Patent Publication Number: US-2023151779-A1

Title: Electrochemical rocket motor

Description:
BACKGROUND 
     Field of the Inventions 
     This disclosure relates to a rocket motor that uses electrochemical activation of the oxidizer and fuel prior to activation. This rocket motor can be shipped and stored with an inert oxidizer and/or fuel that can be activated prior to use. The use of inert oxidizer and fuel allows for safe transport, storage, and handling of the solid rocket motor, as well as a controllable oxidizer to fuel ratio and thrust level. 
     Description of the Related Art 
     The current state of the art of rocket motors consists of solid motors, liquid motors, and hybrid motors. Solid motors combine a solid fuel with an active solid oxidizer and are susceptible to premature activation from environmental conditions. It also has a predetermined thrust level based on motor design and manufacture. Liquid rocket motors typically use pressurized oxidizers and complex pumps to move liquids through the motor to the fuel. This allows for selectable thrust levels, but often requires not only moving pumps but also cryogenic liquids. Hybrid motors typically use a solid fuel and a liquid oxidizer. Hybrid motors behave like the fully liquid systems in their complexity and thrust control. 
     Solid rocket motors require extensive handling and storage requirements to avoid accidental triggering of the motor. Other controllable motors such as liquid or hybrid rocket motors require pumps and moving parts, increasing complexity and failure points. Liquid and hybrid motors may require pressurized oxidizers and/or fuels or cryogenic liquids in addition to complex pumps to move the liquids through the motor. 
     Typical solid rocket motors are comprised of high energy materials such as oxidizing salts or materials and carbonaceous or other types of fuels. These mixtures of oxidizer and fuel are classed as explosives and the manufacturing, storage, and distribution of them is not without risk. The manufacturing stage is often the most dangerous step and many chemical plants manufacturing these materials have exploded. In addition, many applications for solid rocket motors are in highly unpredictable locations such as war zones. 
     Current solid state rocket motors have a thrust capability fixed at the point of fabrication, which does not allow for a variable impulse. For conventional rocket motors, the amount of thrust is set from the design and manufacture point and cannot be changed. This is due to several factors, including the defined mixture and mass of the active oxidizer and fuel. 
     SUMMARY OF THE INVENTIONS 
     An aspect of at least one of the inventions disclosed herein includes the realization that an electrochemical rocket motor can be manufactured using oxidizer and/or fuel in an inert state and later activated. For example, an electrochemical rocket motor according to some embodiments disclosed herein can be manufactured with materials that can be electrochemically converted to oxidizing or reducing states from an inert state. Prior to activating such a device, there is no substantial amount of oxidizing material available for supporting combustion. Thus, the completed motor, prior to activation, can be incorporated into a space launch vehicle, military vehicle, or ordnance without risk of accidental ignition. The motor can then be activated at a desired time, for example but without limitation, after the space launch vehicle has been set on the launchpad and otherwise, fully prepared and oriented for launch, or in a military rocket launcher prior to engaging an enemy. The motor can be activated by way of an electrochemical process, creating an oxidizing material from the as manufactured solid rocket material(s), for example, by applying an electrical potential to the material. This potential forces an electrochemical change in the oxidizer and fuel precursors converting them into mission ready oxidizer and fuel. The solid rocket motor would then be ready for ignition. 
     Another aspect of at least one of the inventions disclosed herein includes the realization that using an electrochemically activated material for a solid rocket motor allows for adjustment of the thrust generated by the motor, after final design, assembly, transport, storage, and/or deployment of the motor. For example, adjusting the quantity of electricity applied to the electrochemical material or by adjusting the voltage at which the electricity is applied, the amount of oxidizing material created can be adjusted. Due to the balance of oxidizer and fuel, more oxidizer will produce more thrust and less oxidizer will produce less thrust. Thrust output of conventional solid rocket motors cannot be adjusted after manufacture as the ratio of oxidizer and fuel is preset by the quantities of the actively oxidizing materials. Thus, such embodiments create additional opportunities for accommodating late payload changes, for example, in missions with late-addition rideshare capabilities or other changes to payload, space vehicle, or other launch parameters. It allows control of landing location for terrestrially targeted rockets by increasing or decreasing the amount of thrust. 
     Another aspect of at least one of the inventions disclosed herein includes the realization that by forming a solid rocket motor with a spiral or planar configuration allows for a simpler manufacturing process. For example, with the spiral configuration, thin layers of oxidizer, fuel, and separator can be alternatingly stacked and then rolled into a spiral. Thus, such embodiments which can provide enhanced manufacturing efficiency. This can also be achieved through the use of interdigitated planes, rods, or other structures that creates a defined mixing of the oxidizer and fuel, a critical and difficult to control feature in solid rocket motor manufacture. 
     Another aspect of at least one of the inventions disclosed herein includes the realization that creation of oxidizer and/or fuel on demand allows for the use of materials that are typically considered too unstable or reactive for solid rocket motors. These materials may be too unstable to last from manufacture to usage, too shock sensitive for transport, or too high energy to risk in manufacture. Since the electrochemical rocket motor generates the oxidizer and/or fuel within the motor prior to activation potentially at the location of usage, the range of materials that can be used can encompass compounds that would otherwise be too dangerous for conventional solid rocket motor application. 
     Thus, in some embodiments, an electrochemical rocket includes a rocket body, a motor disposed within the rocket body, and a nozzle. The motor is disposed within the rocket body. The motor includes an oxidizable framework, a reducible framework, and a non-electrically conductive separator. The oxidizable framework comprises an oxidizable material. The oxidizable material being electrochemically convertible such that during electrical charging, at least a portion of the oxidizable material is converted into an active oxidizer. A first conductive framework is in electrical communication with the oxidizable material. The reducible framework comprises a reducible material, which, during charging, is at least partially reducible to a fuel. A second conductive framework is in electrical communication with the reducible material. The non-electrically conductive separator is positioned between and electrically separating the oxidizable material and the reducible material. The nozzle is fluidically connected to an end of the motor, wherein the nozzle is shaped to generate thrust by discharging gases. Prior to charging, the oxidizable material and the reducible material are substantially inert and wherein after charging, in use, the active oxidizer and the fuel can be combined to combust, and thereby create combustion gases discharged through the nozzle and generate thrust. 
     In some embodiments, the electrochemical rocket includes a mechanism for piercing the non-electrically conductive separator. 
     In some embodiments, the thrust is controlled by partially charging the oxidizable material and the reducible material. 
     In some embodiments, the oxidizable material and the reducible material are shaped as thin spiral sleeves separated by thin spiral sleeves of the non-electrically conductive separator. 
     In some embodiments, the oxidizable material and the reducible material are configured in thin planar layers separated by thin planar layers of the non-electrically conductive separator. 
     In some embodiments, the oxidizable material and the reducible material are arranged in an interdigitated array. 
     In some embodiments, the oxidizable material and the reducible material comprise thin flat layers. 
     In another embodiment, an electrochemical motor comprises a housing enclosing an interior space. The interior space of the housing comprises an oxidizable framework, a reducible framework, and a non-conductive framework. The oxidizable framework comprises an oxidizable material. The oxidizable material is electrochemically convertible such that during electrical charging at least a portion of the oxidizable material is converted into an active oxidizer. The reducible framework comprises a reducible material, which, during charging, is at least partially reducible to a fuel. The non-electrically conductive separator is positioned between the oxidizable material and the reducible material. Prior to charging, the oxidizable material and the reducible material are substantially inert and wherein after charging, in use, the active oxidizer and the fuel can be combined to combust, and thereby create combustion gases discharged through a nozzle and generate a thrust. 
     In some embodiments, the reducing framework is converted into the fuel. 
     In some embodiments, the thrust is controlled by partially charging the oxidizable material and partially charging the reducible material. 
     In some embodiments, the oxidizable material and the reducible material are spiral sleeves of thin layers separated by spiral sleeves of thin layers of the separator. 
     In some embodiments, the oxidizable material and the reducible material comprise planar layers separated by thin planar layers of the separator. 
     In some embodiments, the oxidizable material and reducible material are arranged in an interdigitated array. 
     In some embodiments, the oxidizable material and the reducible material comprise thin, flat layers. 
     In another embodiment, a method of using an electrochemical rocket motor is provided. The method includes orienting the electrochemical rocket motor. The electrochemical rocket motor comprises an oxidizable framework, a reducible framework, a non-electrically conductive separator, and a nozzle. The oxidizable framework comprises an oxidizable material. The oxidizable material being electrochemically convertible such that during electrical charging, at least a portion of the oxidizable material is converted into an active oxidizer. A first conductive framework is in electrical communication with the oxidizable material. The reducible framework comprises a reducible material, which, during charging, is at least partially reducible to a fuel. A second conductive framework is in electrical communication with the reducible material. The non-electrically conductive separator is positioned between and electrically separating the oxidizable material and a reducible material. The nozzle is connected to the end of a motor for channeling gas release. The method further includes electrochemically oxidizing the inert oxidizer, triggering the ignition of the oxidizer and the fuel to produce hot gasses and channeling the gasses through the nozzle to generate thrust. 
     In some embodiments, the triggering occurs via piercing the separator. 
     In some embodiments, the triggering occurs via electrically sparking a hole in the separator. 
     In some embodiments, the triggering occurs via thermally melting the separator. 
     In some embodiments, the amount of thrust generated is controlled. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       These and other features, aspects, and advantages of the present disclosure will now be described with reference to the drawings of embodiments, which embodiments are intended to illustrate and not to limit the disclosure. One of ordinary skill in the art would readily appreciate that the features depicted in the illustrative embodiments are capable of combination in manners that are not explicitly depicted but are both envisioned and disclosed herein. 
         FIG.  1    is a schematic cross sectional diagram of an embodiment of a solid rocket motor. 
         FIG.  2    is a schematic diagram of another embodiment of the solid rocket motor having an oxidizing framework and reducing framework within the motor. 
         FIG.  3    is a schematic diagram of yet another embodiment of the solid rocket including paired layers of oxidizable material and paired layers of reducible material within a motor. 
         FIG.  4    is a diagram of a prismatic or stacked design of a solid rocket motor. 
         FIG.  5    illustrates an interdigitated design of a solid rocket motor. 
         FIG.  6    is a diagram of a spiral design of a solid rocket motor. 
         FIGS.  7 A and  7 B  are schematic diagrams of the operation of a spark gap trigger. 
         FIGS.  8 A and  8 B  are schematic diagrams of the operation of a pressure trigger or a mechanical trigger. 
         FIGS.  9 A and  9 B  are schematic diagrams of the operation of a thermal decomposition trigger. 
         FIG.  10    depicts the channeling and ejecting of hot gasses out of the nozzle to generate thrust. 
         FIG.  11    is a diagram of a cylindrical design of a solid rocket motor. 
         FIG.  12    is a flow chart of a method of using a solid rocket motor. 
     
    
    
     DETAILED DESCRIPTION 
     This disclosure is directed to solid rocket motors that can be shipped and stored with an inert oxidizer and or/fuel and that can be activated after manufacture and prior to use, allowing for safe transport, storage, and handling. The motor consists of a housing containing fuel and an inert oxidizer, separated by an electrically non-conductive, but ion conducting interface. The housing has a nozzle at the end for gas release and channeling. Prior to use, the inert oxidizer is activated by electrochemically oxidizing it, generating an active oxidizer. Optionally, the same procedure can also drive a reduction process for generating additional fuel. Ignition can be triggered with various techniques, including but without limitation to thermally by melting a separator between the oxidizer and fuel, electrically by creating a spark to form a hole in the separator, mechanically by piercing the separator, electrically/thermally by inducing thermal breakdown of the oxidizer and/or fuel, or other techniques. The contact of the oxidizer and fuel may start a chain reaction whereby the contents of the housing ignite and combust, generating hot gasses to be funneled out through the nozzle to generate thrust. Other ignition techniques can also be used wherein triggering can be caused by high temperatures such as sparks, flames, or plasmas. 
     Solid Rocket Motor 
       FIG.  1    is a schematic diagram of an embodiment of a rocket  100 . The rocket  100  can comprise a rocket body  102 , a solid rocket motor  104 , a housing  106  and a nozzle  114 . 
     The motor  104  can comprise an oxidizer material  205  on a first conductive framework  111 . The motor  104  can also comprise a fuel material  204  on a second conductive framework  113 . The oxidizer  205  can be in an inert state, as can the fuel  204  on conductive framework  113 . The conductive frameworks  111 ,  113  can also be the oxidizer  205  and fuel  204  themselves for cases where the oxidizer  205  and fuel  204  in their initial or manufactured states are electrically conductive. For example, in some embodiments, the oxidizer material  205  and the fuel material  204  can be used without conductive frameworks  111 ,  113 . The oxidizer material  205  and the fuel material  204  can be sufficiently conductive that no additional conductive framework is needed. In other embodiments, the conductive frameworks  111 ,  113  can be composed of conductive materials such as metals, conductive carbons or polymers, or other electrically conductive materials. 
     In some embodiments, the oxidizer  205  includes an oxidizing or oxidizable material in a chemical state such that the oxidizer is not available for supporting oxidation (combustion) in the inactive state, but can be released by activation, for example, by applying an oxidizing electric current to the oxidizer  205 . 
     The conductive frameworks  111 ,  113 , can extend throughout the respective oxidizer and fuel materials  205 ,  204 . The conductive material of the conductive frameworks  111 ,  113  can be, for example, aluminum or copper. The thickness of the conductive materials can be up to 10&#39;s of cm thick. However, other thicknesses can also be used. The ratio of conversion material (i.e., the oxidizer  205  or fuel  204 ) to conductive material can be from 1:10 10,000:1, however, other ratios can also be used. The ratio can be zero when the oxidizer  205  and the fuel  204  are used without conductive frameworks  111 ,  113  as described above, for example where the oxidizers and fuels are conductive. 
     The oxidizer  205  and the fuel  204  can be separated by a separator  108 . The separator  108  can be a thin, electrically non-conductive, ionically conductive layer. In some embodiments, the separator  108  can comprise a porous polymer film or a ceramic material. The separator  108  can be ion transporting, and in some embodiments function as an electrolyte. In some embodiments, there can be liquid, solid, polymer, or gel electrolyte containing ions that bridges the oxidizer and fuel. In some embodiments, the separator  108  can include a liquid, gel, polymer, solid, or ceramic electrolyte, or other suitable material to bridge the oxidizer  205  and fuel  204 . 
     By storing the oxidizer  205  in its inert state and maintaining a physical and/or electrical separation between the inert oxidizer  205  and fuel  204 , the rocket  200  is in a benign state until the oxidizer  205  is activated, for example, by electrical charging or techniques for electrochemical or chemical oxidization. Therefore, the overall safety when storing, transporting, or handling the rocket  100  can be increased. 
     The inert oxidizer  205  and fuel  204  materials can be electrically and/or ionically conductive, or can include materials for conduction throughout, in layers, rods, grids, or other arrangements that allow for electrical and/or ionic current to flow into and out of the materials. 
     A positive lead  206  can be electrically connected to the oxidizer  205  and a negative lead  207  can be electrically connected to the fuel  204 . In some embodiments, the negative lead  207  and the positive lead  206  can be mounted so as to be accessible on the exterior of the rocket  100 , for example, to be connected to a power source  208 , described below. 
     Optionally, the oxidizer  205  can be in the form of a lithium ion battery cathode material having alternating layers of metals and oxygen in its crystal structure. Fully discharged, this material (examples are lithium cobalt oxide, (LiCoO 2 , LCO), lithium nickel cobalt aluminum oxide (LiNi 0.8 Co 0.17 Al 0.03 , NCA), lithium nickel manganese cobalt oxide (Li m Ni x Mn y Co z O 2 , NMC), lithium iron phosphate (LiFePO 4 , LFP), lithium manganese oxides (Li 2 MnO 2  of Li 2 Mn 2 O 4 ), LMO), and others) is very stable and are not oxidizing. During normal activation operations, the Li-ions are removed, creating oxidizing materials available for oxidizing the fuel with an electrochemical potential in excess of 4 V vs. Li/Li + . The amount of Li that is extracted can be adjusted to create different amounts of oxidizer for the rocket. Equation 1 shows an example with LCO having half of its lithium removed from the crystal structure spontaneously decomposing to release heat (Δ) and oxygen. This energy of decomposition heats up the gasses released and helps to generate thrust. 
       6Li 0.5 CoO 2 →2Co 3 O 4 +2O 2 +3Li+Δ  (1)
 
     In some embodiments, the fuel can be a carbonaceous anode material, with the carbon in a layered structure similar to graphite, graphene, or other sp 2  carbons. The layered carbon can be electrochemically reduced in the presence lithium ions such that the lithium ions are incorporated into the carbon material structure between the carbon layers and the material accepts an electron from the electrical power supply. This reduced material is highly reducing, as low as 0.05 V vs. Li/Li + . This material can react for example with oxygen (or similarly with other oxidizing materials) in a manner described in Equation 2: 
       4LiC 6 +50O 2 →2Li 2 O+24CO 2 +Δ  (2)
 
     This reduced material is a more energy dense fuel than conventional carbon type fuels such as butyl rubbers, polymers, or alkanes/alkenes/alkynes. In some embodiments this charged carbon fuel can be supplemented or replaced through the formation of lithium (or other highly reactive metals such as sodium, magnesium, aluminum, or hydrogen) to serve as a fuel. These metals are formed by the electrochemical reduction of the ions of these metals to form deposits of the solid metal (or bubbles of hydrogen) which can form on the surface of a conductive material such as carbon or another metal and serve as a fuel. 
     Equation 3 shows the combustion of lithium metal with oxygen: 
       4Li+O 2 →2Li 2 O+Δ  (3)
 
     Additionally, the oxidizer  205  can include a first conductive framework  111 , extending therethrough or otherwise in electrical contact with the material forming oxidizer  205 . Similarly, the fuel  204  can include a second conductive framework  113 , extending therethrough or otherwise in electrical contact with the material forming the fuel  204 . The first and second conductive frameworks  111 ,  113  can be made from materials, including but without limitation, metals, typically copper, titanium, stainless steel, aluminum; conductive polymers, carbon materials, or other electrically conductive materials. Together, the oxidizer  205  and first conductive framework  111  can be considered as forming an oxidizer framework or an oxidizable framework  111 . Similarly, fuel  204  and the second conductive framework  113  can be considered as forming a fuel framework or a reducible framework  113 . In such embodiments, the negative lead  207  can be electrically connected to the first conductive framework  111  and the positive lead  206  can be electrically connected to the second conductive framework. Conductive frameworks such as the first and second conductive frameworks  111 ,  113 , can be included in all of the embodiments of oxidizer frameworks and reducible frameworks disclosed below. 
     One technique for triggering ignition of the oxidizing agents and fuel, in some embodiments, is heating. Combustion can be initiated in a number of ways. In one mode, for example, when using certain polymer separators heated past ˜140° C. internal temperature the polymer separator keeping the oxidizing cathode and the reducing anode (or fuel) melts. The two materials, cathode and anode, oxidizer and fuel, touch and release their stored energy, both the electrochemically stored energy as well as the chemical energy of combustion of the materials. This heats the adjacent activated oxidizing materials cathode, causing spontaneous decomposition forming oxygen and heat, which rapidly spreads the thermal runaway condition causing combustion which is discharged as an exhausting plume. Other oxidizers and reducers and triggering techniques can also be used in a similar manner. 
       FIG.  1    also depicts a charging and monitoring circuit  202 . The charging and monitoring circuit  202  can be connected to the negative lead  207  and the positive lead  206  mounted so as to be accessible on the exterior of the motor  100 . The charging and monitoring circuit  202  can include an activation device configured to activate the oxidizer  205  and/or the fuel  204 , e.g., converting the oxidizer  205  from an inactive state to an active state, e.g., freeing oxidizing agents from inactive oxidizer  205 . In some embodiments, the activation device can comprise a power source  208  configured to drive an electrochemical process that converts oxidizer  205  to its target activated (oxidizing) state. In some embodiments, switches (not shown) can be used to activate the conductive frameworks power source  208 , but other activation devices are possible. The charging and monitoring circuit  202  can include a voltage sensor  209  for monitoring the state of charge of the motor. For example, the motor  200  can be charged to different degrees, further detailed below. In some embodiments, the power source  208  can also be used to activate the fuel  204 . 
     The leads  206  and  207  can be made of any suitable material. Non-limiting examples of a suitable material include metals, conductive polymers, carbon materials, or other electrically conductive materials. In some embodiments, the conductive materials incorporated into any conductive framework, such as aluminum, polymers, and carbons can be converted into fuel, combusted in the motor  200 . 
       FIG.  2    is a schematic representation of an optional internal structure of a motor  200  in which an oxidizable framework  302  serves as the oxidizer  205  and a reducible framework  304  serves as the fuel  204  of the embodiment of  FIG.  1   . As shown in  FIG.  2   , the oxidizing framework  302  and reducing framework  304  can be arranged in an alternating spacing and are electrically separated by an electrically nonconductive separator  108 , for example a non-electrically conductive separator. The oxidizable framework  302  is connected to the negative lead  207 . The reducible framework  304  is connected to the positive lead  206 . 
     The negative and positive leads  207 ,  206  can be electrically isolated from each other. The leads  207 ,  206  can be connected to an activation device, such as the power source  208  of  FIG.  1   . As with the embodiment of  FIG.  1   , the oxidizable framework  302  can be configured to be charged or electrochemically oxidized so as to convert the inert oxidizer within the oxidizable framework  302  into an active state. The reducible framework  304  can also be configured to convert a reducible material into fuel. 
     As noted above, in some embodiments, the power source  208  can be used to fully or partially activate the motor  200 , for example, by electrically “charging” the oxidizable framework  302  and reducible framework  304 . In some embodiments, partial charging can occur, at any percentage, examples of which include 0%, 25%, 50%, 75%, and 100%, or any percentage therebetween. In some embodiments, due to the charging process, the partial charging of the motor will be uniform across the materials of the motor, for example, oxidizer and fuel will be generated uniformly or substantially uniformly through the oxidizable material and reducible material, respectively. 
     The voltage sensor  209  can be used to monitor the state of charge of the motor  200 . The voltage sensor  209  can detect a voltage differential produced by additional electrons being provided to the oxidizable material within the oxidizable framework  302  during the charging process. The electrons removed from the oxidizable material can, in some embodiments, increase the electrochemical potential (increase oxidizing capability). The deficit of electrons in the oxidizable material in the oxidizer framework  302 , can create a more positive electrochemical potential. The addition of electrons to the reducible material in the reducible framework  304  can lower the electrochemical potential (more energetic fuel). The changes in the electrochemical potential of the two frameworks  302 ,  304  can establish the measured voltage differential which can be detectable by the voltage sensor  209 . The electrochemical potential difference can be proportional to the “charged” state of the motor, for example, the larger the voltage detected by the voltage sensor  209 , the more oxidizing the cathode material is. Thus, voltages detected by the voltage sensor  209  can be correlated to a percentage activation of the motor, e.g., X volts corresponds to Y% activation. 
     Prior to charging, the motor  200  is in a benign state. The oxidizable material  205  of the oxidizable framework  302  can be in its inert state and not have been charged or electrochemically oxidized. The reducible material  204  of the reducible framework  304  can also be in an inert state and not yet been converted to more active fuel. 
     The motor  200  can be partially or fully charged by applying a sufficient voltage and current to the leads  206 ,  207 . In some embodiments, the motor  200 , and more specifically, the oxidizable framework  302  and the reducible framework  304  can be sized and arranged such that application of a current and voltage to the frameworks  302 ,  304  results in a predetermined amount of the available oxidizing agent in the oxidizable material  205  within the oxidizable framework  302  being released and a predetermined amount of the fuel material available in the reducible material in the reducible framework  304  being converted to fuel. Similarly, the motor  200  can be “charged” to any desired degree, e.g., 0%, 25%, 75%, 100%, or any amount therebetween or greater. 
     The thrust ultimately produced by the motor  200  can be controlled by the amount of oxidizer  205 , fuel  204 , or combination thereof activated by charging. The user can decide how much charge at the time of use. For example, the rocket motor can be partially charged to 0%, 25%, 50%, 75%, or any value up to or exceeding 100%. This can allow for more flexibility and adaptability of the rocket motor. The amount of charge can determine the total thrust output during the burn of the motor  200 . The amount of charge can also determine how quickly or slowly the rocket motor ignites or the thrust profile (i.e., a long or short a burn). The capability of the motor to produce thrust is given by the ratio of oxidizer  205  to fuel  204  generated in the motor  200 . In the uncharged state there can be no activated oxidizer  205 , and a baseline amount of fuel  204 . The charging of the motor with an electrical current to generate more oxidizer  205  and make the fuel  204  more energetic activates the motor  200 . Due to the excess of fuel  204  in this system, the activated state of the battery is defined as the percent of total oxidizing capability that the motor  200  is at in any given charged state. 
     The oxidizable material  205  and reducible material  204  can be configured in a variety of designs within the housing of a motor (e.g., motor  200 ). 
     For example,  FIG.  3    illustrates another optional internal structure of a motor  200  including an oxidizable framework  312  and a reducible framework  314 . In this embodiment, layers of the oxidizable framework  312  are arranged in pairs of layers, with alternating pairs of layers of the reducible framework  314 , and with single layers of oxidizable framework  312  as the outermost layers. The oxidizable framework  312  can be separated from the reducible framework  314  by a separator  108 , as described above. The oxidizable framework  312  can be connected to the charging lead  306  to allow for conversion of the oxidizable framework  312  from an inert state to an active or charged state. The reducible framework  314  can be connected to the charging lead  308  to convert the reducible material to a fuel. The leads  306 ,  308  can be connected to a charging and monitoring circuit  202 . The charging and monitoring circuit  202  can have a power source  208  and a voltage sensor  209 . 
       FIG.  4   , illustrates an embodiment of a prismatic or stacked configuration  600 . In this embodiment, thin layers of an oxidizable framework  602  can be alternatingly stacked with thin layers of a reducible framework  604 . The thin layers  602  and  604  can be separated by thin layers of a separator (not shown) at positions  606 . The layers of oxidizable framework  602  are connected to a first (negative) lead  603  and the layers of reducible framework  604  are connected to a second (positive) lead  605 . The leads  603 ,  605  can be connected to a charging and monitoring circuit (not shown), such as the charging and monitoring circuit  202  shown in  FIGS.  1 ,  2 , and  3   . 
       FIG.  5    illustrates an interdigitated structure configuration  700  of an inert oxidizable framework  702  and a reducible framework  704 . The oxidizable framework  702  and the reducible framework  704  are configured in rod-like shapes and placed alternatingly next to each other. Although not shown, a separating material (e.g., separator  108 ) can be included in this embodiment to separate the oxidizable framework  702  and the reducible framework  704 . The oxidizable framework  702  is connected to a first (negative) lead  703  and the reducible framework  704  is connected to a second (positive) lead  705 . The leads  703 ,  705  can be connected to a charging and monitoring circuit (not shown), such as the charging and monitoring circuit  202  shown in  FIGS.  1 ,  2 , and  3   . 
       FIG.  6    illustrates a spiral configuration  800  of an oxidizer framework  802 , a reducible framework  804 , and a separator  806 .  FIG.  8    is a top view of the spiral design  800 . A thin layer of oxidizer framework  802 , a thin layer of reducible framework  804  and thin layers of a separator  806  are stacked together and shaped to form a spiral type structure, as shown. The spiral configuration  800  can ease the manufacturing process because individual concentric sleeves are not needed. The thin layers  802 ,  804 , and  806  can be stacked, then rolled to form a compact configuration that is more space efficient for the typical, cylindrical configuration of a rocket motor body. 
     Various different techniques can be used to ignite the oxidizer and fuel.  FIGS.  7 - 9    depict three possible triggering processes. The triggering of the solid rocket motor is not limited to the three triggering processes depicted; other triggering processes can also be used. At the time of ignition, hot gasses will be produced. 
       FIGS.  7 A and  7 B  depict a spark gap trigger. Pre-triggered state  900  illustrates a separator  108  and a trigger  902   a  in an inactive state ( FIG.  7 A ). The spark gap trigger  902   a  can electrically spark  902   b  a hole in the separator  108  to trigger contact and ignition between an oxidizer and a fuel ( FIG.  7 B ). 
       FIG.  8 A  depicts a pressure trigger comprising a first portion  904   a  and a second portion  904   b  in a pre-triggered state  903 . In some embodiments, the first portion  904   a  can apply a force on a separator  108  moving the separator  108  towards the second portion  904   b.  The second portion  904   b  can puncture or pierce the separator  108  to trigger contact and ignition between the oxidizer and fuel as shown by the triggering process  905  ( FIG.  8 B ). 
       FIGS.  9 A and  9 B  depict a thermal decomposition triggering event. Pre-triggered state  907  shows a fully intact separator  108  with no thermal energy being applied ( FIG.  9 A ). The triggering process  906  can produce thermal energy or heat  908  to thermally melt the separator  108 . The thermal decomposition of the separator  108  can trigger contact and ignition of the fuel and oxidizer ( FIG.  9 B ). 
       FIG.  10    is a schematic illustration of the motor  200 , after charging and igniting, for example, with any of the above ignition devices. As described above, the motor  200  can include an oxidizable framework  302  and a reducible framework  304 . The oxidizable framework  302  can be connected to a negative lead  207  and the reducible framework  304  can be connected to a positive lead  206 . The leads  206 ,  207  can be connected to a charging and monitoring circuit  202  as shown, for example, in  FIG.  2   . As illustrated, the combustion results in the channeling and ejecting of hot gasses  254  out of the nozzle  114  to generate thrust. More specifically, after the ignition is triggered, the contact of the fuel  204  and oxidizer  205  starts a chain reaction. 
     Ignition can be triggered by any of the methods and devices described above, including an electrical spark  902   b,  a pressure trigger  904   a,    904   b,  and thermal heat  908  as shown. The content of the housing  106  ignites and generates hot gasses  254 . The hot gasses  254  can pass through gas flow channels  250  comprising compartments  251  to an expansion chamber  252  for gas expansion and be funneled out the nozzle  114  to generate a controlled thrust as shown by arrow  253 . The amount of thrust  253  generated can be controlled by how much oxidizer  205  and fuel  204  is generated by the conductive frameworks as described throughout this application. 
       FIG.  11    illustrates an embodiment of a cylindrical motor  500 . The cylindrical motor  500  can include thin layers of an oxidizable framework  502  in its inert state and thin layers of a reducible framework  504  separated by thin layers of a separator  510 . The thin layers of an oxidizable framework  502 , a reducible framework  504 , and a separator  510  are shaped as concentric sleeves or as spiral rolled sleeves. For example, a concentric sleeve of an oxidizable framework  502  can have a concentric sleeve of a separator  510  positioned inside it and the concentric sleeve of the separator  510  can have a concentric sleeve of a reducible framework  504  positioned inside it. Any number of layers of concentric sleeves may be used. Any of the above describe triggering devices and methods can be used with motor  500 . For example, an electrical spark  902   b  can be used as shown. Any trigger described above can be used and connected to a trigger lead  535 . The trigger lead  535  can be connected to a launch control box  540 . 
     The oxidizable framework  502  can be connected to a first lead  506  and the reducible framework  504  can be connected to a second lead  508 . The leads  506 ,  508  can be connected to a charging and monitoring circuit  202  which can have a power source  208  and voltage sensor  209 . The leads  506 ,  508  can also be connected to the launch control box  540 . The thin layers of concentric sleeves  502 ,  504 ,  510  are configured to form a cylindrical shape, as shown in  FIG.  11   . In some embodiments the concentric sleeves  502 ,  504 ,  510  can be formed as rings of material. The cylindrical motor  500  can include an insulator  512  positioned between the internal elements of the motor  500  and a motor housing  106 . The insulator  512  can limit or reduce the amount of heat exposed to the housing  106  during ignition. The cylindrical motor  500  can include a passage  518  to a nozzle  114  for gas release after ignition of an activated oxidizer and fuel. The gas can move to expansion chamber  252  to smooth the flow of the gas and then the gas can move to and down passage  518  and then out the nozzle  114  as shown by the arrows. The motor  500  can also include a top cover  530  and a PTC  531 . 
     Methods 
       FIG.  12    depicts an exemplary method of using a solid rocket motor. Starting at block  1102  the electrochemical or solid rocket motor can be oriented for use. The rocket motor used can be any solid rocket motor including but not limited to any of the embodiments previously described. 
     Moving to block  1104  the inert oxidizer of the solid rocket motor can be electrochemically oxidized or charged. The motor can be charged to any value up to or exceeding 100% (fully charged). For example, the motor can be charged 25%, 50%, 75%, 100% or any other possible value. The amount of charge can determine how quickly the motor is ignited or determine the total thrust produced. The electrochemically oxidizing of the inert oxidizer generates an active oxidizer. In some embodiments the electrochemically oxidizing process can generate additional fuel. 
     Moving to block  1106  the fuel and the oxidizer can be combined to trigger ignition of the solid rocket motor. As discussed above, ignition of the oxidizer and fuel can be triggered in any suitable way, including but not limited to, thermally melting the separator, electrically sparking a hole in the separator, and mechanically piercing the separator. The contact of the oxidizer and the fuel can start a chain reaction whereby the contents of the housing ignite and generate hot gasses. 
     Moving to block  1108  the hot gases can expand in the compartments for expansion and can be directed through the gas flow channels. The gasses can be ejected out of the nozzle generating thrust. The amount of thrust generated can be controlled by the conductive frameworks or through other methods as described throughout this application. For example, the thrust output can be defined by the amount of oxidizer generated which can allow for a more controlled ignition. Additionally, the thrust does not need to be set from the time of design or manufacture of the motor. 
     Applications 
     The following description of possible applications of the inventions described herein are non-limiting examples. The inventions described herein can be applied to rocket motors that are expected to see dangerous handling or storage conditions, such as those on the battlefield. For example, a recoilless rifle, RPG round, or missile motor is in danger of activation prior to use. In addition, the simple and lightweight nature of the disclosure means it could be used for small sat maneuvering, as safe storage in rideshares requires no active stored energy. Other possible applications of the inventions include, but are not limited to, safe ammunition movement, launch assistance, launch vehicles, gas generators, any application of current state solid motors, short take off runways, and in connection with small satellites.