For research purposes, it is necessary to present the projects of sounding rocket systems (SRS) with rockets designed to reach the altitute from 10,000 m to 120,000 m above the surface of the Earth.
Sounding rockets (also known as research rocket) as part of the sounding rocket systems are a tool for making measurements or conducting scientific experiments during their sub-orbital flights.
-
RVC components
-
RVC requirements
-
LV requirements
-
Main propulsion system requirements
-
Data collection and transmission requirements
-
Launch complex should ensure
RVC components
- Launch vehicle (LV).
- Launch complex (LC).
RVC requirements
-
Basic criteria for developing RVC:
- RVC shall provide preparation for launch, launch, control of basic parameters of the LV trajectory in flight, conducting post-launch operations, conducting operations in the event of launch cancellation.
- RVC shall provide preparation and launch at temperatures from -5 ºС to +35 ºС, wind speeds at a height of 10 meters not more than 5 meters per second, as well as in the absence of precipitation during daylight hours.
- Preparations for launch and launch of LV must be carried out remotely (without the involvement of launching personnel) from a distance of at least 500 meters.
LV requirements
-
The launch vehicle must be equipped with a parachute rescue system. LV start type is a ground launcher due to the thrust of the main propulsion system.
-
The LV must not have uncontrolled detachable structures or uncontrolled structures, assemblies, and discharges.
-
The payload must be separated from the LV when it reaches the specified or allowable altitude.
-
The LV launches must be carried out in a trajectory close to the vertical.
-
The LV must be unmanned and statically stable on the active flight path.
-
The rescue system should ensure that the product is minimally destroyed.
-
The rescue system (if possible) should ensure the return of the LV in a radius of 5 kilometers around the launch point - additional points.
-
The LV must be designed to allow for repeated use of components after inspection.
Main propulsion system requirements
- Liquid rocket engine with the propellant or pump pressurization of fuel components or solid propellant rocket engine.
- Fuel components are affordable, non-cryogenic and environmentally friendly.
Data collection and transmission requirements
-
During the flight, it is necessary to collect the following data:
-
flight altitude;
-
the parameters of power plant (PP) and pneumatic-hydraulic circuit (PHC) (depending on the implementation scheme);
-
flight coordinates;
-
video registration.
-
During the flight, it is necessary to transmit the following data:
- flight altitude;
- flight coordinates.
Launch complex should ensure
-
Required scope of checks for ground and airborne systems.
-
Setting the LV at the starting position.
-
Placement of launch operators.
-
Remote control and control over the pre-launch operations, launch, post-launch operations, operations in case of launch cancellation.
-
Control over the basic parameters of the LV trajectory in flight.
-
Full operation for finding the LV at the starting position within 48 hours.
-
Search for depleted LV.
-
At least 10 launches.
It is necessary to present the project of the launch vehicle or CanSat device. The project must be designed and implemented based on the technical requirements to launch vehicles or CanSat's experimental educational microsatellites and in accordance with their weight-and-dimensional characteristics and performance specifications.
CanSat launch vehicles are designed for output and safe deployment from two to four CanSats under the parachutes at altitudes of 1,000 to 3,000 meters above ground level, thereby ensuring that each CanSat "hovers" in the air for some time to conduct the experiments.The deployment of satellites should be carried out by separating them from the vehicle, performing a safe drop of the product due to a rescue system, transmitting telemetry and location information, making video recording of all phases of product operation.
CanSat is a space payload standard used to teach the principles of design and construction of space engineering. But CanSat satellites are non-orbital and never leave the atmosphere.
Under the CanSat requirements, an operative satellite model must have:
-
66 mm
diameter
-
115 mm
height (the size of a 0.33
volume soda can )
-
350g
mass
-
< $500
cost of components
The model may have mounted external elements (antennas, booms, etc.), but the diameter can't increase until the satellite is detached from the launch vehicle. The satellite must be equipped with a rescue system to minimize damage to the apparatus and to enable its recovery and reuse. CanSat must be equipped with a parachute system that allows it to land safely.
The satellite must measure and process the external and internal parameters during the drop, and downlink them via radio signals.
-
Required parameters
-
Key components
-
Secondary elements
Required parameters
-
Temperature
-
Pressure
-
Location
-
Other
By the decision of the team
Key components
This is the main body of the robot, as it is responsible for receiving signals from external sensors (such as an altimeter, accelerometer or transmitter), and also processes them so that they act under the programmed algorithm. Most microprocessors include or may contain internal memory to store data and information from various sensors during the flight.
It provides power for the operation of all satellite systems and is important for any electronic system. The most commonly used lithium polymer batteries (LiPo) through their efficiency and current weight.
Secondary elements
It consists of a pressure measuring cell, which is connected to the microprocessor and sends a voltage signal in accordance with the pressure that it is experiencing. The microprocessor uses standardized atmospheric conditions to measure altitude.
The operation it performs is similar to a barometer, but the voltage signal that is sent to the microprocessor depends on the measured temperature. The microprocessor interprets this signal by assigning a temperature value.
This is a land positioning system, which consists of a satellite network, moves around the earth and constantly delivers its position or transmission time. From this data, the receiver triangulates its position with all available satellites in order to obtain greater accuracy. This position is sent to the microprocessor through the serial port as a data line.
At the design level, GPS receivers should be located in a place where the satellite lines of pointing are as straight as possible so that they are do not stay outside during the flight. In a CanSat metal structure, receivers should always be located where the structure does not affect this line of pointing.
This system is implemented from one or more accelerometers in various axes. All accelerometers allow you to measure acceleration in the distinct axes. Accelerometers can be used to collect data or to determine a position (by integration). The best accelerometers made to determine positions are called the INS - Inertial Navigation System.
They are applicable to some CanSat models. The indeterminacy of this system depends on the error during sensor calibration. The advantage of this system is no need for GPS and the occurrence of resistance to magnetic interference. This allows making multiple locations within CanSat.
Sometimes it is necessary to have cognizance of the direction that CanSat follows (for instance, to launch a monitored start). In this case, the compass sensor is very small, being a traditional one it measures the angle between the direction and the North. This angle is transmitted to the microprocessor due to the potential difference. The microprocessor interprets the incoming signal and acts accordingly. Thus, if CanSat intended to achieve the goal without using a GPS receiver, this sensor will play a critical role.
Our global goal is to create the Ukrainian segment of the international CanSat project based on its line of launch vehicles (similar to ARLISS - A Rocket Launch for International Students Satellites), NASA Student Launch, The European CanSat Competition).
A mini-camera can be included in CanSat to take a picture of the Earth's surface during CanSat launch. Considering that CanSat cannot control the camera when the satellite is in the air, the microporcessor must be included in the CanSat structure for camera managing.
Would be appreciated:
- Possible use of sub-orbital rockets
- Scientific or academic projects on the launch vehicles payloads
- Projects of instruments and systems allowing to conduct measurements and/or scientific experiments during a sub-orbital flight
You can pitch projects related to automation of launch preparation and launch process. As well as flight monitoring systems, systems for adjustment of flight and/or descent trajectory of the launch vehicle or parts thereof.
Projects may be pitched with the original ideas and new functionalities, without restrictions on design properties.
