Method of measuring height and detecting obstacles, a radioaltimeter, and an aircraft

• US 9,239,381 B2
• Filed: 03/07/2012
• Issued: 01/19/2016
• Est. Priority Date: 03/11/2011
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Airbus Helicopters
• Inventors: Dutruc, Herve
• Primary Examiner(s): McGue, Frank J
• Application Number:
  US13/413,700
• Publication Number:
  US 20120229325A1
• Time in Patent Office: 1,413 Days
• Field of Search: 342/29
• US Class Current: 1/1
• CPC Class Codes: G01S 13/87 Combinations of radar systems, e.g. primary radar and secondary radar
• CPC Class Codes: G01S 13/882 for altimeters measuring height using barometric means G01C5/06
• CPC Class Codes: G01S 13/91 for traffic control G01S13/93 takes precedence
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft
• CPC Class Codes: G01S 13/935 for terrain-avoidance
• CPC Class Codes: G01S 7/03 Details of HF subsystems specially adapted therefor, e.g. common to transmitter and receiver

Abstract

A radioaltimeter (5) having a signal generator-receiver (10) and signal transceiver means (20) connected to the generator-receiver (10), and a display member (30), said transceiver means (20) comprising a transceiver main member (21) for sending a signal towards a ground (S) in order to determine the height (H) between said main member (21) and said ground (S), said display member (30) having main display means (31) for displaying said height (H). Furthermore, the radioaltimeter (5) includes switch means (40) together with a control unit (50), and secondary display means (32) of said display member (30).

Claims

1. A radioaltimeter having a signal generator-receiver and signal transceiver means connected to the signal generator-receiver, the signal transceiver means having a transceiver main member for sending a signal towards ground (S) overflown by an aircraft in order to determine a height (H) between the transceiver main member and the ground (S), the radioaltimeter further including switch means together with a control unit, the signal transceiver means including a plurality of transceiver secondary members for detecting obstacles other than the ground (S), the transceiver main member and each of the plurality of transceiver secondary members being connected to the switch means, the radioaltimeter further including at least one position-determination member configured to determine the position of the aircraft, the control unit being connected to the switch means to alternately put the transceiver main member and the transceiver secondary members in direct connection with the signal generator-receiver one transceiver member at a time at least one time each in a cycle with a frequency at which the transceiver secondary members are put in direct connection with the signal generator-receiver during the cycle being dependent on a position of the aircraft, provided by the at least one position-determination member, while no obstacle other than the ground is detected by any of the transceiver secondary members, such that depending on the position of the aircraft at least one of the transceiver secondary members is put in direct connection with the signal generator-receiver at a greater frequency during the cycle than at least one other of the transceiver secondary members, and to modify the cycle when an obstacle other than the ground is detected.

2. The radioaltimeter according to claim 1, wherein the control unit is connected to the signal generator-receiver to receive information relating to propagation duration of a signal transmitted by one of the transceiver secondary members and reflected by an obstacle back to the one of the transceiver secondary members.

3. The radioaltimeter according to claim 1, wherein the at least one position-determination member is configured to determine the position of the aircraft based on at least one of forward speed of the aircraft, a map, an altitude of the aircraft, and an attitude of the aircraft.

4. The radioaltimeter according to claim 1, including a manual selector connected to the control unit to enable an individual to select the cycle from a predetermined catalog.

5. The radioaltimeter according to claim 1, wherein:

the control unit modifies the cycle when an obstacle other than the ground is detected such that each transceiver secondary member detecting an obstacle is put in direct connection with the signal generator-receiver at a greater frequency during the cycle than the transceiver secondary members not detecting an obstacle.

6. The radioaltimeter according to claim 1, including alarm means for indicating the presence of an obstacle.

7. The radioaltimeter of claim 1 further including a member for evaluating detected obstacles to determine a level of danger for each detected obstacle.

8. The radioaltimeter of claim 7 further including a display member having main display means for displaying the height (H) and secondary display means for displaying information relating to the detected obstacle presenting a highest level of danger.

9. The radioaltimeter of claim 8, wherein the control unit is connected to the display member to display information relating to at least one detected obstacle on the secondary display means.

10. An aircraft, including a radioaltimeter according to claim 1 for measuring the height (H) of the aircraft and for detecting obstacles other than the ground overflown by the aircraft, in a spherical volume surrounding the aircraft.

11. The aircraft according to claim 10, wherein the aircraft extends longitudinally from a rear end to a front end, in elevation from a bottom portion to a top portion, and transversely from a left side to a right side, the aircraft being included in the spherical volume presenting a bottom main sector between the ground and the bottom portion of the aircraft, at least one front secondary sector facing the front end, at least one rear secondary sector facing the rear end, at least one left side secondary sector facing the left side, and at least one right side secondary sector facing the right side, the transceiver main member having the function of pointing towards the bottom main sector, and the plurality of transceiver secondary members comprise at least:

a front transceiver secondary member for detecting an obstacle in the front secondary sector;

a rear transceiver secondary member for detecting an obstacle in the rear secondary sector;

a left side transceiver secondary member for detecting an obstacle in the left side secondary sector; and

a right side transceiver secondary member for detecting an obstacle in the right side secondary sector.

12. A method of making safe the flight of an aircraft by avoiding obstacles other than the ground overflown by the aircraft, the aircraft extends longitudinally from a rear end to a front end, in elevation from a bottom portion to a top portion, and transversely from a left side to a right side, a spherical volume surrounding the aircraft and including a main sector directed towards the ground and a plurality of secondary sectors directed towards respective portions of the spherical volume surrounding the aircraft other than towards the ground, the method comprising:

determining a position of the aircraft using a position-determination member;

transmitting successively in a given modifiable cycle;

firstly a main signal into the main sector to measure height (H) between the aircraft and the ground (S); and

secondly a number of secondary signals into each of the secondary sectors in order to detect the presence of obstacles in the secondary sectors, wherein the number of secondary signals transmitted into the secondary sectors during the cycle depends on a position of the aircraft, provided by the position-determination member, while no obstacles are detected in the secondary sectors, such that depending on the position of the aircraft a number of secondary signals transmitted into at least one of the secondary sectors is greater than a number of secondary signals transmitted into at least one other of the secondary sectors;

if an obstacle is detected in a given secondary sector, then referred to as a risky sector, modifying the given modifiable cycle to increase a first number of secondary signals transmitted into the risky sector compared with a second number of secondary signals transmitted into the other secondary sectors;

establishing a level of danger for each obstacle detected in secondary sectors; and

displaying the height (H) of the aircraft on main display means, and displaying information relating to the detected obstacle having the highest level of danger.

13. The method according to claim 12, wherein the given modifiable cycle is established with the help of a selector operable by a pilot of the aircraft.

14. The method according to claim 12, wherein once an obstacle has been detected in a front secondary sector situated in front of the aircraft relative to a forward direction of the aircraft, a safety distance between the aircraft and the obstacle is established and then the time to a potential impact with the obstacle is established, the level of danger being established as a function of the time or of the distance.

15. The method according to claim 14, wherein when a forward speed of the aircraft is less than a predetermined threshold, the level of danger is established as a function of the safety distance;

and wherein when the forward speed of the aircraft is greater than or equal to the predetermined threshold, the level of danger is established as a function of the time.

16. The method according to claim 12, wherein once an obstacle has been detected in a side secondary sector of the spherical volume situated on the left side or on the right side of the aircraft relative to a forward direction of the aircraft, the distance between the aircraft and the obstacle is established, and the level of danger is established as a function of the distance.

17. The method according to claim 12, wherein for an aircraft having a rotary wing describing a circle of given radius (R), the measured distance between the obstacle and transceiver means of the aircraft is established and the level of danger is established as a function of a security distance that is equal to the difference between the radius (R) and the measured distance.

18. A radioaltimeter for an aircraft, the radioaltimeter comprising:

a signal generator-receiver;

a signal transceiver connected to the signal generator-receiver, the signal transceiver having a transceiver main member for detecting a height of the aircraft above ground overflown by the aircraft and a plurality of transceiver secondary members for detecting obstacles other than the ground;

a position-determination member configured to determine a position of the aircraft;

a switch connected to the signal generator-receiver and the signal transceiver; and

a controller configured to control the switch to alternately put the transceiver main member and the transceiver secondary members in direct connection with the signal generator-receiver one transceiver member at a time at least one time each in a cycle with a frequency at which the transceiver secondary members are put in direct connection with the signal generator-receiver during the cycle being dependent on a position of the aircraft, provided by the at least one position-determination member, while no obstacle other than the ground is detected by any of the transceiver secondary members, such that depending on the position of the aircraft at least one of the transceiver secondary members is put in direct connection with the signal generator-receiver at a greater frequency during the cycle than at least one other of the transceiver secondary members, the controller further configured to modify the cycle when an obstacle other than the ground is detected.

19. The radioaltimeter of claim 18 wherein:

the aircraft is a helicopter.