US 12,466,582 B2Granted

Combined launch vehicle and satellite system

AssigneeAgnikul Cosmos Private Limited

InventorsSyed Peer Mohamed Shah Khadri, Srinath Ravichandran

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Abstract

A combined launch vehicle and satellite system relates to the satellite combined with the launch vehicle's upper stage to provide a more efficient system that includes tank separation technology which allows the satellite system to shed tanks that have used up all the propellants stored therein. The method separation of the tank set is enabled by using a merman band or pneumatic type of separation system; wherein the three bottom tanks are emptied first during the process, followed by the separation of the emptied tanks herein the fuel is completely filled in the second set of tanks. The first pair of tanks is then separated after the fuel is emptied. Similarly, the plumbing lines are also separated. The separation of the used components is achieved herein and the satellite is ready for orbit insertion.

Claims10

Dependent claims

A combined launch vehicle and satellite system comprising:

satellite (101);
a first separation plane (102);
a first set of propellant tanks (103),
a second separation plane (104) positioned below the first set of propellant tanks;
a second set of propellant tanks (105);
and
plumbing lines (106);
and
an engine (107), wherein the plumbing lines are configured to connect the first set of propellant tanks and the second set of propellant tanks to the engine for supplying propellants from the second set of propellant tanks and then from the first set of propellant tanks,
wherein, when in operation, the combined launch vehicle and satellite system is configured to:
enable in-built separation mechanisms of the plumbing lines to separate the second set of propellant tanks from a primary load of the combined launch vehicle and satellite system, when the second set of propellant tanks are emptied by disconnecting and closing respective connections of the plumbing lines of the second set of propellant tanks;
and
enable in-built separation mechanisms of the plumbing lines to separate the first set of propellant tanks from the primary load of the combined launch vehicle and satellite system, when the first set of propellant tanks are emptied by disconnecting and closing respective connections of the plumbing lines of the first set of propellant tanks,
wherein a separation for the first set of propellant tanks and the second set of propellant tanks is enabled by a merman band or a pneumatic separation system, wherein the plumbing lines are placed at the end of the line away from the respective propellant tank that is emptied, to reduce mass of the plumbing lines being carried during a flight after separation.

11 more elements

A method of tank separation technology for a combined launch vehicle and satellite comprising the steps of:

performing a stage wise separation of a first set of propellant tanks and a second set of propellant tanks after usage, including
emptying the second set of propellant tanks initially of fuel,
enabling in-built separation mechanism of plumbing lines to separate the second set of propellant tanks from a primary load of the combined launch vehicle and satellite system by disconnecting and closing respective connections of the plumbing lines of the second set of propellant,
emptying the first set of propellant tanks,
enabling in-built separation mechanisms of the plumbing lines to separate the first set of propellant tanks from the primary load of the combined launch vehicle and satellite system by disconnecting and closing respective connections of the plumbing lines of the first set of propellant tanks, and
enabling a satellite to ready for orbit insertion (206),
wherein the separation of the tanks (103, 105) is enabled by a merman band or a pneumatic separation system, wherein the plumbing lines are placed at the end of the line away from the respective propellant tank that is emptied, to reduce mass of the plumbing lines being carried during a flight after separation.

4 more elements

Dependencies are inferred from the claim text.