New, alternative candidates of hypergolic propellants to be used on the next-generation satellite platforms for the ACS systems or for the orbit transfers has been proposed. The main purpose of this study is to introduce benefits through the evaluation of ignition delay time, performance and handling requirements for new green hypergolic propellant systems based on highly concentrated hydrogen peroxide, at 98% of concentration, used as oxidizer. The novel green propellants combinations for the spacecraft mainly base on such substances as ADN and HAN, and are LMP-103S and AF-M315E, respectively. Nonetheless, highly concentrated hydrogen peroxide, H_2O_2, can also be used widely, not only in monopropellant, but also in bipropellant thrusters, especially in hypergolic systems. Highly concentrated hydrogen peroxide in contact with some organic fuel mixtures can lead to their self-initiated combustion, with reliable ignition that results in IDT on the level of several milliseconds. However, this is very dependent on the activity and amount of additives mixed with selected fuels. On the other hand, performance of such propellant compositions (liquid organic substance plus additive) can be similar to the toxic ones or even higher, in sense of density impulse. Thus, the propulsion units based on 98% hydrogen peroxide can be successfully used for many various missions of the near-future spacecraft. The utilization of highly concentrated hydrogen peroxide in the space sector can significantly decrease the total cost of satellite missions, due to its low toxicity, high power density, high stability, long duration storability and relatively cheaper safety and handling procedures.
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