Relaying of missile body roll angle

• US 9,605,934 B1
• Filed: 01/01/2015
• Issued: 03/28/2017
• Est. Priority Date: 01/30/2014
• Status: Expired due to Fees

• Current Assignee: Mordechai Shefer
• Original Assignee: Mordechai Shefer
• Inventors: Shefer, Mordechai
• Primary Examiner(s): Gregory, Bernarr
• Application Number:
  US14/588,417
• Time in Patent Office: 817 Days
• US Class Current: 1/1
• CPC Class Codes: F41G 7/30 Command link guidance systems homing F41G7/2206
• CPC Class Codes: F41G 7/301 Details
• CPC Class Codes: F41G 7/306 for transmitting guidance signals; F41G7/308 takes precedence
• CPC Class Codes: F42B 10/60 Steering arrangements F42B19/01 takes precedence
• CPC Class Codes: F42B 15/01 Arrangements thereon for guidance or control steering arrangements F42B10/60; aircraft flight control B64C; guidance systems other than those installed aboard F41G7/00, F41G9/00; locating by use of radio or other waves G01S; flight control in general G05D1/00; computer aspects G06]
• CPC Class Codes: H03C 1/00 Amplitude modulation H03C5/00, H03C7/00 take precedence
• CPC Class Codes: H03C 2200/0058 Quadrature arrangements

Abstract

A method is presented by which a missile body roll angle relative to earth coordinates can be deciphered onboard the missile from ground-data relayed to the missile during flight The present method comprises of a horizontal pair and a vertical pair of antennas on the ground and an up-down pair and a right-left pair of antennas onboard the missile. The ground to pairs signals are sinusoidally amplitude modulated in 90° phase difference between the two pairs, causing the transmitted wave polarity to rotate in the modulation frequency. A reference pulse is transmitted from the ground whenever the wave polarity vector crosses a prescribed ground antenna direction, thereby enabling the missile to measure its body up, down, right and left directions relative to earth up, down, right and left directions and to further respectively align them together.

Claims

1. A method of guiding a missile from a ground station, the missile including a missile body, the missile body and the ground station having respective up, down, left, and right directions, the missile body directions defined in the reference frame of the missile body, wherein the ground station includes an up transmitting antenna, a down transmitting antenna, a right transmitting antenna and a left transmitting antenna, the ground station antennas aligned with the ground station respective up, down, right and left directions, the method comprising:

transmitting data from the ground station to the missile, the data including a value of the missile roll angle in a horizontal axis reference frame of the ground station;

receiving the transmitted data on missile; and

aligning the missile body up, down, left, and right directions with corresponding ground station up, down, left, and right directions according to the value in the received data.

2. The method of claim 1, wherein the missile includes an up receiving antenna, a down receiving antenna, a right receiving antenna and a left receiving antenna, the missile receiving antennas aligned with the missile body respective up, down, right and left directions.

3. The method of claim 1, wherein the transmitting data from the ground station to the missile includes:

transmitting a first sinusoidally amplitude-modulated signal from the up-down pair of ground antennas, and

transmitting a second sinusoidally amplitude-modulated signal from the right-left pair of ground station antennas, the second signal having a ninety degrees phase-difference from the first signal, such that, the transmitted wave polarity vector of the combined first and second signals rotates in time in the modulation frequency about the horizontal axis reference frame of the ground station perpendicular to the plane of the ground station antennas.

4. The method of claim 3, wherein the frequency of the first and second sinusoidally amplitude-modulated signals is approximately 1,000 Hz.

5. The method of claim 3, wherein the transmitting data from ground station to the missile further includes:

transmitting a short reference pulse whenever the transmitted wave polarity vector of the combined first and second signals crosses a prescribed ground antenna direction.

6. The method of claim 5, wherein the missile includes an up receiving antenna, a down receiving antenna, a right receiving antenna and a left receiving antenna, the missile receiving antennas aligned with the missile body respective up, down, right and left directions, and the method further comprises:

receiving the short reference pulses on the missile; and

measuring the direction of each missile antenna relative to the corresponding ground station up, down, left, and right directions based on the received short reference pulses.

7. A method of guiding a missile from a ground station, the missile including a missile body, the missile body and the ground station having respective up, down, left, and right directions, the missile body directions defined in the reference frame of the missile body, wherein the missile includes an up receiving antenna, a down receiving antenna, a right receiving antenna and a left receiving antenna, the missile receiving antennas aligned with the missile body respective up, down, right and left directions, the method comprising:

transmitting data from the ground station to the missile, the data including a value of the missile roll angle in a horizontal axis reference frame of the ground station;

receiving the transmitted data on missile; and

aligning the missile body up, down, left, and right directions with corresponding ground station up, down, left, and right directions according to the value in the received data.

8. The method of claim 7, wherein the ground station includes an up transmitting antenna, a down transmitting antenna, a right transmitting antenna and a left transmitting antenna, the ground station antennas aligned with the ground station respective up, down, right and left directions.

9. The method of claim 8, wherein the transmitting data from the ground station to the missile includes:

transmitting a first sinusoidally amplitude-modulated signal from the up-down pair of ground antennas, and

transmitting a second sinusoidally amplitude-modulated signal from the right-left pair of ground station antennas, the second signal having a ninety degrees phase-difference from the first signal, such that, the transmitted wave polarity vector of the combined first and second signals rotates in time in the modulation frequency about the horizontal axis reference frame of the ground station perpendicular to the plane of the ground station antennas.

10. The method of claim 9, wherein the frequency of the first and second sinusoidally amplitude-modulated signals is approximately 1,000 Hz.

11. The method of claim 9, wherein the transmitting data from ground station to the missile further includes:

transmitting a short reference pulse whenever the transmitted wave polarity vector of the combined first and second signals crosses a prescribed ground antenna direction.

12. The method of claim 11, wherein the missile includes an up receiving antenna, a down receiving antenna, a right receiving antenna and a left receiving antenna, the missile receiving antennas aligned with the missile body respective up, down, right and left directions, and the method further comprises:

receiving the short reference pulses on the missile; and

measuring the direction of each missile antenna relative to the corresponding ground station up, down, left, and right directions based on the received short reference pulses.