Edit: re-reading the question this is not an answer, which is looking for solutions involving gravity assists only.

The study here (summary is section 6.4) found that for an example mission profile while substantial mass/cost savings would be possible it would involve several years of orbital shaping to step orbit inward, the radiation environment incredibly hostile (and applying over that multi year period) notably Juno has stayed out of the region of peak radiation due to radiation concerns by using a polar orbit, and still required careful design to survive. Assuming aim of aerobraking is to reach the moons passing through the peak radiation regions becomes necessary.

The biggest concern is that while the gas pressures are very low at the proposed pass altitude the very high velocity produces temperatures high enough that it does not matter what type of degrees you are using (40,000 kelvin). The low pressure means this temperature will not necessarily melt the bulk of the craft in a single pass but will attack any low mass exposed components like antenna or foil thermal covering, requiring more complex design and allowance for erosion.

Moving to a higher pass altitude lowers the pressure/heat load but does not do much for the speed, so still problematic and massively increases the number of needed passes going from years to decades to reach final orbit.

This tends to suggest that aerobraking at Jupiter is not automatically a more efficient choice than carrying a rocket engine and fuel, unless for other reasons the craft is radiation shielded and physically robust.

Edit: re-reading the question this is not an answer, which is looking for solutions involving gravity assists only while this only covers aerobraking orbit adjustment

The study here (summary is section 6.4) found that for an example mission profile while substantial mass/cost savings would be possible it would involve several years of orbital shaping to step orbit inward, the radiation environment incredibly hostile (and applying over that multi year period) notably Juno has stayed out of the region of peak radiation due to radiation concerns by using a polar orbit, and still required careful design to survive. Assuming aim of aerobraking is to reach the moons passing through the peak radiation regions becomes necessary.

The biggest concern is that while the gas pressures are very low at the proposed pass altitude the very high velocity produces temperatures around 39,000 kelvin. The low pressure means this temperature will not necessarily melt the bulk of the craft in a single pass but will attack any low mass exposed components like antenna or foil thermal covering, requiring more complex design and allowance for erosion.

Moving to a higher pass altitude lowers the pressure/heat load but does not do much for the speed, so still problematic and massively increases the number of needed passes going from years to decades to reach final orbit.

This tends to suggest that aerobraking at Jupiter is not automatically a more efficient choice than carrying a rocket engine and fuel, unless for other reasons the craft is radiation shielded and physically robust.

The study here (summary is section 6.4) found that for an example mission profile while substantial mass/cost savings would be possible it would involve several years of orbital shaping to step orbit inward, the radiation environment incredibly hostile (and applying over that multi year period) notably Juno has stayed out of the region of peak radiation due to radiation concerns by using a polar orbit, and still required careful design to survive. Assuming aim of aerobraking is to reach the moons passing through the peak radiation regions becomes necessary.

The biggest concern is that while the gas pressures are very low at the proposed pass altitude the very high velocity produces temperatures high enough that it does not matter what type of degrees you are using (40,000 kelvin). The low pressure means this temperature will not necessarily melt the bulk of the craft in a single pass but will attack any low mass exposed components like antenna or foil thermal covering, requiring more complex design and allowance for erosion.

Moving to a higher pass altitude lowers the pressure/heat load but does not do much for the speed, so still problematic and massively increases the number of needed passes going from years to decades to reach final orbit.

This tends to suggest that aerobraking at Jupiter is not automatically a more efficient choice than carrying a rocket engine and fuel, unless for other reasons the craft is radiation shielded and physically robust.

Edit: re-reading the question this is not an answer, which is looking for solutions involving gravity assists only.

The study here (summary is section 6.4) found that for an example mission profile while substantial mass/cost savings would be possible it would involve several years of orbital shaping to step orbit inward, the radiation environment incredibly hostile (and applying over that multi year period) notably Juno has stayed out of the region of peak radiation due to radiation concerns by using a polar orbit, and still required careful design to survive. Assuming aim of aerobraking is to reach the moons passing through the peak radiation regions becomes necessary.

The biggest concern is that while the gas pressures are very low at the proposed pass altitude the very high velocity produces temperatures high enough that it does not matter what type of degrees you are using (40,000 kelvin). The low pressure means this temperature will not necessarily melt the bulk of the craft in a single pass but will attack any low mass exposed components like antenna or foil thermal covering, requiring more complex design and allowance for erosion.

Moving to a higher pass altitude lowers the pressure/heat load but does not do much for the speed, so still problematic and massively increases the number of needed passes going from years to decades to reach final orbit.

This tends to suggest that aerobraking at Jupiter is not automatically a more efficient choice than carrying a rocket engine and fuel, unless for other reasons the craft is radiation shielded and physically robust.