## 1 Introduction  
An effective way of measuring horizontal atmospheric winds is to observe the Doppler shift of atmospheric emission lines. In order to measure winds speeds within 5 m/s precision, the instrument should measure the position of Doppler shifted lines within 10\({}^{-5}\) nm or better. Space-borne measurements, which can provide global scale coverage, have become an important measurement means in many domains [1, 2]. Space-borne DASH wind instruments, such as the High-Resolution Doppler Imager (HARDI), TIMED Doppler Interferometer (TIDI), Wind Imaging Interferometer (WINDII), and Michelson Interferometer for Global High-resolution Thermospheric Imaging (MIGHTI) [3, 4, 5, 6, 7], have measured the global distribution of upper atmospheric (60-300 km) winds. As a new wind interferometer concept proposed in recent years, DASH consists of a Michelson interferometer with the return mirrors replaced by fixed, titled diffraction gratings. Therefore, it measures many more path difference samples within a larger path difference interval without moving parts [8, 9]. This feature enables the interferometer to measure multiple atmospheric lines and to simultaneously monitor an on-board calibration line to track instrumental drifts. Therefore, it has become a focus of active research. However, the mounting for the interferometer, which is a key part of the space-borne DASH wind instrument, should meet the mechanical conditions of being space-borne and minimize the impact of ambient temperature. Therefore, the design of a stable support structure with reduced heat conduction has become an urgent issue. To achieve highly stable rugged support for the interferometer, many researchers at home and abroad have investigated the support structure of the interferometer. [PERSON] researched stable and rugged etalons, realizing a micro-stress mounting with low heat conduction for a Fabry-Perot interferometer (FPI) using six epoxy pads [10]. However, the construction of the FPI is limited to mounting an interferometer with a rotationally symmetric structure. The method for a mesh bonding surface micro-stress mounting of the Sagnac interferometer prism has been proposed, which could meet the requirements of the launch environment [11]. However, the bonding area is too large, and the thermal insulation installation requirements could not be met. An approach to assembling split infrared Spatial Heterodyne Spectroscopy (SHS) using three loaded plungers that provide well-controlled compression forces to the optical components and precision spacers was proposed by [PERSON] [12]. [PERSON] designed a semi-kinematic clamping structure of three straight columns connecting the upper and lower plates, adding an interferometer vacuum \"housing,\" preferential thermal path, foam, and multi-layer insulation (MLI), which could be used to reduce the impact of ambient temperature. This could realize thermally stable mounting for a common path DASH interferometer [13]. Moreover, [PERSON] designed a micro-stress support structure with low heat conduction for the space-borne non-common path DASH interferometer. The interferometer (weighing 0.274 kg) was clamped using a combination of four bonding surfaces (the diameter of each bonding area was 10 mm) on a base made of Invar, which is a low thermal expansion metal, and four-pad elastic compression [14]. This method realized stable mounting for the DASH interferometer by improving its natural frequency (the lowest natural frequency is 1947.15 Hz). The spring constant was proportional to the natural frequency; therefore, as the dimensions of the DASH interferometer increased (because of the spectral resolution being improved), the most effective method of achieving stable support for the interferometer was through increasing the bonding area and improving the rigidity performance of the assembly, thereby minimizing the shear stress of the gluing surface. This increases the bonding area, which contrasts with the principle of adiabatic mounting and decreasing heat transfer.