Abstract
The paper studies the issues of design and structural layout of ammoniac corrective engine units (CEU) with electrothermal micromotors (ETMM) for manoeuvrable small space vehicles (SSV) using all-purpose approach. CEU and ETMM structural schemes are defined, adaptation questions of CEU to SSV are addressed, CEU mass analysis is carried out, and experimental study’s findings are given.
Highlights
The modern stage of cosmic space exploration is characterized by large-scale development and use of small space vehicles (SSV) of 30-400 kg for solving scientific and application problems launched by group and additional ways (Sadovnichy e.t al., 2011; Sadovnichy et al, 2007; Blinov et al, 2010; Blinov et al, 2010; Blinov et al, 2010)
By their structural and methodical construction ammoniac corrective engine units (CEU) are designed for low-orbiting manoeuvrable SSV (MSSV) of various applications with the use of all-purpose design methods and dimensions & mass method to calculate mass characteristics of CEU and their adaptation means to MSSV
The design method of CEU and electrothermal micromotor (ETMM) with convertible and extensible structure was used for ammoniac CEU construction with a fuel reserve of 2.7 kg, 4.0 kg, and 0.4 kg (Figure 11-13)
Summary
The modern stage of cosmic space exploration is characterized by large-scale development and use of SSV of 30-400 kg for solving scientific and application problems launched by group and additional ways (Sadovnichy e.t al., 2011; Sadovnichy et al, 2007; Blinov et al, 2010; Blinov et al, 2010; Blinov et al, 2010). Electric CEU used for the orbital manoeuvring of “larger” space devices are marked by the greater value of thrust (for example, stationary plasma engines - up to 20W/MN and more), that makes them not applicable for SSV with limited electrical power supply. Developed ammoniac CEU with electrothermal micromotor (ETMM) thrust 30 MN is characterized by thrust value to 4W/MN and is successfully used in many SSV
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