Thruster assembly
A thruster assembly, including a switch connected to a power source, a thruster, a propellant tank for storing and pressurising a propellant, and a propellant channel for guiding the propellant to the thruster. The thruster includes a space for receiving the propellant from the propellant channel, an electrically controlled heating element, a thruster body having a first thermal expansion coefficient, a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body, and a nozzle, wherein the valve component includes a sealing surface closing the nozzle in a first temperature, and the electrically controlled heating element in response to actuation of the switch heats said thruster to a second temperature where the thermal expansion of the thruster opens the nozzle.
1. A thruster assembly, comprising:
a switch connected to a power source;
a thruster;
a propellant tank configured to store and pressurize a propellant; and
a propellant channel configured to guide the propellant to the thruster,
wherein the thruster comprises:
a space configured to receive the propellant from the propellant channel;
an electrically controlled heating element;
a thruster body having a first thermal expansion coefficient; and
a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body,
wherein the thruster assembly further comprises a converging-diverging nozzle comprising a propelling nozzle bore, wherein the converging-diverging nozzle is manufactured at the same time as and formed as one integral part with the thruster body,
wherein the valve component comprises a sealing surface closing the converging-diverging nozzle in a first temperature, wherein a front end of the valve component further comprises channels for propellant flow and the sealing surface is located at an opposite end, and
wherein the electrically controlled heating element in response to actuation of the switch is configured to heat said thruster to a second temperature where the thermal expansion of the thruster opens the converging-diverging nozzle.
2. The thruster assembly according to claim 1 , wherein one end of the valve component is in fixed connection with the thruster body.
3. The thruster assembly according to claim 1 , wherein the valve component is a capsule comprising a cylindrical section.
4. The thruster assembly according to claim 1 , wherein the thruster body has a higher thermal expansion coefficient than the valve component.
5. The thruster assembly according to claim 1 , wherein the thruster body comprises a laminar structure with laminated ceramics or MEMS.
6. The thruster assembly according to claim 1 , wherein the sealing surface is a surface of the valve component contacting the thruster body, or a surface of the valve component contacting the propellant channel.
7. The thruster assembly according to claim 1 , wherein the thruster body is surrounded by a sleeve.
8. The thruster assembly according to claim 1 , wherein the assembly further comprises a main valve for controlling propellant flow to the thruster.
9. The thruster assembly according to claim 1 , wherein the electrically controlled heating element comprises a resistive wire coiled around the thruster body or situated inside the thruster body.
10. The thruster assembly according to claim 1 , wherein the thruster is less than 5 mm long.
11. A thruster assembly, comprising:
a switch connected to a power source;
a thruster;
a propellant tank configured to store and pressurize a propellant; and
a propellant channel configured to guide the propellant to the thruster,
wherein the thruster comprises:
a space configured to receive the propellant from the propellant channel;
an electrically controlled heating element;
a thruster body having a first thermal expansion coefficient; and
a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body,
wherein the thruster assembly further comprises a converging-diverging nozzle manufactured to a same part with the thruster body and comprising a propelling nozzle bore,
wherein the valve component comprises a sealing surface closing the converging-diverging nozzle in a first temperature,
wherein the electrically controlled heating element in response to actuation of the switch is configured to heat said thruster to a second temperature where the thermal expansion of the thruster opens the converging-diverging nozzle,
wherein the thruster body comprises a laminar structure with laminated ceramics or MEMS, and
wherein the valve component is a valve strip comprising at least one aperture.
12. The thruster assembly according to claim 11 , wherein the valve strip has a higher thermal expansion coefficient than the thruster body, and both ends of the valve strip are in fixed connection with the thruster body such that when heated to the second temperature, the valve strip is configured to bend inward because of thermal expansion.
13. A thruster assembly, comprising:
a switch connected to a power source;
a thruster;
a propellant tank configured to store and pressurize a propellant; and
a propellant channel configured to guide the propellant to the thruster,
wherein the thruster comprises:
a space configured to receive the propellant from the propellant channel;
an electrically controlled heating element;
a thruster body having a first thermal expansion coefficient; and
a valve component having a second thermal expansion coefficient, which is different than the first thermal expansion coefficient, inside the thruster body,
wherein the thruster assembly further comprises a converging-diverging nozzle manufactured to a same part with the thruster body and comprising a propelling nozzle bore,
wherein the valve component comprises a sealing surface closing the converging-diverging nozzle in a first temperature,
wherein the electrically controlled heating element in response to actuation of the switch is configured to heat said thruster to a second temperature where the thermal expansion of the thruster opens the converging-diverging nozzle,
wherein the thruster body comprises a laminar structure with laminated ceramics or MEMS, and
wherein the laminar structure allows the propellant channel to be manufactured to the same part with the thruster body.