A Tether Swing Suppression Method Utilizing the Maneuvering of a Towed Aircraft in a Towed Orbit Change
A technology of aircraft and tethers, which is applied in the direction of attitude control, etc., can solve the problems of target star attitude stability conflicts, tethers cannot be quickly released, etc., to avoid the problem of quick release, avoid tether tension conflicts, and avoid quick release effects
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[0033] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:
[0034] In order to achieve the above object, the technical solution adopted in the present invention comprises the following steps:
[0035] Step 1: Establish a dynamic model of orbit change by tether dragging
[0036] Assumptions: 1. Since the tether is always in a tight state during the thrust orbit change section, the elasticity and flexibility of the tether are ignored;
[0037] 2. Since the out-of-plane swing and in-plane swing of the tether can be decoupled, the out-of-plane swing of the tether is ignored
[0038] 3. Ignore the volume of the towing vehicle and the target star, and assume that the dragging orbit change is an in-plane orbit change
[0039] The schematic diagram of dragging the track and the definition of the coordinate system are attached figure 1 shown. 1 is the towed aircraft, 2 is the space tether, 3 is the target star, 4 is the earth,...
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