| 词条 | FG-02 |
| 释义 |
|name =FG-02 |image = |image_size = |caption = |country_of_origin=China |date =1966-1970 |first_date =1970-04-24 |last_date =1971-03-03 |designer =China Hexi Chemical and Machinery Corporation |manufacturer = |purpose =Upper stage |associated =Long March 1 |predecessor = |successor = |status =Retired |type =solid |oxidiser = |fuel =Polysulfide |grain = |core = |casing = |nozzle = |description = |combustion_chamber=1 |nozzle_ratio = |thrust = |thrust_at_altitude= |thrust(Vac) ={{convert|118|kN|lbf|abbr=on}} |thrust(SL) = |thrust_to_weight= |chamber_pressure= |specific_impulse= |specific_impulse_vacuum={{convert|254|isp|abbr=on}} |specific_impulse_sea_level= |total_impulse ={{convert|4500|kN|abbr=on}} |burn_time =38s |gimbal = |capacity ={{convert|1806|kg|lb|abbr=on}} |dimensions = |length ={{convert|3.95|m|in|abbr=on}} |diameter ={{convert|0.77|m|in|abbr=on}} |dry_weight ={{convert|246|kg|lb|abbr=on}} |used_in =Long March 1 third stage. |references =[1][2] |notes = }} The FG-02 was a Chinese solid rocket motor burning Polysulfide.[2] It was developed by China Hexi Chemical and Machinery Corporation (also known as the 6th Academy of CASIC) for use in the Long March 1 third stage. It has a total nominal mass of {{convert|2052|kg|lb|abbr=on}}, of which {{convert|1806|kg|lb|abbr=on}} is propellant load. It has an average thrust of {{convert|118|kN|lbf|abbr=on}} with a specific impulse of 254 seconds burning for 38 seconds, with a total impulse of {{convert|4500|kN|abbr=on}}. It used spin stabilization and a timing device to ignite in flight.[1][6] The Long March 1 is basically a DF-4 with a solid third stage and a fairing. So the FG-02 was developed as the third stage to add to the stack. It was initially tested on two launches aboard T-7A sounding rockets to validate high altitude ignitions. Both successful flights were performed on August 1968. Before going into the launch vehicle, the propellant load was increased from {{convert|900|kg|lb|abbr=on}} to {{convert|1806|kg|lb|abbr=on}}. It performed just two orbital flights, both from Jiuquan and both successful. The first was on April 14, 1970, to orbit the indigenous satellite, the Dong Fang Hong I. And the second was on March 3, 1971, on the Shijian 1 mission. See also
References1. ^1 {{cite web |url=http://www.b14643.de/Spacerockets_1/China/CZ-1/Propulsion/engines.htm |title=Propulsion CZ-1 & CZ-1D |website=B14643.DE |author=Norbert Bgügge |accessdate=2015-07-25}} [1][2][3]2. ^1 2 {{cite web |url=http://www.b14643.de/Spacerockets/Diverse/SpaB_aerospace_motors/index.htm |title=Some Chinese solid fuel aerospace motors |website=B14643.DE |author=Norbert Bgügge |accessdate=2015-07-25 |deadurl=yes |archiveurl=https://web.archive.org/web/20150926034320/http://www.b14643.de/Spacerockets/Diverse/SpaB_aerospace_motors/index.htm |archivedate=2015-09-26 |df= }} 3. ^1 2 {{cite web |url=http://www.astronautix.com/engines/gf02.htm |title=GF-02 |publisher=Encyclopedia Astronautica |accessdate=2015-07-25}} }}{{Upper stages}}{{Rocket engines}}{{DEFAULTSORT:FG-02}}{{rocket-stub}} 3 : Rocket stages|Rocket engines of China|Solid-fuel rockets |
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