Design of a Payload Spin Stabilization System for an All-Rotating Aerial Vehicle

This paper details the electrical and mechanical design of a de-spin mechanism for the payload of an all-rotating aerial vehicle. The system is designed to be compatible with the Aeroseed aircraft developed by Aerospace Corporation. The system consists of a motor housing and a de-spun payload plate. The payload plate serves as a mounting surface for the desired de-spun payload, an IMU, an Arduino Nano, and a SD card module. The Arduino receives rotational velocity readings of the payload plate from the IMU and calculates the necessary spin rate to stabilize the rotation. This spin rate is sent through a slip ring to the motor and ESC enclosed within the motor housing, which implement the commands. The electronics on the payload plate are protected by a thin shroud that extends down from the motor housing. A slider mechanism with two degrees of translational freedom serves as the interface between the system and the aircraft and allows for the alignment of their respective centers of rotation. The final design has a total mass of 589.67 g and a height of 109.1 mm.

Influence of Quiet Spike on Supersonic Transport for Low Boom Effect

One of the biggest technical challenges of supersonic flight is the mitigation of sonic boom. To deal with this problem, the Gulfstream Aerospace Corporation came up with the spike concept, and it showed to be efficient. However, there also remain several problems, the first one is that installing the spike makes it harder to balance for supersonic transport and the another one is that the movement equipment is complex. In this paper, a new concept by replacing the multi-stage of the normal spike with smooth transistion cones is proposed. The concept simultaneously uses the CFD solver HUNS3D based on the Reynolds average (RANS) equation and the far-field FL-BOOM sound explosion propagation program based on Thomas waveform parameter method. The effectiveness of the present scheme to suppress supersonic aircraft sound explosion is verified according to the concept. It is proved that the increased length is good for low blast and the main factor affecting the blast reduction effect of multistage mute cone is length rather than series by the analysis. The results have important reference value for the silent cone design of supersonic aircraft.