Research On Strapdown Guidance Method For Micro - Aircraft

Miniature flight vehicle which refers to small scale, can be used for special missionand be capable of autonomous flight, including miniature unmannded aerial vehicle(MUAV), small guided munitions, agile satellites, etc. These miniature flight vehicle arewidely used in military and civilian fields.Due to the constraints of miniature flight vehicle self space, besides the strapdowninertial measurement unit, a body-fixed strapdown seeker in adopted instead of traditonalstabilized seeker system, which thus formulates a strapdown guidance framework toguidance and control the miniature flight vehicle. This thesis takes small guided strapdownminiature flight vehicle as research object. The aerodynamic features is analyzed firstlyfrom the aerodynamic layout. A novel requirement method for inertial guidanceinformation is derived, then a novel guidance law considering strapdown guidanceconstraints is derived and analyzed. The main contents are as follows:Firstly, a canard miniature flight vehicle is designed. Then, adjust the massdistribution to meet the center of pressure index. And combines with aerodynamic datacomputed using computational fluid dynamics (CFD) approach evaluate the designrationality.Then, a novel acquirement for inertial guidance information approach is derived usingthe equivalent coordinate transformation that the angular rate of rotation in groundcoordinate and in light-of-sight coordinate is equal. then the decoupling equations forlight-of-sight (LOS) angle and angular rate are presented.Meanwhile, analyzes the forces and moments of the proposed vehicle model, gets themass center and rotation of the center kinematics and dynamics equations, sets up its6degree-of-freedom (6DOF) kinematics and dynamics model, and builds this6DOF modelin Matlab/simulink for further analysis.Next, considering the field-of-view (FOV) and impact angle constraints, a two boostguidance solution is proposed, thus a proportional/sliding-mode guidance law and animproved biased pursuit guidance law are derived respectively. Finally, an engagementcase is simulated and validated the proposed model and methods.