The shuttle had a empty gross weight of 172,000 lb (78,000 kg), and the only feasible way shedding the 27,724 kilometres (17,227 mi) per hour, of the relative speed of the ISS is Aerobraking. A four passenger Cessna 172 has an empty weight of under 2,500 lb (1,136 kg).
While actually using Cessna as a reentry vehicle would not be practical, the image allows for exploring the concept of an lite reentry vehicle (as opposed to How possible are 'space jumps'? ). Assuming we swap out the gas engine of the Cessna, and replace the mass with fuel, then strap some rockets (clearly an oversimplification) to the plane to decrease the orbital velocity, we have a nice glider with 2% of the mass and twice or more of the glide capacity.
If your pilot and passengers are in space suits for the trip, you won't need to add mass for keeping the vehicle pressurized.
So could a lite winged reentry vehicle use rockets to decelerate, and allow reentry with out having drag/heat issues? Would the fuel requirements to decelerate safely outweigh the benefits of creating vehicle that does not need to stand up to high speed Aerobraking?
Edit This answer to this question comes down what what is more economical; The extra mass for aerobraking heat shielding or the mass for fuel to decelerate. There was a comment addressing this but it has been deleted.