The invention discloses a missile control surface space linkage type control mechanism to solve the problem that steering engine installation requires occupying more missile body space currently. The missile control surface space linkage type control mechanism is characterized in that each first cockpit and an adjacent second cockpit are fixed through a connecting compartment; the first cockpits are connected with first rudders; the second cockpits are connected with second rudders; a first rudder shaft fixed to one first rudder and one first cockpit form a rotation pair correspondingly; rotation blocks are fixed to the first rudder shafts; a sliding rod and a second through hole of one rotation block form a sliding pair correspondingly; a guide rail and a sliding block with a boss formed at the top form a sliding pair correspondingly; the two ends of a first connecting rod are hinged to one boss and one sliding rod correspondingly; one end of a second connecting rod and one sliding block are fixed correspondingly; a nut block fixed to the other end of each second connecting rod and a screw rod form a helical pair correspondingly; one end of each screw rod is connected with an output shaft of a second steering engine through a coupler; a second rudder shaft of each second rudder and a third through hole of the corresponding second cockpit form a rotation pair; and an output shaft of a first steering engine and one second rudder shaft are fixed correspondingly. According to the missile control surface space linkage type control mechanism, the steering engines of certain rudders are moved to the cockpits where the other rudders are located, and the size occupation of a missile body is reduced.