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87-631: VS-50 (suborbital rocket VS-50) is a joint development of sounding rocket from the Institute of Aeronautics and Space (IAE) and German Aerospace Center (DLR). It is a suborbital vehicle that uses solid propellant , having two stages: the first uses the S50 engine (made of composite material ) and the second uses the S44 engine. It is 12 m long, 1.46 m in diameter, and has a mass of approximately 15 tons, and can carry up to 500 kg of payload. Brazil (IAE)

174-536: A Sounding Rocket such as the Nike-Apache may deposit sodium clouds to observe very high altitude winds. Larger, higher altitude rockets have multiple stages to increase altitude and/or payload capability. The freefall part of the flight is an elliptic trajectory with vertical major axis allowing the payload to appear to hover near its apogee . The average flight time is less than 30 minutes; usually between five and 20 minutes. The rocket consumes its fuel on

261-417: A crane. This is generally not practical for larger space vehicles, which are assembled off the pad and moved into place on the launch site by various methods. NASA's Apollo / Saturn V crewed Moon landing vehicle, and Space Shuttle , were assembled vertically onto mobile launcher platforms with attached launch umbilical towers, in a Vehicle Assembly Building , and then a special crawler-transporter moved

348-510: A dragon's head with an open mouth. The British scientist and historian Joseph Needham points out that the written material and depicted illustration of this rocket come from the oldest stratum of the Huolongjing , which can be dated roughly 1300–1350 AD (from the book's part 1, chapter 3, page 23). Another example of an early multistaged rocket is the Juhwa (走火) of Korean development. It

435-408: A higher cost for deployment. Hot-staging is a type of rocket staging in which the next stage fires its engines before separation instead of after. During hot-staging, the earlier stage throttles down its engines. Hot-staging may reduce the complexity of stage separation, and gives a small extra payload capacity to the booster. It also eliminates the need for ullage motors , as the acceleration from

522-518: A launch vehicle, a useful performance metric to examine is the thrust-to-weight ratio, and is calculated by the equation: The common thrust-to-weight ratio of a launch vehicle is within the range of 1.3 to 2.0. Another performance metric to keep in mind when designing each rocket stage in a mission is the burn time, which is the amount of time the rocket engine will last before it has exhausted all of its propellant. For most non-final stages, thrust and specific impulse can be assumed constant, which allows

609-472: A multistage rocket introduces additional risk into the success of the launch mission. Reducing the number of separation events results in a reduction in complexity . Separation events occur when stages or strap-on boosters separate after use, when the payload fairing separates prior to orbital insertion, or when used, a launch escape system which separates after the early phase of a launch. Pyrotechnic fasteners , or in some cases pneumatic systems like on

696-466: A rocket system will be when performing optimizations and comparing varying configurations for a mission. For initial sizing, the rocket equations can be used to derive the amount of propellant needed for the rocket based on the specific impulse of the engine and the total impulse required in N·s. The equation is: where g is the gravity constant of Earth. This also enables the volume of storage required for

783-638: A small Liquid-propellant rocket to provide the GALCIT team necessary experience to aid in developing the Corporal missile. Malina with Tsien Hsue-shen ( Qian Xuesen in Pinyin transliteration), wrote "Flight analysis of a Sounding Rocket with Special Reference to Propulsion by Successive Impulses." As the Signal Corps rocket was being developed for the Corporal project, and lacked any guidance mechanism, it

870-511: A sounding rocket also makes launching from temporary sites possible, allowing field studies at remote locations, and even in the middle of the ocean, if fired from a ship. Weather observations, up to an altitude of 75 km, are done with rocketsondes , a kind of sounding rocket for atmospheric observations that consists of a rocket and radiosonde . The sonde records data on temperature , moisture , wind speed and direction, wind shear , atmospheric pressure , and air density during

957-556: A survey or a poll". Sounding in the rocket context is equivalent to "taking a measurement". The basic elements of a modern sounding rocket are a solid-fuel rocket motor and a science payload . In certain Sounding Rockets the payload may even be nothing more than a smoke trail as in the Nike Smoke which is used to determine wind directions and strengths more accurately than may be determined by weather balloons . Or

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1044-399: A technical algorithm that generates an analytical solution that can be implemented by a program, or simple trial and error. For the trial and error approach, it is best to begin with the final stage, calculating the initial mass which becomes the payload for the previous stage. From there it is easy to progress all the way down to the initial stage in the same manner, sizing all the stages of

1131-483: Is a commonly used rocket system to attain Earth orbit. The spacecraft uses three distinct stages to provide propulsion consecutively in order to achieve orbital velocity. It is intermediate between a four-stage-to-orbit launcher and a two-stage-to-orbit launcher. Other designs (in fact, most modern medium- to heavy-lift designs) do not have all three stages inline on the main stack, instead having strap-on boosters for

1218-415: Is a safe and reasonable assumption to say that 91 to 94 percent of the total mass is fuel. It is also important to note there is a small percentage of "residual" propellant that will be left stuck and unusable inside the tank, and should also be taken into consideration when determining amount of fuel for the rocket. A common initial estimate for this residual propellant is five percent. With this ratio and

1305-453: Is generally assembled at its manufacturing site and shipped to the launch site; the term vehicle assembly refers to the mating of all rocket stage(s) and the spacecraft payload into a single assembly known as a space vehicle . Single-stage vehicles ( suborbital ), and multistage vehicles on the smaller end of the size range, can usually be assembled directly on the launch pad by lifting the stage(s) and spacecraft vertically in place by means of

1392-428: Is intermediate between a five-stage-to-orbit launcher and a three-stage-to-orbit launcher, most often used with solid-propellant launch systems. Other designs do not have all four stages inline on the main stack, instead having strap-on boosters for the "stage-0" with three core stages. In these designs, the boosters and first stage fire simultaneously instead of consecutively, providing extra initial thrust to lift

1479-546: Is responsible for developing the S50 and S44 engines, the backup navigation system, the launch and flight safety infrastructure, and project documentation management. The development and qualification of the other systems are the responsibility of Germany (DLR). The rocket will be used primarily to develop, manufacture and flight qualify the S50 engine, as well as components to be used in the VLM-1 rocket. It will also be used in microgravity testing and hypersonic experiments (such as

1566-393: Is the initial to final mass ratio, which is the ratio between the rocket stage's full initial mass and the rocket stage's final mass once all of its fuel has been consumed. The equation for this ratio is: Where m E {\displaystyle m_{\mathrm {E} }} is the empty mass of the stage, m p {\displaystyle m_{\mathrm {p} }}

1653-402: Is the mass of the oxidizer and m f u e l {\displaystyle m_{\mathrm {fuel} }} is the mass of the fuel. This mixture ratio not only governs the size of each tank, but also the specific impulse of the rocket. Determining the ideal mixture ratio is a balance of compromises between various aspects of the rocket being designed, and can vary depending on

1740-404: Is the mass of the propellant, and m P L {\displaystyle m_{\mathrm {PL} }} is the mass of the payload. The second dimensionless performance quantity is the structural ratio, which is the ratio between the empty mass of the stage, and the combined empty mass and propellant mass as shown in this equation: The last major dimensionless performance quantity

1827-455: Is the payload ratio, which is the ratio between the payload mass and the combined mass of the empty rocket stage and the propellant: After comparing the three equations for the dimensionless quantities, it is easy to see that they are not independent of each other, and in fact, the initial to final mass ratio can be rewritten in terms of structural ratio and payload ratio: These performance ratios can also be used as references for how efficient

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1914-480: The Falcon 9 Full Thrust , are typically used to separate rocket stages. A two-stage-to-orbit ( TSTO ) or two-stage rocket launch vehicle is a spacecraft in which two distinct stages provide propulsion consecutively in order to achieve orbital velocity. It is intermediate between a three-stage-to-orbit launcher and a hypothetical single-stage-to-orbit (SSTO) launcher. The three-stage-to-orbit launch system

2001-734: The RTV-G-4 Bumper rockets tested at the White Sands Proving Ground and later at Cape Canaveral from 1948 to 1950. These consisted of a V-2 rocket and a WAC Corporal sounding rocket. The greatest altitude ever reached was 393 km, attained on February 24, 1949, at White Sands. In 1947, the Soviet rocket engineer and scientist Mikhail Tikhonravov developed a theory of parallel stages, which he called "packet rockets". In his scheme, three parallel stages were fired from liftoff , but all three engines were fueled from

2088-509: The Singijeon , or 'magical machine arrows' in the 16th century. The earliest experiments with multistage rockets in Europe were made in 1551 by Austrian Conrad Haas (1509–1576), the arsenal master of the town of Hermannstadt , Transylvania (now Sibiu/Hermannstadt, Romania). This concept was developed independently by at least five individuals: The first high-speed multistage rockets were

2175-490: The Soviet and U.S. space programs, were not passivated after mission completion. During the initial attempts to characterize the space debris problem, it became evident that a good proportion of all debris was due to the breaking up of rocket upper stages, particularly unpassivated upper-stage propulsion units. An illustration and description in the 14th century Chinese Huolongjing by Jiao Yu and Liu Bowen shows

2262-584: The Veronique (rocket) was began in 1949, it was not until 1952 that the first full scale Veronique was launched. Veronique variants were flown until 1974. The Monica (rocket) family, an all solid fueled which was pursued in a number of versions and later replaced by the ONERA. series of rockets. Japan was another early user with the Kappa (rocket) . Japan also pursued Rockoons. The People's Republic of China

2349-844: The WAC Corporal , Aerobee , and Viking . The German V-2 served both the US and the USSR's R-1 missile as sounding rockets during the immediate Post World War II periods. During the 1950s and later the inexpensive availability of surplus military boosters such as those used by the Nike , Talos , Terrier , and Sparrow . Since the 1960s designed for the purpose rockets such as the Black Brant series have dominated sounding rockets, though often having additional stages, many from military surplus. The earliest attempts at developing Sounding Rockets were in

2436-473: The exoatmospheric region between 97 and 201 km (60 and 125 miles). The origin of the term comes from nautical vocabulary to sound , which is to throw a weighted line from a ship into the water to measure the water's depth. The term itself has its etymological roots in the Romance languages word for probe , of which there are nouns sonda and sonde and verbs like sondear which means "to do

2523-443: The first stage of the rising part of the flight, then often separates and falls away, leaving the payload to complete the arc, sometimes descending under a drag source such as a small balloon or a parachute . Sounding rockets have utilized balloons, airplanes and artillery as "first stages." Project Farside utilized a Rockoon composed of a 106,188-m3 (3,750-ft3) balloon, lifting a four stage rocket composed of 4 Recrute rockets as

2610-523: The "stage-0" with two core stages. In these designs, the boosters and first stage fire simultaneously instead of consecutively, providing extra initial thrust to lift the full launcher weight and overcome gravity losses and atmospheric drag. The boosters are jettisoned a few minutes into flight to reduce weight. The four-stage-to-orbit launch system is a rocket system used to attain Earth orbit. The spacecraft uses four distinct stages to provide propulsion consecutively in order to achieve orbital velocity. It

2697-785: The Aerobee ultimately powered the second stage of the Vanguard (rocket) , the first designed for the purpose Satellite Launch Vehicle , Vanguard. The AJ10 engine used by many Aerobees eventually evolved into the AJ10-190 which formed the Orbital Maneuvering System of the Space Shuttle. The Viking (rocket) was intended from the start by the Navy not only to be a sounding rocket capable of replacing, even exceeding

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2784-468: The German SHEFEX project). Sounding rocket A sounding rocket or rocketsonde , sometimes called a research rocket or a suborbital rocket , is an instrument-carrying rocket designed to take measurements and perform scientific experiments during its sub-orbital flight. The rockets are used to launch instruments from 48 to 145 km (30 to 90 miles) above the surface of the Earth,

2871-635: The Soviet Union. While all of the early rocket developers were concerned largely with developing the ability to launch rockets some had the objective of investigating the stratosphere and beyond. The All-Union Conference on the Study of Stratosphere was held in Leningrad (now St. Petersburg) in 1936. While the conference primarily dealt with balloon Radiosondes , there was a small group of rocket developers who sought to develop "recording rockets" to explore

2958-619: The U.S.S.R in Moscow designed the R-06 which eventually flew but not in the meteorological role. The early Soviet efforts to develop a sounding rocket were the earliest efforts to develop a sounding rocket and ultimately failed before WWII. P. I. Ivanov built a three-stage which flew in March 1946. At the end of summer 1946 development ended because it lacked sufficient thrust to loft a sufficient research payload. The first successful sounding rocket

3045-833: The V-2, but also to advance guided missile technology. The Viking was controlled by a multi-axis guidance system with gimbled Reaction Motors XLR10-RM-2 engine. The Viking was developed through two major versions. After the United States announced it intended to launch a satellite in the International Geophysical Year (1957-1958) the Viking was chosen as the first stage of the Vanguard Satellite Launch Vehicle. The last two Vikings were fired as Vanguard Test Vehicle 1 and 2. During

3132-558: The altitude generally between weather balloons and satellites ; the maximum altitude for balloons is about 40 km (25 miles) and the minimum for satellites is approximately 121 km (75 miles). Certain sounding rockets have an apogee between 1,000 and 1,500 km (620 and 930 miles), such as the Black Brant X and XII , which is the maximum apogee of their class. For certain purposes Sounding Rockets may be flown to altitudes as high as 3,000 kilometers to allow observing times of around 40 minutes to provide geophysical observations of

3219-401: The breakup of a single upper stage while in orbit. After the 1990s, spent upper stages are generally passivated after their use as a launch vehicle is complete in order to minimize risks while the stage remains derelict in orbit . Passivation means removing any sources of stored energy remaining on the vehicle, as by dumping fuel or discharging batteries. Many early upper stages, in both

3306-440: The cost of the lower stages lifting engines which are not yet being used, as well as making the entire rocket more complex and harder to build than a single stage. In addition, each staging event is a possible point of launch failure, due to separation failure, ignition failure, or stage collision. Nevertheless, the savings are so great that every rocket ever used to deliver a payload into orbit has had staging of some sort. One of

3393-696: The course of investigations by the German peace movement , this cooperation was revealed by a group of physicists in 1983. The international discussion that was thus set in motion led to the development of the Missile Technology Control Regime (MTCR) at the level of G7 states. Since then, lists of technological equipment whose export is subject to strict controls have been drawn up within the MTCR framework. First stage (rocketry) By jettisoning stages when they run out of propellant,

3480-489: The delta-v into fractions. As each lower stage drops off and the succeeding stage fires, the rest of the rocket is still traveling near the burnout speed. Each lower stage's dry mass includes the propellant in the upper stages, and each succeeding upper stage has reduced its dry mass by discarding the useless dry mass of the spent lower stages. A further advantage is that each stage can use a different type of rocket engine, each tuned for its particular operating conditions. Thus

3567-419: The different stages of the rocket should be clearly defined. Continuing with the previous example, the end of the first stage which is sometimes referred to as 'stage 0', can be defined as when the side boosters separate from the main rocket. From there, the final mass of stage one can be considered the sum of the empty mass of stage one, the mass of stage two (the main rocket and the remaining unburned fuel) and

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3654-404: The drawbacks of a less efficient specific impulse rating. But suppose the defining constraint for the launch system is volume, and a low density fuel is required such as hydrogen. This example would be solved by using an oxidizer-rich mixture ratio, reducing efficiency and specific impulse rating, but will meet a smaller tank volume requirement. The ultimate goal of optimal staging is to maximize

3741-598: The entire vehicle stack to the launch pad in an upright position. In contrast, vehicles such as the Russian Soyuz rocket and the SpaceX Falcon 9 are assembled horizontally in a processing hangar, transported horizontally, and then brought upright at the pad. Spent upper stages of launch vehicles are a significant source of space debris remaining in orbit in a non-operational state for many years after use, and occasionally, large debris fields created from

3828-444: The equation for burn time to be written as: Where m 0 {\displaystyle m_{\mathrm {0} }} and m f {\displaystyle m_{\mathrm {f} }} are the initial and final masses of the rocket stage respectively. In conjunction with the burnout time, the burnout height and velocity are obtained using the same values, and are found by these two equations: When dealing with

3915-411: The equations for determining the burnout velocities, burnout times, burnout altitudes, and mass of each stage. This would make for a better approach to a conceptual design in a situation where a basic understanding of the system behavior is preferential to a detailed, accurate design. One important concept to understand when undergoing restricted rocket staging, is how the burnout velocity is affected by

4002-486: The first stage of the American Atlas I and Atlas II launch vehicles, arranged in a row, used parallel staging in a similar way: the outer pair of booster engines existed as a jettisonable pair which would, after they shut down, drop away with the lowermost outer skirt structure, leaving the central sustainer engine to complete the first stage's engine burn towards apogee or orbit. Separation of each portion of

4089-493: The first stage with 1 Recruit as the second stage, with 4 Arrow II motors composing the third stage and finally a single Arrow II as the fourth stage. Sparoair , air launched from Navy F4D and F-4 fighters were examples of air launched sounding rockets. There were also examples of artillery launched sounding rockets including Project HARP 's 5", 7", and 15" guns, sometimes having additional Martlet rocket stages. The earliest Sounding Rockets were liquid propellant rockets such as

4176-574: The first successful Sounding Rocket the WAC Corporal . By the early 1960s the Sounding Rocket was established technology. Sounding rockets are advantageous for some research because of their low cost, relatively short lead time (sometimes less than six months) and their ability to conduct research in areas inaccessible to either balloons or satellites. They are also used as test beds for equipment that will be used in more expensive and risky orbital spaceflight missions. The smaller size of

4263-521: The flight. Position data ( altitude and latitude / longitude ) may also be recorded. Common meteorological rockets are the Loki and Super Loki , typically 3.7 m tall and powered by a 10 cm diameter solid fuel rocket motor . The rocket motor separates at an altitude of 1500 m and the rest of the rocketsonde coasts to apogee (highest point). This can be set to an altitude of 20 km to 113 km. Sounding rockets are commonly used for: Due to

4350-467: The fuel to be calculated if the density of the fuel is known, which is almost always the case when designing the rocket stage. The volume is yielded when dividing the mass of the propellant by its density. Asides from the fuel required, the mass of the rocket structure itself must also be determined, which requires taking into account the mass of the required thrusters, electronics, instruments, power equipment, etc. These are known quantities for typical off

4437-414: The fueled-to-dry mass ratio and on the effective exhaust velocity of the engine. This relation is given by the classical rocket equation : where: The delta v required to reach low Earth orbit (or the required velocity of a sufficiently heavy suborbital payload) requires a wet to dry mass ratio larger than has been achieved in a single rocket stage. The multistage rocket overcomes this limit by splitting

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4524-664: The high military relevance of ballistic missile technology, there has always been a close relationship between sounding rockets and military missiles. It is a typical dual-use technology , which can be used for both civil and military purposes. During the Cold War , the Federal Republic of Germany cooperated on this topic with countries that had not signed the Non-Proliferation Treaty on Nuclear Weapons at that time, such as Brazil, Argentina and India. In

4611-451: The initial rocket stages usually have a lower specific impulse rating, trading efficiency for superior thrust in order to quickly push the rocket into higher altitudes. Later stages of the rocket usually have a higher specific impulse rating because the vehicle is further outside the atmosphere and the exhaust gas does not need to expand against as much atmospheric pressure. When selecting the ideal rocket engine to use as an initial stage for

4698-443: The largest rocket ever to do so, as well as the first reusable vehicle to utilize hot staging. A rocket system that implements tandem staging means that each individual stage runs in order one after the other. The rocket breaks free from the previous stage, then begins burning through the next stage in straight succession. On the other hand, a rocket that implements parallel staging has two or more different stages that are active at

4785-402: The largest, the second stage and subsequent upper stages are above it, usually decreasing in size. In parallel staging schemes solid or liquid rocket boosters are used to assist with launch. These are sometimes referred to as "stage 0". In the typical case, the first-stage and booster engines fire to propel the entire rocket upwards. When the boosters run out of fuel, they are detached from

4872-420: The lower-stage engines are designed for use at atmospheric pressure, while the upper stages can use engines suited to near vacuum conditions. Lower stages tend to require more structure than upper as they need to bear their own weight plus that of the stages above them. Optimizing the structure of each stage decreases the weight of the total vehicle and provides further advantage. The advantage of staging comes at

4959-536: The magnetosphere, ionosphere, thermosphere and mesosphere. Sounding rockets have been used for the examination of atmospheric nuclear tests by revealing the passage of the shock wave through the atmosphere. In more recent times Sounding Rockets have been used for other nuclear weapons research. Sounding rockets often use military surplus rocket motors. NASA routinely flies the Terrier Mk 70 boosted Improved Orion , lifting 270–450-kg (600–1,000-pound) payloads into

5046-403: The mass of the payload. High-altitude and space-bound upper stages are designed to operate with little or no atmospheric pressure. This allows the use of lower pressure combustion chambers and engine nozzles with optimal vacuum expansion ratios . Some upper stages, especially those using hypergolic propellants like Delta-K or Ariane 5 ES second stage, are pressure fed , which eliminates

5133-464: The mass of the propellant calculated, the mass of the empty rocket weight can be determined. Sizing rockets using a liquid bipropellant requires a slightly more involved approach because there are two separate tanks that are required: one for the fuel, and one for the oxidizer. The ratio of these two quantities is known as the mixture ratio, and is defined by the equation: Where m o x {\displaystyle m_{\mathrm {ox} }}

5220-408: The mass of the remaining rocket is decreased. Each successive stage can also be optimized for its specific operating conditions, such as decreased atmospheric pressure at higher altitudes. This staging allows the thrust of the remaining stages to more easily accelerate the rocket to its final velocity and height. In serial or tandem staging schemes, the first stage is at the bottom and is usually

5307-423: The most common measures of rocket efficiency is its specific impulse, which is defined as the thrust per flow rate (per second) of propellant consumption: When rearranging the equation such that thrust is calculated as a result of the other factors, we have: These equations show that a higher specific impulse means a more efficient rocket engine, capable of burning for longer periods of time. In terms of staging,

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5394-566: The nearly spent stage keeps the propellants settled at the bottom of the tanks. Hot-staging is used on Soviet-era Russian rockets such as Soyuz and Proton-M . The N1 rocket was designed to use hot staging, however none of the test flights lasted long enough for this to occur. Starting with the Titan II, the Titan family of rockets used hot staging. SpaceX retrofitted their Starship rocket to use hot staging after its first flight , making it

5481-708: The need for complex turbopumps . Other upper stages, such as the Centaur or DCSS , use liquid hydrogen expander cycle engines, or gas generator cycle engines like the Ariane 5 ECA's HM7B or the S-IVB 's J-2 . These stages are usually tasked with completing orbital injection and accelerating payloads into higher energy orbits such as GTO or to escape velocity . Upper stages, such as Fregat , used primarily to bring payloads from low Earth orbit to GTO or beyond are sometimes referred to as space tugs . Each individual stage

5568-419: The number of stages that split up the rocket system. Increasing the number of stages for a rocket while keeping the specific impulse, payload ratios and structural ratios constant will always yield a higher burnout velocity than the same systems that use fewer stages. However, the law of diminishing returns is evident in that each increment in number of stages gives less of an improvement in burnout velocity than

5655-454: The oldest known multistage rocket; this was the " fire-dragon issuing from the water " (火龙出水, huǒ lóng chū shuǐ), which was used mostly by the Chinese navy. It was a two-stage rocket that had booster rockets that would eventually burn out, yet, before they did so, automatically ignited a number of smaller rocket arrows that were shot out of the front end of the missile, which was shaped like

5742-525: The outer two stages, until they are empty and could be ejected. This is more efficient than sequential staging, because the second-stage engine is never just dead weight. In 1951, Soviet engineer and scientist Dmitry Okhotsimsky carried out a pioneering engineering study of general sequential and parallel staging, with and without the pumping of fuel between stages. The design of the R-7 Semyorka emerged from that study. The trio of rocket engines used in

5829-632: The overall payload ratio of the entire system. It is important to note that when computing payload ratio for individual stages, the payload includes the mass of all the stages after the current one. The overall payload ratio is: Where n is the number of stages the rocket system comprises. Similar stages yielding the same payload ratio simplify this equation, however that is seldom the ideal solution for maximizing payload ratio, and ΔV requirements may have to be partitioned unevenly as suggested in guideline tips 1 and 2 from above. Two common methods of determining this perfect ΔV partition between stages are either

5916-573: The payload ratio (see ratios under performance), meaning the largest amount of payload is carried up to the required burnout velocity using the least amount of non-payload mass, which comprises everything else. This goal assumes that the cost of a rocket launch is proportional to the total liftoff mass of the rocket, which is a rule of thumb in rocket engineering. Here are a few quick rules and guidelines to follow in order to reach optimal staging: The payload ratio can be calculated for each individual stage, and when multiplied together in sequence, will yield

6003-615: The post WWII era the USSR also pursued V-2 base sounding rockets. The last two R-1As were flown in 1949 as sounding rockets. They were followed between July 1951 and June 1956 by 4 R-1B, 2 R-1V, 3 R-1D and 5 R-1Es, and 1 R-1E (A-1). The improved V-2 descendant the R-2A could reach 120 miles and were flown between April 1957 and May 1962. Fifteen R-5Vs were flown from June 1965 to October 1983. Two R-5 VAOs were flown in September 1964 and October 1965. The first solid-fueled Soviet sounding rocket

6090-402: The previous increment. The burnout velocity gradually converges towards an asymptotic value as the number of stages increases towards a very high number. In addition to diminishing returns in burnout velocity improvement, the main reason why real world rockets seldom use more than three stages is because of increase of weight and complexity in the system for each added stage, ultimately yielding

6177-441: The problem of calculating the total burnout velocity or time for the entire rocket system, the general procedure for doing so is as follows: The burnout time does not define the end of the rocket stage's motion, as the vehicle will still have a velocity that will allow it to coast upward for a brief amount of time until the acceleration of the planet's gravity gradually changes it to a downward direction. The velocity and altitude of

6264-430: The rest of the rocket (usually with some kind of small explosive charge or explosive bolts ) and fall away. The first stage then burns to completion and falls off. This leaves a smaller rocket, with the second stage on the bottom, which then fires. Known in rocketry circles as staging , this process is repeated until the desired final velocity is achieved. In some cases with serial staging, the upper stage ignites before

6351-748: The results. After the start of WWII the CIT rocketry enthusiast found themselves involved in a number of defense programs, one of which, deemed Corporal, was intended to produce a bombardment guided missile the Corporal. Eventually known as the MGM-5 Corporal it became the first guided missile deployed by the US Army. During WWII the Signal Corps created a requirement for a sounding rocket to carry 25 pounds (11 kg) of instruments to 100,000 feet (30 km) or higher. To meet that goal Malina proposed

6438-430: The rocket after burnout can be easily modeled using the basic physics equations of motion. When comparing one rocket with another, it is impractical to directly compare the rocket's certain trait with the same trait of another because their individual attributes are often not independent of one another. For this reason, dimensionless ratios have been designed to enable a more meaningful comparison between rockets. The first

6525-427: The rocket system. Restricted rocket staging is based on the simplified assumption that each of the stages of the rocket system have the same specific impulse, structural ratio, and payload ratio, the only difference being the total mass of each increasing stage is less than that of the previous stage. Although this assumption may not be the ideal approach to yielding an efficient or optimal system, it greatly simplifies

6612-518: The same time. For example, the Space Shuttle has two Solid Rocket Boosters that burn simultaneously. Upon launch, the boosters ignite, and at the end of the stage, the two boosters are discarded while the external fuel tank is kept for another stage. Most quantitative approaches to the design of the rocket system's performance are focused on tandem staging, but the approach can be easily modified to include parallel staging. To begin with,

6699-419: The separation—the interstage ring is designed with this in mind, and the thrust is used to help positively separate the two vehicles. Only multistage rockets have reached orbital speed . Single-stage-to-orbit designs are sought, but have not yet been demonstrated. Multi-stage rockets overcome a limitation imposed by the laws of physics on the velocity change achievable by a rocket stage. The limit depends on

6786-518: The shelf hardware that should be considered in the mid to late stages of the design, but for preliminary and conceptual design, a simpler approach can be taken. Assuming one engine for a rocket stage provides all of the total impulse for that particular segment, a mass fraction can be used to determine the mass of the system. The mass of the stage transfer hardware such as initiators and safe-and-arm devices are very small by comparison and can be considered negligible. For modern day solid rocket motors, it

6873-590: The stratosphere and beyond. Amongst the speakers at the conference was Sergey Korolev who later became the leading figure of the Soviet space program. Specifically interested in sounding rocket design were V. V. Razumov, of the Leningrad Group for the Study of Jet Propulsion. A. I. Polyarny working in a special group within the Society for Assistance to the Defense, Aviation and Chemical Construction of

6960-406: The type of fuel and oxidizer combination being used. For example, a mixture ratio of a bipropellant could be adjusted such that it may not have the optimal specific impulse, but will result in fuel tanks of equal size. This would yield simpler and cheaper manufacturing, packing, configuring, and integrating of the fuel systems with the rest of the rocket, and can become a benefit that could outweigh

7047-718: The upper stage of the first two staged rocket the RTV-G-4 Bumper . Captured V-2s dominated American sounding rockets and other rocketry developments during the late 1940s. To meet the need for replacement a new sounding rocket was developed by the Aerojet Corporation to meet a requirement of the Applied Physics Laboratory and the Naval Research Laboratory . Over 1,000 Aerobees of various versions for varied customers were flow between 1947 and 1985. One engine produced for

7134-676: Was Without Attitude Control. Thus it was named the WAC Corporal . The WAC Corporal served as the foundation of Sounding Rocketry in the USA. WAC Corporal was developed in two versions the second of which was much improved. After the war the WAC Corporal was in competition for sounding mission funding with the much larger captured V-2 rocket being tested by the U.S. Army. WAC Corporal was overshadowed at its job of cost-effectively lifting pounds of experiments to altitude, thus it effectively became obsolescent. WAC Corporals were later modified to become

7221-548: Was created at the California Institute of Technology , where before World War II there was a group of rocket enthusiasts led by Frank Malina , under the aegis of Theodore von Kármán , known amidst the people of the CIT as the "Suicide Squad." The immediate goal of the Suicide Squad was exploring the upper atmosphere which required developing the means of lofting instruments to high altitude and recovering

7308-515: Was proposed by medieval Korean engineer, scientist and inventor Ch'oe Mu-sŏn and developed by the Firearms Bureau (火㷁道監) during the 14th century. The rocket had the length of 15 cm and 13 cm; the diameter was 2.2 cm. It was attached to an arrow 110 cm long; experimental records show that the first results were around 200m in range. There are records that show Korea kept developing this technology until it came to produce

7395-655: Was the M-100. Some 6640 M-100 sounding rockets were flown from 1957 to 1990. Other early users of Sounding Rockets were Britain, France and Japan. Great Britain developed the Skylark (rocket) series and the later Skua for the International Geophysical Year . France had begun the design of a Super V-2 but that program had been abandoned in the late 1940s due to the inability of France to manufacture all components necessary. Though development of

7482-541: Was the last nation to launch a new liquid fueled sounding rocket, the T-7. It was first fired from a very primitive launch site, where the "command center" and borrowed power generator were in a grass hut separated from the launcher by a small river. There was no communications equipment- not even a telephone between the command post and the rocket launcher. The T-7 led to the T-7M, T-7A, T-7A-S, T-7A-S2 and T-7/GF-01A. The T-7/ GF-01A

7569-772: Was used in 1969 to launch the FSW satellite technology development missions. Thus the I-7 led to the first Chinese satellite, the Dong Fang Hong 1 (The East is Red 1), launched by a DF-1. Vital to the development of Chinese rocketry and the Dong Feng-1 was Qian Xuesen (Tsien Hsue-shen in Wade Guiles transliteration) who with Theodore von Kármán and the California Institute of Technology "Suicide Squad" created

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