pressure gas generated by the propellant particles 115. The first valve 151 may be movable between an open position (see, for example, Figure 1B) and a closed position (see, for example, Figures 1C and 1D). In this regard, the propellant particles 115 may be in fluid communication with the propellant particles 135 in response to the first valve 151 moving to the open position. Conversely, the propellant particles 115 can be sealed away from the propellant particles 135 in response to the first valve 151 moving to the closed position. In this regard, a conduit 155, or other suitable flow structure, can be connected between the primary motor 102 and the auxiliary gas generator 132.

[0039] The auxiliary power generator 130 may further include a second valve 152 for discharging high-temperature, high-pressure gaseous combustion byproducts (also referred to herein as auxiliary high-pressure gases) from the housing 134, for example, when the auxiliary power generator 130 is in power generation mode. The second valve 152 may be controlled by a control unit 120. The second valve 152 may be connected between the primary motor 102 and the auxiliary gas generator 132. In this regard, the second valve 152 may be configured to direct the auxiliary high-pressure gas from the propellant particles 135 towards the rocket motor 110, and then discharge it from the rocket motor 110 through a nozzle structure 195. In various embodiments, the second valve 152 meters the auxiliary high-pressure gas to the turbine of the generator 140 (see turbine 14 in Figure 3). In this regard, the auxiliary high-pressure gas generated by the propellant particles 135 may be directed through a nozzle structure 195. The second valve 152 may include a needle valve, ball valve, gate valve, butterfly valve, or any other suitable valve capable of withstanding the high temperature and pressure of the auxiliary high-pressure gas generated by the propellant particles 135. The second valve 152 may be movable between an open position (see Figure 1C) and a closed position (see Figures 1B and 1D). In this regard, the primary motor 102 may be in fluid communication with the propellant particles 135 in response to the second valve 152 moving to the open position. In this regard, the nozzle structure 195 may be in fluid communication with the propellant particles 135 in response to the second valve 152 moving to the open position. Conversely, the primary motor 102 may be sealed off from the auxiliary gas generator 132 in response to the second valve 152 moving to the closed position. In this regard, a conduit 156, or other suitable flow structure, may be connected between the primary motor 102 and the auxiliary gas generator 132.

[0040] The auxiliary generator 130 may further include a third valve 153 for discharging auxiliary high-pressure gas from the housing 134, for example, to extinguish propellant particles 135. The third valve 153 may be controlled by a control unit 120. The third valve 153 may be connected to the housing 134. In this regard, the third valve 153 may be configured to direct the auxiliary high-pressure gas from the auxiliary gas generator 132 to the ambient environment 196. In this regard, the auxiliary high-pressure gas generated by the propellant particles 135 may be discharged through the third valve 153. The third valve 153 may include a ball valve, a gate valve, a butterfly valve, or any other suitable valve that can withstand the high temperature and pressure of the auxiliary high-pressure gas generated by the propellant particles 135 and can open to rapidly reduce the pressure inside the housing 134—for example to ambient pressure—to extinguish the propellant particles 135. The third valve 153 may be movable between an open position (see Figure 1D) and a closed position (see Figures 1B and 1C). In this regard, the propellant particles 135 may be in fluid communication with the surrounding environment 196 in response to the third valve 153 moving to the open position. Conversely, the propellant particles 135 may be sealed from the surrounding environment 196 in response to the third valve 153 moving to the closed position. In this regard, a conduit 157, or other suitable flow structure, may be connected between the housing 134 and the third valve 153. Alternatively, the third valve 153 may be directly coupled to the housing 134, and the conduit 157 may extend from the third valve 153.

[0041] The auxiliary power generator 130 further includes a generator 140 (also referred to herein as a turbine generator or power generator) according to various embodiments. The generator 140 may be a turbine generator. The generator 140 may be a small generator suitable for mounting on the body 104 of the rocket 100. The generator 140 can be connected inline with a second valve 152. In this regard, in response to the second valve 152 moving to the open position, the auxiliary high-pressure gas produced by the propellant particles 135 expands across the generator turbine, thereby rotating the turbine and causing the generator 140 to generate power, which can then be supplied to the control unit 120 and / or components 124. In other words, the turbine converts the energy available in the high-pressure exhaust gas into rotation, while the generator converts the rotation into electricity. Turbine generators are known in the art and can be selected according to the expected pressure, expected flow rate, expected power requirements, weight requirements, and other desired design features.

[0042] The auxiliary power generator 130 can operate in various modes depending on whether additional power is desired. Referring to Figure 1B, the rocket 100 is shown with the auxiliary power generator 130 in ignition mode for igniting propellant particles 135. In ignition mode, the first valve 151 is moved to the open position. The control unit 120 can command the first valve 151 to the open position (for example, by a voltage signal or a current signal). With the first valve 151 in the open position and the propellant particles 115 ignited, the primary high-pressure gas generated by the propellant particles 115 (indicated by arrow 197 in Figure 1B) flows from the primary motor 102 through the first valve 151 to the housing 134, igniting the propellant particles 135. In other words, in response to the first valve 151 moving to the open position, a portion 197 of the primary high-pressure gas 199 is diverted to the auxiliary solid propellant particles 135 to ignite them. In this regard, the propellant particles 135 can be selected to be ignitable at the temperature of the primary high-pressure (and high-temperature) gas 197. Once the propellant particles 135 are ignited, the control unit 120 can command the auxiliary generator 130 to switch from ignition mode to generator mode.

[0043] Referring to Figure 1C, the rocket 100 is shown with an auxiliary power generator 130 in power generation mode to generate additional power for the rocket 100. To switch from ignition mode to power generation mode, a first valve 151 is moved to the closed position and a second valve 152 is moved to the open position. The control unit 120 can command the first valve 151 to the closed position (e.g., by a voltage signal or a current signal). The control unit 120 can command the second valve 152 to the open position (e.g., by a voltage signal or a current signal). With the first valve 151 in the closed position, the second valve 152 in the open position, and the third valve 153 in the closed position, and the propellant particles 135 ignited, the auxiliary high-pressure gas (indicated by arrow 198 in Figure 1C) generated by the propellant particles 135 flows from the auxiliary gas generator 132 through the generator 140, which rotates the generator turbine (see turbine 14 in Figure 3) to generate power for the rocket 100. The auxiliary high-pressure gas 198 can flow into the primary motor 102 through the second valve 152 and be discharged through the nozzle structure 195. In other words, in response to the ignition of the auxiliary solid propellant particles 135, the auxiliary solid propellant particles 135 are configured to burn to produce the auxiliary high-pressure gas 198 for rotating the turbine of the generator 140 (see turbine 14 in Figure 3). As the propellant particles 135 burn, the auxiliary high-pressure gas 198 continues to expand across the generator turbine of the generator 140 to generate electricity. Furthermore, as the auxiliary high-pressure gas 198 exits the auxiliary generator 130 and the nozzle structure 195, the weight of the auxiliary generator 130 decreases. In various embodiments, the auxiliary generator 130 can be selectively shut off by operating in power generation mode for a period of time (e.g., seconds) and then switching from power generation mode to fire extinguishing mode (see Figure 1D).

[0044] Referring to Figure 1D, rocket 100 is shown with an auxiliary power generator 130 in fire suppression mode for extinguishing propellant particles 135. To switch from power generation mode to fire suppression mode, a second valve 152 is moved to the closed position and a third valve 153 is moved to the open position. The first valve 151 remains in the closed position. Control unit 120 can command the second valve 152 to the closed position. Control unit 120 can command the third valve 153 to the open position (e.g., by a voltage signal or a current signal). With the first valve 151 in the closed position, the second valve 152 in the closed position, the third valve 153 in the open position, and the propellant particles 135 ignited, the auxiliary high-pressure gas 198 generated by the propellant particles 135 exits the housing through the third valve 153 and is released into the ambient environment 196, rapidly reducing the pressure inside the housing 134 to or near the ambient pressure. In other words, the third valve 153 can release pressure from the housing 134 to extinguish the auxiliary solid propellant particles 135. In response to the pressure drop, the propellant particles 135 can be extinguished, and the remaining propellant particles 135 can be reserved for the next power generation cycle. With the auxiliary power generator 130 effectively turned off, the auxiliary power generator 130 can be turned on again later by switching between ignition mode and power generation mode, thereby enabling multiple individual uses of the power generator 130, with power being generated as needed. In this regard, the propellant particles 135 can be selectively turned "on" and "off" by, for example, the control unit 120, according to the power demand of the rocket 100. In other words, the propellant particles 135 can be reignited after being extinguished.

[0045] In various embodiments, the propellant particles 115 and / or propellant particles 135 may consist of a composite propellant comprising both fuel and oxidizer mixed and immobilized within a cured polymer-based binder. For example, the propellant particles 115 and / or propellant particles 135 may include an ammonium nitrate-based composite propellant (ANCP) or an ammonium perchlorate-based composite propellant (APCP). In various embodiments, the propellant particles 115 and / or propellant particles 135 may include a distribution of AP(NH4ClO4) particles embedded in a hydroxyl-terminated polybutadiene (HTPB) matrix.

[0046] Referring to Figure 2, flowcharts are disclosed showing methods 200 for generating power for a rocket in various embodiments. Method 200 includes burning primary solid propellant particles to generate primary high-pressure gas to supply thrust to the rocket (step 210). Method 200 includes opening a first valve to divert some of the high-pressure gas to auxiliary solid propellant particles and igniting the auxiliary solid propellant particles (step 220). Method 200 includes burning the auxiliary solid propellant particles to generate auxiliary high-pressure gas to rotate a turbine (step 230). Method 200 includes driving a generator with the turbine (step 240). Method 200 includes generating power using the generator (step 250).

[0047] Referring to Figures 1B and 2 in combination, step 210 may include burning primary solid propellant particles 115 to generate primary high-pressure gas 199 to supply thrust to rocket 100 (step 210). Step 220 may include opening a first valve 151 to divert a portion 197 of the high-pressure gas 199 to auxiliary solid propellant particles 135 and igniting the auxiliary solid propellant particles 135. Referring to Figures 1C and 2, step 230 may include burning the auxiliary solid propellant particles 135 to generate auxiliary high-pressure gas 198 to rotate a turbine (see turbine 14 in Figure 3). Step 240 may include driving a generator 140 with the turbine (see turbine 14 in Figure 3). Step 250 may include generating electricity with the generator 140.

[0048] Referring to Figure 3, block diagrams of exemplary turbine generator assemblies 12 in various embodiments are shown. The generator 140 may be similar to the turbine generator assembly 12. In various embodiments, the second valve 152 may be similar to the speed control valve 20. However, it should be noted that the specific configuration of the turbine generator assembly 12 is not particularly limited, and various other turbine generator configurations can be used without departing from the scope of this disclosure.

[0049] The turbine-generator assembly 12 includes a turbine 14 and a generator 16. The turbine-generator assembly 12 may further include a gear assembly 18, a speed control valve 20, a lubricating oil pump 22, a lubricating oil filter 24, a lubricating oil bypass valve 26, and a cooling circuit 28), an exhaust gas inlet 38, and an exhaust gas path 40. In various embodiments, the exhaust gas path 40 is a metered exhaust gas path 40. The turbine 14 is any turbine known in the art, such as a single-stage, multi-nozzle impulse turbine. The generator 16 is any generator known in the art.

[0050] Solid propellant particles (e.g., propellant particles 135 in Figure 1C) are burned in an auxiliary propellant particle housing (e.g., housing 134 in Figure 1C) to generate an auxiliary exhaust gas (e.g., auxiliary high-temperature, high-pressure gas in Figure 1C), as described herein. This auxiliary exhaust gas is diverted from the housing and supplied to a velocity control valve 20 through an exhaust gas inlet 38. The velocity control valve 20 can adjust the amount of gas supplied to the spin turbine 14. In various embodiments, the velocity control valve 20 can be opened without active adjustment of the gas supplied to the spin turbine 14. The turbine 14 powers the generator 16 via a gear assembly 18. In various embodiments, the turbine 14 powers the generator 16 without a gear assembly (e.g., directly coupled to the generator rotor). The generator 16 generates electricity and powers the system (e.g., rocket 100). The system can use the electricity supplied by the generator 16 to power one or more components mounted on the rocket, such as motor-driven linear electromechanical actuators.

[0051] The lubrication oil pump 22 may be a standard lubrication oil pump known in the art and may be contained within a reservoir housing. The oil pump 22 can provide lubrication and cooling to both the turbine 14 and the generator 16 via the cooling circuit 28. Alternatively, the oil pump 22 may provide lubrication to only one of the turbine 14 and the generator 16. The oil can first pass through the filter 24. Then the oil can exit the gear assembly 18, travel through the cooling circuit 28, and then re-enter the gear assembly 18. A filter bypass valve 26 may allow oil to bypass the filter 24 if the filter 24 is clogged. This can be achieved by measuring the oil pressure at the filter bypass valve 26. For example, if the pressure at the filter bypass valve 26 is greater than the maximum value, e.g., 300 pounds per square inch (PSI), the unfiltered oil will bypass the filter 24 to the turbine 14 so as not to deplete the oil in the turbine 14. A separate valve may set the oil pressure in the cooling circuit 28 to, for example, 65 PSI downstream of the filter 24.

[0052] Benefits, other advantages, and solutions to problems have been described herein with respect to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and / or physical connections between various elements. It should be noted that many alternative or additional functional relationships or physical connections may exist in actual systems. However, benefits, advantages, and solutions to problems, as well as any elements that may produce or make more prominent any benefits, advantages, or solutions, shall not be construed as material, necessary, or essential features or elements of this disclosure. Accordingly, the scope of this disclosure is limited to the additional claims, and references to singular elements are intended to mean "one or more" rather than "unique" unless expressly stated. Furthermore, where statements similar to "at least one of A, B, or C" are used in the claims, such statements are intended to be construed as meaning that in some embodiments only A may exist, in some embodiments only B may exist, in some embodiments only C may exist, or in a single embodiment any combination of elements A, B, and C may exist. For example, A and B, A and C, B and C, or A, B and C. Different cross-hatching patterns are used throughout the diagram to represent different parts, but they do not necessarily have to represent the same or different materials.

[0053] Systems, methods, and apparatus are provided herein. In embodiments for carrying out the inventions herein, references such as “one embodiment,” “an embodiment,” and “various embodiments” indicate that the embodiments described may include certain characteristics, structures, or features, but not all embodiments may necessarily include certain characteristics, structures, or features. Furthermore, such wording may not necessarily refer to the same embodiment. Moreover, when certain characteristics, structures, or features are described in relation to an embodiment, it is assumed that achieving such characteristics, structures, or features in relation to other embodiments is within the knowledge of those skilled in the art, whether explicitly stated or not. After reading the description, it will be clear to those skilled in the art how to implement the disclosure in alternative embodiments.

[0054] Furthermore, elements, components, or steps of a method in this disclosure are not intended for public disclosure, whether or not they are expressly described in the claims. The claimed elements of this specification do not constitute an invocation of § 115(f) of the U.S. Patent Act unless the element is expressly referenced using the phrase “means for.” As used herein, the terms “comprise,” “comprising,” or any other variation thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus including a list of elements may include other elements that are not expressly listed or are inherent to such process, method, article, or apparatus, rather than including only those elements.

Claims

1. A system that can be connected to a rocket, A primary motor containing primary solid propellant particles configured to burn to generate primary high-pressure gas, An auxiliary gas generator containing auxiliary solid propellant particles arranged in a separate housing from the primary solid propellant particles, First valve, generator, A turbine connected to the aforementioned generator, A second valve for measuring auxiliary high-pressure gas to the turbine, and The nozzle structure is located at one end of the primary motor, In response to the first valve moving to the open position, the primary motor fluidly communicates with the auxiliary gas generator to ignite the auxiliary solid propellant particles. In response to the ignition of the auxiliary solid propellant particles by the primary high-pressure gas, the auxiliary solid propellant particles are configured to burn in order to generate the auxiliary high-pressure gas. The auxiliary high-pressure gas is configured to be directed towards the turbine in response to the second valve moving to the open position. The primary solid propellant particles have a central perforation that extends longitudinally through the primary solid propellant particles, When the first valve is in the closed position and the second valve is in the open position, the auxiliary high-pressure gas exits the nozzle structure through the central perforation. system.

2. The system according to claim 1, further comprising: a third valve for releasing pressure from the housing to extinguish the auxiliary solid propellant particles; a controller configured to control at least one of the first valve, the second valve, and the third valve in order to selectively supply power to the generator; and a power supply configured to supply a second power to the controller.

3. The system according to claim 1, wherein the auxiliary solid propellant particles are sealed from the primary solid propellant particles in response to the first valve moving to the closed position.

4. A method for generating power for rockets, To burn primary solid propellant particles to generate primary high-pressure gas for supplying thrust to the rocket, To ignite auxiliary solid propellant particles, a first valve is opened to divert a portion of the primary high-pressure gas to the auxiliary solid propellant particles, wherein the auxiliary solid propellant particles are located in a separate housing from the primary solid propellant particles, the opening of the valve is performed. The auxiliary solid propellant particles are burned to generate an auxiliary high-pressure gas. Rotating the turbine using the aforementioned auxiliary high-pressure gas, The turbine drives the generator, To generate electricity with the aforementioned generator, Closing the first valve, In response to the closing of the first valve, the auxiliary solid propellant particles are sealed from the primary solid propellant particles. Opening the second valve, In response to the opening of the second valve, the auxiliary high-pressure gas is directed throughout the turbine, and Discharging the auxiliary high-pressure gas from the nozzle structure through the central perforation of the primary solid propellant particles, Methods that include...

5. Closing the second valve, To reduce the pressure inside the housing, the third valve is opened, and The method according to claim 4, further comprising extinguishing the auxiliary solid propellant particles in response to a decrease in the pressure within the housing.

6. Closing the third valve, The first valve is opened again to divert the second portion of the primary high-pressure gas to the auxiliary solid propellant particles, and In response to the second portion of the primary high-pressure gas being diverted to the auxiliary solid propellant particles, the auxiliary solid propellant particles are reignited. The method according to claim 5, further comprising:

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