Development of a hardware and software model of a rocket motion correction system

The paper deals with the development of a motion correction system for an unguided rocket of a certain class. The existing method for calculating the rocket flight range based on the dependence of flight path on the initial rocket pitch angle and average parameters of disturbing effects does not provide the required accuracy of the specified flight range. This is mainly due to uncontrolled range wind deviations in the flight area. At the same time, conducting test rocket launches to identify dispersion characteristics and improve the target accuracy leads to significant material costs. Therefore, computer simulation is the most promising approach for studying rocket dispersion laws and developing a motion correction system for the unguided rocket on this basis. When developing the correction system, classical differential equations were used describing the aerodynamics of a variable-mass rocket, as well as adaptive control methods with a reference model. As a result of the study, a method for recording a program that implements the reference model on the Arduino Due platform was developed. A general Simulink model that simulates the process of rocket flight path correction was built. A half-scale rocket flight model with a correction block was developed. Based on this model, a series of experiments were carried out, which showed a high degree of rocket target accuracy due to rocket path correction. The results make it possible to take the developed system as a basis for developing a practical path correction system for Grad rockets

Design and implementation of remote image processing system for space launch site

Telemetry image has the characteristics of intuitive image in the process of rocket flight. Through real-time acquisition of rocket flight video image, it can provide the working status of key nodes in the process of rocket flight, and provide intuitive decision-marking auxiliary information for commanders. This paper analyzes the design content of the image processing system of the space launch site from the aspects of image transmission mechanism, information flow, image data processing and image decoding, so as to provide technical basis for the image receiving, transmission and decoding process in the engineering practice of the image processing system.

INCREASING DATA TELEMETRI SOUNDING ROCKET LAPAN WITH PULSE CODE MODULATION METHODE

The telemetry data of the sounding rocket when flight in the space is very important to known. This data will be used for next mission or evaluation the last rocket flight. Commonly the data of the sensor in the sounding rocket are accelerometer, gyroscope, magnetometer, GPS and so on. As much data as possible than can be sent to the ground control system when the rocket flies. The problem is when the baud rate is low so not much data can be transmitted. Another problem is when the using serial bit standard communication such as the baud rate is 115.200 which mean that the maximum data in one second is 14,400 characters. It is less than when using the PCM bit rate. Application of PCM in the telemetry for sounding rocket LAPAN is new and need development to reach the optimal. With the PCM method the communication data can transmit around 1.25Mbps or 156,250 characters based on the TR FM02-S-2 full S-band transmitter. In this research, focus to the implementation the PCM method on the FPGA for sending and receiving the data via cable. Two FPGA boards can work together for sending and receiving data with PCM method with the total bit is 1.25Mbps.