US2708342A - Mixed fuel control system for a rocket motor - Google Patents

Mixed fuel control system for a rocket motor Download PDF

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Publication number
US2708342A
US2708342A US240216A US24021651A US2708342A US 2708342 A US2708342 A US 2708342A US 240216 A US240216 A US 240216A US 24021651 A US24021651 A US 24021651A US 2708342 A US2708342 A US 2708342A
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United States
Prior art keywords
oxidizer
pump
valve
reservoir
fuel
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Expired - Lifetime
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US240216A
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English (en)
Inventor
Allen Sidney
Hurden Dennis
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Armstrong Siddeley Motors Ltd
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Armstrong Siddeley Motors Ltd
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Publication of US2708342A publication Critical patent/US2708342A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/44—Feeding propellants
    • F02K9/56—Control

Definitions

  • This invention relates to a control system for a rocket motor of the kind having igniter equipment and combustion equipment for a mixture of a liquid fuel (for example, methyl alcohol and water) and liquid oxidizer (for example, liquid oxygen or nitric acid) forming the propellent, and a pump and valve means both for the fuel and for the oxidizer.
  • a liquid fuel for example, methyl alcohol and water
  • liquid oxidizer for example, liquid oxygen or nitric acid
  • the main object is to ensure satisfactory and economical operation of the motor.
  • the oxidizer system (through the pump as far as the associated valve means) is first supplied with liquid oxidizer whereby to cool the oxidizer system and initiate the priming of the oxidizer pump, and the fuel pump will not commence delivery until after the oxidizer pump has attained a stable delivery to a by-pass leading back to a reservoir for the oxidizer.
  • the fuel pump is automatically caused to effect delivery only on the operation of a time-delay switch which is energized when the outlet pressure of the oxidizer pump reaches a predetermined value.
  • the fuel pump on commencing delivery, may immediately deliver to the igniter equipment, the oxidizer pump being automatically caused to deliver to the igniter equipment only when the outlet pressure of the fuel pump reaches a predetermined value.
  • both the valve means are partially opened automatically to deliver limited supplies to the combustion equipment; whilst, when full thrust is required, the by-pass for the oxidizer is closed and both the valve means are fully opened to deliver full supplies to the combustion equipment.
  • Figures 1 and 2 jointly show a diagram of electrical, pneumatic and other control means according to the invention, Figure 1 fitting to the left of Figure 2;
  • FIG. 3 is a sectional elevation of the valve means for the oxidizer system, such as is described in the specification accompanying co-pending Application Serial No. 240,217;
  • Figure 4 is a sectional elevation of the ignition end of the combustion equipment to a larger scale.
  • FIG. 3 shows a casing with an inlet 11 and an outlet 12.
  • the latter is connected with a passage 13 by means of openings 14 in the head of a throttle valve member 15 biassed to the ofi position shown and movable to the open position by the application of fluid pressure to the inlet 16.
  • the passage 13 is shown as shut off from the inlet 11 by the head of a stop valve member 17 biassed to the closed position and movable to the open position by the application of fluid pressure to the inlet 18.
  • 19 is a normallyopen outlet connected to a by-pass pipe 20 ( Figure 2) and closable by the head of a valve member 21 when "ice fluid pressure is applied to the inlet 22.
  • valve 23 is an outlet connected to a pipe 95 ( Figure 2) which is hereinafter referred to, the outlet 23 being normally segregated from the inlet 11 by the head of a valve member 24 which is biassed to the closed position shown and movable to the open position by the application of fluid pressure to the inlet 25.
  • Each of the four valve members 15, 17, 21 and 24 has a pressure-responsive plunger 26 operating in a cylinder 27 provided with a venting means 23.
  • 31 represents a fuel tank and 32 a liquid oxygen tank, and each is provided with a pressurizing valve 33, 33 which when opened admits a supply of nitrogen from storage Vessels 34, 34 by way of a filter 35, a main pressure reducing valve 36, and two subsidiary reducing valves 37, 37.
  • the oxygen tank is additionally provided with a safety valve, indicated at 38.
  • the first step to be taken involves operating the control valve 44 whereby nitrogen at an appropriate pressure is delivered to a pneumatic actuator 45 by means of which a valve 46, at the outlet side of the oxygen tank 32, is opened.
  • the oxygen is then free to flow by gravity through the oxygen pump, indicated at 47, and along the outlet line 48 leading to the inlet 11 of combined stop and throttle valve means 49, shown in detail in Figure 3.
  • the pressure-responsive valve So (having the valve member 21) is open to connect the inlet 11 with the by-pass return pipe 26 leading back to the upper end 51 of the oxygen tank 32.
  • a further by-pass pipe 52 connecting with the highest point of the pump 47, whereby to permit the removal of any vaporised liquid oxygen so as to initiate the priming of the pumpthis by-pass pipe 52 including a pressure-responsive valve 53 connected by a pipe 54 to be operated from the output side of the pump so as to close the passage of the pipe 52 when the output of the pump reaches a predetermined value, as disclosed in the specification of co-pending patent application Ser. No. 242,555, filed August 18, 1951.
  • a master switch 56 is operated, and this completes a circuit through a switch 57 and conductors 58 and 59 for an electrically operated valve 60 to supply nitrogen passed by the reducing valve 40 to the two pressurizing valves 33 by way of the pipes 61, 62 and 63, whereby to open these pressurizing valves.
  • the pressurizing valve for the fuel tank could, if preferred, be opened later.
  • nitrogen released by the valve 69 is also applied to a pneumatic device 64, from the pipe 63, whereby a clutch 65 is engaged, the engagement of the clutch serving mechanically to connect both the oxygen pump 47 and the fuel pump 66 to appropriate driving means (not shown).
  • the oxygen pump being already primed with liquid, starts working and immediately develops a pre-determined pressure, whereupon a pressure-operated two-way switch 68, associated with its output, is operated to energize the coil 69 of a known form of time-delay switch 70 by way of the conductor 71, switch 68, conductors 72, 73, 74, and switch and the switch 79 will operate after, say, about four seconds-this delay being advisable in the sequence of operation in order to allow the oxygen pump to stabilize itself before the oxygen flow is disturbed. Until the end of this period of delay the oxygen is pumped through the by-pass valve 50 ( Figure 2) back to the tank 32 as previously described.
  • the operation of the switch 70 completes a circuit. by way of conductors 71, switch 68, and conductors 72, 76 and 77, for an operating coil 78 to open a valve 79 at the outlet side of the fuel tank 31.
  • the valve 79 is closed by another operating coil 80. when the pressure-operated switch .68 is in the position shown in Figure 1, by way of conductor 71,'switch 68 and conductor 80a.
  • This allows fuel to flow into the pump 66 which then starts delivering fuel along a pipe 81 to the inlet side of a stop and throttle valve means 82, which is in general similarto that of Figure 3.
  • the valve means 82 passes some of the fuel through a normally-open, pressure-operated by-pass 83 (like the'valve 50) to waste at 84, and, in parallel, along a V pipe 85 to the igniter equipment, indicated at 86.
  • the valve means 82 passes some of the fuel through a normally-open, pressure-operated by-pass 83
  • a pressure-operated switch 87 closes to provide a circuit from the conductor 58 through conductors 59a, 88, 89 for the coil of a solenoid-operated valve 90, the circuit being completed by a conductor. 90a .connected to conductor 74.
  • Valve 90 consequently opens to supply nitrogen along pipes 61, 91 and 92 to open a normally-closed valve 93 (valve member 24) of the valve means 49, in consequence of which a small supply of oxygen is delivered along the line 95 to the igniter equipment 86.
  • both 'the pressureoperated switches 68, 87 also effects the energizing of a booster coil 97, by way of the conductors 88 and 98 and switch 99, by means of which a sparking plug or the like for the igniter equipment is energized.
  • a portion of the oxygen therefore enters the'combustion chamber directly througha ring of holes 110, and a portion of the fuel, after circulating round the cooling jacket space 111 round the combustion chamber 112, .travels along a pipe 113 to the annular space 114, to enter the chamber through a ring of holes 115.
  • These two ingredients are then ignited in the combustion chamber by a pencil of flame issuing from the nozzle 116 of the igniter equipment 86.
  • the rocketmotor is now operating, and the rise of pressure in the combustion chamber operates the pressure-operated switch 75 to de-energize the coil of the solenoid-operated valve 90, in consequence of which the valve 93 closes under its bias to cut off the supply of oxidizer to the igniter equipment.
  • the coil 69 of the time-delay switch 70 is de-energized to allow this to re-set for the next start of the motor.
  • the operation of the switch 75 also builds up part of a circuit, through the conductor 118, for the control of the throttle valves of the valve means 49 and 82.
  • the main switch 56 can be opened (i. e., moved to the position shown, in which case the switch 68 will also move to the position shown to close the fuel valve 79), or an emergency switch 124 operated to open the switch 57.
  • the full thrust switch 119 should also be opened, but no harm will result if it is left closed,
  • 125 represents a dump valve, as disclosed in the specification of co-pending patent specification No. 240,725,
  • PatentNo. 2,664,701 which is operated by pressure supplied along the pipe 126 from the delivery side of the fuel pump.
  • the oxidizer pump being of the kind which will allow a fiow through it when it is not being operated; including an additional valve interposed in the conduit connecting the oxidizer reservoir to the associated pump, the oxidizer pump and the associated valve means being arranged at a level to be supplied with oxidizer by gravity when said additional valve is open in order to cool these parts to a temperature at which evaporation ceases, a conduit extending from the oxidizer valve means to the associated reservoir to return evaporated oxidizer to the reservoir and, when the oxidizer pump is running, to initially return its output to the oxidizer reservoir, means responsive to the pressure of the output of the oxidizer pump, a valve in the conduit interconnecting the fuel reservoir and the associated pump, and delay means for actuating said last-mentioned valve from said pressureresponsive means after the pressure of the output of the oxidizer pump reaches a predetermined value.
  • A-control system for a rocket motor of the kind having igniter equipment and combustion equipment for a mixture of liquid fuel and liquid oxidizerforming the propellent, a reservoir, pump and valve means for the fuel and conduits connecting the reservoir to the pump and the pump to the valve means respectively, a reservoir, pump and valve means for the oxidizer and conduits connecting the oxidizer reservoir to the oxidizer pump and the latter to the oxidizer valve means respectively, and conduits respectively connecting both of said valve means both to said igniter equipment and to said combustion equipment, the oxidizer pump being of the kind which will allow a flow through it when it is stationary; including an additional valve inthe conduit between the oxidizer pump and its associated reservoir, the oxidizer pump and its associated valve means being placed relatively to the oxidizer reservoir so that oxidizer can flow through the pump to the valve means for the oxidizer when said additional valve is opened to cool these parts to a temperature at which evaporation ceases, a conduit from the valve means for the oxidizer leading to the oxidizer reservoir to return to the latter the latter
  • both said valve means include further pressure-responsive valves biassed to isolate said combustion equipment from the output of both said pumps, a third pressureoperated switch and a third solenoid-operated valve, said third solenoid-operated valve normally interrupting a pressure supply to said further valves, said third pressureoperated switch connected to be subject to the internal pressure of said ignition equipment whereby, when a predetermined internal pressure is reached, to energise said third solenoid-operated valve and thereby cause said further valves to open against their biases for delivering, through respective constrictor valves, a limited supply of oxidizer and fuel to said combustion equipment, the remainder of the outputs of both pumps being delivered to respective by-passes.
  • a control system in which both constrictor valves are biassed to close respective unconstricted communications to said combustion equipment and have ducts in them providing the constrictions
  • pressure-responsive means respectively associated with said constrictor valves for moving them against their biases, a pressure-responsive valve controlling the bypass of said oxidizer valve means, and a manually operable switch and an associated solenoid valve, the latter when energised opening a pressure supply to the pressure-responsive valve of the by-pass of said oxidizer valve means whereby to close said by-pass, and also applying said pressure supply to both said pressure-responsive means for moving said constrictor valves to open said unconstricted communications whereby to deliver a fuel supply of fuel and oxidizer to said combustion equipment.
  • a control system for a. rocket motor of the kind having igniter equipment and combustion equipment for a mixture of liquid fuel and liquid oxidizer forming the propellent, a pump and a valve means both for the fuel and for the oxidizer, and a reservoir for the oxidizer, including'means for initially supplying liquid oxidizer from the reservoir through the oxidizer pump to the valve means for the oxidizer, a by-pass pipe from the oxidizer valve means to the reservoir, means 'for subsequently starting up both the pumps, and means for preventing the fuel pump from commencing delivery. until the oxidizer pump has attained a constant delivery of liquid oxidizer to the by-pass;

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Testing Of Engines (AREA)
US240216A 1950-09-08 1951-08-03 Mixed fuel control system for a rocket motor Expired - Lifetime US2708342A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB22153/50A GB694371A (en) 1950-09-08 1950-09-08 Control system for a rocket motor

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US2708342A true US2708342A (en) 1955-05-17

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US (1) US2708342A (US06368395-20020409-C00050.png)
BE (1) BE508931A (US06368395-20020409-C00050.png)
CH (1) CH323427A (US06368395-20020409-C00050.png)
FR (1) FR1049903A (US06368395-20020409-C00050.png)
GB (1) GB694371A (US06368395-20020409-C00050.png)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2829491A (en) * 1954-09-02 1958-04-08 Bendix Aviat Corp Two-stage liquid fuel rocket
US2850874A (en) * 1954-03-22 1958-09-09 Plessey Co Ltd Control and ignition system for liquid fuel combustion apparatus
US2946186A (en) * 1956-02-10 1960-07-26 Thompson Ramo Wooldridge Inc Balanced regulator valve
US2971332A (en) * 1956-11-13 1961-02-14 Bendix Corp Electrical timing control apparatus
US2976682A (en) * 1958-04-09 1961-03-28 United Aircraft Corp Pneumatic control system for fuel-air starter
US2982503A (en) * 1954-12-14 1961-05-02 English Electric Co Ltd Rocket motor attachments
US4899536A (en) * 1988-07-21 1990-02-13 Sundstrand Corporation Starting system for a turbine engine
CN112879805A (zh) * 2021-01-19 2021-06-01 北京航空航天大学 自带增压系统的车载移动式过氧化氢供应系统
CN114837853A (zh) * 2022-05-20 2022-08-02 西北工业大学 固液混合发动机多次启动点火方法及装置
CN116296421A (zh) * 2022-12-30 2023-06-23 北京天兵科技有限公司 一种火箭氧箱动力系统试车增补压装置及方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2699602B1 (fr) * 1992-12-22 1995-03-10 Europ Propulsion Système de délestage de liquide, notamment pour ensembles propulsifs.

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395113A (en) * 1940-04-01 1946-02-19 Daniel And Florence Guggenheim Mechanism for feeding combustion liquids to rocket apparatus
US2397657A (en) * 1941-06-23 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2469678A (en) * 1943-12-18 1949-05-10 Edwin T Wyman Combination steam and gas turbine
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system
US2479888A (en) * 1943-07-06 1949-08-23 Reaction Motors Inc Controlling system for reaction motors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2395113A (en) * 1940-04-01 1946-02-19 Daniel And Florence Guggenheim Mechanism for feeding combustion liquids to rocket apparatus
US2397657A (en) * 1941-06-23 1946-04-02 Daniel And Florence Guggenheim Control mechanism for rocket apparatus
US2479888A (en) * 1943-07-06 1949-08-23 Reaction Motors Inc Controlling system for reaction motors
US2469678A (en) * 1943-12-18 1949-05-10 Edwin T Wyman Combination steam and gas turbine
US2470564A (en) * 1944-11-15 1949-05-17 Reaction Motors Inc Reaction motor control system

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2850874A (en) * 1954-03-22 1958-09-09 Plessey Co Ltd Control and ignition system for liquid fuel combustion apparatus
US2829491A (en) * 1954-09-02 1958-04-08 Bendix Aviat Corp Two-stage liquid fuel rocket
US2982503A (en) * 1954-12-14 1961-05-02 English Electric Co Ltd Rocket motor attachments
US2946186A (en) * 1956-02-10 1960-07-26 Thompson Ramo Wooldridge Inc Balanced regulator valve
US2971332A (en) * 1956-11-13 1961-02-14 Bendix Corp Electrical timing control apparatus
US2976682A (en) * 1958-04-09 1961-03-28 United Aircraft Corp Pneumatic control system for fuel-air starter
US4899536A (en) * 1988-07-21 1990-02-13 Sundstrand Corporation Starting system for a turbine engine
CN112879805A (zh) * 2021-01-19 2021-06-01 北京航空航天大学 自带增压系统的车载移动式过氧化氢供应系统
CN114837853A (zh) * 2022-05-20 2022-08-02 西北工业大学 固液混合发动机多次启动点火方法及装置
CN114837853B (zh) * 2022-05-20 2024-01-16 西北工业大学 固液混合发动机多次启动点火方法及装置
CN116296421A (zh) * 2022-12-30 2023-06-23 北京天兵科技有限公司 一种火箭氧箱动力系统试车增补压装置及方法

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Publication number Publication date
FR1049903A (fr) 1954-01-04
CH323427A (fr) 1957-07-31
GB694371A (en) 1953-07-22
BE508931A (US06368395-20020409-C00050.png)

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