Abstract:
An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. A predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the system&#39;s impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute. If the system reaches a position substantially above target area prior to the parachute transition altitude the flight computer controls the system into a spiral dive or other rapid altitude dropping maneuver until the transition altitude is reached. Once transitioned to the landing parachute the system descends for a brief period unguided under the landing parachute until touchdown.

Description:
This application claims priority to U.S. Provisional Application Ser. No. 60/341,006 filed Dec. 7, 2001. 

   BACKGROUND OF THE INVENTION 
   1. Field of the Invention 
   The invention relates generally to unmanned parachutes for cargo drops. More particularly, it relates to a control system and method for targeted landing of cargo using controllable parachutes. 
   2. Discussion of Related Art 
   Parachutes have evolved over the years into highly sophisticated systems, and often include features that improve the safety, maneuverability, and overall reliability of the parachutes. Initially, parachutes included a round canopy. A skydiver was connected to the canopy via a harness/container to suspension lines disposed around the periphery of the canopy. Such parachutes severely lacked control. The user was driven about by winds without any mechanism for altering direction. Furthermore, such parachutes had a single descent rate based upon the size of the canopy and the weight of the parachutist. 
   In the mid-1960&#39;s the parasol canopy was invented. Since then, variations of the parasol canopy have replaced round canopies for most applications, particularly for aeronautics and the sport industry. The parasol canopy, also known as gliding or ram air parachute, is formed of two layers of material—a top skin and a bottom skin. The skins may have different shapes but are commonly rectangular or elliptical. The two layers are separated by vertical ribs to form cells. The top and bottom skins are separated at the lower front of the canopy to form inlets. During descent, air enters the cells of the canopy through the inlets. The vertical ribs are shaped to maintain the canopy in the form of an airfoil when filled with air. Suspension lines are attached along at least some of the ribs to maintain the orientation of the canopy relative to the pilot. The canopy of the ram air parachute functions as a wing to provide lift and forward motion. Guidelines operated by the user allow deformation of the canopy to control direction and speed. Ram air parachutes have a high degree of lift and maneuverability. 
   Despite the increased lift from a ram air parachute, round canopies are still used for cargo drops. However, as tile weight of cargo increases, the size of the canopy must increase to obtain an appropriate descent rate. Reasonable sizes of round parachutes greatly limit the amount of cargo which can be dropped. Therefore, a need exists for a parachute system which can carry additional cargo weight. Additionally, accurate placement of cargo drops from high altitude with round parachutes is impossible. Adjustments can be made for prevailing winds at various altitudes but the cargo is likely to drift off course due to variations. Furthermore, improvements in surface-to-air missiles requires higher altitude drops in order to protect aircraft. In military use, round parachutes are generally used from an altitude around one thousand (1000) feet to ensure accurate placement. However, new, inexpensive, hand held surface-to-air missiles can put in jeopardy airplanes up to twenty-five thousand (25,000) feet in altitude. Current military technique is to use a special forces soldier to pilot both parachute and cargo to the ground from altitudes of twenty-five to thirty-five thousand (25-35,000) feet. This limits cargo to six hundred fifty (650) pounds, as it must be attached to a human. Therefore, a need exists for an autonomous guided parachute system for cargo which can operate at high altitudes as well as scale to heavier cargo weights. 
   Autonomous ram air parachutes systems have been developed for cargo drops but suffer from several problems that have prevented them from being generally adopted into military techniques. Prior art guided systems include a harness/container system, a single parachute, flight computer, guidance and navigation control software, a GPS, and electric motor actuators. The flight computer must calculate a flight path and glide the system from the drop point all the way to the ground target. In order for the flight computer to accomplish this, the parachute used must b of low wing loading to ensure docile and slow flight. Such lightly loaded parachutes fly with free flight forward speeds of approximately twenty-five (25) miles per hour or slower. Typical wing loadings are around one (1) pound per square foot of wing area. Such slow systems present several problems, first they are greatly effected by winds aloft. At high altitudes winds are quite strong and can be several times the forward speed of the wing. This necessitates the need to map out specific winds at each altitude by dropping radio frequency transmitting sensors units. The collected data must be analyzed and imported to the autonomous systems flight computer to enable a drop position to be calculated and then a flight path. Another problem is the systems time in the air with such light wing loaded parachutes is quite long, increasing their vulnerability and delivery time. Another problem is that higher weight cargo requires proportionally larger wings which become completely impractical far below the maximum weight desired for military use. Therefore, a need exists for an improved autonomous guided parachute system which can provide accurate targeting control from high altitudes, while flying at higher speeds to reduce or negate wind effects, and be able to scale to the ultimate high weight cargo required by militaries. 
   Typically, static line deployment is used for cargo drops. A line from the harness/container is attached to the cargo hold of the delivery aircraft. The cargo is then pushed out of the hold. The line causes the parachute to be deployed, with or without the use of a drogue. However, air currents around the delivery aircraft can interfere with proper deployment of a gliding parachute using a static line. Also, the cargo is not typically falling stable upon immediate exit which can cause difficulties during opening of the gliding parachute. In order to slightly delay opening, existing systems utilize a double-bag deployment system. However, the double-bag system is complicated and expensive to construct as well as complicated to pack. Therefore, a need exists for an improved system for delaying the deployment of a gliding parachute. 
   Additionally prior art systems use electric motor actuators and batteries. Typically the motors are overly complicated DC servo drive motors. At high altitudes temperatures are very low. Such systems suffer from the requirement for very large, low power density cold weather batteries. To meet military demand high altitude systems must operate up to −65 F. and existing systems do not function at such temperatures. As such there exists a need for lighter simpler actuators and power system that are unaffected by extreme temperatures. 
   SUMMARY OF THE INVENTION 
   The deficiencies of the prior art are substantially overcome by the guided, multi-stage parachute system of the present invention. According to an aspect of the invention, the parachute system includes two different kinds of parachutes for use during different phases of the cargo drop process. The requirements of guidance and soft landing have been separated. A fast, high performance ram air parachute is used to guide the cargo in substantially a straight line from exit point to substantially overhead of the target location and then rapidly spiral dive down to lose altitude. The system transitions to a larger unguided landing parachute prior to impact. The multi-stage parachute system utilizes the advantages of different kinds of parachutes to achieve greater control and improved performance. Since the gliding parachute is not used for landing of the cargo, it can be designed for extremely high speed and high wing load capabilities. These features allow higher reliability in high altitude drops by limiting the effect of winds and greatly reduce time aloft. Since the landing parachute is not used to control location, it can be designed for a soft landing of large cargos. Also, it can be deployed at the lowest possible altitudes to minimize unguided drift. 
   According to another aspect of the invention, a novel flight controller provides control for the parachute system. The flight controller determines the position and altitude of the parachute system. The flight controller operates the steering controls of the guidance parachute. Once within a specified radius of overhead the target location, the flight controller further operates steering controls of the guidance parachute for a rapid, controlled descent overhead the target location until a predetermined minimum altitude is reached. Once the predetermined altitude is reached, the flight controller releases the guidance parachute to transition to the landing parachute. 
   According to another aspect of the invention, static line drogue deployment of the parachute system is performed with a time delay on releasing the drogue to extract and deploy the main. The time delay may be a mechanical delay or may be controlled by the flight controller. The time delay allows the system to stabilize under drogue before deployment of the main guidance wing. 
   According to other aspects of the invention, the release of the guidance parachute operates to static line deploy the landing parachute. According to another aspect of the invention, a two stage harness is used to attach the parachute system to the cargo. During transport and release of the cargo from the airplane, the parachute system is closely attached to the cargo. Following deployment of the drogue chute, the parachute system is spaced further away from the cargo. 
   According to another aspect of the invention, the parachute system of the invention is used with explosive cargo to create a “smart” bomb. The gliding parachute and flight controller are used to steer the explosive cargo over a desired target location. The landing parachute may be used to land the explosive cargo when it is over the target location. Alternatively, according to another aspect of the invention, a landing parachute is not used. The gliding parachute is used to fly the explosive cargo at high speed into the target or the flight controller detonates the explosive at a preset altitude over the target. 
   According to another aspect of the invention, a flight controller determines position of the parachute system using GPS signals and controls the guidance parachute to reach a desired destination. 
   According to another aspect of the invention, the flight controller logs position and control information and optional sensor data during flight. The flight controller includes a microprocessor and memory. During flight, in order to control the parachute, the flight controller determines the position and altitude of the parachute system. This information can be recorded at predetermined intervals. Information from the memory can be retrieved to analyze performance of the flight controller and the parachute system. 
   According to another aspect of the invention, the flight controller includes a transceiver, preferably a radio frequency transceiver. During flight, the transceiver is used to transmit position, altitude, orientation or other information to a base location. The base location may be located on the ground, in the deploying airplane, or other location. The information from the flight controller may be used to monitor operation of the system in real-time. Additionally, the transceiver may receive information from the base location. Such information may include manual override control of the system or change in target coordinates. 
   According to another aspect of the invention the steering and release actuators are pneumatic, being powered by compressed gas instead of battery power. Miniature carbon fiber high pressure compressed gas tanks can store far more power density than cold weather batteries and are unaffected by extreme cold. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
       FIG. 1  is a side view of a parachute system according to an embodiment of the present invention. 
       FIG. 2  is a top view of the parachute system of FIG.  1 . 
       FIG. 3  is a flow diagram for operation of a parachute system according to an embodiment of the present invention 
       FIGS. 4A-G  illustrate the sequence of operation of a parachute system according to an embodiment of the present invention. 
       FIG. 5  is a top view of a flight controller according to an embodiment of the present invention. 
       FIG. 6  is a block diagram of the components of the flight controller. 
   

   DETAILED DESCRIPTION 
   In order to provide improved performance for automatic control of cargo drops, the parachute system of the present invention includes multiple parachutes and a flight controller.  FIGS. 1 and 2  are respectively a side view and a top view of an embodiment of the parachute system  10  of the present invention when packed for deployment. The parachute system includes a drogue  20 , a high wing loaded, guidance parachute or wing  30 , and a landing parachute  40 . Preferably, the guidance parachute is a high wing loaded, high speed, steerable, ram air parachute. However, any controllable wing or parachute may be used. Preferably, the landing parachute is a larger parachute allowing slow unguided vertical descent. A flight controller  50  is disposed below the parachutes and operates to control deployment of the parachutes and steering of the guidance parachute. The parachutes  20 ,  30 ,  40  may be of any known design based upon the type of chute required for the specific operation. 
     FIG. 3  is a block diagram illustrating the operation of the parachute system  10  under control of the flight controller  50 . Illustrations relating to the sequence of operation of the parachute system  10  are illustrated in  FIGS. 4A-4G . As illustrated in  FIG. 4A , the parachute system  10  is attached closely to the cargo  70  to prevent movement in the cargo hold of the plane.  FIG. 4A  illustrates the cargo  40  as a barrel, but any other type of cargo container, including pallets, could be used. The orientation of the parachute system and the mechanisms for attachment to the cargo will depend upon the type of cargo being dropped. 
   To start the cargo drop process, illustrated in  FIG. 3 , the cargo and parachute system are deployed in a known manner from the delivery aircraft at step  110 . Preferably, a static line deployment is used. Upon deployment of the cargo and parachute system, the drogue  20  is deployed (step  120 ;  FIG. 4B ) preferably using a static line  21  (FIG.  1 ). Of course, other mechanisms could be used to deploy the drogue, including a controllable release operable from by the flight controller  50 . The drogue properly orients the cargo with the parachute system  10  on top and releases the tie downs  25 . 
   During the delivery flight and upon discharge of the cargo, the parachute system  10  is tightly retained against the cargo  70 . However, for improved flight, the cargo  70  is preferably suspended below and away from the parachute system  10  via a swivel. Thus, at step  130 , the drogue chute releases tie downs  25  between the parachute system  10  and the cargo  70 . Preferably, the parachute system is closely attached to the cargo using 3-ring releases. Cable  24  ( FIG. 4B ) from the drogue bridal to the 3-ring releases allows the cargo to separate from the parachute system upon deployment of the drogue. Following release of the tie downs  25 , the cargo  70  is attached to the parachute system  10  with a harness  71 . The harness  71  allows the cargo to hang from the parachute system  10 . Any type of harness  71  can be used to retain a proper orientation of the cargo below the parachute system  10 . Preferably, a swivel  72  is included in the harness  71  to allow for spurious movement of the cargo from winds during descent. The parachute system  10  of the present invention is not limited to any particular tie down  25  or harness  71 . Furthermore, the parachute system  10  could be directly attached to the cargo  70  with out the need for the separation in step  130 . 
   According to an embodiment of the present invention, at step  140 , an inventive hydraulic time delay is introduced for the drogue  20 . Tension on the drogue bridal is applied to a piston in hydraulic fluid. The piston has an orifice drilled through it to allow passage of fluid from one side of the piston to the other. As fluid is incompressible the flow can not go supersonic and the speed the piston can move is able to be fixed. The motion of the piston is transferred to a cable that initiates the guidance wing deployment at the end of its stroke. The purpose of the time delay is to ensure the system is in stable drogue fall before deploying the guidance parachute  30 . The delay may also be controlled by the flight controller via an actuator (not shown). Alternatively, a double bag system could be used for the guidance parachute instead of the drogue delay. 
   Following the drogue delay, the guidance parachute  30  is deployed (step  150 ; FIG.  4 D). As illustrated in  FIG. 2 , the guidance parachute is retained in a multiple flap container  31  prior to deployment. Following the delay, the release cable  23  is pulled which opens the bag  31 . According to an embodiment of the invention, the release cable  23  removes a pin from a string holding the flaps of the multiple flap container  31  closed. The string also retains riser extensions  65 ,  66 ,  67 ,  68  at the bridal  22 . The riser extensions  65 ,  66 ,  67 ,  68  are connected to the harness/container system  10  to carry the weight of the system and cargo and relieve stresses on the fabric of the harness/container system during use of the drogue. The drogue bridal  22  attached to the guidance parachute bag  30  causing it to be deployed when the container  31  is released. Alternatively, the release cable  23  could be operated by the flight controller  50 . 
   The guidance parachute  30  is preferably of a type having high wing load and high speed. According to an embodiment of the invention, the guidance parachute is preferably wing loaded in the range of five to twenty (5-20) pounds per square foot wing loading, and has forward flight speeds of forty to one hundred forty (40 to 140) miles per hour. An exception to such performance characteristics may to be when the system is used with extremely small payload, i.e., seventy-five (75) pounds. With small payloads, further reducing the size of the parachute becomes impractical. Lightweight systems may fly at lower wing loadings. Current systems of the invention have been tested from four and one half to ten (4.5-10) pounds per square foot loading. 
   The guidance parachute  30  is connected via four risers  61 ,  62 ,  63 ,  64  attached to the harness/container system  10 . The four risers  61 ,  62 ,  63 ,  64  extend from the suspension harness  71 , and preferably from the swivel  72  to the parachute system  10 . The webbing from the swivel are sewn to the sides of the container of the parachute system. Each riser includes a 3-ring release  61   a ,  62   a ,  63   a ,  64   a  between the container system and the guidance parachute. Before deployment of the guidance parachute, the risers  61 ,  62 ,  63 ,  64  extend into the multiple flap bag  31  through the corners. Upon deployment, the risers suspend the parachute system  10  and the cargo  70  from the guidance parachute  30 . 
   Brake lines  81 ,  82  are connected to the guidance parachute  30  for control. The brake lines  81 ,  82  are retained in sleeves  81   a ,  82   a  attached to the risers  61 ,  64 , and extend into the parachute system for attachment to the steering actuators. The steering actuators are operated by the flight controller  50  to steer the canopy  30  in a known manner. The steering actuators are preferably pneumatic and built as an integrated steering module possessing multiple functions. Pneumatically controlled stages can transverse linearly to pull either the left or right control line. The lines are each routed through a pneumatic guillotine cutter which allows the line connection to the actuator to be severed when transitioning from the guidance parachute to the landing parachute. Additionally, many ram air parachutes deploy best when the brake lines are partially pulled during deployment. The force required to hold the brake lines during deployment is typically many times the force required to actuate a turn once in flight. As such, so as not to over design the strength of the steering actuators, an additional pneumatic actuator is provided to pull a pin for each line. There is a loop on each brake line that can be set or trapped by the actuation prior to retracting the pin. The pin allows a very high holding force on the brake lines during deployment and then is retracted freeing the brake lines to be controlled by the steering actuators. 
   At step  160 , the flight controller adjusts the direction of the guidance parachute  30  using the brake lines  81 ,  82  to direct the cargo towards the desired target location. Operation of the flight controller  50  for steering the guidance parachute is discussed below. 
   Once the cargo  70  and parachute system  10  reaches an area approximately overhead of the desired target location, the guidance parachute is controlled to fly in a spiral dive or holding pattern (step  170 ; FIG.  4 E). Other holding patterns, such as a  FIG. 8  or flat spiral (slow altitude drop maneuver), could also be used. A spiral will initiate the fastest possible vertical decent. Tested systems with a wing load of four and one half (4.5) have shown a vertical decent rate in a spiral dive of 120 mph. The cargo  70  and parachute system  10  descends without significant variation from the target location. If the flight computer detects significant drift it will stop t,he spiral correct and reinitiate, if time permits once corrected and parachute system  10  reaches an area approximately overhead of the desired target location, the guidance parachute is controlled to fly in a spiral dive or holding pattern (step  170 ; FIG.  4 E). Other holding patterns, such as a  FIG. 8  or flat spiral (slow altitude drop maneuver), could also be used. A spiral will initiate the fastest possible vertical decent. Tested systems with a wing load of four and one half (4.5) have shown a vertical decent rate in a spiral dive of one hundred twenty (120) mph. The cargo  70  and parachute system  10  descends without significant variation from the target location. If the flight computer detects significant drift it will stop the spiral correct and reinitiate, if time permits once corrected. 
   Prior to the system spiraling into the ground, at a minimum altitude preset into the flight computer, actuators pull cables from the four 3-ring releases on the guidance parachute risers to release the guidance parachute  30 . At the same time the guillotine cutters sever the brake lines to the steering actuator. A line (not shown) connects at least one of the risers from guidance parachute  30  to a release on a multi flap container  41  containing the landing parachute. This line further attaches the guidance parachute  30  to the landing parachute  40  so its drag extracts and deploys the landing parachute. Additionally by remaining tethered, nothing is lost. The guidance parachute  30 , thus, operates as a drogue for the landing parachute  40 . The landing parachute, preferably a round canopy parachute, allows the cargo to slowly descend, landing unguided. The landing parachute should be released at a low enough altitude to prevent significant deviations from wind drift. Risers  42  for the landing parachute are sewn on the inside of the bag to the risers  61 ,  62 ,  63 ,  64  on the outside of the bag. Upon deployment of the landing parachute, the parachute system maintains the same orientation due to the consistent placement of the risers. 
   Militaries are content to use round parachutes from low altitudes, i.e., one thousand (1000) feet. Drift from such a low altitude is easy to correct and accuracy is high. This invention simply seeks to create a system to transport cargo from a high altitude plane out of harms way as rapidly as possible to a targeted low altitude for subsequent landing under a conventional round cargo parachute. 
     FIG. 5  is a top view of components of the flight controller according to an embodiment of the present invention.  FIG. 6  is a block diagram of the components of the flight controller. While specific components are illustrated and discussed herein, the flight controller may be designed in any manner to provide the desired functions and operations. Preferably, the flight controller  50  includes a microprocessor  200  and associated memory  250 . The instructions for operation of the microprocessor  200  are stored in the memory. They may be created and operated in any known computer programming language. The microprocessor  200  is programmed to provide the steps set forth in FIG.  3 . 
   Attached to or integrated with the microprocessor  200  are other devices to provide inputs to or outputs from the microprocessor  200  for operation of the parachute system. In particular, the flight controller  50  may include a Global Positioning Satellite (GPS) system receiver  210 , a barometric altimeter sensor  220 , inertial sensors  221 , a decent arming switch  222 , or other sensors  225 , integrated with the microprocessor  200  as a single unit. Alternatively, discrete sensors may be used to provide inputs to the microprocessor  200 . The microprocessor  200  uses information from the integrated or discrete sensors to determine the position of the parachute system  10 . The altitude is provided based on a three dimensional GPS fix using the GPS receiver  210 . However, an additional barometric pressure sensor  220  may be used for redundancy. Other sensors may include inertial navigation or gyros  221  for determining position in the event that GPS signals are lost or jammed. 
   The microprocessor  200  uses the information from the sensors to determine position and to control the parachute system  10 . The microprocessor  200  has outputs connected to electro pneumatic solenoids  240  for controlling pneumatic actuators  230 ,  241 ,  242 ,  243 . The pneumatic actuators are powered by a source of compressed gas  235 , preferably compressed nitrogen or dry air. Alternatively, electric motors could be used instead of the actuators. However, the use of pneumatic actuators with compressed gas is advantageous for the parachute system of the present invention. The extremely cold air at the high altitudes at which the parachute system is deployed would greatly drain a battery or other source of electric power. By using the pneumatic actuators, the electrical requirements of the system for operating the microprocessor  200  is very low and system weight is reduced. 
   The embodiment of the present invention uses two principal types of actuators: steering control actuators  240  and guidance wing release actuators  230 . Other actuators could be included to provide additional functionality. For example, the flight controller  50  could be used to deploy the drogue or to deploy the glide parachute. If the flight controller performs these functions, additional actuators and solenoids would be necessary. 
   The steering control actuators  241 ,  242 ,  243  operate the brake lines  81 ,  82  of the glide parachute  30  to direct the parachute system to the target location. Upon deployment of the guidance parachute  30 , the brake lines  81 ,  82  must be held in for proper inflation and stabilization. A pair of deployment actuators  242 ,  243  are used to hold the brake lines in. Loops in the brake lines  81 ,  82  are held by the deployment actuators  242 ,  243 . Once the guidance parachute is deployed and stabilized, the deployment actuators  242 ,  243  release the loops and the brake lines  81 ,  82  are positioned for normal operation. The brake lines  81 ,  82  are controlled by steering actuators  241 , which may include one actuator  241   a ,  241   b  for each line. The actuators  241  pull or release the brake lines to alter the direction of flight of the system. Upon release of the guidance parachute  30 , the brake lines also need to be released. Actuators  236 ,  237  are used for this purpose. Actuators  236 ,  237  are positioned around the brake lines  81 ,  82  at the entrance to the steering actuators  241 . Actuators  236 ,  237  operate guillotine cutters to cut the brake lines  81 ,  82  for release. Other combinations of actuators are possible for control of the brake lines. The steering actuators  241  may be used to hold in the brake lines during deployment rather than the deployment actuators. Other kinds of release mechanisms may also be used instead of the guillotine cutters. 
   Four release actuators  231 ,  232 ,  233 ,  234  are used to release the risers  61 ,  62 ,  63 ,  64  holding the glide parachute  30  to the parachute system  10 . Each of the release actuators  231 ,  232 ,  233 ,  234  is connected to one of the release cables  61   b ,  62   b ,  63   b ,  64   b  for the 3-ring releases on the risers. When the glide parachute is to be released, the microprocessor  200  operates the release actuators  231 ,  232 ,  233 ,  234  to pull the release cables  61   b ,  62   b ,  63   b ,  64   b . Alternative methods, including guillotine cutters could be used to release the risers  61 ,  62 ,  63 ,  64  under control of the microprocessor  200 . 
   The flight controller  50  may be powered and operated at any time during the deployment process depending upon when it is needed. According to an embodiment of the invention, the flight controller  50  is powered prior to deployment from the drop plane to allow a GPS fix to be obtained before dropping. Software ‘arming’ of the system is possible by detecting the vertical decent rate. However, a steeply diving airplane can falsely arm the system and then the units would begin steering and possible release actuators while the system is still in the cargo bay. A preferred method uses an arming switch that senses when the guidance parachute has left the container. This has been accomplished by use of a magnet sewn into the parachute bag and a magnetic reed switch connected to the flight computer. 
   Once the guidance parachute  30  is released, the microprocessor  200  operates to control the direction of flight. The GPS receiver  210  provides position information which is also used to determine orientation. The microprocessor  200  provides signals to the steering control actuators  241  attached to the brake lines  81 ,  82  of the guidance parachute  30  to steer the system. The target location is stored in memory  250 . The system determines the necessary changes in flight direction to move from the currently traveled vector to one that would intersect overhead of the target. Preferably, the system uses PID control algorithms to prevent oversteering when correcting the flight vector. Such oversteering results in a system that flys a sinewave or damped sinewave flight path instead of perfectly straight. 
   Once the target location has been reached, as determined by the microprocessor  200 , the microprocessor  200  actuates steering actuators  241  to initiate a sustained turn or spiral dive or other holding pattern. The cargo and parachute system continues to descend over the target location. Once a set altitude is reached, as stored in the memory  250 , as determined by the altimeter  220  or the GPS receiver  210 , the microprocessor  200  sends a signal to the guidance wing release actuators  230  to release the risers  61 ,  62 ,  63 ,  64  of the guidance parachute  30  and sever the brake lines, thus deploying the landing parachute. The system continues it descent using the landing parachute until touchdown. 
   The flight controller  50  needs to be programmed with the target location and altitude information for the landing parachute release. Input/output (I/O) ports are attached to the microprocessor  220  for the purpose of inputting the necessary information. The I/O ports may be of any known type, and may include a display, keyboard, mouse, disk or other memory drive, or a port for connection to a computer or other storage device.  FIG. 6  illustrates a wireless modem  260  and antenna  261  as an I/O port for inputting information. Additionally, if appropriate, the drogue delay time may also be entered into the system using the I/O ports. 
   When the glide ratio of the system is known, the flight computer may be connected to an indicator light to show when the drop plane is within the cone of acceptability to drop the cargo and have it fly to its intended target. This aids drop personnel in the cargo plane. 
   Since the microprocessor  200  of the flight controller  50  is receiving information about the flight, such as position and altitude, the information can be stored in the memory  250 . A timer (not shown) can be used to provide time based information in the memory  250 . Upon completion of the drop, the stored information from the memory  250  can be retrieved through the I/O ports for analysis and review. Other sensors could also be included in the flight controller  50  for determining and recording data for analysis. For example, sensors could be used to determine G-forces, stress and strain placed on various components of the parachute and the cargo. These sensors can be connected to the microprocessor  200  to store the sensed information in the memory. 
   The flight controller  50  may also include a transceiver for wireless communication with the flight controller. The wireless modem  260  and antenna  261  illustrated in  FIG. 6  can also function as a transceiver. The transceiver is preferably RF, but can include an infrared or other transmission medium. The transceiver can be used to output position, altitude or other information, in real time to a base station. The base station may be in the delivery aircraft, at the target location, or some other control position. The information transferred from the flight controller  50  to the base station can be used to monitor flight and operation of the system. Additionally, the transceiver can be used to receive information from the base station. The base station could transfer information changing any of the flight parameters, such as the target location. Alternatively, direction information could be transmitted to the flight controller for the steering controller  240 . Thus, the parachute system could be remote controlled by an operator at the base station, instead of automatic operation. In a preferred embodiment telemetry data sent to the base station is graphically displayed on a screen to allow remote control without visual contact with the parachute system. 
   A GPS repeater provides the GPS signals within the cargo area of the aircraft. Thus, the GPS receiver of the flight controller can acquire a position lock prior to being dropped. The flight controller must be powered on several minutes before drop to allow a valid ephemeris to be downloaded which can take up to four (4) minutes. If they are then shut off, the software directs them to look for GPS satellites as if they were in the same position from time of power off. With the inventive system, it has been found that up to two (2) hours ‘black out’ period results in a reacquisition of position lock in forty (40) ms to eight (8) sec, after two (2) hours extending out to four (4) hours the time lengthens to its maximum of up to four (4) minutes. 
   A GPS repeater provides the GPS signals within the cargo area of the aircraft. Thus, the GPS receiver of the flight controller can acquire a position lock prior to being dropped. The flight controller must be powered on several minutes before drop to allow a valid 
     FIG. 3  illustrates the steps for operation of the flight controller after launch of cargo and parachute system from the delivery aircraft. The flight controller would also include a program for operation in a pre-launch mode to prepare for launch. The pre-launch mode include the steps of uploading target coordinates through the I/O ports and downloading a valid ephemeris for the drop location to the GPS receiver. Target coordinates on the inventive system may be uploaded by an RS232 or other connection from a laptop or dedicated handheld terminal, or simply by inserting a memory chip with the data into the flight computer, i.e. a compact flash card is uploaded with target data from the laptop software and then inserted into the flight computer. The ephemeris is automatically acquired by the GPS. 
   In another embodiment, the parachute system of tile present invention is used to convert dumb bomb to guided ‘smart’ bombs. Militaries have been converting inexpensive ‘dumb’ bombs into more effective guided weapons by a bolt on tail kit that includes a guidance computer/sensors/software and actuators for piloting the tail fins of the bomb, i.e., JDAN/conversion. These devices have received extensive use in the Gulf War and in Afghanistan. Cost wise they are very desirable, but performance wise they have certain shortcomings. The bombs typically weigh from five hundred to two thousand (500-2000) pounds. The tail fins are an extremely small wing surface for guiding such a heavy weight; as such, they are not capable of much course correction or significant glides. They suffer from accuracy and standoff shortcomings. A parachute system of the present invention attached to a dumb bomb, typically at the tail, to create a bomb guided by a high performance guidance parachute overcomes the problems of limited standoff and accuracy while remaining economically competitive. The coordinates of the desired target are loaded into the system. Since the bomb is intended to explode at impact, the landing parachute can be eliminated. Soft landing required for cargo is not required for bombs. Thus, step  180  in  FIG. 3  can be eliminated alloying the system to fly under the high speed, high wing load guidance wing until impact with the target or triggered to detonate at a predetermined distance above the target. 
   While the present inventions have been described with a certain degree of particularity, it is obvious from the foregoing detailed description that one skilled in the art may make one or more modifications which are suggested by the above descriptions of the novel embodiments.