The invention discloses a space vehicle control moment computing system based on a proportional derivative (PD) control law. The problems that existing space vehicle attitude control moment computing systems based on software design are slow in speed and low in accuracy are solved. The system comprises a Microblaze processor, a Reset global control signal input register, a Kp input register, a Kd input register, an angle input register, a standard angle input register, an angular velocity input register, an input switching unit, an output switching unit, a first subtracter, a second subtracter, a first multiplying unit, a second multiplying unit, a moment Tk output register and a marking signal Flag output register. When Reset=1, the processor allows the computing system to perform calculation, once the calculation ends, a global signal Flag is sent out, the processor is informed that the calculation is finished, and the moment Tk is withdrawn. The system is applicable to space vehicle control moment computing.