Задачи точной регулировки положения центра масс летательного аппарата, являются неотъемлемой частью авиационного производства. Особую актуальность балансировка приобретает для  обеспечения движения по разгонной траектории, аппаратов разгоняемых при помощи специального ускорителя. Для обеспечения стабильного движения таких аппаратов на разгонной траектории, необходимо обеспечить совпадение направления вектора тяги разгонного двигателя и положения центра масс ЛА, с минимальными отклонениями.

The balancing system offered by Aviation Consulting-TECHNO accurately localizes the aircraft center of mass and determines the booster engine installation angle (thrust vector direction). It is capable of calculating weight characteristics of the object being measured accurate to within ±0.5% of the total product mass. The center of mass location in a three-coordinate system is calculated accurate to within ±0.5 mm or better while the thrust vector angular position is calculated accurate to within ±15' or better. The system design is suitable for measuring aircraft having various sets of components. The system may be modified at customer’s option to balance aircraft of different overall dimensions.

The aircraft weight characteristics are determined with the aid of precision strain gage transducers. The aircraft center of mass location is determined based on a three-point weighting method wherein the reaction force of supports is measured in three fixed positions and the aircraft center of mass coordinates are determined based on the measurement results thus obtained. The test results are used by the system to issue recommendations on placing/removing balance weights in/from the aircraft structure.

The thrust vector is determined and controlled with the aid of an appliance having a laser designator and installed in the power plant nozzle. An optical device is used to determine deviation of the takeoff booster thrust vector from a theoretical location of the aircraft center of mass. The results of calculations at each stage are displayed on the control stand. On completion of testing, a test record is issued in the form required by the customer. An inclinometer built in the system is used to compensate for errors arising in the system position with reference to the horizon and frame structure deformations in the process of measurements.

The laser designator and precision optical equipment are used to measure and control the booster engine thrust vector directly in the system. A UAV can be fixed in the balancing system using standard yoke assemblies which require no modification and use of special fittings.