This invention relates to the general subject of aircraft instrumentation or avionics. In particular, it is an invention for an altimeter which uses radio signals 05 transmitted from another airborne platform or location to measure height above the ground.

Background of the Invention

The altitude of airplanes and other aircraft has traditionally been determined by means of an instrument

10 based on a barometer. This is the so-called barometric altimeter. Although such altimeters have been widely used, they have their shortcomings. For example, they should be corrected for atmospheric pressure variations due to weather changes and measure height above mean sea

15 level not height above the ground.

A radio altimeter is an altimeter which uses electromagnetic radiation to determine the altitude of the aircraft. Such an altimeter depends upon the time difference between the transmission of a radio signal and

20 the reflected signal. U.S. patent 2,020,347 describes an early device. A radar altimeter is still another type of altimeter (see U.S. 3,543,270). Conventional radio altimeters generate signals .at approximately 4.3 gigahertz (GHz). Although the radio altimeter or radar altimeter

25 have advantages over the barometric altimeter, they cannot be used under all circumstances.

In particular, during aircraft missions over unfriendly terrain, it is often necessary to prevent detection of the aircraft by securing all sources of radio energy. Thus, radio transmitters, radars and radio

05 altimeters are turned off to prevent the enemy from using their emissions for detection and weapons homing. Although barometric altimeters can be used under these circumstances, they do not have the desired degree of accuracy and responsiveness needed for such missions.

10 They do not measure height above the ground.

Thus, it would be highly desirable for a means to be found to provide the advantages of a radio or radar altimeter, while not producing emissions which can result in the aircraft being detected. In effect, there is a

15 need for a passive radio altimeter. Passive ranging devices are not unknown to the art. U.S. patent 4,130,360 teaches a laser altimeter. U.S. patent 4,558,323 describes a method of passive measurement of range, velocity and the course of a target relative to a test

20 aircraft. However, the subject of passive altitude measurement has been neglected.

Clearly, a method and apparatus which would allow one to passively determine the altitude of one's own aircraft above the ground with the degree of accuracy 25 expected from a radio altimeter would solve a difficult problem and satisfy a need long felt by military and commercial aviation.

Summary of the Invention

In accordance with the present invention, an 30 apparatus and method is disclosed for measuring the altitude of an aircraft without that aircraft having to emit electromagnetic energy. Specifically, the altitude of one aircraft is passively determined by using the electromagnetic radiation emitted by a second aircraft 35 which is located at an altitude higher than the first

aircraft. In particular, the higner altitude aircraft is provided witti a source o£ electromagnetic radiation directed towards the earth and in the general direction of the second or passive aircraft, and tne second aircraft is 5 provided with a means for receiving tne electromagnetic radiation emitted directly troπi tne first aircraft and a means for receiving the radiation emitted from tne first aircraft and reflected from the earth's surface. By observing the time difference between tne receipt of the 0 direct path signal, the reflected signal and the angle at which the two signals are received, the altitude of the passive aircraft can be calculated.

In one embodiment, the lower aircraft is provided with an antenna on the upper part of the aircraft's body 5 or hull and another antenna on the lower part of the aircraft. Each antenna is ot the type which produces an output signal which can be used to calculate the anqle of incidence of the received electromagnetic energy. In one very specific embodiment, the higher altitude aircraft is

20 located vertically above the lower aircraft, such that the angle at which the direct radiation and reflected radiation are received is essentially zero degrees. This situation simplifies the calculation of altitude. Otner advantages and features of the present invention will

25 become readily apparent from the detailed description of the invention, the embodiments presented, tne accompanyin drawings and the claims.

Brief Description of the Drawings

FIG. 1 is a pictorial representation of the 30 environment under which the present invention may be used

FIG. 2 is a drawing showing the general relationshi of two aircratt which carry tne apparatus that is the subject of the invention; and

FIG. 3 is a drawing showing the geometry of the altitude computation.

Detailed Description

While this invention is susceptible of embodiment in 05 many different forms, there is shown in the drawings and will herein be described in detail, one specific embodiment, with the understanding that the present disclosure is to be considered an exemplification of the principles of the invention and is not intended to limit 10 the invention to the specific embodiment illustrated.

Turning to FIG. 1, there is shown two aircraft and a satellite positioned above the surface of the earth. Specifically, there is illustrated a satellite 10 in earth orbit, an aircraft 12 disposed at a niqh altitude relative

15 to the surface -of the earth 14, and a second aircraf 16 disposed between the first aircraft and the earth's surface. This second aircraft 16 will be referred to as the passive aircraft or platform since that aircraft will not transmit any electromagnetic radiation for puposes of

20 altitude determination. Tne higher located aircraft 12 or the sateLlite 10 will be referred to as the active aircraft or active platform, inasmuch as it will be a source of electromagnetic radiation to determine the altitude of the passive aircraft 16.

25 The utility of a passive apparatus for determining altitude of an aircraft with the degree of accuracy expected from a radio altimeter can be best understood from the following examples. There are many times during military operations in which an aircraft will penetrate an

30 enemy's defenses by flying in at extremely low altitude or "tree-top" level. An aircraft, flying at such a low altitude, is more likely to pass beneath the search path of conventional land based radar systems. As can be

expected, when a aircraft flies at low altitude, particularly at high speed, the determination of altitude is of extreme importance to the pilot. More often than not, the aircraft can only be operated at a high speed at low altitude if an automatic system is used to control the aircraft in response to the altitude of tne aircraft. In other words, an altimeter, with a high degree of accuracy, such as that found in a radio or radar altimeter, is extremely important to tne success of such an operation. Similarly, it is often desirable to fly a missile, such as a cruise missile, at a very low altitude, such as just above the surface ot the ocean, to enable that missile to penetrate defenses and remain undetected until target impact. While infrared terminal guidance may be used, that guidance does not provide high accuracy altitude information. Finally, there are occasions when the installed equipment must be Kept to a minimum, when secondary or back-up radio altimeters are too costly to install, or when complete redundancy cannot be justified. Thus, an alterntive radio altimeter that is accurate and inexpensive must be found to improve the probability of a successful mission.

Turning to FIG. 2, two helicopters 10' and 16 are shown disposed vertically above the surface of the earth 14. The utility of such an arrangement, where one aircraft is directly above the other, will become apparent from the discussion wnich follows. Also shown, for purpose of generality, is a third aircraft 12 depicted as a fixed wing aircraft. Al no gn only one active and one passive aircraft or other airborne platform are needed, a plurality ot aircraft disposed at different altitudes may be used for altitude comparison purposes. Similarly, different emitters may be used at different points in the mission. For that matter, as will become more clear from tne explanation which follows, the hiqher altitude platform may be a geosynchronous or other satellite (see FIG. 1) and laser radiation may be used instead of a radio or radar transmission.

Turning now to FIG. 3, tnere is depicted a source S of radio frequency energy emitted from a platform disposed above a lower altitude platform P using the passive radio altimeter (PRA) that is the subject of the present invention. The aircraft P with tne PRA has antennea on the top TA and bottom BA of the aircraft. By measuring the time between the signal arrival at tne top antenna TA and the signal arrived at the bottom antenna BA of the aircraft P, the altitude or the aircraft can be calculated. Generally speaking, this calculation is similar to that performed by conventional radio altitmeters where the aircraft has both a transmitting antenna and receiving antenna generally located at the bottom of the aircraft and horizontally separated from each other. (See U.S. 3,364,485.) As shown in the drawings, Rl represents the direct distance between the source S and the top antenna TA; R2 represents the distance between the source S and the point of reflectioon R on the earth's surface 14; R3 represents the distance from the point of reflection R on the earth's surface 14 to the bottom antenna BA; Al is tne angle from tne vertical to the direct path between the two aircraft; A2 is the angle from the vertical to the path of the reflected radiation; DA is the vertical distance between tne two antennas TA and BA on the passive aircraft P; HA is the altitude of the active aircraft S; and HP is the altitude of the passive aircraft P.

Now, if Tl is the time of travel from the active aircraft S to the top antenna TA; T2 is the time of travel from the active aircraft S to the point of reflection R on the earth's surface 14; and T3 is the time of travel from the point of reflection R to the bottom antenna BA, then the time difference is:

DT = T2 + T3 - Tl

since distance equals rate multiplied by time:

C Tl ^■ Rl

C T2 = R2 C T3 = R 3

where C is the speed of light, or:

C DT = R2 + R3 - Rl

By inspection, it can be shown that:

HP = C/2 [CT2 + T3) cos A ^' 2 - Tl cos Al]

Now, when the two aircraft are essentially vertically disposed above each other, A2 » Al. Therefore:

HP = 0.5 C DT cos Al

and if Al and A2 are small,

HP = 0.5 C DT

where we have also assumed that DA is approximately "0", considering the distances HA and HP. If that assumption is not made, then:

HP = 0.S DT C - DA.

In any event, by measuring the angle of arrival at TA and BA, a more exact determination of altitude can be made. Radio altimeter antennas suitable for use in the 4-5 gigahertz (GHz) range can be obtained from Ball Aerospace. Such an antenna has an accuracy of approximately 5 degrees and has a physical size of approximately 3 x 3 x 1/16 inches.

From the foregoing, it will be observed that numerous variations and modi ications may be effected without departing from the true spirit and scope of the

novel concept ot tne invention. For example, althouqh the invention has been described in detail in the specific environment of the measurement of altitude relative to the surface of the earth, tne basic principles of the

05 invention are equally applicable to the measurement of range to another fixed object from which electromagnetic radiation may be reflected (i.e., a space station with the passive platform being an astronaut) . Similarly, other forms of radiation wnich are reflected may be used,

10 including lasers and visible light. In addition, the invention has utility in the field of. ground proximity warning systems wherein those systems often employ a radio altimeter in conjunction with a barometric altimeter. Finally, the passive ranging technique described may be

1.5 used to cross reference, cross check or otherwise verify the accuracy and performance of other altitude measuring means. Thus, it should be understood that no limitation with respect to the specific apparatus illustrated herein is intended or should be inferred. It is, of course,

20 intended to cover, by the appended claims, all such modifications as fall within the scope of the claims.