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42-405: The goal of the development was to produce a large, low-cost, easy-to-manufacture booster engine. The design used a single element coaxial pintle injector , a robust type of injector. It also used ablative cooling of the combustion chamber and nozzle instead of the more costly to manufacture regenerative cooling. The use of the pintle injector allows the engine thrust to be widely throttleable , as

84-546: A crewed spacecraft during the Apollo Program in the Lunar Excursion Module 's Descent Propulsion System , however, it was not until October 1972 that the design was made public. and U.S. patent 3,699,772 was granted to its inventor Gerard W. Elverum Jr. A pintle injector is a type of coaxial injector. It consists of two concentric tubes and a central protrusion. Propellant A (usually

126-406: A more evenly distributed combustion across the chamber section and more even heating. This has to be contemplated when designing the cooling system, or it might cause burn-through. The pintle injector is known to have caused throat-erosion problems in the early ablatively cooled Merlin engines due to uneven mixing causing hot streaks in the flow, however, as of 2021, it is not clear whether this

168-479: A normal consistency like that of smooth peanut butter . Gelled propellants typically use either aluminum powder or carbon powder to increase the energy density of the liquid fuel base (typically MMH ) and they use additives to rheologically match the oxidizer (typically IRFNA based) to the fuel. For gelled propellants to be used on a rocket, face shutoff is mandatory to prevent dry-out of the base liquid during off times between pulses, which would otherwise result in

210-449: A pintle injector tends to create a self-stabilizing flow pattern. Therefore, pintle-based engines are specially suitable for applications that require deep, fast, and safe throttling, such as landers . Pintle injectors began as early laboratory experimental apparatuses, used by Caltech 's Jet Propulsion Laboratory in the mid-1950s, to study the mixing and combustion reaction times of hypergolic liquid propellants. The pintle injector

252-754: A pintle injector was considered for simplicity and lower cost on the Sea Dragon . In parallel with those projects, TRW continued development of other pintle engines, including by 1966 the URSA ( Universal Rocket for Space Applications ) series. These were bipropellant engines offered at fixed thrusts of 25, 100, or 200 lbf, (111, 445, or 890 N) with options for either ablative or radiatively cooled combustion chambers. These engines were capable of pulsing at 35 Hz , with pulse widths as small as .02 seconds, but also had design steady state firing life in excess of 10,000 seconds (with radiatively-cooled chambers). In 1967

294-592: A very compact, 8,200 lbf N 2 O 4 / MMH engine employing this feature was developed as a pitch and yaw thruster for the army's SENTRY missile program. This engine could throttle over a 19:1 thrust range and deliver repeatable "on" pulses as small as 8 milliseconds at any thrust level. A further refinement of the face shutoff injector was used on the Army Strategic Defense Command's Exoatmospheric Reentry-vehicle Interceptor Subsystem (ERIS). In its 900 lbf lateral divert engines

336-400: Is concentric . Common examples: A coaxial cable has a wire conductor in the centre (D), a circumferential outer conductor (B), and an insulating medium called the dielectric (C) separating these two conductors. The outer conductor is usually sheathed in a protective PVC outer jacket (A). All these have a common axis. The dimension and material of the conductors and insulation determine

378-592: Is a problem that applies to all pintle-based engines, or this was a design problem of the Merlin. Pintle injectors work very well with liquid propellants and can be made to work with gelled propellants, but for gas–liquid or gas–gas applications, conventional injectors remain superior in performance. The pintle injector is desirable for engines that have to be throttled or restarted repeatedly, but it does not deliver optimal efficiency for fuel and oxidizer mixing at any given throttle rate. In 1957, Gerard W. Elverum Jr.

420-504: Is a type of propellant injector for a bipropellant rocket engine . Like any other injector, its purpose is to ensure appropriate flow rate and intermixing of the propellants as they are forcibly injected under high pressure into the combustion chamber , so that an efficient and controlled combustion process can happen. A pintle-based rocket engine can have a greater throttling range than one based on regular injectors, and will very rarely present acoustic combustion instabilities, because

462-588: Is not reacted immediately as it passes through the oxidizer stream is projected onto the combustion chamber walls and cools them through evaporation, thus providing fuel film cooling to the combustion chamber walls, without incurring the mass penalty of a dedicated coolant subsystem. While pintle injectors have been developed for applications in rocket propulsion, due to their relative simplicity, they could easily be adapted for industrial fluid handling processes requiring high flowrate and thorough mixing. A given injector's performance can be easily optimized by varying

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504-639: The Apollo Descent Propulsion System was qualified for flight. From 1968 to 1970, a 250,000 lbf (1,112,055 N) engine was tested. In 1972 the Apollo Descent Propulsion System ended production, but starting in 1974, and continuing through 1988, the TR-201 , a simplified, low cost derivative of it, featuring ablative cooling and fixed thrust, was used in the second stage of the Delta 2914 and 3914 launch vehicles. In October 1972,

546-604: The Falcon 9 and Falcon Heavy. The pintle injector was also used on the Reaver 1 engine by Firefly Aerospace . [REDACTED]  This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration . Coaxial In geometry , coaxial means that several three- dimensional linear or planar forms share a common axis . The two-dimensional analog

588-435: The cable's characteristic impedance and attenuation at various frequencies. Coaxial rotors are a three-dimensional planar structure: a pair of helicopter rotors (wings) mounted one above the other on concentric shafts, with the same axis of rotation (but turning in opposite directions). In loudspeaker design, coaxial speakers are a loudspeaker system in which the individual drivers are mounted close to one another on

630-413: The cylindrical stream of propellant A. In the typical pintle-based engine design, only a single central injector is used, differing from "showerhead" injector plates which use multiple parallel injector ports. Throttleability can be obtained either by placing valves before the injector, by moving the inner pintle or outer sleeve, or both. Many people have experienced throttleable pintle sprayers in

672-436: The design of high-performance booster engines. Attempts to use direct injection of cryogenic hydrogen in other types of injectors had until then consistently resulted in the onset of combustion instabilities. In late 1991 and early 1992, a 16,000 lbf (71,172 N) LOX / LH2 test engine was successfully operated with direct injection of liquid hydrogen and liquid oxygen propellants. A total of 67 firings were conducted, and

714-724: The development of the SpaceX Merlin engine. Mueller joined SpaceX in 2002, becoming its head of propulsion, along with other TRW staffers. The turbopump, meanwhile, was contracted to Barber-Nichols, Inc., which derived their pump from their work on the FASTRAC turbopump. After SpaceX accused Northrop Grumman, TRW's parent, of letting engineers supervising SpaceX under a Pentagon contract use that information on Northrop's own rocket technology, Northrop Grumman then sued for theft of trade secrets. The dueling suits were settled in early 2005. Pintle injector The pintle injector

756-449: The device from blowing itself apart during high energy tests, the outer tube was retracted, thus constituting a primitive pintle injector. Peter Staudhammer, under the supervision of Program Manager Elverum, had a technician cut multiple slots across the end of an available inner tube and subsequent tests of this new configuration showed a substantial improvement in mixing efficiency. By 1960, Elverum, Grant, and Staudhammer had moved to

798-584: The dual mode TR-308 was used to place NASA 's Chandra spacecraft on its final orbit. The early FSO injector and gel propellant development work of the late 1980s and early 1990s led to the world's first missile flights using gelled oxidizer and gelled fuel propellants on the Army's/AMCOM's Future Missile Technology Integration (FMTI) program, with the first flight in March 1999 and the second flight in May 2000. In

840-463: The early 2000s TRW continued development of large LOX / LH2 pintle engines, and test-fired the TR-106 at NASA's John C. Stennis Space Center . This was a 650,000 lbf (2,892,000 N) engine, a 16:1 scale-up from the largest previous LOX / LH2 pintle engine and about a 3:1 scale-up from the largest previous pintle engine ever tested. This injector's pintle diameter was 22 inches (56 cm), by far

882-488: The engine demonstrated excellent performance and total absence of combustion instabilities. Subsequently, this same test engine was adapted for and was successfully tested with LOX / LH2 at 40,000 lbf (177,929 N) and with LOX / RP-1 at 13,000 and 40,000 lbf. (57,827 and 177,929 N). At the same time, TR-306 liquid apogee engines were used on the Anik E-1/E-2 and Intelsat K spacecraft. In August 1999

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924-509: The engine to be operated in pulses, and this is usually done in pintle-based RCS thrusters and missile divert thrusters. In a variant of the Face Shutoff pintle, the pintle itself is hydraulically actuated by the fuel via a pilot valve, and no extra valves are required between the engine and tanks. This is called an FSO (Face Shutoff Only) pintle. In some variants the pintle has grooves or orifices cut into it to produce radial jets in

966-530: The engine's performance envelope; engineers also replaced the ablative chamber once while the engine was on the test stand—demonstrating the LCPE's ease of operation. Test results demonstrated that the engine was stable over a wide variety of thrust levels and propellant ratios. Development of the engine was temporarily discontinued with the cancellation of the Space Launch Initiative. In 2002 TRW

1008-403: The flow of propellant B, this allows for extra unburned fuel to impinge on the walls of the combustion chamber, and provide fuel film cooling. The pintle pictured here is of this type. Compared to some injector designs, pintle injectors allow greater throttling of bipropellant flow rates, although throttling rocket engines in general is still very difficult. If only one central injector is used,

1050-411: The form of standard garden hose-end sprayers. In pintle engines that do not require throttling, the pintle is fixed in place, and propellant valves for startup and shutdown are placed somewhere else. A movable pintle allows for throttleability, and, if the moving part is the sleeve, the pintle itself can act as the propellant valve. This is called a Face Shutoff pintle. A fast-moving sleeve allows for

1092-406: The geometries of the outer propellant's annular gap and the central propellant slots (and/or continuous gap, if used). As this requires only two new pieces to be made, trying variations is usually cheaper and less time-consuming than with regular injectors. Because combustion tends to occur in the surface of a frustum , peak thermal stresses are localized on the combustion chamber wall rather than

1134-434: The injector shutoff element provided the only control of propellant flow. The large bipropellant valve normally required in such engines was replaced by a small pilot valve that used high pressure fuel ( MMH ) to hydraulically actuate the moveable injector sleeve. This feature, called FSO (Face Shutoff Only) greatly improved overall thruster response and significantly reduced engine size and mass. Another design challenge from

1176-454: The largest built to date. In 2002 the larger TR-107 was designed. Tom Mueller , who had worked on the TR-106 and TR-107, was hired by SpaceX and started development of the Merlin and Kestrel engines. The Merlin engine was the only pintle injector engine in operation, used for all SpaceX Falcon 9 and Falcon Heavy flights. In the early 2020s, the Merlin engine continued to be used on

1218-415: The mass flow inside the combustion chamber will have two main recirculation zones which decrease acoustic instability without necessarily requiring acoustic cavities or baffles. The pintle injector design can deliver high combustion efficiency (typically 96–99%). If fuel is chosen for the inner flow (which is the case in most pintle-based engines), the injector can be tuned so that any excess fuel which

1260-584: The mid 1980s and early 1990s was that of obtaining miniaturization of rocket engines. As part of the Air Force Brilliant Pebbles program, TRW developed a very small 5 lbf (22 N) N 2 O 4 / hydrazine thruster using a pintle injector. This radiatively-cooled engine weighed 0.3 lb (135 grams) and was successfully tested in August 1993, delivering over 300 seconds I sp with a 150:1 nozzle expansion ratio. The pintle diameter

1302-427: The newly-formed Space Technology Laboratories, Inc. (Later TRW, Inc .) to pursue development of monopropellant and bipropellant rocket engines. By 1961, the pintle injector was developed into a design usable in rocket engines, and subsequently, the pintle injector design was matured and developed by a number of TRW employees, adding such features as throttling, rapid pulsing capability, and face shutoff. Throttling

TR-106 - Misplaced Pages Continue

1344-411: The oxidizer, represented with blue in the image) flows through an outer tube, coming out as a cylindrical stream, while propellant B (usually the fuel, represented with red in the image) flows within an inner tube and impinges on a central pintle -shaped protrusion, (similar in shape to a poppet valve like those found on four-stroke engines ), spraying out in a broad cone or a flat sheet that intersects

1386-456: The pintle injector design was patented and made public. In the early 1980s, a series of design refinements were applied to the pintle injector obtaining exceptionally fast and repeatable pulses on command and linear throttling capability. By enabling shutoff of propellants at their injection point into the combustion chamber, the pintle injector provided excellent pulse response by eliminating injector "dribble volume" effects. Starting in 1981,

1428-406: The same axis, and thus radiate sound along the same axis and roughly from the same point. A coaxial weapon mount places two weapons on roughly the same axis – as the weapons are usually side-by-side or one on top of the other, and thus oriented in parallel directions – they are technically par-axial rather than coaxial, however the distances involved mean that they are effectively coaxial as far as

1470-775: The solids within the gels plugging the injector passages. FSO pintle injectors were used on a variety of programs, the McDonnell Douglas Advanced Crew Escape Seat – Experimental (ACES-X) program and its successor, the Gel Escape System Propulsion (GESP) program. Another major design adaptation in this time period was the use of pintle injectors with cryogenic liquid hydrogen fuel. Beginning in 1991, TRW joined with McDonnell Douglas and NASA Lewis (now Glenn) Research Center to demonstrate that TRW's pintle engine could use direct injection of liquid hydrogen to simplify

1512-439: Was (1.6764 mm) and scanning electron microscopy was needed to verify the dimensions on the ± (0.0762 mm ±0.00762 mm) radial metering orifices. The preceding technology innovations enabled the first exoatmospheric kinetic kill of a simulated reentry warhead off Kwajalein atoll on 28 January 1991 on the first flight of ERIS . In the late '90s, FSO pintle injectors were used with gelled propellants, which have

1554-482: Was acquired by Northrop Grumman and development of a LOX/RP-1 engine ( TR-107 ) continued, under contract to NASA , for potential use on next-generation launch and space transportation vehicles. Tom Mueller became TRW vice president of propulsion. In 2002, Elon Musk asked Mueller to join him as a founding member of SpaceX. Technology lessons from the Low Cost Pintle Engine project were used in

1596-519: Was employed by the Jet Propulsion Laboratory , and working under the supervision of Art Grant to characterize the reaction rates of new rocket propellants by using a device consisting of two concentric tubes, through which propellants were fed at a known flowrate, and a set of thermocouples to measure their reaction rates. The device encountered problems, because as the propellants were flowing parallel to each other, not much mixing

1638-404: Was happening. Elverum then placed a tip at the end of the innermost tube, attached to an internal support, which forced the inner propellant to flow outwards and mix with the outer propellant. This device worked fine for low energy propellants, but when high energy combinations started being tested, it proved impractical due to nearly instantaneous reaction times at the mixing point. In order to keep

1680-430: Was reduced to practice and developed by Space Technology Laboratories (STL), then a division of Ramo-Wooldridge Corp., later TRW , starting in 1960. There have been pintle-based engines built ranging from a few newtons of thrust up to several millions, and the pintle design has been tested with all the common and many exotic propellant combinations, including gelled propellants. Pintle-based engines were first used on

1722-660: Was tested in the 1961 MIRA 500 , at 25 to 500 lbf (111 to 2,224 N ) and its 1962 successor, the MIRA 5000 , at 250 to 5,000 lbf (1,112 to 22,241 N). In 1963, TRW introduced the MIRA 150A as a backup for the Thiokol TD-339 vernier thruster to be used in the Surveyor probes , and started development of the Apollo Lunar Excursion Module 's Descent Propulsion System . Near this time,

TR-106 - Misplaced Pages Continue

1764-508: Was the case for the lunar module descent engine . Tom Mueller was a lead engineer for development of the LCPE, a 650,000 lbf thrust LOX/LH2 engine. In the summer of 2000, this LCPE was successfully hot fire tested at 100 percent of its rated thrust as well as at a 65 percent throttle condition at NASA's John C. Stennis Space Center in Mississippi. TRW changed the pintle injector configuration three times during testing to explore

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