Proson-M1
| Function | meteorological sounding rocket |
|---|---|
| Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value). | Argentine Institute of Science and Technology |
| Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value). | Argentina |
| Size | |
| Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value). | 3.261 m (10.70 ft) |
| Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value). | 0.20 m (7.9 in) |
| Lua error in Module:WikidataIB at line 555: attempt to index field 'wikibase' (a nil value). | 51.8 kg (114 lb) |
| Stages | 2 |
| Capacity | |
| Launch history | |
| Launch sites | CELPA Chamical |
| Total launches | 4 |
| First flight | August 23, 1963 |
| Last flight | August 26, 1963 |
| First stage | |
| Thrust | 1700 kg |
| Burn time | 5 seconds |
| Propellant | nitrocellulose + nitroglycerin |
| Second stage | |
| Thrust | 750 kg |
| Burn time | 3.5 seconds |
| Propellant | nitrocellulose + nitroglycerin |
The Proson-M1 was a two-stage meteorological sounding rocket developed by the Argentine Institute of Science and Technology for CITEFA in the 1960s, first launched on August 23, 1963, from CELPA (El Chamical).[1][2][3] The rocket was launched using a delayed ignition system, with an 18-second interval between the first and second stages. Smoke charges were often used instead of payloads to study flight paths using optical tracking tools.[2]
Details
[edit | edit source]The Proson-M1 was a dual-stage design built primarily from steel (API-N80) and reinforced with duralumin fins for aerodynamic stability. The fins had trapezoidal shapes, with the first-stage surfaces being conical and the second-stage surfaces flat and parallel.[2]
The first stage measured 1678 mm in length, 200 mm in diameter, and weighted 38.5 kg. The second stage measured 1583 mm in length, 110 mm in diameter, and weighted 13.3 kg.[2] Both were powered by a solid-propellant engine made of a double-base propellant consisting of nitrocellulose and nitroglycerin. Maximum thrust was 1700 kg for the first stage and 750 kg for the second stage, with burn times of 5 seconds and 3.5 seconds, respectively.[2]
Proson-M1 could reach a maximum velocity of Mach 4 and was capable of carrying payloads of up to 5 kg to 50 km.[1]
Launches
[edit | edit source]The Proson-M1 had four launches in August 23 and 26, 1963, to study flight paths using optical tracking tools like cine-theodolites.[1][2]
References
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