Butler Parachute Systems, Inc. has designed, tested and manufactured a wide variety of Deep Stall Recovery Systems and Spin Recovery Systems.  These systems include redundant release mechanisms, latch/unlatch mechanisms, rocket deployment, and either a mechanical or electrical interface.  Below are some examples:

SPINBRO1.BMP (391174 bytes)

The photo above shows the stinger and cockpit controls for a spin recovery system that was designed for the AASI JetCruzer 450 turboprop pusher. The system was delivered in July, 1993 and utilizes a completely mechanical interface with redundant pyrotechnic line cutters for release. It also provides a latch/unlatch mechanism to allow the parachute to separate without loading the aircraft if the chute is somehow inadvertently deployed. The first part of the control lever travel inserts the latch pin and the second half of the travel activates the rockets. The small T-handles activate independent releases. The design load of this system is 5,000# in any direction at the fairlead.

Note that the spin recovery and deep stall recovery parachutes are very similar. However, a deep stall system will generally have a smaller diameter chute but a much longer riser than the spin recovery system.


SPINBRO2.BMP (277138 bytes)

The photo above shows the control panel, battery pack and forward end of the stinger for an electrical interface system. The latch/unlatch mechanism is driven by a small electro-mechanical actuator that moves a pin through a loop in the load line. After the latch pin seats, power is applied to the large round switches and thus is available to fire the rocket.  Power is not available to activate the release mechanism. If the rocket is fired, a time-delay relay applies power to the square release switches after a four-second (selectable) delay. The release mechanism contains redundant parallel electro-pyrotechnic line cutters. The design load of this system is 3,000# applied in any direction at the fairlead.


The photo below shows an overall view of the stinger. Note that the system is inverted in this view. The rocket motor will be on the top when the stinger is mounted to the aircraft. This system was designed for the Swearingen SJ-30 business jet. Delivered in September, 1992.

SPINBRO3.BMP (1117798 bytes)


SPIN-4.TIF (441448 bytes)

The photo above shows a deep stall recovery system as installed on the Swearingen SJ-30 Aircraft. Note that the tail is highly swept and requires a rather long stinger to ensure that the parachute riser does not contact the structure. The total length of the stinger is approximately 48".


SPIN-5.TIF (461347 bytes)

The photo above shows a spin recovery system installed on the JetCruzer 450 aircraft. Note that the ventral fin has been reinforced and braced with struts by the aircraft manufacturer. Control cables can be seen running forward along the bottom of the aircraft. The total length of the stinger is approximately 40".

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