Compatibility between ZQ-2’s control system and engine confirmed with breakthrough in rear sway techniques
From May 9 to May 13, 2020, the compatibility between the ZQ-2 rocket’s control system and TQ 80t-thrust-level LOX+LCH4 engine was confirmed. At the same time, triple hot-firing test run for rear sway techniques were completed successfully.
According to LandSpace’ rocket development engineer, ZQ-2 was the first double cryogenic rocket adopting electromechanical servo technology in China. The control system of the rocket uses a high-power electromechanical servo to promote the oscillation, while the thrust vectoring of the engine is applied to achieve constant attitude and high-precision control. In comparison with conventional pump front sway, the advanced pump rear sway techniques adopted by the TQ 80t LOX+LCH4 engine helped to reduce the size, structural weight, and sway torque of the engine.
In this test, the sway with various angles, frequencies, and waveforms was conducted; the compatibility between the engine and the high-power servo was confirmed; the static and dynamic characteristics of the engine sway system were obtained, marking another milestone in the development of ZQ-2.
The sway angle achieved ±8° at a frequency of 0-20 Hz; tested waveforms included sine wave, triangle wave, and square wave. The tests covered various control requirements for the flight of ZQ-2, and tightened inspection was also conducted. The large joint sway test was a big success.
This test represented an important breakthrough at the prototype development stage of the TQ 80t LOX+LCH4 engine and the ZQ-2 carrier rocket. Besides, LandSpace has completed the full-system test and long-range test.
By this test, the compatibility between the engine and the rocket control system was confirmed for the first time. The success indicates that the flight status of the engine has been confirmed, and the ZQ-2 liquid carrier rocket has entered the stage of joint compatibility verification after completing engine verification. This lays a solid foundation for the maiden flight of the rocket.