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RLV-TD: Difference between revisions
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{{short description|Reusable launch vehicle technology demonstrator}} | {{short description|Reusable launch vehicle technology demonstrator}} | ||
{{Merge to|RLV Technology Demonstration Programme|discuss=Talk:RLV-TD#Request for merger with RLV Technology Programme}} | {{Merge|date= June 2023 to|RLV Technology Demonstration Programme|discuss=Talk:RLV-TD#Request for merger with RLV Technology Programme}} | ||
{{Infobox rocket | {{Infobox rocket | ||
|name = RLV-TD | |name = RLV-TD | ||
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==Development history== | ==Development history== | ||
RLV-TD was developed by [[ISRO]] under the [[RLV Technology Demonstration Programme]]. The Technology Demonstration Programme consists of development of [[hypersonic speed|hypersonic]] [[rocket]] with [[air-breathing engine]]s and the [[reusable launch vehicle]].<ref name="India’s Reusable Launch Vehicle Successfully Flight Tested">{{cite news|title=India's Reusable Launch Vehicle Successfully Flight Tested|publisher=[[ISRO]] website|access-date=23 May 2016|url=http://www.isro.gov.in/update/23-may-2016/india%E2%80%99s-reusable-launch-vehicle-technology-demonstrator-rlv-td-successfully}}</ref | RLV-TD was developed by [[ISRO]] under the [[RLV Technology Demonstration Programme]]. The Technology Demonstration Programme consists of development of [[hypersonic speed|hypersonic]] [[rocket]] with [[air-breathing engine]]s and the [[reusable launch vehicle]].<ref name="India Flies Winged Space Plane On Experimental Suborbital Launch"/><ref name="India’s Reusable Launch Vehicle Successfully Flight Tested">{{cite news|title=India's Reusable Launch Vehicle Successfully Flight Tested|publisher=[[ISRO]] website|access-date=23 May 2016|url=http://www.isro.gov.in/update/23-may-2016/india%E2%80%99s-reusable-launch-vehicle-technology-demonstrator-rlv-td-successfully}}</ref> The RLV-TD is being designed and built at the Vikram Sarabhai Space Centre. Its navigational equipment was supplied by the ISRO Inertial Systems Unit in Thiruvananthapuram and ISRO's Satellite Applications Centre in Ahmedabad. The RLV-TD's landing gear is supplied by Hindustan Aeronautics Limited. | ||
===Engines=== | ===Engines=== | ||
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RLV-TD was launched mounted on top of a [[Single-stage-to-orbit|single stage]] [[solid fuel]] [[Booster (rocketry)|booster]] (HS9 booster), derived from [[strap-on booster]]s flown on India's [[Polar Satellite Launch Vehicle]]. Once the booster consumed its [[solid fuel|solid]] [[propellant]] in 91 seconds, the RLV-TD separated and peaked to a sub-orbital altitude of about {{convert|65|km}}. The [[heat shield]], [[Guidance system|guidance]], [[navigation]] and [[Aircraft flight control system|control]] [[algorithm]]s were tested by accurately steering the vehicle during the [[hypersonic speed]] [[Descent (aeronautics)|descent]] phase. During this phase, the test vehicle was programmed to pitch its nose up, exposing silica tiles on its underside and [[reinforced carbon–carbon]] nose cap to the [[airflow]] into the thick lower layers of the atmosphere. The RLV-TD's [[thermal protection system]] enabled the vehicle to endure high temperatures of descent through the atmosphere. | RLV-TD was launched mounted on top of a [[Single-stage-to-orbit|single stage]] [[solid fuel]] [[Booster (rocketry)|booster]] (HS9 booster), derived from [[strap-on booster]]s flown on India's [[Polar Satellite Launch Vehicle]]. Once the booster consumed its [[solid fuel|solid]] [[propellant]] in 91 seconds, the RLV-TD separated and peaked to a sub-orbital altitude of about {{convert|65|km}}. The [[heat shield]], [[Guidance system|guidance]], [[navigation]] and [[Aircraft flight control system|control]] [[algorithm]]s were tested by accurately steering the vehicle during the [[hypersonic speed]] [[Descent (aeronautics)|descent]] phase. During this phase, the test vehicle was programmed to pitch its nose up, exposing silica tiles on its underside and [[reinforced carbon–carbon]] nose cap to the [[airflow]] into the thick lower layers of the atmosphere. The RLV-TD's [[thermal protection system]] enabled the vehicle to endure high temperatures of descent through the atmosphere. | ||
All stages of the test flight were tracked by ground station at the launch site and a shipborne terminal. All the mission objectives were met and technologies like [[Proximity operations|autonomous navigation]], [[Guidance system|guidance]] and [[Aircraft flight control system|control]], reusable [[thermal protection system]] and descent mission management were successfully validated.<ref name=" | All stages of the test flight were tracked by ground station at the launch site and a shipborne terminal. All the mission objectives were met and technologies like [[Proximity operations|autonomous navigation]], [[Guidance system|guidance]] and [[Aircraft flight control system|control]], reusable [[thermal protection system]] and descent mission management were successfully validated.<ref name="India Flies Winged Space Plane On Experimental Suborbital Launch"/><ref name="India’s Reusable Launch Vehicle Successfully Flight Tested"/> | ||
== Landing experiment == | == Landing experiment == | ||