Thrust Stands-LS2407205-曼卡尼- 3rd HOMEWORK.pptx

Micro-Newton Thrust Stands

1. DESIGN AND TESTING OF A MICRO-NEWTONTHRUST STAND FOR FEEP ——Final Homework Prepared by: Mankani Mlungisi Date: 2024/12/03

2. 2 Contents 01 Gimbaled/Pivoted Configuration 02 Radial Configuration 03 Static Measurement Configuration 04 References

3. 3 Contents 01 Gimbaled / Pivoted Configuration 02 Radial Configuration 03 Static Measurement Configuration 04 References

4. 4 1. Gimbaled/Pivoted Configuration Fig. 1. Prototype thrust stand using 6-DOF  magnetic levitation . Fig. 2. Levitator (top view) Fig. 1 ,  Fig. 2  show schematics of the prototype thrust stand and the levitator, respectively. The  z -axis is parallel to the normal vector of the regular-triangle levitator of 200 mm sides, while the  x - and  y -axes are set in the directions of the tangent to the levitator surface. The origin O is the center of the levitator on the upper surface. The levitator, placed horizontally, was suspended by six voice-coil motors (VCMs)

5. 5 1. Gimbaled/Pivoted Configuration Fig. 3. Calibration setup Calibrator (model thruster) The correlation between the VCM-driving current and thrust must be determined through calibration A sensitivity matrix S, which is expressed as shown in the equation will be obtained by the measurement of  i  under the exertion of reference  T . In the calibration, a model thruster comprising a load cell and cylindrical neodymium magnet exerted reference thrust to the levitator. As shown in  Fig. 3 , the magnet was inserted into a hollow solenoid. The reference thrust (electromagnetic force), which the load cell measured, was adjusted with the driving current.  

6. 6 Contents 01 Gimbaled/Pivoted Configuration 02 Radial Configuration 03 Static Measurement Configuration 04 References

7. 7 2. Radial Configuration 1. Load-bearing frame (base) 2. 360-degree turntable 3 .Loading hydraulic cylinder 4. Multi-component force measurement platform 5. Simulated engine Fig. 4. Schematic of the Vector Thrust Calibration Structure. The multi-component force platform and the multi-degree-of freedom vector central loading device are installed between the simulated engine and the load-bearing frame (base). The multi degree-of-freedom vector central loading device applies a vector force to the entire system, and the multi-component platform outputs a standard vector force, thus completing the vector thrust calibration for the engine stand. A schematic of the vector thrust calibration is shown in Figure 4.

8. 8 2. Radial Configuration Fig. 5 . Structural Diagram of the Multi-component Force Measurement Platform The main direction capacity of the multicomponent force platform is designed to be 200kN, and the side direction capacity is 100kN. Since the forces in the lateral direction are equal, the platform is designed with asymmetrical structure. The upper and lower platforms of the force measurement platform are chosen to be square structures. The horizontal force measurement components are designed with a set of four groups arranged symmetrically at 90°, and the vertical force measurement components are also designed with a set of four groups arranged symmetrically at 90°.

9. 9 2. Radial Configuration Fig. 6 . shows the multi-component calibration device. The static calibration of the multi-component force platform requires calibration using a multi-component force calibration apparatus. It can be entirely placed within the calibration device, realizing the traceability of engine vector thrust values. The superimposed multi-component force standard machine specifically comprises the main frame, workbench, movable force beam, and piston power system. Features of the calibration device include designing suitable load sources in the Z direction and the X and Y directions, respectively, connected in series with the standard force sensor through decoupling components. With the help of auxiliary devices, forces from different positions and directions are coordinated and loaded onto the multi-component force sensor fixed on the workbench for calibration.

10. 10 Contents 01 Gimbaled/Pivoted Configuration 02 Radial Configuration 03 Static Measurement Configuration 05 References

11. 11 3. Static Measurement Configuration Fig. 7. Photograph of the thrust stand. The thrust stand mainly consists of a thrust dynamometer, a connecting frame, a base frame, and a data acquisition and processing system.

12. 12 3. Static Measurement Configuration Fig. 8. The deformation of the model of the dynamometer shell established by finite element analysis software The resulting deformation of the dynamometer shell is shown in Fig. 5. From Fig. 8 the two double-elastic-half-rings have same deformation, but deformation of two sides of each long groove is different. Deformation on the side near the worktable is much larger than that on the side near the fixed end. The different deformation will cause static friction forces on fitting surface, which are transferred to the piezoelectric quartz sensors to achieve the measurement of the force.

13. 13 3. Static Measurement Configuration Fig. 9. Schematic of static calibration . A series of pressures are applied to a piston and hydraulic cylinder assembly through the hydraulic loading device. These pressures are converted to forces which pull the front end of the connecting frame through the wire rope. These forces are transferred to the thrust dynamometer, and the output voltage signals are recorded. The magnitudes of these forces are measured by the standard force sensor with one end anchored to the piston and other end attached to the wire rope. The standard force sensor with operating range from 0 to 30 N is previously calibrated and used as a calibration reference.

14. 14 Contents 01 Gimbaled/Pivoted Configuration 02 Radial Configuration 03 Static Measurement Configuration 04 References

15. 15 04. References [1] A. Kakami, K. Hanyu, and Y. Yano, “Magnetically-levitated thrust stand for evaluating 6-component thrust vector of 1-N class onboard propulsion devices,” Aerospace Science and Technology, vol. 104, Sep. 2020, doi: 10.1016/j.ast.2020.105896 . [2] J. Chai, S. Lin, Y. Zhang, H. Qin, and S. Tian, “Development of a Multi-component Force Measurement Platform for Vector Thrust Calibration of Aviation Engines,” in IET Conference Proceedings, Institution of Engineering and Technology, 2023, pp. 279–289. doi: 10.1049/icp.2023.2951. [3] Q. Xing, J. Zhang, M. Qian, Z. Y. Jia, and B. Y. Sun, “Thrust stand for low-thrust liquid pulsed rocket engines,” Review of Scientific Instruments, vol. 81, no. 9, Sep. 2010, doi: 10.1063/1.3481788.

16. Thank You ！