User’s Manual December 2009 Release 1.2. ORBITAL SCIENCES CORPORATION. The Taurus® II is a two-stage launch vehicle designed to provide responsive, cost-effective, and reliable. The launch services described in this Taurus II Launch System User’s Guide is intended to. It featured a Mitsubishi engine and this launch ended the Proton’s reliability on other automobile manufacturers for the vehicle parts and platforms. Then, in 2004, Proton launched the first car having the Malaysian-made engine, Campro. In 2004, Proton increased its empire by purchasing 57.57 percent of MV Augusta’s share.
Interesting Facts About Proton You Probably Don’t Know – Common Problems – and PDF Manuals for Download…
Proton or PROTON Holdings Berhad is an automobile manufacturing, designing, distribution and sales organization based in Malaysia. The company was established in 1983 and is headquartered in Selangor.
Originally, Proton was a manufacturer of Mitsubishi Motors rebadged products in the 1980s and 1990s; but in the year 2000, the company designed and produced its first non-badge engineered car.
This led Malaysia to become the 11th country in the world which can design and produce cars from the ground. Since then, the company has been producing many badge engineered and locally engineered vehicles.
At present, more than 15 countries are the markets for Proton cars and most of them are in Asia.
Currently, Proton is undergoing a major transformation process which is the part of a long-term turnaround plan.
The company which was heavily dependent on the domestic market is making changes in its structure in the hope of regaining the profits and increase its presence in the international markets.
The concept was envisioned by the Malaysian Government in 1979 and in 1982, the project was approved by the Cabinet.
In 1983, Proton was founded and wholly owned by the Malaysian government. In the beginning, it approached Mitsubishi and agreed to jointly build the first production of Malaysian cars.
The result was 1985 model, Proton Saga which was based on Mitsubishi engine. After that, few other models were launched that shared the engine from Mitsubishi and one of the new models, Saga Iswara was widely used for commercial purposes in Malaysia.
Among all the models launched till late, 1990s were made with the collaboration from Mitsubishi until the company began producing its own indigenously designed car in August 2000.
It featured a Mitsubishi engine and this launch ended the Proton’s reliability on other automobile manufacturers for the vehicle parts and platforms.
Then, in 2004, Proton launched the first car having the Malaysian-made engine, Campro.
In 2004, Proton increased its empire by purchasing 57.57 percent of MV Augusta’s share. But the misfortunes of MV Augusta affected Proton as well and the company sold MV Augusta next year.
Then in the later part of the 2000 decade, Proton launched Persona saloon as the replacement of Proton Wira. The external appearance was almost similar, and had many new and advanced features at discounted prices.
It was an immediate hit in Malaysia and recorded huge sales volume in the coming time. In 2008, the product collaboration with Mitsubishi was resumed and Proton gained the special rights to rebadge Mitsubishi Lancer of 2007.
Proton Inspira was the collaborative result and this launch also strengthened the ties between both the companies. Braun multiquick 5 k700 user manual.
From the very beginning, Proton has actively maintained its presence in motorsports. Proton with Japanese company Mitsubishi has participated in various Asian and International motor rallies.
Mitsubishi was not the only company it partnered with and rebadged their cars, as it partnered with different other automobile companies for their different models.
The other companies it partnered with are Citroen of France, Youngman of China, Honda and Suzuki. When it partnered with Suzuki, it rebadged their famous model Ertiga.
Common Proton Problems
Proton Launch Failure
Proton is the most well-known brand in Malaysia. The company used Mitsubishi engines in its cars and later used the self-made engines.
The technological support from Japanese auto maker and highly progressive facilities led it to produce of the best cars in Malaysia.
The cars are also exported to other countries. Here are some commonly found problems in different models of Proton that can be solved using the repair manuals.
Very few car owners had these complaints and knowing them will lead to diagnose the problems at an early stage in your car.
Engine Lights: In some Proton G2 cars, the users experienced that engine warning light lit without any reason. Even after finding the engine in good condition, the light didn’t shut. The cause of the problem might be faulty wiring. Get your car checked from an experienced automobile technician or go through the repair manual.
Proton Distributor problem: In some Proton cars, distributor related problems have been commonly reported. A hall effect sensor is with which Proton distributor units are connected. With the rotation of the distributor, ECU receives a signal and a pulse is sent to ignition module that amplifies current to send to the coil. In case of malfunctioning of sensor, no signal develops which results in no spark at the plug. The only solution to this problem is replacing the hall sensor using the repair manual.
Airflow Meter: In Proton cars, failure of airflow meter is also found commonly. The amount of air passing in the engine is measured by airflow meter. The working of airflow meter can be classified as the amount of current it can take to keep the wire at a specific temperature. The fault may not be detected in the simple diagnostic and you can see the meter still operating in the limits that are believed to be sufficient. To get it properly diagnosed put right amount of fuel, give full throttle and the result will be a weak mixture and a lack of power. Good thing is that airflow meters are very easy to change and usually take only 5 minutes to fit.
Ignition Coil: In some makes of Proton Waja, owners complained that their cars were not starting properly and sometimes they experienced cold start. The root cause of this type of problem may be bad ignition coil and if the car is not starting at all, the ignition coil might have failed. In case of ignition coil failure, the correct amount of charge is not transmitted to spark plug. This issue can alleviate in winter season and a replacement of ignition coil will solve the problem.
Fuel Pump Failure: Some users of the Proton Waja model complained that while driving the car and accelerating it, its speed was not increasing. This is a common problem in Waja model and the reason is failure of the fuel pump. Replacement will get the car back to normal.
Conclusion
These are some of the common problems that people reported about Proton brand cars. Not all cars suffer from these problems and if you are aware of them, you can quickly get your car repaired on time using your car repair manual.
Purpose of this is to catalog and include one of most comprehensive, useful and accessible “automotive repair PDF manual” database on the web for all Proton models.
It’s your go-to source for learning all about Proton – when you can’t find it elsewhere.
To get started, select the intended car model below…
(Redirected from Geosynchronous transfer orbit)
An example of a transition from GTO to GSO. EchoStar XVII·Earth.
A geosynchronous transfer orbit or geostationary transfer orbit (GTO) is a Hohmann transfer orbit—an elliptical orbit used to transfer between two circular orbits of different radii in the same plane—used to reach geosynchronous or geostationary orbit using high-thrust chemical engines.[1]
Geosynchronous orbits (GSO) are useful for various civilian and military purposes, but demand a great deal of delta-v to attain. Since, for station-keeping, satellites intended for this orbit typically carry highly efficient but low-thrust engines, total mass delivered to GSO is generally maximized if the launch vehicle provides only the delta-v required to be at high thrust, i.e., to escape Earth's atmosphere and overcome gravitational losses, and the satellite provides the delta-v required to turn the resulting intermediate orbit, which is the GTO, into the useful GSO.
Technical description[edit]
GTO is a highly elliptical Earth orbit with an apogee of 42,164 km (26,199 mi),[2] or 35,786 km (22,236 mi) above sea level, which corresponds to the geostationary altitude. The period of a standard geosynchronous transfer orbit is about 10.5 hours.[3] The argument of perigee is such that apogee occurs on or near the equator. Perigee can be anywhere above the atmosphere, but is usually restricted to a few hundred kilometers above the Earth's surface to reduce launcher delta-V () requirements and to limit the orbital lifetime of the spent booster so as to curtail space junk. If using low-thrust engines such as electrical propulsion to get from the transfer orbit to geostationary orbit, the transfer orbit can be supersynchronous (having an apogee above the final geosynchronous orbit). However, this method takes much longer to achieve due to the low thrust injected into the orbit.[4][5] The typical launch vehicle injects the satellite to a supersynchronous orbit having the apogee above 42,164 km. The satellite's low-thrust engines are thrusted continuously around the geostationary transfer orbits in an inertial direction. This inertial direction is set to be in the velocity vector at apogee but with an out-of-plane component. The out-of-plane component removes the initial inclination set by the initial transfer orbit, while the in-plane component raises simultaneously the perigee and lowers the apogee of the intermediate geostationary transfer orbit. In case of using the Hohmann transfer orbit, only a few days are required to reach the geosynchronous orbit. By using low-thrust engines or electrical propulsion, months are required until the satellite reaches its final orbit.
The orbital inclination of a GTO is the angle between the orbit plane and the Earth's equatorial plane. It is determined by the latitude of the launch site and the launch azimuth (direction). The inclination and eccentricity must both be reduced to zero to obtain a geostationary orbit. If only the eccentricity of the orbit is reduced to zero, the result may be a geosynchronous orbit but will not be geostationary. Because the required for a plane change is proportional to the instantaneous velocity, the inclination and eccentricity are usually changed together in a single maneuver at apogee, where velocity is lowest.
The required for an inclination change at either the ascending or descending node of the orbit is calculated as follows:[6]
For a typical GTO with a semi-major axis of 24,582 km, perigee velocity is 9.88 km/s and apogee velocity is 1.64 km/s, clearly making the inclination change far less costly at apogee. In practice, the inclination change is combined with the orbital circularization (or 'apogee kick') burn to reduce the total for the two maneuvers. The combined is the vector sum of the inclination change and the circularization , and as the sum of the lengths of two sides of a triangle will always exceed the remaining side's length, total in a combined maneuver will always be less than in two maneuvers. The combined can be calculated as follows:[6]
where is the velocity magnitude at the apogee of the transfer orbit and is the velocity in GEO.
Other considerations[edit]
Even at apogee, the fuel needed to reduce inclination to zero can be significant, giving equatorial launch sites a substantial advantage over those at higher latitudes. Baikonur Cosmodrome in Kazakhstan is at 46° north latitude. Kennedy Space Center is at 28.5° north. Guiana Space Centre, the Ariane launch facility, is at 5° north. Sea Launch launches from a floating platform directly on the equator in the Pacific Ocean.
Expendable launchers generally reach GTO directly, but a spacecraft already in a low Earth orbit (LEO) can enter GTO by firing a rocket along its orbital direction to increase its velocity. This was done when geostationary spacecraft were launched from the space Shuttle; a 'perigee kick motor' attached to the spacecraft ignited after the shuttle had released it and withdrawn to a safe distance.
Although some launchers can take their payloads all the way to geostationary orbit, most end their missions by releasing their payloads into GTO. The spacecraft and its operator are then responsible for the maneuver into the final geostationary orbit. The 5-hour coast to first apogee can be longer than the battery lifetime of the launcher or spacecraft, and the maneuver is sometimes performed at a later apogee or split among multiple apogees. The solar power available on the spacecraft supports the mission after launcher separation. Also, many launchers now carry several satellites in each launch to reduce overall costs, and this practice simplifies the mission when the payloads may be destined for different orbital positions.
Because of this practice, launcher capacity is usually quoted as spacecraft mass to GTO, and this number will be higher than the payload that could be delivered directly into GEO.
For example, the capacity (adapter and spacecraft mass) of the Delta IV Heavy is 14,200 kg to GTO, or 6,750 kg directly to geostationary orbit.[7]
If the manoeuvre from GTO to GEO is to be performed with a single impulse, as with a single solid-rocket motor, apogee must occur at an equatorial crossing and at synchronous orbit altitude. This implies an argument of perigee of either 0° or 180°. Because the argument of perigee is slowly perturbed by the oblateness of the Earth, it is usually biased at launch so that it reaches the desired value at the appropriate time (for example, this is usually the sixth apogee on Ariane 5 launches[8]). If the GTO inclination is zero, as with Sea Launch, then this does not apply. (It also would not apply to an impractical GTO inclined at 63.4°; see Molniya orbit.)
Proton Launch Vehicle User's Manual Download
The preceding discussion has primarily focused on the case where the transfer between LEO and GEO is done with a single intermediate transfer orbit. More complicated trajectories are sometimes used. For example, the Proton-M uses a set of three intermediate orbits, requiring five upper-stage rocket firings, to place a satellite into GEO from the high-inclination site of Baikonur Cosmodrome, in Kazakhstan.[9] Because of Baikonur's high latitude and range safety considerations that block launches directly east, it requires less delta-v to transfer satellites to GEO by using a supersynchronous transfer orbit where the apogee (and the maneuver to reduce the transfer orbit inclination) are at a higher altitude than 35,786 km, the geosynchronous altitude. Proton even offers to perform a supersynchronous apogee maneuver up to 15 hours after launch.[10]
Proton Launch Vehicle User's Manual 2017
See also[edit]
References[edit]
^Larson, Wiley J. and James R. Wertz, eds. Space Mission Design and Analysis, 2nd Edition. Published jointly by Microcosm, Inc. (Torrance, CA) and Kluwer Academic Publishers (Dordrecht/Boston/London). 1991.
^Vallado, David A. (2007). Fundamentals of Astrodynamics and Applications. Hawthorne, CA: Microcosm Press. p. 31.
^Mark R. Chartrand (2004). Satellite Communications for the Nonspecialist. SPIE Press. p. 164. ISBN978-0-8194-5185-9.
^Spitzer, Arnon (1997). Optimal Transfer Orbit Trajectory using Electric Propulsion. USPTO.
^Koppel, Christophe R. (1997). Method and a system for putting a space vehicle into orbit, using thrusters of high specific impulse. USPTO.
^ abCurtis, H. D. (2010) Orbital Mechanics for Engineering Students, 2nd Ed. Elsevier, Burlington, MA, pp. 356–357.
^United Launch Alliance, Delta IV Launch Services User's Guide June 2013, p. 2-10, Figure 2-9; 'Archived copy'(PDF). Archived from the original(PDF) on 2013-10-14. Retrieved 2013-10-14.CS1 maint: archived copy as title (link) accessed 2013 July 27.
^ArianeSpace, Ariane 5 User's Manual Issue 5 Revision 1, 2011 July, p. 2-13, 'Archived copy'(PDF). Archived from the original(PDF) on 2016-03-09. Retrieved 2016-03-08.CS1 maint: archived copy as title (link) accessed 8 March 2016.
^International Launch Services, Proton Mission Planner's Guide Rev. 7 2009 November, p. 2-13, Figure 2.3.2-1, accessed 2013 July 27.