Retrofit digital electronics unit for a tube-launched missile

• US 5,123,610 A
• Filed: 07/21/1989
• Issued: 06/23/1992
• Est. Priority Date: 07/21/1989
• Status: Expired due to Term

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Oaks, Richard W.
• Primary Examiner(s): Steinberger, Brian S.
• Application Number:
  US07/384,229
• Time in Patent Office: 1,068 Days
• Field of Search: 244/3.1, 244/3.12, 244/3.13, 244/3.14, 244/3.21, 244/3.11
• US Class Current: 244/3.12
• CPC Class Codes: F41G 7/301 Details
• CPC Class Codes: F41G 7/32 for wire-guided missiles
• CPC Class Codes: G05D 1/107 specially adapted for missiles

Abstract

A retrofit digital electronics unit replaces the analog electronics unit of a tube-launched optically-tracked wire-guided missile. The retrofit digital electronics unit is smaller in size permitting the warhead of the missile to be enlarged. Additionally, the retrofit digital electronics unit is more susceptible to modification through simple changes in software.

Claims

1. A hybrid analog/digital electronics control unit for replacing an analog electronics unit in a tube-launched missile comprising:

a) positional status means (10) having,

1) a roll conversion means (10a) for converting a signal from the roll gyro (17) to a roll status signal, and,

2) a yaw conversion means (10b) for converting a signal from the yaw gyro (18) to a yaw status signal;

b) directional means (11) being responsive to signals from an operator and for generating a directional pitch signal and a directional yaw signal therefrom;

c) said positional status means and said directional means being analog; and

,

d) digital control means (12) being responsive to the yaw status signal, the roll status signal, the directional yaw signal, and the directional pitch signal, and for generating therefrom a primary yaw control signal, a secondary yaw control signal, a primary pitch control signal, and a secondary pitch control signal.

2. The digital electronics unit according to claim 1 further comprising:

a) means for amplifying (13a) said primary yaw control signal;

b) means for amplifying (13b) said secondary yaw control signal;

c) means for amplifying (13c) said primary pitch control signal; and

,

d) means for amplifying (13d) said secondary pitch control signal.

3. The digital electronics unit according to claim 2 wherein said digital control means includes means for generating a first motion signal which initiates generation of the primary yaw control signal, the secondary yaw control signal, the primary pitch control signal, and the secondary pitch control signal.

4. The digital electronics control unit according to claim 1 further comprising:

a) means for amplifying (13a) said primary yaw control signal;

b) means for amplifying (13b) said secondary yaw control signal;

c) means for amplifying (13c) said primary pitch control signal; and

,

d) means for amplifying (13d) said secondary pitch control signal.

5. A missile being guidable by operator generated signals comprising:

a) a body portion (70) having,

1) a first pitch control surface (73),

2) a second pitch control surface,

3) a first yaw control surface, and,

4) a second yaw control surface;

b) a flight motor (74) located within said body portion for propelling said body portion;

c) a gyro system (80) mounted in said body portion and having,

1) a roll gyro (17) generating a roll gyro signal, and,

2) a yaw gyro (18) generating a yaw gyro signal; and

,

d) a communication link being a continuous physical connection (71a) between an operator and the missile, for communicating said operator generated signals;

e) an electronics control unit (81) having,

1) positional determination means (10) having,

a) a roll conversion means (10a) for converting the roll gyro signal to a roll status signal, and,

b) a yaw conversion means (10b) for converting the yaw gyro signal to a yaw status signal,

2) directional means (11) being responsive to the operator generated signals received via said communication link, for generating therefrom a directional pitch signal and a directional yaw signal, and,

3) digital control means (12) being responsive to the yaw status signal, the roll status signal, the directional yaw signal, and the directional pitch signal, for generating therefrom a primary yaw control signal, a secondary yaw control signal, a primary pitch control signal, and a secondary pitch control signal,

4) amplification means (13) having,

a) means for amplifying (13a) said primary yaw control signal to an amplified primary yaw control signal,

b) means for amplifying (13b) said secondary yaw control signal to an amplified secondary yaw control signal,

c) means for amplifying (13c) said primary pitch control signal to an amplified primary pitch control signal, and,

d) means for amplifying (13d) said secondary pitch control signal to an amplified secondary pitch control signal; and

,

f) means for manipulating the control surfaces having,

1) a first actuator (19a) being responsive to said amplified primary yaw signal for physical movement of said first yaw control surface,

2) a second actuator (19b) being responsive to said amplified primary pitch signal for physical movement of said first pitch control surface,

3) a third actuator (19c) being responsive to said amplified secondary yaw signal for physical movement of said second yaw control surface, and,

4) a fourth actuator (19d) being responsive to said amplified secondary pitch signal for physical movement of said second pitch control surface.

6. The missile according to claim 5 wherein said digital control means includes means for generating a first motion signal which iniitates generation of the primary yaw control signal, the secondary yaw control signal, the primary pitch control signal, and the secondary pitch control signal.

7. An enhanced missile system comprising:

A) an operator input device (16) for generating operator generated signals; and

,

B) a missile having,

1) a body portion (70) having,

a) a first pitch control surface (73),

b) a second pitch control surface,

c) a first yaw control surface, and,

d) a second yaw control surface,

2) a flight motor (74) located within said body portion and for propelling said body portion,

3) a gyro system (80) mounted in said body portion and having,

a) a roll gyro (17) generating a roll gyro signal, and,

b) a yaw gyro (18) generating a yaw gyro signal;

4) a communication link (71a) being a continuous physical connection between the operator input device and the missile for communicating said operator generated signals to the missile,

5) an electronics control unit (81) having,

a) positional status determination means (10) having,

1) a roll conversion means (10a) for converting the roll gyro signal to a roll status signal, and,

2) a yaw conversion means (10b) for converting the yaw gyro signal to a yaw status signal,

b) directional means (11) being responsive to the operator generated signals received via said communication link for generating therefrom a directional pitch signal and a directional yaw signal, and,

c) digital control means (12) being responsive to the yaw status signal, the roll status signal, the directional yaw signal, and the directional pitch signal, for generating therefrom a primary yaw control signal, a secondary yaw control signal, a primary pitch control signal, and, a secondary pitch control signal,

d) amplification means (13) having,

1) means for amplifying (13a) said primary yaw control signal to an amplified primary yaw control signal,

2) means for amplifying (13b) said secondary yaw control signal to a secondary yaw control signal,

3) means for amplifying (13c) said primary pitch control signal to an amplified primary pitch control signal, and,

4) means for amplifying (13d) said secondary pitch control signal to an amplified secondary pitch control signal, and,

6) means for manipulating the control surfaces having,

a) a first actuator (19a) being responsive to said amplified primary yaw signal for physical movement of said first yaw control surface,

b) a second actuator (19b) being responsive to said amplified primary pitch signal for physical movement of said first pitch control surface,

c) a third actuator (19c) being responsive to said amplified secondary yaw signal for physical movement of said second yaw control surface, and,

d) a fourth actuator (19d) being responsive to said amplified secondary pitch signal for physical movement of said second pitch control surface.

8. The enhanced missile system according to claim 7 wherein said digital control means includes means for generating a first motion signal which initiates generation of the primary yaw control signal, the secondary yaw control signal, the primary pitch control signal, and the secondary pitch control signal.